Monitoring system

Abstract

A monitoring system (100) for the flight crew (99), for example the pilot, the aviation pilot, the pilot, the co-pilot, of an aircraft or a flying machine, for example an airplane or a helicopter of civil or military aviation, a passenger plane in scheduled or charter flights, in particular also a hypersonic aircraft, is described. By means of a sensor device (60), the air concentration is detected with measuring technology.

Description

TECHNICAL FIELD

[0001] The invention relates to a monitoring system for the flight crew or passengers of an aircraft or flying machine. An aircraft or flying machine is to be understood as meaning an aircraft or helicopter of civil or military aviation, such as a passenger aircraft in scheduled or charter flights and also supersonic aircraft in the range up to and above the speed of sound. In particular, the use of jets with supersonic speeds and / or flights at altitudes above 15,000 m place high demands on the fitness, attention, concentration and alertness of the flight crew, in particular of the pilots of jets, in terms of airworthiness. In order to ensure fitness and alertness at any time in high-altitude regions, in extremely fast flight maneuvers or flight attitudes, such as, for example, curved flight with high speeds (> 1 Mach) and accelerations above or even many times the force of gravity, dives, inverted flight and also in-flight refueling, in addition to the reliable equipment of the aircraft, it is also important to supply the pilots with satisfactory and health-friendly breathing air in a safe manner. In order to supply the aircraft pilots, aircraft drivers, pilots, co-pilots or passengers with breathing air or breathing gas, systems are used, for example, which use external air from the surroundings (mostly processed or air-conditioned and filtered) as a source of breathing gas, but also systems in which additional oxygen is added to the breathing air or breathing gas. Here, oxygen can be carried, for example, at high pressure (< 200 bar), by means of compressed oxygen bottles in the aircraft, and can be reduced to a breathable pressure by means of appropriate devices for pressure reduction, or, in order to be consumed directly in use, oxygen can be generated in a chemical process by means of a chemical oxygen generator (for example from carried sodium chlorate). It is often possible for aircraft pilots, pilots or co-pilots here to activate the dosing or supply of oxygen independently and / or to set or predefine the amount and / or concentration of oxygen and / or the composition of the breathing gas independently. The breathing air / breathing gas supply can be carried out here directly from the air in the cabin or cockpit, but also a hose system with a mouth / nose mask for direct supply and / or removal of breathing air / breathing gas for the aircraft pilot, pilot or co-pilot. In any case, the on-board equipment of the aircraft or flying machine is required to supply the aircraft pilot, pilot or co-pilot with satisfactory and health-friendly breathing gas in use. Belonging to this, on the one hand, is that the qualitative and quantitative composition of the breathing gas, in particular the proportion of oxygen and / or carbon dioxide in the breathing gas, is in a health-friendly range. In the natural atmosphere, in addition to the proportion of nitrogen and inert gases, oxygen (O2) amounts to a proportion of 21% by volume. The proportion of carbon dioxide (CO2) is currently below 0.05% by volume in the natural atmosphere worldwide on average.According to the recommendations of the Federal Aviation Administration (FAA), a carbon dioxide concentration of 30,000 ppm (corresponding to 3% by volume of carbon dioxide) is the maximum permissible value for passengers in an aircraft. The American Society of Heating, Refrigerating and Air-Conditioning Engineers (ASHRAE) recommends a carbon dioxide concentration of 1,000 ppm (corresponding to 0.1% by volume of CO2) as an upper limit. Therefore, in order to also provide breathing gas for the pilots, co-pilots or passengers, in use, the fraction of oxygen is striven for a concentration of above 21% by volume and the fraction of carbon dioxide is striven for at least the upper limit of 0.1% by volume of CO2 according to the recommendations of the Federal Aviation Administration (FAA) or according to the recommendations of the American Society of Heating, Refrigerating and Air-Conditioning Engineers (ASHRAE). It is considered scientifically safe that a carbon dioxide concentration of above 1% to 3% by volume can cause carbon dioxide poisoning, which is characterised, for example, by nausea, headache and dizziness. A carbon dioxide concentration of above 12% is immediately fatal. An oxygen deficiency can also be harmful to health, in particular for pilots, co-pilots or passengers, since in the case of an oxygen deficiency, the partial pressure of oxygen in the blood can decrease, a so-called hypoxic state (hypoxia) occurring. This decrease in the arterial partial pressure of oxygen in the blood, also known as hypoxemic hypoxia, often occurs at high-altitude dwellings. Symptoms of hypoxia are, for example: anxiety and restlessness, dyspnoea, cyanosis, tachycardia, elevated blood pressure, confusion, dizziness, bradycardia up to cardiac arrest. BACKGROUND

[0002] From EP 3 287 173 A1, a device and a method for monitoring inhaled gas are known. During the flow of breathing air into a mask of a person, the pressure level of the entire inhaled breathing air and the partial pressure of oxygen in the inhaled breathing air are determined and from this the partial pressure of oxygen in the lungs of the person is estimated. From US 2007 181 129 A, a breathing mask with a display device is known, which is configured to visually provide data and / or information to a pilot, a co-pilot or a flight attendant. The display device is built as a so-called head-up display. Here, the data and / or information are projected on the inside onto the visor that enters the field of vision of the pilot, co-pilot or flight attendant. From US 7 391 574 B2, another head-up display is known. From US 2016 253 561 A, a mask with a detection device for the ambient temperature and a display and visualization device thereof is known. From US 2019 118 008 A, a display device for a mask in a construction as a so-called in-mask display is known. From US 8 210 175 B, a device for supplying oxygen to an aircraft, for example according to the principle of pressure swing adsorption, is known. In addition, oxygen is provided from an oxygen reserve. Air is processed with a molecular sieve bed, which has been purged at the beginning of the operation with oxygen from the oxygen reserve. From US 7 407 528 B, US 2004 245 390 A and US 7 264 647 B, other devices for oxygen supply in an aircraft are known. From DE 10 2010 014 222 B4, a compressed air monitoring device for monitoring compressed air is known, which has a measuring air line for continuously extracting compressed air from a compressed air supply line and at least one sensor for continuously detecting at least one parameter of the compressed air. A sensor for detecting the carbon dioxide concentration, a sensor for detecting the nitrogen dioxide concentration, a sensor for detecting the carbon monoxide concentration, a sensor for detecting the sulfur dioxide concentration, a sensor for detecting the oxygen concentration and a sensor for detecting the relative air humidity are named as sensors for continuously detecting at least one parameter of the compressed air. EP 2 148 616 B1 shows a measuring system with a plurality of sensor mechanisms, such as flow sensor mechanisms, temperature sensor mechanisms, pressure sensor mechanisms, humidity sensor mechanisms, gas sensor mechanisms for measuring oxygen, carbon dioxide, carbon monoxide, nitrogen, nitrogen oxides, anesthetic gases, gas components in exhalation and other gases. DE 10 2006 030 242 A1 shows a configurable measuring system with a plurality of gas sensors. Electrochemical, infrared optical and catalytic gas sensors in the measuring system are configurable as gas sensors.From US20130167843A1, a pump for conveying an air quantity is known. The pump has a piezoelectric mode of action. Such a pump is suitable for conveying a gas quantity from a measurement site to a site of a sensor mechanism and / or for detecting with measurement technology by means of a measurement gas line (sample line) and for example for use in a side stream for analyzing the gas components (especially also carbon dioxide and oxygen) close to the mouth / nose region of a person or patient for the analysis of inhaled / exhaled air. From the patent documents WO2018033224A1, US20180163712A1, WO2018033225A1, US20180133420A1, US20180110957A1, WO2019072606A1, DE102017009605A1, DE102017009606A1, DE102018004341A1 and also from the patent document DE202012013442U1, many different embodiments and constructional solutions of gas conveying devices, pumps for supplying breathing gas to a person or devices for gas transport are known and many different embodiments and constructional solutions of gas conveying devices, pumps for supplying breathing gas to a person or devices for gas transport are known which are partly in the constructional solution and are suitable for ventilating a person. From the (not yet published) German patent applications 102019003643.3, 102019003607.7, 102019004450.9 and 102019004451.7, further constructional solutions of gas conveying devices, pumps for supplying breathing gas to a person or devices for gas transport are known which are partly in the constructional solution and are suitable for ventilating a person. From the patent documents DE102016013756A1, US20180143171A1, US20180143170A1 and US20180335410A1, many different embodiments and constructional solutions of gas conveying devices, pumps for conveying measurement gas to a gas measurement device or devices for gas transport are known. From US2008264418A, a connection element, a so-called Y-piece, for connecting a ventilation hose at the mouth / nose region of a person or patient is known which has sensor mechanism components, components for measurement value detection, signal processing, signal analysis and display. The sensor mechanism components include a respiratory flow sensor mechanism with a pressure sensor mechanism, a sensor mechanism for oxygen partial pressure measurement, a temperature sensor mechanism, a flow volume sensor mechanism (Durchflussmengen-Sensorik) which is constructed as a hot wire anemometer or an ultrasonic flow sensor and a connection element for EKG and blood pressure measurement.From US7897109B, US7335164B, US6616896B, US5789660B and US6312389B, oxygen sensors are known according to the measuring principle of so-called luminescence quenching, which can be arranged in the respiratory gas path of a patient or in a sidestream at the respiratory gas path. From DE102010037923B4, an oxygen sensor with a bioreactor array is known. From US9867563B, a system for identifying a reduced oxygen supply to a pilot and for reducing a reduced oxygen supply to a pilot is known. From US2003194351A, a galvanic cell for measuring oxygen is known. From DE102004062052B4, DE19726453C2, electrochemical oxygen sensors are known. From DE2155935, an electrochemical sensor for measuring gaseous components in a gas mixture is known. From US5958200B, DE102009010773B4, DE102005026491B4, DE102005026306B4 and US8496795B, many different constructional solutions of electrochemical gas sensors are known, which are suitable for detecting oxygen or other gases with measuring technology. DE102005007539A1 shows an electrochemical gas sensor for quantitatively determining redox-active substances in very low concentration ranges. Depending on the construction of the electrodes and the electrolyte, the electrochemical measuring principle is suitable for detecting many different gases, for example, oxygen, ammonia, sulfur dioxide, hydrogen peroxide, hydrogen sulfide, nitrogen dioxide, nitric oxide, arsine, silane, formaldehyde, acetylene, carbon monoxide, phosgene and phosphine. From DE19912100A1, an electrochemical carbon monoxide sensor is known. From US4851088B, an electrochemical carbon dioxide sensor is known. US5473304B and DE4020385C2 show thermal effect sensors manufactured in ceramic membrane technology. US7875244B, GB2210980A1 and DE19610912A1 show thermal effect sensors in the implementation of catalytic oxidation sensors (Pellistor). US2010221148A, US5902556B show catalytic gas sensors with a semiconductor chip as a measuring element. From US2816863B, US2019178827A, US8425846B, US9625406B, US6756016B, US2016178412A, US6344174B, catalytic gas sensors are known.The catalytic measuring principle, also referred to as the thermal effect principle, is particularly suitable for detecting flammable and / or explosive gases, in particular hydrocarbons, and for determining residual components of a combustion process. For example, toluene, ammonia, benzene, propane, methane, methanol, octane, butane, ethylene can be detected with the thermal effect principle using measuring technology. Catalytic sensors are often used to monitor limit values, for example the UEG (lower explosion limit). US 4 175 422 B shows a gas sensor with a semiconductor element as a measuring element. From US 9 958 305 B, a gas sensor device with a semiconductor sensor mechanism is known, which is constructed in chip technology, for monitoring a combustion process in an internal combustion engine of a motor vehicle. From DE 10 2004 048 979 B4, US 4 902 138 B, a miniaturized semiconductor gas sensor is known. From DE 10 2012 022 136 B4, a semiconductor type carbon monoxide sensor is known. From US 9 818 937 B and US 9 234 876 B, a miniaturized semiconductor oxygen sensor is known, which is implemented in microstructured technology, the so-called MEMS technology. Furthermore, gas sensors with solid electrolytes are known, for example zirconium dioxide-based gas sensors. In this way, DE 10 2008 056 279 B4 shows a device with a heated solid electrolyte oxygen sensor and with an ultrasonic sensor for indirect detection of carbon dioxide concentration. US 5 026 992 B shows a gas sensor for the measurement-technical optical detection of methane. US 8 399 839 B shows a gas sensor for the measurement-technical optical detection of carbon dioxide. From EP 0 149 619 A1, a device with a lambda probe is known for detecting the amount of residual oxygen in the exhaust gas of an internal combustion engine. From US 4 667 157 B, a Hall effect oxygen sensor is known. US 8 596 109 B, US 8 596 109 B, US 9 360 441 B2, US 4 808 921 B, US 6 430 987 B, US 6 952 947 B, US 6 895 802 B, US 6 405 578 B, US 4 683 426 B, US 4 173 975 B, US 3 646 803 B, US 3 584 499 B, US 2 944 418 B and WO 161 622 87 A1 show devices for measuring the concentration of paramagnetic gases. With this device, it is possible, in particular qualitatively and also quantitatively, to detect oxygen with measurement technology, since oxygen has paramagnetic properties. From US 9 360 441 B, a measuring element for paramagnetic gas sensors, in particular for oxygen sensors, is known. The paramagnetic gas sensor or the oxygen sensor can preferably be arranged in a sidestream in the respiratory airway of a patient or at the respiratory airway. In DE 10 2010 047 159 B4 and US 2004 238 746 A, a gas measuring device is described.In US 5739535 B an infrared optical gas measuring device is described. From US 8399839 B an infrared optical carbon dioxide sensor (so-called IR carbon dioxide sensor) is known. From DE 102010047159 B4 and US 6895802 B devices for measuring the carbon dioxide concentration in respiratory gases by measuring the thermal conductivity are known. The embodiment according to DE 102010047159 B4 shows a carbon dioxide sensor with a semiconductor chip as a measuring element for detecting a change in thermal conductivity. From US 5696379 B, US 2004203169 A and US 4050823 B infrared optical carbon dioxide sensors are known. From US 8448642 B, US 5095900 B, US 5067492 B, WO 20109115 A1, US 2019105457 A, US 6095986 B, USD 727492 S1 and US 5942755 B infrared optical carbon dioxide sensors are known which can be arranged in the main stream in the respiratory gas path of a patient. From US 2002036266 A, US 2004238746 A, US 20180120224 A1 and US 20180116555 A1 gas measuring devices or sensors for detecting carbon dioxide with measuring technology are known, in particular also suitable for detecting carbon dioxide in respiratory gases with measuring technology. Further gas measuring devices or sensors for detecting carbon dioxide with measuring technology are known from the (not yet published) German patent applications 102020114972.7, 102020114968.9. From US 6571622 B a combined sensor consisting of an infrared optical carbon dioxide sensor and a flow sensor is known which can be arranged in the main stream in the respiratory gas path of a patient. From US 2004238746 A, US 2002036266 A infrared optical carbon dioxide sensors are known which can be arranged in a side stream in the respiratory gas path of a patient. US 6954702 B, US 7606668 B, US 8080798 B, US 7501630 B, US 7684931 B, US 7432508 B, US 7183552 B show gas measuring systems for detecting gas concentrations in a side stream and a main stream. In US 9939374 B and US 7705991 B interferometers in the construction of a gas measuring device are described. From US 6274879 B and EP 2788739 B1 laser-based devices for detecting gas components are known.From US 9 459 235 B, a gas sensor embodied as a photoionization detector is known. Further aspects with respect to the qualitative and quantitative composition of the breathing gas involve that the breathing gas is to be as free as possible of impurities, for example of foreign substances or particles, such as, for example, soot, dust, pollen or material vapors, which foreign substances or particles flow through the breathing gas on the way to the aircraft pilots, crew members, co-pilots, passengers. Furthermore, in the breathing gas there should not be or there should not be a significant amount of gases or gas mixtures which are harmful to health, such as, for example, carbon monoxide (CO), ozone, traces of other gases or traces of aviation gasoline or kerosene, large amounts of exhaust gases or combustion residues or other air pollutants. Belonging to this, for example, are hydrocarbons of many different components, benzene, nitrogen oxides (NO2, NO. x ), sulfur oxides (SO2, SO x ), dioxins, furans, particles, for example soot, fine dust and ultrafine particles. In addition to the above-mentioned carbon dioxide poisoning, carbon monoxide poisoning is to be mentioned in particular at this point. Concentrations above 200 ppm (0.02%) already cause headaches and loss of judgment, concentrations above 800 ppm (0.08%) cause dizziness, restlessness, nausea, anxiety and cramps within 45 minutes and within 2 hours loss of consciousness, perhaps with fatal consequences. In the case of carbon monoxide poisoning, a reduced oxygen transport capacity of the blood occurs due to a reduced hemoglobin content (anemia) or anemic hypoxia occurs due to impairment of the oxygen binding capacity in the blood. SUMMARY

[0003] Thus, a need arises to secure the following situation for aircraft pilots, crew members, co-pilots, passengers: during the flight operation, a satisfactory and high-quality breathing gas is always provided by the on-board equipment of the aircraft or flying machine and can be given to the aircraft pilots, crew members, co-pilots, passengers of the aircraft or flying machine. As a result, it is the task of the present invention to provide a monitoring system for aircraft pilots, crew members, co-pilots, passengers of an aircraft or flying machine or to provide a method which enables the monitoring of the breathing gas and breathing air in an aircraft or flying machine with measuring technology. As a result, it is a further task of the present invention to provide a method for monitoring the breathing gas and breathing air in an aircraft or flying machine with measuring technology.

[0004] These tasks are solved by the attached independent patent claims. In particular, the task is solved by a monitoring system for monitoring the gas composition of the breathing gas in an aircraft or flying machine having the features of independent claim 1.

[0005] The task is also solved by a method for operating a monitoring system for monitoring the gas composition of breathing gas in an aircraft or spacecraft, having the features of independent claim 33. Further features and details and advantageous design options of the invention result from the dependent claims, the description and the drawings. The back references used here indicate that the subject matter of the main claim is further configured by the features of the respective dependent claim and is not to be understood as a waiver of independent protection of the specific combination of features of the back-referenced dependent claim. Furthermore, in the interpretation of the claims and the description, in the further specification of the features in the dependent claims, it is to be started from the fact that such a limitation is not present in the respectively preceding claim and in the more general implementation form of the specific system or method. Even if not expressly indicated, any reference in the description to aspects of a dependent claim is therefore to be explicitly interpreted as a description of an optional feature. Finally, it is to be noted that the monitoring system suggested here can also be extended in correspondence with the method claims and vice versa, for example in such a way that the monitoring system comprises means determined and / or established for carrying out one or more method steps, or in such a way that the method comprises steps which can be carried out by means of the monitoring system or which are suitable for operating the monitoring system. In this respect, the features and details described in connection with the suggested monitoring system for the flight crew or passengers of an aircraft or spacecraft and possible design options are of course also applicable in connection with and in view of the method carried out when the monitoring system is operated and vice versa, respectively, so that with respect to the disclosure always or can always refer to the respective aspects of the invention to one another.

[0006] Embodiments propose the possibility of monitoring the gas composition of air, breathing air or breathing gas in an aircraft or flying machine by means of measurement technology. At least some embodiments of the invention relate to a monitoring system for monitoring the gas composition of air, breathing air or breathing gas in an aircraft or flying machine. At least some embodiments of the invention relate to a method for operating a monitoring system for monitoring the gas composition of air, breathing air or breathing gas in an aircraft or flying machine. In at least some embodiments, it can be possible to enable the detection of properties of at least one gas by means of a sensor mechanism of the monitoring system by means of measurement technology. The following physical and other properties can belong to the properties of a gas, for example: pressure, density, viscosity, thermal conductivity, electrical and magnetic properties, temperature, gas composition, moisture content, toxicity, calorific value, flammability, binding ability to other gases or liquids, for example water or blood. In at least some embodiments, it can be possible to enable the qualitative detection of at least one gas by means of measurement technology. In at least some embodiments, it can be possible to enable the quantitative detection of at least one gas and / or the concentration of a gas by means of measurement technology. In at least some embodiments, it can be possible to enable the qualitative and quantitative detection of at least one gas by means of measurement technology. In at least some embodiments, it can be possible to enable the qualitative and quantitative detection of oxygen by means of measurement technology. In at least some embodiments, it can be possible to enable the qualitative and quantitative detection of carbon dioxide by means of measurement technology. In at least some embodiments, it can be possible to enable the qualitative and quantitative detection of another gas, in particular carbon monoxide, by means of measurement technology.

[0007] In at least some embodiments, a control unit is arranged in the monitoring system or is assigned to the monitoring system. The control unit is configured and set up to organize, check, control or regulate the process of monitoring the gas composition of air, breathing air or breathing gas in an aircraft or flying machine by means of measurement technology. The control unit is preferably configured from components (μC, μP, PC) with an associated operating system (OS), data memory (RAM, ROM, EEPROM) and SW code, software for process control, checking, control, regulation. In at least some embodiments, the control unit is assigned or connected to other electronic components, such as, for example, components for signal detection (AD μC), components for signal amplification, components for analog and / or digital signal processing (ASIC), components for analog and / or digital signal filtering (DSP, FPGA, GAL, μC, μP), components for signal conversion (A / D converter).

[0008] In at least some embodiments, the sensing mechanism can enable qualitative and quantitative detection of the oxygen concentration by means of measurement technology. Here, the oxygen concentration can be determined by means of measurement technology, for example in the form of a partial pressure in a gas mixture, for example in the breathing air or in the breathing gas, or in the form of a volume concentration, or in the form of a mass concentration per unit volume. In at least some embodiments, the sensing mechanism can enable qualitative and quantitative detection of the carbon dioxide concentration by means of measurement technology. Here, the carbon dioxide concentration can be determined by means of measurement technology, for example in the form of a partial pressure in a gas mixture, for example in the breathing air or in the breathing gas, or in the form of a volume concentration, or in the form of a mass concentration per unit volume. In at least some embodiments, the sensing mechanism can have at least one sensor. Here, the at least one sensor is preferably configured as an oxygen sensor, a carbon dioxide sensor or at least one other gas sensor, in particular a carbon monoxide sensor. In at least some embodiments, for qualitative and quantitative detection of the oxygen concentration by means of measurement technology, a paramagnetic oxygen sensor or a measurement module having a paramagnetic oxygen sensor can be used. Here, in a further advantageous manner, an electrochemical oxygen sensor or a measurement module having an electrochemical oxygen sensor can be used. Here, in a further advantageous manner, an oxygen sensor or a measurement module with an oxygen sensor can be used, which oxygen sensor functions according to the principle of luminescence quenching or fluorescence quenching. Here, in a further advantageous manner, a semiconductor oxygen sensor, preferably in the form of a so-called MEMS oxygen sensor, or a measurement module having a semiconductor oxygen sensor or having a MEMS oxygen sensor can be used. Here, in a further advantageous manner, an electrochemical oxygen sensor and / or a paramagnetic oxygen sensor can be used, or a measurement module having an electrochemical oxygen sensor and / or having a paramagnetic oxygen sensor can be used. Here, in a further advantageous manner, an electrochemical oxygen sensor and / or a semiconductor oxygen sensor can be used, or a measurement module having an electrochemical oxygen sensor and / or having a semiconductor oxygen sensor can be used. Here, in a further advantageous manner, a paramagnetic oxygen sensor and / or a semiconductor oxygen sensor and / or an electrochemical oxygen sensor can be used, or a measurement module having a paramagnetic oxygen sensor and / or having a semiconductor oxygen sensor and / or having an electrochemical oxygen sensor can be used. Here, in a further advantageous manner, a paramagnetic oxygen sensor and / or a semiconductor oxygen sensor can be used, or a measurement module having a paramagnetic oxygen sensor and / or having a semiconductor oxygen sensor can be used.In at least some embodiments, for the qualitative and quantitative detection of the carbon dioxide concentration with measurement technology, an optical carbon dioxide sensor, preferably in the form of an infrared-optical so-called IR carbon dioxide sensor, or a measurement module with an optical, preferably infrared-optical, carbon dioxide sensor, i.e. a so-called IR sensor, can be used. Here, in a further advantageous manner, a semiconductor carbon dioxide sensor, preferably in the form of a so-called MEMS carbon dioxide sensor, or a measurement module with a semiconductor carbon dioxide sensor or with a MEMS carbon dioxide sensor, can be used. Here, in a further advantageous manner, a semiconductor carbon dioxide sensor, preferably in the form of a so-called MEMS carbon dioxide sensor, and / or an optical carbon dioxide sensor, preferably in the form of an infrared-optical so-called IR carbon dioxide sensor, or a measurement module with a semiconductor carbon dioxide sensor or a MEMS carbon dioxide sensor and / or with an optical carbon dioxide sensor or an IR carbon dioxide sensor, can be used.

[0009] A measurement module with at least one oxygen sensor is also referred to as an oxygen measurement module in the context of the present application. A measurement module with at least one carbon dioxide sensor is also referred to as a carbon dioxide measurement module in the context of the present application.

[0010] In some embodiments, the oxygen measurement module and / or the carbon dioxide measurement module can also have or, in some embodiments, can also be assigned other sensors, and / or the oxygen measurement module and / or the carbon dioxide measurement module can also be arranged at the module. In some embodiments, the oxygen measurement module and / or the carbon dioxide measurement module can be implemented in combination with other gas sensors and, if necessary, with other sensors for detecting measurement variables or material variables (Stoffgroessen) with measurement technology, such as, for example, pressure, ambient pressure, airway pressure, mask pressure, density, temperature, thermal conductivity, heat capacity, volume flow, mass flow, flow rate, volume, and can be configured as a gas measurement module, a measurement module or as a module for ambient or environmental analysis. In this way, a pressure sensor in the monitoring system can be arranged, for example, as an element of the oxygen measurement module or the carbon dioxide measurement module, which is configured to detect the pressure level in the measurement gas line. Furthermore, a flow sensor (Stroemungssensor) or a flow rate sensor in the monitoring system can be arranged, for example, as an element of the oxygen measurement module or the carbon dioxide measurement module, which is configured to detect the flow rate or flow in the measurement gas line. The measurement values of the flow sensor, the flow rate sensor and also of the pressure sensor can be provided to the control unit.

[0011] In some embodiments, the monitoring system or such a module, such as a gas measuring module, a measuring module, a module for ambient or environmental analysis, can have at least one module for gas transport. To this end, the module for gas transport has a gas delivery device, preferably a pump, with a gas port, which is configured to deliver a defined quantity of gas from a measurement location remote from the sensor mechanism or the oxygen measuring module, the carbon dioxide measuring module or the gas measuring module to the oxygen measuring module, the carbon dioxide measuring module or the gas measuring module or to the oxygen sensor, the carbon dioxide sensor, in order to enable the detection of the oxygen concentration and / or the carbon dioxide concentration by means of measuring technology. The module for gas transport or the pump is configured to draw a quantity of breathing gas or breathing air, in particular from a breathing mask and / or from a cabin or cockpit, and to deliver it towards the monitoring system or the oxygen measuring module and / or the carbon dioxide measuring module or towards the sensor mechanism, in particular the oxygen sensor and / or the carbon dioxide sensor. The breathing mask may, for example, be configured as a partial mask, a half mask or a full mask or as a combination of a protective helmet and a mask. In order to largely or completely prevent backflow or to avoid undesired flows or flows through, a valve can additionally be arranged at the inflow upstream of the pump or at the outflow downstream of the pump. The module for gas transport is preferably connected pneumatically and / or fluidically to the measurement location in a gas-conducting manner by means of a measuring gas line. In order to monitor the breathing gas supply of a pilot, a co-pilot or a flight attendant, the gas-conducting component in the facial region, that is to say close to the mouth / nose region of the pilot, co-pilot or flight attendant, is preferably used as the measurement location. One end of the measuring gas line is preferably arranged at the mouth / nose region, for example at the breathing mask, in order to enable the flow of the gas quantity from the mouth / nose region towards the module for gas transport of the monitoring system. The other end of the measuring gas line is preferably pneumatically or fluidically connected to the gas port for inflow into the module for gas transport, so that a quantity of breathing gas can be delivered towards the oxygen measuring module and / or the carbon dioxide measuring module by means of the module for gas transport, for example with a flow rate in the range from 25 ml / min to 250 ml / min. To this end, the module for gas transport is pneumatically and / or fluidically connected to the oxygen measuring module and / or the carbon dioxide measuring module with a further gas port for outflow or delivery. By means of a flow sensor or a flow rate sensor, the control unit can check the module for gas transport and can check, control, regulate or set the quantity of gas to be delivered or to be drawn in the measuring gas line. By means of a pressure sensor, the control unit can monitor the pressure level in the measuring gas line and, by means of the module for gas transport, can also check, control, regulate or set the pressure level.If the flow sensor is constructed as a differential pressure sensor (ΔΡ sensor) which measures the pressure difference as the difference between two pressure measurement points above a flow barrier (Stroemungsblende), it is also possible to achieve a pressure measurement of the pressure level in the measuring gas line in this case if one of the two pressure measurement points is detected with the sensor with respect to the environment.

[0012] In a preferred embodiment, the module for gas transport in the form of a pump can be arranged at the gas inlet of the monitoring system. In this exemplary configuration (Konstellation), the module for gas transport draws a volume of gas from the pilot's breathing mask through the measuring gas line into the monitoring system and then transports the volume of gas and through the sensing mechanism for the gas concentration determination. After flowing through the sensing mechanism, the volume of gas reaches the environment through the gas outlet.

[0013] In other preferred embodiments, the module for gas transport in the form of a pump can be arranged at the gas outlet of the monitoring system. In this exemplary configuration, the module for gas transport draws the volume of gas from the pilot's breathing mask through the measuring gas line into the monitoring system for gas concentration determination through the sensor mechanism. After flowing through the pump, the volume of gas reaches the environment through the gas outlet. In the case of the pump arranged at the gas outlet, possible impurities passing through the pump cannot reach the sensor mechanism. Via the module for gas transport, in particular the pump, a volume or a partial amount of breathing gas can be transported to the oxygen measurement module and / or the carbon dioxide measurement module, or to the oxygen sensor and / or the carbon dioxide sensor, so that a concentration of up to oxygen and / or carbon dioxide can be detected with measurement technology. The monitoring system is constructed in such a way that it can be placed in or on the clothing of a pilot, a pilot or a co-pilot. The measuring gas line has a corresponding length so that this placement is possible. It is particularly advantageous to place or position the monitoring system in the breast pocket, leg pocket or thigh pocket of a flight suit (Flieger-Overall). The module for gas transport is designed and constructed in such a way that the gas volume can be transported from the measuring point to the preferred point placed in the breast pocket, leg pocket or thigh pocket of the flight suit. The module for gas transport can be constructed, for example, as a centrifugal pump, a axial pump, a radial pump, a reciprocating pump or a diaphragm pump. Pumps with low energy consumption are particularly advantageous for the use of the monitoring system in mobile and energy self-sufficient use. For example, pumps operated piezoelectrically (often also called piezoelectric pumps) enable energy-saving use for gas concentration measurement in the monitoring system. For example, such pumps are sold by the company Murata Manufacturing Corp. in Kyoto, Japan, under the names MZB1001T02 and MZB1001 as so-called "piezoelectric blowers" or "micro blowers". These pumps do not block the flow even without electrical actuation or activation, so that it is advantageous in the use of the monitoring system to provide a valve for reliably, repeatedly and unambiguously ensuring the inflow into the measuring gas line in two states "release" and "block". A stop valve (so-called "Flow-Lock-Valve") is suitable for the embodiment with a pump at the gas outlet and for the embodiment with a pump at the gas inlet, which stop valve can preferably be arranged at the gas outlet.Arranging a shut-off valve at the gas outlet of the monitoring system makes it possible to use a pressure sensor arranged inside the monitoring system for determining the pressure in the breathing mask of the aircraft pilot by means of measuring manoeuvres for determining the breathing mask pressure, since the pressure level inside the monitoring system in the flow-free state when the shut-off valve is closed corresponds to the pressure level in the measuring gas line and the pressure level in the breathing mask. Alternatively, a changeover valve (so-called "3 / 2-way valve") is suitable for embodiments with a pump at the gas inlet, which changeover valve can preferably be arranged at the gas inlet. On the one hand, this changeover valve makes it possible to supply a large amount of gas from the measuring gas line into the monitoring system, on the other hand it is also possible to supply a large amount of gas from the environment, that is to say the cabin of the aircraft, as a result. During the supply of the gas quantity from the cabin, the control unit can simultaneously determine the pressure level in the breathing mask by means of the measuring manoeuvres for determining the breathing mask pressure.

[0014] In a preferred embodiment, a further gas port with a changeover valve is arranged in the monitoring system. In a further preferred embodiment, the further gas port with a changeover valve is arranged in or at the module for gas transport. The changeover valve makes it possible to switch between the supply of a large amount of gas from the measuring gas line and the supply of a gas quantity from the environment, for example from the cabin of the aircraft, by means of the further gas port. In a further preferred embodiment, a further pump is arranged in or at the further gas port. The further pump makes it possible to supply a gas quantity from the environment, for example from the cabin of the aircraft, by means of the further gas port. For embodiments with a pump at the gas outlet, in addition to the shut-off valve at the gas outlet, an optional changeover valve can also be arranged at the gas inlet for switching between monitoring the gas quantity from the measuring gas line from the breathing mask and monitoring the gas quantity from the cabin. As a result, the control unit is then made capable of, independently of the time of the mask pressure determination, carrying out the switching between the supply of a large amount of breathing gas to the breathing mask of the aircraft pilot and the supply of gas from the cabin at any time.

[0015] In some embodiments, the control unit can be configured to determine breathing phase information, that is to say to determine the duration of inhalation, the duration of exhalation, the ratio of inhalation duration to exhalation duration (I:E ratio), and to determine the breathing frequency of the aircraft pilot, the pilot or the co-pilot, from the measured values of the carbon dioxide sensor.

[0016] In at least some embodiments, the sensor system and the control unit can be configured to detect at least one environmental parameter and / or at least one operating parameter. The operating parameter can be, for example, a parameter from the flight operation, a parameter from the supply of breathing gas to the aircraft pilot, the co-pilot or the crew, a parameter from the inspection, control, regulation of the aircraft or of components of the aircraft. In at least some embodiments, the sensor system and the control unit can be configured to take into account the at least one environmental parameter together in the course of the inspection and / or to incorporate the at least one environmental parameter into the course.

[0017] In a preferred embodiment, the control unit is configured in conjunction with the pressure sensor to determine the current pressure level in the breathing mask. In the flight operation of a jet aircraft, the aircraft pilot (pilot, co-pilot) is supplied with breathing gas by means of a breathing mask arranged at the mouth / nose region. It is therefore of particular interest to monitor the current pressure level in the breathing mask of the aircraft pilot, the pilot or the co-pilot. It is thereby ensured that the aircraft pilot, the pilot or the co-pilot is provided with a sufficient pressure level of breathing gas by means of the breathing mask in the flight operation.

[0018] The embodiment shows the possibility of detecting the pressure level in the breathing mask by means of the sensor system and the control unit and thus monitoring, providing, outputting and / or recording the pressure level in the breathing mask. The control unit detects the pressure level in the measuring gas line by means of a pressure sensor which is arranged in the monitoring system and which is pneumatically and fluidically connected to the components, i.e. the breathing mask, the measuring gas line, the connecting element and optionally the HME filter element connected in series to the measuring gas line, in the pneumatic system, in order to detect a pressure measurement value which is indicative of the pressure level in the pneumatic system. In another preferred embodiment for detecting the current pressure level, in a measurement situation in which the monitoring system is operated, in which no significant amount of gas is supplied from the breathing mask to the sensor system, i.e. the measurement of the gas concentration by the sensor system is temporarily interrupted or paused, a pressure measurement is initiated by the control unit, in which the monitoring system is deactivated for the gas transport and in which the pump is deactivated. In this measurement situation, the measurement value which is indicative of the pressure level in the pneumatic system corresponds to the current pressure level in the breathing mask. In addition to the deactivation of the pump, a shut-off valve can be brought into a closed state in order to prevent any gas exchange between the pneumatic system and the environment. With this embodiment, the implementation of the measurement and the checking of the pressure level in the breathing mask can be carried out discontinuously if the gas quantity supply by the pump is deactivated at defined time intervals.

[0019] In another preferred embodiment for detecting the current pressure level, the pressure measurement is initiated by the control unit while the monitoring system is continuously in operation, in which the sensor mechanism is constantly supplied with a quantity of gas from the breathing mask by means of the module for gas transport or by means of the activated pump. With this embodiment, the implementation of the measurement and verification of the pressure level in the breathing mask can be performed continuously, if the pressure drop of the pneumatic system with the components, i.e. the breathing mask, the measuring gas line, the connecting element and the HME filter element, which itself changes in operation, is not adapted or calibrated discontinuously at defined time intervals. In this preferred embodiment, the adaptation or calibration, which is discontinuously and at defined time intervals executable, can be built by a measurement operation, which is coordinated and performed by the control unit in interaction with the module for gas transport or the pump, the shut-off valve and the data memory. This measurement operation can be performed from time to time during the flight operation in order to determine the change in the pneumatic system or at the pneumatic system at defined points in time during the time change of the service duration while the aircraft pilot is in use. The measurement operation comprises the detection of the pressure level with measuring technology in order to dispose of zero or to perform an offset determination at two operating points. The measurement operation is divided into a pressure measurement of the static pressure level at an operating point in the pneumatic system without gas flow and a detection with measuring technology of the dynamic pressure level in the form of a measurement at another predefined operating point in the pneumatic system with a defined flow. In the detection of the static pressure level with measuring technology, the pressure measurement value is detected without gas flow within the pneumatic system with the components: breathing mask, measuring gas line, connecting element and optionally HME filter element arranged in series in the measuring gas line. Without gas flow, that is to say with the pump switched off and the resulting flow amount of 0.00 ml / min, no pressure drop due to the components occurs in the pneumatic system between the breathing mask and the pressure sensor or the pump in the monitoring system. The HME filter element serves to prevent the moisture from the breathing gas supply with the breathing hose and the breathing mask from reaching the monitoring system for monitoring the gas composition of the breathing gas, which is introduced into the measuring gas line in operation by the exhalation of the aircraft pilot. This HME (HME = Heat Moisture Exchange) filter element is configured to retain a quantity of moisture. In the preferred embodiment, the HME filter element is arranged in the measuring gas line at the gas inlet or at the module for gas transport. In operation, a quantity of moisture or liquid constantly accumulates in the HME filter element due to the exhalation of the aircraft pilot with moist breathing gas. As a result, a change in the flow resistance occurs during the time change of the service duration in the flight operation with the monitoring system in operation.In addition to switching off the pump, the shut-off valve is advantageously brought into the closed state in order to prevent any gas exchange of the pneumatic system with the environment. The detected pressure measurement in the measuring gas line without gas flow corresponds to an instantaneous recording of the current pressure in the breathing mask when the shut-off valve is closed and is stored in the data memory as the static pressure of the pneumatic system. In the detection of the dynamic pressure level with the measuring technology, the pressure measurement in the case of a defined quantity of gas flow is detected using the pressure drop on the components of the pneumatic system corresponding to the gas flow, said components of the pneumatic system having the measuring gas line, the connecting element and optionally the HME filter element. The detected pressure measurement in the case of a defined quantity of fluid flow is stored in the data memory as the dynamic pressure of the pneumatic system. As the appropriate and defined quantity of gas flow in the measuring gas line, a range from 10 ml / min up to 400 ml / min can be activated, checked, controlled or set by the control unit. The pressure measurement in the flow case corresponds to the current total pressure drop of the dynamic of the pneumatic system. This pressure measurement then corresponds to the sum of the pressure drops in the components such as the breathing mask, the HME filter element, the measuring gas line and the connecting element, that is to say the sum of the pressure drops on the components. From the difference between the previously determined static pressure level and the sum of the dynamic pressure drop, the control unit can determine the pressure drop originating from the components as the offset pressure level of the pneumatic system. The change in the determined difference between the dynamic and static pressure measurements between two or more times of performing the measuring operation enables the control unit to make inferences about the change in the pressure drop in the pneumatic system and the change in the offset pressure level during operation. These offset pressure levels in the pneumatic system and their difference and their change are constantly detected or determined by the control unit during the flight operation and are stored in the data memory, for example in the form of data sets or tables or as a log file. In a preferred embodiment, the control unit is advantageously configured by means of the measuring operation to determine the determined offset pressure level as a calibration value for determining the current mask pressure by detecting the static and dynamic pressure drop on the pneumatic system with the measuring technology, it then provides, outputs and / or stores the determined offset pressure level in the form of data sets or tables. Thereby, the measuring operation provides trends and changes in the offset pressure level during the operation of the monitoring system on the aircraft pilot, the pilot or the co-pilot in use. In this way, it is possible to determine and monitor the respectively current prevailing mask pressure of the aircraft pilot even between components of the pneumatic system which change during the flight operation. In particular, by constantly repeating the measuring operation, a pressure drop increase on the HME filter element due to moisture saturation can be detected as a change in the offset pressure level and is compensated when calculating the current pressure level in the breathing mask.This repetition of the test can take place, for example, every 15 to 60 minutes; more frequent execution is not advantageous, since the monitoring of the gas concentrations for the execution of the measuring operation is interrupted or paused for a short time. The determination of the current pressure in the breathing mask can be carried out by the control unit on the basis of the last determined offset pressure level using the measuring operation of the components of the pneumatic system, also during the activated pump operation and the detection of the gas concentrations of oxygen and / or carbon dioxide and, if necessary, further gases or cabin air using the measuring technology. The current pressure level present in the breathing mask is derived by subtracting the last determined offset pressure level stored and provided in the data memory from the current pressure measurement value indicating the pressure level in the pneumatic system when flowing through the measuring gas line. Subsequently, also in view of the integration of the measuring operation for the detection of the gas concentrations, preferably of carbon dioxide and oxygen, using the function of the components involved here into the measuring operation of the monitoring system, which has been described previously for the determination of the pressure in the breathing mask, the measuring operation is elucidated. At a predetermined time from the continuous measuring operation of the monitoring system, the measuring operation can be activated or started. In the step sequence from the start until the end, the following steps are activated, initiated and carried out by the control unit:

[0020] - in a first step, a deactivation of the pump is carried out,

[0021] - in a second step, the closing of the shut-off valve is carried out,

[0022] - in a third step, a first measuring process by the pressure sensor is carried out, which has a pressure measurement for determining the static pressure level,

[0023] - in a fourth step, the opening of the shut-off valve is carried out,

[0024] - in a fifth step, the pump is activated in order to deliver a defined delivery quantity of gas in the range from 50 ml / min up to 100 ml / min from the breathing mask through the measuring gas line into the monitoring system to the sensor mechanism; the check and monitoring of the delivery quantity takes place here by means of a flow measurement by means of a flow sensor,

[0025] - in a sixth step, a further measuring process by the pressure sensor is carried out, that is to say a pressure measurement for determining the dynamic pressure level is carried out,

[0026] - in a seventh step, a determination of the difference is carried out using the pressure measurement values of the first pressure measurement and the further pressure measurement.

[0027] The difference thus determined represents an offset pressure level and can be provided and used as a calibration value for monitoring the further operation of the system when the aircraft is in use. In an alternative construction of the sequence of steps of the measurement operation, in the third, fifth and sixth steps, the static and dynamic pressure levels and / or the flow rate can be detected by the control unit in synchronism with the breathing of the pilot, the pilot or the co-pilot using measurement technology. In this way, the pressure measurement and / or the flow measurement can be carried out, preferably, during an inhalation or exhalation pause.

[0028] In a preferred embodiment, the control unit can be configured, when carrying out the measurement operation for determining the pressure in the breathing mask, to take into account information on the breathing phase of the pilot of the aircraft when detecting and / or determining the static pressure measurement value and / or the dynamic pressure measurement value using measurement technology. It is advantageous to detect the pressure measurement value using the detection of the measurement value during a pause between inhalation and exhalation in synchronism with the breathing, since in such a pause, no pressure effects of superimposed static and / or dynamic pressure levels due to the breathing can alienate or influence the pressure measurement value. By means of the breathing phase information, a synchronization with the breathing can be carried out by the control unit on the basis of the concentration changes of carbon dioxide and / or oxygen detected using measurement technology in the monitoring system. The physiological concentration difference of the oxygen content in the breathing gas between inhalation (21%) and exhalation (16%) and the concentration difference of the carbon dioxide content between exhalation (~5%) and inhalation (<1%) can be used by the control unit for determining the breathing phase. In the absence of such a synchronization of the pressure measurement, an appropriate signal filtering (for example by means of a low-pass filter) or averaging (preferably smoothing) of the measurement values of the pressure sensor is meaningful for the signal processing in order to remove the share of the breathing or the breathing frequency from the pressure measurement values.

[0029] Thus, in a particularly preferred embodiment it can be provided that the control unit, together with the signal processing device, is configured to determine the static and / or dynamic pressure measurement values, with removal of the signal fraction induced by the pilot's breathing by means of signal filtering, using appropriate signal filtering. In an advantageous manner, in the case of the use of a changeover valve during the time of determination of the mask pressure, a gas analysis of the cabin air can be carried out. For example via a data interface, a pre-defined value (desired value), a reference value can be provided by an external system as a threshold value for the breathing mask pressure. On the basis of this value, the monitoring system can then determine an alarm condition when the threshold value is exceeded or not reached and provide a corresponding alarm signal and / or data. For example, this provision can take place wired, wirelessly by means of radio transmission to an external system, wirelessly by means of infrared transmission to an external system. Other possibilities for alerting the pilot can be able to be realized by means of a visual, optical or acoustic signaling system, for example a lamp, a light-emitting diode, a display unit, a loudspeaker, a buzzer, a horn or similar elements. Another possibility for alerting the pilot can be given haptically, for example in the form of a vibration alarm.

[0030] Further embodiments can show how further environmental parameters can be determinable by the control unit in addition to the mask pressure. Belonging to the environmental parameters during the operation of the aircraft or flying machine are, for example:

[0031] - the ambient pressure outside the cockpit or cabin of the aircraft or flying machine

[0032] - the ambient temperature inside the cockpit or cabin of the aircraft or flying machine

[0033] - the gas composition inside the cockpit or cabin of the aircraft or flying machine

[0034] - the absolute and / or relative humidity inside the cockpit or cabin of the aircraft or flying machine

[0035] - the density and / or ambient pressure inside the cockpit or cabin of the aircraft or flying machine

[0036] - the ambient temperature inside the cockpit or cabin of the aircraft or flying machine

[0037] - the gas composition inside the cockpit or cabin of the aircraft or flying machine

[0038] - the ambient pressure outside the cockpit or cabin of the aircraft or flying machine

[0039] - the ambient temperature outside the cockpit or cabin of the aircraft or flying machine

[0040] - gas composition outside the cockpit or cabin of an aircraft or flying machine

[0041] - absolute and / or relative humidity outside the cockpit or cabin of an aircraft or flying machine

[0042] - density and / or ambient pressure outside the cockpit or cabin of an aircraft or flying machine

[0043] - ambient temperature outside the cockpit or cabin of an aircraft or flying machine

[0044] - gas composition outside the cockpit or cabin of an aircraft or flying machine

[0045] - pressure level, pressure change profile, pressure time profile, pressure difference, pressure fluctuations in the breathing gas, breathing gas mixture or in the breathing air in the supply to the aircraft pilot, co-pilot or flight crew,

[0046] - pressure level, pressure change profile, pressure difference, pressure fluctuations in the breathing gas, breathing gas mixture or in the breathing air in the provision of on-board equipment (e.g. gas cylinders, pressurized oxygen bottles, air intake devices, gas treatment devices, filter devices).

[0047] In at least some embodiments, the control unit can be configured to take at least one situational parameter into account in the course of the examination of the measurement-technological monitoring and / or to incorporate at least one situational parameter into the course. Situational or current situational parameters are to be understood as being the conditions and / or states derived from the conditions during the operation of the aircraft or flying machine.

[0048] Examples of this are, for instance:

[0049] - direction of flight

[0050] - flight altitude

[0051] - flight axis position

[0052] - flight attitude, for instance, inverted flight, turning flight, dive, descending flight, climb

[0053] - flight speed

[0054] - direction of flight

[0055] - horizontal acceleration

[0056] - vertical acceleration

[0057] - yaw angle or roll angle

[0058] - remaining reserves of oxygen or air

[0059] - a remaining reserve of compressed oxygen or compressed air.

[0060] In some embodiments, the monitoring system can have a data interface. The data interface can be configured as a unidirectional or bidirectional data interface and can be configured, for example, for data provision, data reception, data exchange or for communication with components of the aircraft or spacecraft. In at least some embodiments, the monitoring system and / or the control unit can receive and / or provide situational and / or environmental parameters by means of the data interface. In at least some embodiments, the situational and / or environmental parameters can be detected by means of measurement technology by means of further sensors of the sensor arrangement in or on the monitoring system and can be provided to the control unit. For this purpose, in addition to the sensor for detecting oxygen and / or carbon dioxide by means of measurement technology, further gas sensors for detecting carbon monoxide by means of measurement technology can also be employed in the sensor arrangement, and further gas sensors, for example in the form of electrochemical gas sensors, catalytic gas sensors, optical, infrared optical gas sensors, photoionization gas sensors, solid electrolyte gas sensors or semiconductor gas sensors, can also be employed in order to monitor the respiratory gas in respect of further substances, such as, for example, hydrocarbons, residues or products of combustion processes, in addition to the concentration of oxygen and carbon dioxide detected by means of measurement technology. A pressure sensor can also be provided as a further sensor in the sensor arrangement, which can be configured to detect the ambient pressure from the environment, in particular the pressure or density inside and / or outside the cockpit or cabin of the aircraft or spacecraft, by means of measurement technology and to provide them to the control unit. A further sensor in the sensor arrangement can be a temperature sensor, which can be configured and arranged to detect the ambient temperature of the environment, in particular the temperature inside and / or outside the cockpit or cabin of the aircraft or spacecraft, by means of measurement technology and to provide them to the control unit. A further sensor in the sensor arrangement can be a humidity sensor for detecting the absolute or relative humidity of the environment, which can be configured and arranged to detect the humidity in the environment, in particular the humidity inside and / or outside the cockpit or cabin of the aircraft or spacecraft, by means of measurement technology and to provide it to the control unit.

[0061] In some embodiments, further sensors on / in the sensor arrangement in the monitoring system can be provided for detecting data for determining the context parameters, or can be assigned to a sensor arrangement which enables the control unit to determine the current flight situation with the flight altitude, the flight direction, the flight speed, the flight acceleration, the flight attitude with the orientation in space and the flight situation or the flight operation (e.g. climbing, descending, turning flight, landing approach, take-off). For this purpose, for example, pressure sensors, acceleration sensors, altitude sensors, compass sensors, gyroscopic sensors, humidity sensors, temperature sensors are arranged on or in the sensor arrangement, or are assigned to the sensor arrangement.

[0062] In some embodiments, the sensor arrangement can be arranged in or on the breathing mask very close to the mouth / nose region. Depending on the flow-technical conditions at the mouth / nose region, in this case the active transport of breathing gas to the sensor arrangement can be partially dispensed with. The breathing gas reaches the sensor arrangement passively, that is to say by diffusion from the mouth / nose region in the mask towards the sensor arrangement. In a particular construction, it can be possible to integrate the sensor arrangement into the breathing mask or into or at a component of the breathing mask. Due to the technical developments in the field of chip and / or MEMS technology, miniaturization of the elements of electrochemical, catalytic or semiconductor sensor arrangements can be expected in the near future, which in turn can enable the direct integration of the sensor arrangement, preferably with oxygen sensor arrangements, carbon dioxide sensor arrangements and further gas sensors, as well as additional and optional pressure sensor arrangements and / or temperature sensor arrangements, at the measurement site.

[0063] In some embodiments, a further gas port can be provided on the module for gas transport. The further gas port enables the connection and supply of a large amount or a partial amount of gas or ambient air from the cabin or cockpit towards the monitoring system. Via a reversing valve, for example a two-position three-way valve, or a system of valves, it is possible to selectively supply gas, from the ambient air or from the mouth / nose region of the aircraft pilot, co-pilot or flight attendant, for example from a breathing mask, to the pump or to the module for gas transport.

[0064] In some embodiments, a further pump can be provided and arranged in such a way that a pump is provided and arranged for transporting gas, ambient air or a partial amount of gas, towards the oxygen measurement module and / or the carbon dioxide measurement module or towards the oxygen sensor and / or the carbon dioxide sensor, and a further pump is provided and arranged for transporting gas, a partial amount of gas of the mouth / nose region of the pilot, the pilot or the co-pilot, for example from a breathing mask, towards the oxygen measurement module and / or the carbon dioxide measurement module or towards the oxygen sensor and / or the carbon dioxide sensor. Thereby, in such embodiments, a changeover valve, for example a two-position three-way valve, or a system of valves for switching between the partial amount of breathing gas can be dispensed with.

[0065] In some embodiments, the control unit can be configured to check the module for gas transport. Checking the module for gas transport can here comprise activation, deactivation, setting, control or regulation of the module for gas transport. Setting can in particular comprise setting of the rotational speed, the delivery volume and / or the pressure level, for example by means of optical or electrical control signals (CAN bus, PWM) or electrical control voltages. In a variant of such an embodiment, based on the detection of the gas concentration measurement and / or the pressure measurement, for example also based on the pressure difference between the mask and the cockpit, a determination can be made as to whether a leak is present in the measurement gas line.

[0066] In some embodiments, the control unit can furthermore be configured to take at least one environmental parameter or at least one situational parameter into account in the checking of the module for gas transport and / or to incorporate the at least one environmental parameter or at least one situational parameter into the checking. Such taking into account can in particular comprise adapting the activation, deactivation, rotational speed, delivery volume and / or pressure level of the module for gas transport. Thereby, it can be possible to deactivate the module for gas transport during a determined flight operation, for example during a climb, descent or turn flight, and / or to activate the module for gas transport with an increased delivery volume, if necessary, after the end of the operation.

[0067] In at least some embodiments, the monitoring system and / or the control unit can be configured for determining and / or recognizing an alarm condition and for organizing an alarm or for triggering an alarm and / or for providing an alarm signal. Depending on the measured values of the sensor device and / or on the information provided by means of the data interface, the control unit can determine and / or recognize an alarm condition and can trigger an alarm and / or provide an alarm signal, for example at the data interface or at another data interface. The alarm can be carried out as a visual and / or acoustic and / or haptic alarm. For example, a visual alarm can be carried out in the form of a white and / or colored light-emitting means (LED, strobe light) or a text output (LCD, LED, display). Such an alarm can also be carried out visually by means of suitable devices for visualization on or in the face mask or breathing mask, for example as a graphic on an in-mask display or a head-up display. An acoustic alarm can be carried out, for example, in the form of a voice output or by means of an acoustic alarm generator (horn, siren). A haptic alarm can be carried out, for example, in the form of a vibration alarm on the aircraft's equipment, for example the seat surface, the control elements (foot pedals, hand grips), and the pilot's, the pilot's or the co-pilot's accessories (breathing mask, breathing hose) or clothing (suit, vest, parachute, shoes).

[0068] In some embodiments, the control unit can take into account and / or incorporate environmental parameters and / or situational parameters in the organization of the alarm and / or in the provision of the alarm signal when organizing an alarm or triggering an alarm. In this way, it can be possible, in an advantageous manner, to present the pilot, the pilot or the co-pilot with relevant and prioritized alarm information in a uniform or compact manner with respect to the conditions in the reference environment (temperature, gas composition in the outside air) and the conditions detected by means of the measurement technology in the breathing gas in the context of the use or operating situation of the aircraft (take-off phase, landing approach, in-flight refueling, descent, turning flight, climb). In a particular construction, the control unit can take into account and / or incorporate environmental parameters and / or situational parameters in the adaptation of the signal processing when performing signal processing and / or signal filtering of the measured values of the sensor device.

[0069] In some embodiments, the control unit can use predetermined threshold values when organizing an alarm, which can be stored in a data memory of the monitoring system for determined values of the gas concentration, in particular of the oxygen or carbon dioxide or carbon monoxide concentration.

[0070] In some embodiments, on the basis of current and temporally past concentration measurements, in the form of a trend monitoring of oxygen and carbon dioxide, and by means of a suitable decision matrix or an algorithm specifically adapted to the problem, a learning-capable or self-learning algorithm (SVM, Random Forest, AI, Deep-Learning, PCA), the control unit can apply a warning system for the recognition of hypoxia, with an alarm management adapted thereto for the onset of an emerging hypoxia if necessary. In a particular design, the control unit can take environmental parameters and / or situational parameters into account here. In a particular design, in the warning system for the recognition of hypoxia, the control unit can take physiological data of the pilot, the aircraft driver, the pilot, the co-pilot, for example by means of a data interface or provided by a measurement system assigned to the monitoring system, for example EKG, heart rate, heart rate variability, blood oxygen saturation, body temperature, into account here.

[0071] In some embodiments, such a module, like a gas measurement module, a measurement module, a module for ambient or environmental analysis, can have at least one energy store, for example a primary cell or a rechargeable battery. As a rechargeable battery type, for example, a lithium-ion battery type, a nickel-hydrogen battery type or a nickel-cadmium battery type is known. As a primary cell type, for example, an alkaline manganese battery type, a silver oxide zinc battery type, a lithium battery type, an aluminum-air battery type is known.

[0072] In embodiments having a rechargeable battery, a battery charging system and / or a battery management system for monitoring the battery charging and / or the battery status and an interface for supplying the battery charging system and / or the battery management system with charging electrical energy can mostly additionally be integrated into the monitoring system. The battery management system mostly has an interface for external communication in order to be able to provide data or information of the battery status, for example; such an interface can be constructed as a wired interface (for example CAN bus), a contactless interface (for example RFID, NFC), a wireless interface (for example Bluetooth) or an infrared-optical interface (for example IrDA). Additionally, such a module, like a gas measuring module, a measuring module, a module for ambient or environmental analysis, can have further components, input and output interfaces, a user interface (User- Interface) to at least one operating element and / or at least one display element, such as for example components for signal detection (ADµC), signal amplification, for analog and / or digital signal processing (ASIC), for analog and / or digital signal filtering (DSP, FPGA, GAL, µC, µP), signal conversion (A / D converter), for checking, controlling, regulating (µC, µP), for flow control for operation and for user interaction (µC, µP). At least one operating element and at least one display element can be arranged in or on the monitoring system or can be assigned to the monitoring system.

[0073] In some embodiments, by means of at least one operating element, the user can be enabled to, for example, operate the start (activation) or the end (deactivation) of the monitoring system, select between different operating modes of the monitoring system, execute a maintenance, adjustment or calibration method.

[0074] In some embodiments, by means of the at least one display element, the user can be informed about events, conditions, current measured values and / or measured values in the past in time, which have been detected and provided by means of sensors or measuring modules, in particular oxygen sensors and / or carbon dioxide sensors or oxygen measuring modules and / or carbon dioxide measuring modules, by means of measurement technology. By means of the display element, the user can also be provided with measurement variables derived from the measured values, such as, for example, maximum values or minimum values, average values, trends, statistics, events, alarm conditions. Furthermore, by means of the display element, the user can be given general information about the current operating state of the monitoring system, such as the battery charge status, the battery remaining life, maintenance information, information about the monitoring system itself, such as the type, name, variant, version, serial number, first put into service, upcoming maintenance intervals, status data, operating state (Ready, In-OP, Stand-by), faults, fault memory and information about the operating instructions.

[0075] In some embodiments, the display element can be configured as a graphical user interface (GUI).

[0076] In addition to the display element, in some embodiments, an input element can also be provided. The input element can be configured as a mechanical or touch-sensitive button or switch, a rotary or slide control, and in the form of a graphical user interface (GUI). In some embodiments, the display element can be implemented in combination with the input element. For example, in a construction with a touch-sensitive display (touch screen), the possibility of a variable design of the display and the possibility of an operation, for example the possibility of using gestures (swiping, dragging), in order thereby to change the display type, for example in order to enlarge or reduce display elements (Zoom-Funktion). The combination of display element and input element can preferably be configured as a graphical user interface (GUI, touchpad).

[0077] In some embodiments, an input element can be provided, which enables a user or user of the monitoring system to initiate, annotate, trigger, start or end a defined condition, a defined action or a state at the monitoring system. Such an input element can be constructed, for example, as an annotation button and / or as an emergency button, which is preferably operable by manual manipulation. Alternatively, an operation with voice commands is also possible, wherein the annotation button and / or the emergency button is then correspondingly constructed with means for voice detection, voice processing and voice recognition with instruction recognition.

[0078] In other alternative embodiments, the input elements can also be supplemented by acceleration sensors or can be constructed by means of such acceleration sensors. For this purpose, for example, the data or measured values of the acceleration sensors can be used by the control unit in order to detect the current flight situation with measurement technology in the monitoring system, which has a flight altitude, a flight direction, a flight speed, a flight acceleration, a flight attitude or a flight operation with an orientation in space and a flight situation, for example a climb, a descent, a turning flight, a landing approach, a takeoff, which are set up as further sensor means on / in the sensor means in the monitoring system for detecting data for determining the situational parameters. Alternatively, additional 2-axis or 3-axis acceleration sensors can be arranged in or on the monitoring system, which, in combination with the control unit, assume the function of input elements. By means of the acceleration sensors, movements or deflections of the monitoring system, movements or deflections of the housing of the monitoring system and mechanical, haptic stimuli or haptic excitations acting on the acceleration sensors can be detected in a sensor manner and can be provided as measured values or data to the control unit. As a force action, energy or force supply (Energie- oder Kraftzuführung) in at least one of the directions or axes towards which a force action, an energy or a force supply in the form of a pressure application, a tapping action (Push, Hit, Tapping) by means of hand movements can be effected on the monitoring system, the acceleration sensors are supplied with mechanical or haptic stimuli or excitations by the aircraft pilot, the pilot or the co-pilot. This can be achieved particularly advantageously for the aircraft pilot, the pilot or the co-pilot if the monitoring system is arranged as a mobile module in a closed pocket in a garment or on a garment, for example on or in a vest, a jacket or a suit. Thus, the force supply can be carried out as an operating activity through the garment onto the acceleration sensors in the monitoring system. The use of the acceleration sensors as input means or input elements makes it possible to operate or manipulate the monitoring system in use by the aircraft pilot, the pilot or the co-pilot when he cannot reach other input elements on the monitoring system constructed as a mobile module. This is the case, for example, when the monitoring system is arranged as a mobile module in a pocket in a garment or on a garment. Thus, the acceleration sensors provide an alternative for operating the monitoring system by means of manual pushbuttons or manual switch elements. For evaluating the measured values or data of the acceleration sensors, the control unit can be used, but an additional unit can also be provided, which is equipped in the monitoring system for detecting and evaluating the data of the acceleration sensors. This evaluation of the data of the acceleration sensors is basically based on a time measurement.By means of a time measurement in combination with a threshold value of the measured values or data of the acceleration sensor, an evaluation can be made in terms of the duration of the haptic excitation and in terms of the duration between two or more haptic excitations of the acceleration sensor. In an exemplary configuration, the control unit can be configured to recognize, by means of a comparison with a threshold value, a first force action or force supply to the acceleration sensor from the measured values or data of the acceleration sensor. If the measured values of the acceleration sensor are exceeded for a first predetermined duration in view of a predetermined threshold value, the control unit interprets this situation as a first force action in at least one of the directions or axes which are detectable by the acceleration sensor in a sensorial manner. Thereby, an indication of the start of an input activity of the aircraft pilot is given by means of the hand movement as an input process. If the measured values of the acceleration sensor are again exceeded for a second predetermined threshold value in a second predetermined period of time immediately thereafter, the control unit interprets this situation as an end of the first force action. If the measured values of the acceleration sensor are then exceeded in view of the first predetermined threshold value for the first predetermined duration thereafter, the control unit interprets this situation as a further force action in at least one of the directions or axes which are detectable by the acceleration sensor in a sensorial manner. Thereby, an indication of the continuation of the input activity of the aircraft pilot is given. If it is derived immediately thereafter that the measured values or data of the acceleration sensor do not reach the second predetermined threshold value within the second predetermined period of time, the control unit interprets this situation as an end of the further force action. If no further force action to the acceleration sensor is detected and recognized further within a fourth predetermined duration, an indication of the end of the input activity of the aircraft pilot is given. With this type of evaluation, the control unit is configured and is able to detect and recognize an input activity of a "double tap" by means of a hand movement of the aircraft pilot by means of an evaluation of the measured values of the acceleration sensor in terms of the first, second threshold values and the first, second, third, fourth durations in the monitoring system operation and can trigger further actions in the monitoring system or on the monitoring system on the basis thereof subsequently. Such an action can correspond, for example, in terms of the mode of action to the function of a note button and / or an emergency button.

[0079] In some embodiments, the construction of the control unit can be extended with respect to the evaluation beyond the "double tap" in order to also enable an input by means of a "triple tap" and / or a "quadruple tap". In this way, a simple coding of the input accomplished by means of the acceleration sensor is obtained, which makes it possible for the control unit to distinguish between different input situations by means of the difference between a "double tap", a "triple tap" or a "quadruple tap". In principle, it is also possible to construct an input of a "single tap", in which the duration of the excitation indicating the "single tap" can be specified in such a way that a confusion with other excitations of the aircraft pilot, the aircraft or the other crew members is not possible.

[0080] In some embodiments, the construction of the control unit can also incorporate the differences in the duration between the tactile excitations of the acceleration sensor into the evaluation in addition to the evaluation of the duration of the tactile excitation. These differences can then be used by the control unit, in addition to the evaluation of the form of the "multiple tap", for example by means of the distinction between a "short pause" and a "long pause" as the duration between the tactile excitations of the acceleration sensor, to increase the number of events that can be distinguished from one another. Thus, by means of this variation in the length of the pause, a Morse code is obtained in the evaluation of the tactile excitation, which is a further possibility for coding events by means of the acceleration sensor as input element.

[0081] Thus, a plurality of possibilities and advantages are obtained by means of the fact that, for example, during a flight operation, the aircraft pilot, the pilot or the co-pilot can manually initiate a measurement operation, can set an entry (annotation) in a logbook or a time marker, or can mark a particular health condition, for example a feeling of dizziness, while using the acceleration sensor as input element when distinguishing between different input situations using the assignment to the assignment relationship (Zuordnung) of the operation or action triggered using the input, without having to operate a key or a switch on the monitoring system in visual contact with the monitoring system. The measurement operation can be given, for example, by means of a measurement operation for determining the static and dynamic pressure levels in the pneumatic system, or by means of a measurement operation for activating a changeover valve for detecting the gas concentration in the cabin.

[0082] In some embodiments, a data memory for storing measured values of measured variables derived from the measured values, such as, for example, maximum or minimum values, average values, trends, statistics, events, alarm conditions, can be arranged in or on the monitoring system or can be assigned to the monitoring system. Such a data memory can be configured as a volatile or non-volatile memory (RAM, ROM, EEPROM) and can be configured both as a fixed component of the monitoring system and as a removable and / or portable storage module (USB-Stick, SD-Card). The data memory can be used for data logging or data storage of inputs made by means of the input elements and, for this purpose, can provide a logbook, a flight recorder function. Here, in an advantageous manner, in a construction scheme with tables, lists, data sets, the logbook can receive evaluations of gas concentration measurements, flow measurements, pressure measurements, temperature measurements in a time-varying process with a temporal assignment and a marking (annotation) by means of the input elements and hold or provide them for a simultaneous or subsequent evaluation. At the time of entering an event, the measurement values or measurement signals of an acceleration sensor can be consulted in order to place the respective measurement values or measurement signals in the context of the flight situation or the flight operation at the time of the marking / notation by the pilot in the logbook for a real-time or post-mortem evaluation. At the time of entering an event, the measurement values or measurement signals of an altitude sensor can be consulted in order to place the respective measurement values or measurement signals in the context of the flight situation (flight altitude) at the time of the marking / notation by the pilot in the logbook for a real-time or post-mortem evaluation. At the time of entering an event, the measurement values or data of a gas sensing mechanism can be consulted in order to place the respective measurement values or data in the context of the gas supply (C02, 02) at the time of the marking / notation by the pilot in the logbook for a real-time or post-mortem evaluation.

[0083] In some embodiments, the control unit can be configured to take into account and / or incorporate environmental and / or situational parameters in the adaptation of the signal processing when performing signal processing and / or signal filtering of the measurement values of the sensing mechanism.

[0084] In some embodiments, the control unit can be configured to use predetermined threshold values for the organization of an alarm, which predetermined threshold values can be stored in a data memory of the monitoring system for determined values of the concentration of the gas, in particular oxygen or carbon dioxide, carbon monoxide.

[0085] In some embodiments, the control unit can be configured to apply a warning system for identifying hypoxia based on current and temporally past measurement values of the sensor system, for example in the form of

[0086] - by means of a decision matrix

[0087] - or by means of a specifically adapted algorithm

[0088] - or by means of a learning-capable or self-learning algorithm (for example: SVM, random forest, AI, deep learning, ICA, PCA)

[0089] In some embodiments, the control unit can be configured to apply a warning system for identifying hypoxia based on current and temporally past measurement values of the sensor system, for example in the form of

[0090] In some embodiments, the control unit can be configured to apply a warning system for identifying hypoxia based on current and temporally past measurement values of the sensor system, for example in the form of

[0091] In some embodiments, the control unit can be configured to apply a warning system for identifying hypoxia based on current and temporally past measurement values of the sensor system, for example in the form of

[0092] Other embodiments propose a method for operating a monitoring system.

[0093] In some embodiments of the method for operating a monitoring system, in a first step, the sensor system of the monitoring system is activated by means of the control unit, in a second step, the data storage is prepared by means of the initialization of the data memory. In a third step, the measurement values of the sensor system of the monitoring system are detected by means of the measurement technology using the time control. In a fourth step, the measurement value data are stored in the data memory using the associated time information. The third and fourth steps are continued by the control unit until the method for operating the monitoring system ends.

[0094] In some embodiments of the method for operating a monitoring system, it can be possible to store additional situational and / or environmental parameters when storing the measurement value data of the sensor system in the data memory using the associated time information.

[0095] In some embodiments of the method for operating a monitoring system, it can be possible to additionally detect the measurement values of the sensor system at the moment of activating the input element (independently of the time control) when the input element is activated by the user. BRIEF DESCRIPTION OF DRAWINGS

[0096] Further refinements of the application result from the subsequent description of several embodiments of the application, which are shown in the drawings. All features and / or advantages resulting from the claims, the description or the drawings, including structural details and spatial arrangements, can be important to the application, not only individually but also in different combinations. Respectively schematically:

[0097] - Figure 1a 、 1b A monitoring system with a sensor mechanism is shown,

[0098] - Figure 2a and 2b A monitoring system with a measuring function for oxygen and carbon dioxide is shown according to Figure 1a 、 1b ,

[0099] - Figure 3 An expanded version of the variant of the monitoring system according to Figure 1a 、 1b , 2a, 2b is shown,

[0100] - Figure 4 and Figure 5 Two variants of the monitoring system with other sensor mechanisms are shown according to Figure 1a 、 1b , 2a, 2b, 3,

[0101] - Figure 6 A variant of the monitoring system is shown according to Figure 3 ,

[0102] - Figure 7 Another variant of the monitoring system is shown according to Figure 3 ,

[0103] - Figure 8 An alternative variant of the monitoring system is shown according to Figure 6 ,

[0104] - Figure 9 A flowchart for determining the pressure of a breathing mask is shown. DETAILED DESCRIPTION

[0105] Figure 1a 、 1b A monitoring system 100 is shown, which is connected with a measuring gas line 10 to a breathing mask 20 of a person 99. Figure 1a 、 1b The same elements in Figure 1a 、 1bThe same reference numerals are used to identify them. In Figure 1, person 99 represents the pilot (pilot, co-pilot) or passenger of an aircraft, particularly a jet aircraft. The breathing mask 20 has an air inlet 21, a connecting element 23, and hoses 24, 25. The hoses 24, 25 are used to transport and supply breathing gas to person 99. Figure 1a In the diagram, the flexible tubing is shown as two separate flexible tubing lines 24 and 25. However, as in... Figure 1b As shown, an embodiment with connecting element 23' is also possible, wherein only one hose line 25 exists for the supply of breathing gas for inhalation, while exhalation is performed to the environment 5 via the exhalation valve 29 in the breathing mask 20. Another possibility is given by utilizing a coaxial hose system, which has two hose lines 24, 25 as a shared element. For clarity of illustration, in Figure 1a The remaining figures do not show the continuation and supply of breathing gas, nor the necessary components or elements in the aircraft or flight vehicle for providing breathing gas. The monitoring system 100 includes: an operating element 40, a display element 44, at least one module 50 for gas delivery, and a sensing mechanism 60 with at least one sensor 66. The module 50 for gas delivery is preferably configured as a pump P. M More preferably, the pump P is configured as a piezoelectric pump. M In addition, the monitoring system 100 has a control unit 70.

[0106] The operating element 40, display element 44, sensing mechanism 60, and gas delivery module 50 are connected to the control unit 70 via signal and data lines or control lines. For example, these control lines or signal and data lines can be configured as a bus system (CAN) or a network. For clarity of illustration, these control lines or signal and data lines are... Figure 1a Other figures not shown. The control unit 70 is configured and set to inspect and / or operate the module 50 for gas delivery, enabling the delivery of breathing gas from the breathing mask 20 through the measuring gas line 10 and gas inlet 51 to the sensing mechanism 60. Thus, a large or partial quantity of breathing gas is then available to at least one sensor 66 in the gas sensing mechanism 60 to detect and / or analyze the large or partial quantity of breathing gas using measurement techniques, and to provide the large or partial quantity of breathing gas as a measurement value to the control unit 70. The control unit 70 enables the evaluation, processing, and display of the measurement value on at least a portion of the display element 44.

[0107] Figure 2a , 2b The following characteristics are shown as evidence. Figure 1a ,1b The monitoring systems 100 and 110: Sensor 66 in sensing mechanism 60 is configured as oxygen sensor 68, and another sensor as carbon dioxide sensor 64 is also arranged in sensing mechanism 60. Figure 1a , 1b The same components in 2a and 2b Figure 1a , 1b The same reference numerals are used to indicate the same information in 2a and 2b. Figure 2b It shows according to Figure 2a A variant 110 of the monitoring system, which includes an oxygen sensor 68 and a carbon dioxide sensor 64, is provided in which the monitoring system 110 is directly mounted on the breathing mask 20 without the measurement gas tubing 10, or is incorporated as part of the breathing mask 20. Here, it is possible to omit, if necessary, the following... Figure 1a , 1b Pump P in variant scheme 2a M The pump P M This is used to deliver a large volume of breathing gas from the breathing mask 20 to the sensing mechanism 60. Alternatively, in cases where a large volume of gas also needs to be delivered from the cabin or cockpit to the sensing mechanism, in accordance with... Figure 2b The optional pump 56 is also arranged within or at the sensing mechanism in the layout. For clarity of illustration, the layout of this optional pump 56 in the monitoring system 110 is not shown together. Figure 2b The image shows an energy storage device 85 as an example, and it should be understood in similar construction schemes as being based on... Figure 1a , 2a Optional components of construction schemes 3, 4, and 5. (Constructed as a primary battery, a rechargeable battery, or a rechargeable battery) This energy storage device 85 is appropriately constructed to supply power to monitoring systems 110 and 108. Figure 4 ), 109 Figure 5 ), 100 ( Figure 1a , Figure 1b , Figure 2a , Figure 3 A variety of components (60, 70, 40, 44, 75) supply electrical energy. Figure 1b The diagram illustrates an alternative configuration with additional display elements 45 arranged at or within the face mask 20, which should also be understood in similar configurations as... Figure 1a , 2aFig. 4 shows a further display element 45, which is an optional component of the constructional solution of Fig. 3, 4, 5. By means of (not shown for reasons of clarity) signal or data lines, the further display element 45 is connected to the control unit 70. The further display element 45 can be employed in addition to or alternatively to the display element 44. The constructional solution of the further display element can be realized, for example, in the form of an in-mask display or a head-up display. Figure 2a Additionally, a data interface 90 is shown, which can be configured, on the one hand, to receive data from the outside and then to provide these data to the control unit 70. For reasons of clear illustration, data lines belonging to the data interface are not shown in Figure 2a Fig. 1 and in the other figures. On the other hand, by means of the data interface 90, for example, measurement values of the monitoring system 100 or of the sensor mechanism 60 can be provided to the outside. In this way, via the data interface 90, current environmental parameters or situational parameters for the condition of the aircraft or spacecraft can be received (for example, from components of the aircraft or spacecraft) and can be provided to the control unit 70 for consideration in the processing of the measurement values and / or in the checking of the pump P M 50. Furthermore, by means of the data interface for components of the aircraft or spacecraft, measurement values and / or measurement variables or parameters derived from the measurement values and information or status data can be provided by the control unit 70. In this way, for example, it is possible to display measurement values and / or measurement variables or parameters derived from the measurement values and information or status data on external display elements of the aircraft or spacecraft. The data interface can be configured unidirectionally or bidirectionally, for example, can be wired (CAN bus, LAN, Ethernet, RS485, NMEA 183) or wireless (WLAN, Bluetooth, NFC). As current environmental parameters for the environmental condition of the aircraft or spacecraft, for example, the following are to be mentioned:

[0108] - ambient pressure outside the cockpit or cabin of the aircraft or spacecraft

[0109] - ambient temperature inside the cockpit or cabin of the aircraft or spacecraft

[0110] - gas composition inside the cockpit or cabin of the aircraft or spacecraft

[0111] - absolute and / or relative humidity inside the cockpit or cabin of the aircraft or spacecraft

[0112] - density and / or ambient pressure inside the cockpit or cabin of the aircraft or spacecraft

[0113] - Ambient pressure outside the cockpit or cabin of the aircraft or flying machine

[0114] - Gas composition inside the cockpit or cabin of the aircraft or flying machine

[0115] - Ambient pressure outside the cockpit or cabin of the aircraft or flying machine

[0116] - Ambient temperature outside the cockpit or cabin of the aircraft or flying machine

[0117] - Gas composition outside the cockpit or cabin of the aircraft or flying machine

[0118] - Absolute and / or relative humidity outside the cockpit or cabin of the aircraft or flying machine

[0119] - Density and / or ambient pressure outside the cockpit or cabin of the aircraft or flying machine

[0120] - Ambient temperature outside the cockpit or cabin of the aircraft or flying machine

[0121] - Gas composition outside the cockpit or cabin of the aircraft or flying machine

[0122] - Pressure level, pressure change process, pressure time change process, pressure difference, pressure fluctuations in the breathing gas, breathing gas mixture or in the breathing air in the supply to the aircraft pilot, co-pilot or flight crew,

[0123] - Pressure level, pressure change process, pressure difference, pressure fluctuations in the provision of on-board equipment (e.g. gas tank, pressurized oxygen bottle, air intake device, gas treatment device, filter device, gas delivery device) for breathing gas, breathing gas mixture or breathing air.

[0124] For example, as situational or current situational parameters for the condition of the aircraft or flying machine, mention can be made of:

[0125] - Flight direction

[0126] - Flight altitude

[0127] - Flight axis position

[0128] - Flight attitude, for example, for example, inverted flight, turning flight, dive, descending flight, climb

[0129] - Flight speed

[0130] - Flight direction

[0131] - Horizontal acceleration

[0132] - Vertical acceleration

[0133] - Yaw angle or roll angle

[0134] - Remaining reserves of oxygen or air

[0135] - Remaining reserves of compressed oxygen or compressed air.

[0136] Figure 3 The following characteristics are shown as evidence. Figure 1a , 1b 2a Monitoring system 100: An input element 80 is arranged on the monitoring system, which has a signal or data connection with the control unit 70. Figure 1a , 1b The same elements in 2a, 2b, and 3 Figure 1a , 1b The same reference numerals are used to indicate these events in reference numerals 2a, 2b, and 3. Through this input element 80, the pilot, operator, or co-pilot can: mark specific events or conditions during flight operations, and mark specific personal (e.g., health) events, conditions, or symptoms (such as fever, palpitations, or dizziness) during the time-varying process of use. This marking can be used by the control unit 70 to combine the event or condition with time information, and then store the combination of time information, event, or condition in the data memory 75. The data memory 75 can be configured as volatile or non-volatile memory (RAM, ROM, EEPROM) and can be arranged in the monitoring systems 100 and 110 as either a fixed component or a removable storage module (USB flash drive, SD card). Figure 2b In or in the monitoring system 100, 110 ( Figure 2b On. For example, by using with Figure 2bThe data interface 90 in a construction variant similar to that shown and described above can also be able to implement the provision of data and / or the exchange of data with an external (not shown in the drawing) evaluation unit. Thereby, the input element 80 can be used to supplement the detected measurement values of the sensing mechanism 60 and the events and conditions of the flight operation with further information and to equip them with time information, for example in the form of a time stamp, which is provided by means of an input element of the aircraft pilot, the pilot or the co-pilot. However, it is also possible to construct the input element as an emergency button which directly enables the aircraft pilot, the pilot or the co-pilot to draw attention to himself in a particular condition out of his perception, for example in a condition with a particular, objectively or subjectively perceived dangerous posture or in a risk condition. For example by means of the data interface 90, the marked measurement values and / or events, conditions can be provided directly to the outside and the particular condition can also be provided directly to the outside and, if necessary, the marked measurement values and / or events, conditions and also the particular condition can be transmitted (also directly (online)) to a ground station or to other aircraft or flying vehicles via the communication system of the aircraft or flying vehicle. Furthermore, by means of the data memory 75 and / or the data interface 90, it is possible to evaluate the marked measurement values and / or events, conditions and the particular condition after use ex post (offline).

[0137] Figure 4 and 5 A variant of the monitoring system 100, 110 according to Figure 1a , 1b , 2a, 2b, 3 is shown, which has further components of the sensing mechanism 60. For reasons of clear illustration, the belonging control lines or signals and data lines for further sensors of the sensing mechanism 60 are not shown in Figure 4 and Figure 5 . Figure 1a , 1b , 2a, 2b, 3, 4, 5 identical elements in Figure 1a , 1b , 2a, 2b, 3, 4, 5 are designated with the same reference signs. These further sensors in the sensing mechanism 60 can be used to determine current environmental parameters within and / or outside the cockpit or cabin of the aircraft or flying vehicle, and / or can be used to determine current situational parameters and conditions, and can be used to determine physical properties, and can be used to further determine the composition of the breathing gas. As further components of the sensing mechanism 60, the following further sensors are exemplarily shown in the monitoring system 108 in Figure 4 , which should also be understood as an alternative possibility for the construction variant of Figure 1a , 1b , 2a, 2b, 3, 5:

[0138] - at least one acceleration sensor 61 in the form of a 2- or 3- axis acceleration sensor (accelerometer)

[0139] - at least one compass sensor 62, for example an electronic compass, a gyrocompass or a fluxgate compass

[0140] - at least one altitude sensor 58

[0141] - at least one gyroscope sensor 63.

[0142] As further components of the sensor system 60, in Figure 5 the following further sensors are exemplarily shown (said further components are also to be understood as optional possibilities for the constructional solution of Figure 1a , 1b 2a, 2b, 3, 4):

[0143] - at least one temperature sensor 69, 69'

[0144] - at least one pressure sensor 67, 67'

[0145] - at least one humidity sensor 59, 59'.

[0146] Further sensors in the sensor arrangement 60 can be embodied as pressure sensors which can be designed and arranged to detect the ambient pressure from the environment, in particular the pressure or density inside and / or outside the cockpit or cabin of an aircraft or flying machine, in a measuring manner and to supply them to the control unit 70. Further sensors in the sensor arrangement 60 can be embodied as temperature sensors which can be designed and arranged to detect the ambient temperature of the environment, in particular the temperature inside and / or outside the cockpit or cabin of an aircraft or flying machine, in a measuring manner and to supply them to the control unit 70. Further sensors in the sensor arrangement 60 can be embodied as humidity sensors for detecting the absolute or relative humidity of the environment, which can be designed and arranged to detect the humidity in the environment, in particular the humidity inside and / or outside the cockpit or cabin of an aircraft or flying machine, in a measuring manner and to supply them to the control unit 70. Further sensors in the sensor arrangement 60 can be embodied as at least one further gas sensor 65 for detecting the gas composition of the environment, which can be designed and arranged to detect the gas composition in the environment, in particular inside and / or outside the cockpit or cabin of an aircraft or flying machine, in a measuring manner and to supply them to the control unit 70. As further gas sensors, electrochemical gas sensors, catalytic gas sensors, optical, infrared optical gas sensors, photoionization gas sensors, solid electrolyte gas sensors or semiconductor gas sensors can be used in order to be able to monitor the respiratory gas not only with respect to the concentration of oxygen and carbon dioxide but also with respect to other substances, such as, for example, carbon monoxide, hydrocarbons, residues or products of combustion processes. In Figure 4 The reversing valve 55 shown in Fig. 6, which is designed, for example, as a valve module or as a part of a valve module, makes it possible to switch a large quantity or a partial quantity of the gas sample between the gas inlet 51 and the further gas port 52. It is thereby possible, on the one hand, to transport the respiratory gas from the respiratory mask 20 to the sensor arrangement 60 by means of the pump P M 50, but, on the other hand, it is also possible to transport a large quantity of gas or gas mixture from the environment 5 to the sensor arrangement 60 by means of the pump P M 50 and to detect it in a measuring manner by means of the sensor arrangement 60. The reversing valve 55 is checked by the control unit 70. In this way, via the further gas port 52, it is possible to supply external air from outside the aircraft or flying machine or to supply internal air from the cabin or cockpit of the aircraft or flying machine, and it is possible, alternately, in the case of a check by the control unit 70, to monitor the gas concentration in the respiratory mask 20, the cockpit, the cabin or the external air.

[0147] In Figure 5The further sensors 59', 64', 68', 69' and the at least one further gas sensor 65' are shown in the monitoring system 109 in addition to the other gas sensors 65 and the sensors 59, 67, 69. The further sensors 59', 64', 68', 69' and the at least one further gas sensor 65' are connected to the further pump P A 56 pneumatically or fluidically. Figure 1a , 1b , identical elements in 2a, 2b, 3, 4, 5 are designated by the same reference signs. The further pump P Figure 1a , 1b , 2a, 2b, 3, 4, 5 are designated by the same reference signs. The further pump P A 56 makes it possible to supply gas from the environment 5 via the further gas port 53, for example to supply external air outside the aircraft or vehicle or internal air from the cabin or cockpit of the aircraft or vehicle. The further pump P A 56 is checked by the control unit 70. In this way, via the further gas port 53, it is possible to supply external air outside the aircraft or vehicle or to supply internal air from the cabin or cockpit of the aircraft or vehicle. In this way, it is possible to monitor the gas concentration in the breathing mask 20 and the gas concentration in the cockpit, cabin or external air at the same time. The further sensors in the sensor system 60 can be configured to detect the current situation of the aircraft or vehicle using measurement technology. In this way, with the aid of the data of an acceleration sensor 61, which is preferably configured as a 3-axis-accelerometer, in combination with a height sensor 58, an altimeter, a gyro sensor 63 and, optionally, the information of a compass sensor 62, it is possible for the control unit 70 to determine the current flight situation and the flight situation or flight operation, for example climb, descent, turning flight, landing approach, take-off, with the flight height, the flight direction, the flight speed, the flight acceleration, the flight attitude with the orientation in space (XYZ orientation).

[0148] Figure 6 A variant is shown in the modification of Figure 3 , in which the pump P M 50 or the module for gas transport is arranged at the gas outlet 49 of the monitoring system 100'. In contrast to the variant shown in Figure 3 , in which there is a pump at the gas inlet of the monitoring system, this has the advantage that no traces or impurities from the pump P M 50 can reach the monitoring system 100', in particular the sensor system 60 with the carbon dioxide sensor 64 and the oxygen sensor 68. Figure 1a , 1b , 2a, 2b, 3, 4, 5, 6 are designated by the same reference signs. The further pump P Figure 1a ,1b The same reference signs are used in Figures 2a, 2b, 3, 4, 5, 6. Preferably, the pump P M 50 is arranged in the vicinity of the pump P M 50 and components that can be required for supplying the gas mass. For this purpose, a pressure sensor 47, a flow sensor 48 and a shut-off valve 57 are arranged in the vicinity of the pump P M 50. The flow sensor 48 serves to check the flow rate delivered by the pump P M 50 using measurement technology. After flowing through the pump P M 50 and the flow sensor 48, the delivered gas mass reaches the environment 5 outside the monitoring system 100'. The pressure sensor 47 is arranged upstream in the gas flow with respect to the shut-off valve 57, so that a pressure measurement can detect the mask pressure in the breathing mask 20 in the closed state of the shut-off valve 57 in the following flowless state, which is then identical to the pressure level at the gas inlet 51 and in the measuring gas line 10. Alternatively, the pressure sensor can also be arranged at the gas inlet in the gas flow, at the measuring gas line 10 or in the vicinity of the gas sensors 60, 64, 68. At the gas inlet 51, a changeover valve 55 is provided, which enables switching of the gas mass or of a partial quantity of the gas mass between the gas inlet 51 and a further gas port 52 in a manner comparable to that described in Figure 4 . Preferably, the changeover valve 55 is configured as a two-position three-way valve. This arrangement makes it possible, on the one hand, to deliver breathing gas from the breathing mask 20 to the sensing mechanism 60 at the gas inlet 51 by means of the pump P M 50, but it is also possible, on the other hand, to deliver a gas mass or a gas mixture from the environment 5 through the further gas inlet 52 to the sensing mechanism 60 by means of the pump P M 50 and to detect the gas mass or the gas mixture using measurement technology by means of the sensing mechanism 60. The changeover valve 55 is checked by the control unit 70. In this way, via the further gas port 52, it is possible to deliver external air outside the aircraft or flying machine, or to deliver internal air from the cabin or cockpit of the aircraft, and alternately, with the checking of the control unit 70, it is possible to monitor the gas concentration in the breathing mask 20, the cockpit, the cabin or the external air. In order to protect the sensing mechanism 60 from moisture and condensation water, which is supplied to the sensing mechanism 60 from the breathing mask 20 by means of the pump P M 50 through the measuring gas line 10, a filter element (HME filter) 54 can be connected in series in the measuring gas line 10 or arranged at the outlet of the changeover valve 55.

[0149] Instead of as in accordance with the Figure 3The input element 80 configured in the form of a switching element in the layout 100 according to Figure 6 The alternative operating or input element or acceleration sensor 61 is thus used to supplement the detected measured values of the sensor mechanism 60 and the events and conditions of the flight operation with further information and to equip them with time information, for example in the form of a time stamp, which is provided by means of the alternative operating or input element or acceleration sensor 61 of the aircraft pilot, the pilot or the co-pilot. However, it is also possible to configure the alternative operating or input element or acceleration sensor 61 as an emergency button, which enables the aircraft pilot, the pilot or the co-pilot directly to introduce himself into the focus in particular conditions out of his perception, for example in conditions with a particularly objectively or subjectively perceived dangerous posture or in a risk situation. For example, by means of the data interface 90, the marked measured values and / or events, conditions can be provided directly to the outside and also the particular conditions, and if necessary (also directly (online) via the communication system of the aircraft or the flying object), the marked measured values and / or events, conditions and also the particular conditions can be transmitted to a ground station or to other aircraft or flying objects. Furthermore, by means of the data storage 75 and / or the data interface 90, it is possible to evaluate the marked measured values and / or events, conditions and also the particular conditions after use retrospectively (offline). Figure 2b

[0150] Partly as a detail view of the area surrounding the gas inlet 51 and different from Figure 6 , Figure 7 ​The following monitoring system 111 is shown: This monitoring system 111 includes a filter element (HME filter) 54 and a pump P arranged in a device at the gas inlet 51. M 50, sensing mechanism 60, pressure sensor 47, flow sensor 48, shut-off valve 57, but no reversing valve for switching between monitoring the pilot's breathing gas and monitoring the cabin air. Figure 1a , 1b The same elements in 2a, 2b, 3, 4, 5, 6, and 7 Figure 1a , 1b The same reference numerals are used to designate the parts 2a, 2b, 3, 4, 5, 6, and 7. The pressure sensor 47 is positioned upstream of the shut-off valve 57 in the airflow, such that pressure measurement can detect the mask pressure in the breathing mask 20 in a subsequently stagnant state with the shut-off valve 57 closed. This mask pressure is then the same as the pressure level at the gas inlet 51 and the pressure level in the measuring gas line 10. Alternatively, the pressure sensor 47 can also be positioned in the airflow near the gas inlet 51, in the measuring gas line 10, or close to the sensing mechanism 60 with the gas sensor.

[0151] Partially as a detailed view of the area surrounding gas inlet 51, and different from... Figure 6 and Figure 7 , Figure 8 The monitoring system 111 shown below has a filter element (HME filter) 54 and a pump P arranged at the gas inlet 51. M 50, sensing mechanism 60, pressure sensor 47, and a directional valve 55 configured as a two-position three-way valve. Figure 1a , 1b The same elements in 2a, 2b, 3, 4, 5, 6, 7, and 8 Figure 1a , 1b The same reference numerals are used to indicate the same items in the attached figures 2a, 2b, 3, 4, 5, 6, 7, and 8. The reversing valve 55 can release the path for the amount of gas from the environment 5 (e.g., the cabin) to the sensing mechanism 60, thereby enabling cabin air monitoring. Simultaneously, the reversing valve closes the path for the amount of gas from the breathing mask 20. (Following the...) Figure 8In this configuration, besides switching between measuring breathing gas and cabin air, the reversing valve 55 also functions as a shut-off valve to perform a measurement operation to determine the pressure in the breathing mask. A pressure sensor 47 is arranged at the gas inlet relative to the reversing valve 55 and the measuring gas line 10, such that pressure measurement can detect the mask pressure in the breathing mask 20 when the reversing valve 55 is in a cabin air detection state. This mask pressure is then the same as the pressure level at the gas inlet 51 and the pressure level in the measuring gas line 10. The reversing valve 55 enables switching between monitoring the pilot's breathing gas and monitoring cabin air.

[0152] Figure 9 The illustration shows the method of using according to Figure 6 The monitoring system 100' determines the breathing mask 20 ( Figure 6 The procedure for measuring pressure levels in (200) Figure 1a , 1b The same elements in 2a, 2b, 3, 4, 5, 6, 7, 8, and 9 are in Figure 1a , 1b The same reference numerals are used to indicate the components 2a, 2b, 3, 4, 5, 6, 7, 8, and 9. Starting from "Start" 201, the components with shut-off valves (flow lock-up valves) 57 (… Figure 6 In the construction scheme of ), the control unit 70 ( Figure 6 Perform the measurement operations in the correct order until completion (210). After "Start" (201), activate pump P. M 50 ( Figure 6 ) Deactivate 202, and in the event of this or a small time delay, shut off valve 57 ( Figure 6 ) Close 203. Therefore, the flow stops in the measuring gas line 10 ( Figure 6 In ), and the sensing mechanism 60 ( Figure 6 This brings the system to a static state. The first measurement process 204, which involves pressure measurement, is used to determine the static pressure level. Immediately afterwards, the shut-off valve 57 ( Figure 6 Turn on 205 and activate pump P in 206. M 50 ( Figure 6 Pump P M 50 ( Figure 6 Starting at a rate defined within the range of 50 ml / min up to 100 ml / min, from the breathing mask 20 ( Figure 6 ) Passing through the measuring gas line 10 ( Figure 6 ) and sensor mechanism 60 ( Figure 6 A large amount of air is drawn in. Here, a flow sensor 48 is used. Figure 6) a flow measurement 207 is carried out in order to check and monitor the delivery quantity. Subsequently, another measurement process 208 of the pressure measurement is carried out in order to determine the dynamic pressure level. From the pressure measurement values of the first pressure measurement 204 and the further pressure measurement 208, a difference value is determined 209, which indicates the current pressure drop on the pneumatic system. Thereupon, the flow of the measurement operation ends 210. The thus determined difference value can then be provided and used when the aircraft is in operation in order to determine the mask pressure when the further operating monitoring system is in operation.

[0153] List of reference signs

[0154] 5 environment, atmosphere, outside air, cockpit or cabin

[0155] 10 measuring gas line

[0156] 20 breathing mask

[0157] 21 gas port at the breathing mask

[0158] 24, 25 hose line

[0159] 23, 23' connection element

[0160] 29 exhalation valve

[0161] 40 operating element

[0162] 44, 45 display element

[0163] 46 wireless interface, radio electrical interface

[0164] 47 pressure sensor

[0165] 48 flow sensor (delta-P-sensor)

[0166] 49 gas outlet

[0167] 50 module for gas delivery, pump P M

[0168] 51 gas inlet

[0169] 52, 53 further gas port

[0170] 54 filter element (HME filter)

[0171] 55 changeover valve, (two-position three-way valve), valve module

[0172] 56 further pump P A

[0173] 57 shut-off valve (flow lock valve)

[0174] 58 altimeter

[0175] 59, 59' humidity sensor

[0176] 60 sensing mechanism

[0177] 61 acceleration sensor

[0178] 62 compass sensor

[0179] 63 gyro sensor

[0180] 64, 64' carbon dioxide sensor

[0181] 65 other gas sensor

[0182] 66 sensor

[0183] 67, 67' pressure sensor

[0184] 68, 68' oxygen sensor

[0185] 69, 69' temperature sensor

[0186] 70 control unit

[0187] 80 input element

[0188] 90 data interface

[0189] 99 person, pilot, aircraft driver

[0190] 100, 100' monitoring system

[0191] 108, 109, 110, 111, 112 monitoring system

[0192] 200 flow of the measuring operation

[0193] 201 start, start (START)

[0194] 202 pump: deactivation

[0195] 203 shut-off valve: closing of the valve

[0196] 204 first pressure measurement: static pressure level

[0197] 205 shut-off valve: opening of the valve

[0198] 206 pump: activation

[0199] 207 flow measurement

[0200] 208 Another pressure measurement: dynamic pressure level

[0201] 209 Determine value of current pressure reduction

[0202] 210 End, stop

Claims

1. Monitoring system (100, 100', 108, 109, 110, 111, 112) for monitoring the gas composition of breathing gas in an aircraft or spacecraft, having a control unit (70), a module for gas transport (50), and a sensor mechanism (60) comprising an oxygen sensor, a carbon dioxide sensor and a flow sensor, characterized in that the module for gas transport (50) has a pump arranged at a gas outlet (49) of the monitoring system (100, 100', 108, 109, 110, 111, 112), which pump is configured to transport a volume or a partial volume of breathing gas from a measurement site of a breathing mask (20) to the sensor mechanism (60) by means of a measurement gas line (10) which constitutes a connection between the measurement site of the breathing mask (20) and a gas inlet (51) of the monitoring system (100, 100', 108, 109, 110, 111, 112), wherein the sensor mechanism has a measurement module having - a paramagnetic oxygen sensor (68) for qualitative and quantitative detection of the oxygen concentration with measurement technology, - an infrared-optical carbon dioxide sensor (64) for qualitative and quantitative detection of the carbon dioxide concentration with measurement technology, - a flow sensor or a flow rate sensor (48) which is configured as a differential pressure sensor with a flow diaphragm, wherein an HME filter element (54) is arranged in the measurement gas line (10), at the gas inlet (51) or at the module for gas transport (50), wherein an increase in the pressure drop on the HME filter element (54) due to moisture saturation is detected as a change in the offset pressure level by constantly repeating the measurement operation, and the change in the offset pressure level is compensated when calculating the current pressure level in the breathing mask, wherein the mask pressure is determined by a difference value which represents the difference between a static pressure level and a dynamic pressure level, wherein the static pressure level is determined when the gas is standing in the gas line (10) and the dynamic pressure level is determined when the gas is flowing through the gas line (10), wherein the control unit (70) is configured to control the module for gas transport (50) by means of the flow sensor or the flow rate sensor (48) in order to transport a volume or a partial volume of breathing gas to the sensor mechanism, and the control unit (70) is configured to organize, check, control or regulate the process of monitoring the gas composition of breathing gas in an aircraft or spacecraft with measurement technology.

2. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1, enabling qualitative and quantitative detection of the concentration of another gas, including the concentration of carbon monoxide, with measurement technology by means of the sensor mechanism (60). ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ wherein ​ 3. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1, wherein, the sensor arrangement (60) has at least one further gas sensor (65, 65', 64', 68').

4. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 3, wherein the at least one further gas sensor (65, 65', 64', 68') is a carbon monoxide sensor.

5. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1, wherein the control unit (70) is configured to take at least one environmental parameter and / or at least one situational parameter into account when checking the process monitored by means of measurement technology and / or to incorporate the at least one environmental parameter and / or at least one situational parameter into the process.

6. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1, wherein, the monitoring system (100, 100', 108, 109, 110, 111, 112) has a data interface (90).

7. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1, wherein the monitoring system (100, 100', 108, 109, 110, 111, 112) has a data interface (90) for receiving and / or providing environmental parameters and / or situational parameters.

8. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1, wherein, the sensor arrangement (60) has further sensors for determining and / or detecting by means of measurement technology environmental parameters and / or for determining and / or detecting by means of measurement technology situational parameters, and wherein the sensor arrangement (60) is configured to provide the environmental parameters and / or situational parameters.

9. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1, wherein the breathing gas is breathing air.

10. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 9, wherein in the monitoring system (100, 100', 108, 109, 110, 111, 112) or in or at the module (50) for gas transport, a further gas port (52) with a changeover valve (55) is arranged.

11. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 10, wherein, at the further gas port (52) a further pump (56) is arranged.

12. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 9, wherein The control unit (70) is configured to take into account at least one environmental parameter and / or at least one situational parameter in conjunction and / or to incorporate the at least one environmental parameter and / or at least one situational parameter in conjunction into the check when checking the module for gas transport (50).

13. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 9, wherein The monitoring system (100, 100', 108, 109, 110, 111, 112) and / or the control unit (70) is configured for determining and / or recognizing an alarm condition and for organizing an alarm or for issuing an alarm and / or for providing an alarm signal.

14. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 13, wherein The control unit (70) is configured to take into account environmental parameters and / or situational parameters in conjunction and / or to incorporate the environmental parameters and / or situational parameters in conjunction into the organization of the alarm when organizing the alarm or issuing the alarm and / or when providing the alarm signal.

15. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims 1 to 9, wherein The monitoring system (100, 100', 108, 109, 110, 111, 112) has at least one energy store (85).

16. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims 1 to 9, wherein At least one operating element (40) for operating the monitoring system is arranged in or on the monitoring system (100, 100', 108, 109, 110, 111, 112) or is assigned to the monitoring system (100, 100', 108, 109, 110, 111, 112).

17. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims 1 to 9, wherein In or on the monitoring system (100, 100', 108, 109, 110, 111, 112) there is arranged at least one display element for displaying - events, conditions, status data, current measured values, - measured values chronologically in the past, - measured variables derived from measured values, or the monitoring system (100, 100', 108, 109, 110, 111, 112) is assigned the at least one display element.

18. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 17, wherein The measurement variables derived from the measured values include statistical figures.

19. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 17, wherein, The measurement variables derived from the measured values include maximum values, minimum values, average values, trends, events, or alarm conditions.

20. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims 1 to 9, wherein, In or on the monitoring system (100, 100', 108, 109, 110, 111, 112) an input element (80) is arranged, wherein the input element (80) is configured such that a user can initiate, annotate, trigger, start or end a defined condition, a defined action or a state at the monitoring system.

21. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 20, wherein The input element (80) is configured by means of an acceleration sensor (61).

22. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims 1 to 9, wherein, A data memory for storing measured values of measurement variables derived from the measured values is arranged in or on the monitoring system (100, 100', 108, 109, 110, 111, 112) or is assigned to the monitoring system (100, 100', 108, 109, 110, 111, 112).

23. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 22, wherein The measurement variables derived from the measured values include statistical figures.

24. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 22, wherein, The measurement variables derived from the measured values include maximum values, minimum values, average values, trends, events, or alarm conditions.

25. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 5 to 9, wherein The control unit (70) is configured to take into account the environmental and / or situational parameters and / or to incorporate the environmental and / or situational parameters into the adaptation of the signal processing of the measured values of the sensor mechanism.

26. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 25, wherein The signal processing includes signal filtering.

27. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims 1 to 9, wherein The control unit (70) is configured to use a predetermined threshold value for the organization of an alarm, which can be stored in a data memory of the monitoring system for a determined value of the gas concentration, including the concentration of oxygen, carbon dioxide or carbon monoxide.

28. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to any of the preceding claims 1 to 9, wherein The control unit (70) is configured to use, for the organization of an alarm, a predetermined threshold value, which can be stored in a data memory of the monitoring system for a determined value of the gas concentration, including the concentration of oxygen, carbon dioxide or carbon monoxide. - a decision matrix - or an adapted algorithm - or a learning-capable or self-learning algorithm, application of an early warning system for the recognition of hypoxia.

29. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 28, wherein, The control unit (70) is configured to take physiological data into account together in the early warning system for the recognition of hypoxia.

30. Monitoring system (100, 100', 108, 109, 110, 111, 112) according to any of the preceding claims 1 to 9, wherein, The control unit (70) is configured together with a pressure sensor (47), a shut-off valve (57) and a data memory (75) for determining a current pressure level in a breathing mask (20).

31. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 30, wherein The control unit is configured by means of a measurement operation (200) - for determining a static pressure level and a dynamic pressure level, - for determining a deviation pressure level on the basis of the static pressure level and the dynamic pressure level, - for taking the dynamic pressure level into account when determining the current pressure level in the breathing mask (20).

32. The monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 31, wherein The control unit is configured to take information on the breathing phase of the aircraft pilot into account together when performing the measurement operation (200) when detecting and / or determining static pressure measurements and / or dynamic pressure measurements with measurement technology.

33. Method for operating a monitoring system (100, 100', 108, 109, 110, 111, 112) according to any of the preceding claims 1 to 32, wherein by means of a control unit (70) - in a first step, activating a sensor mechanism (60) of the monitoring system (100, 100', 108, 109, 110, 111, 112), - in a second step, preparing a data storage with an initialization of a data memory (75), - in a third step, detecting measurements of the sensor mechanism (60) with measurement technology, - in the data memory (75), data storing the measurements with the associated time information.

34. Method according to claim 33, wherein when data storing the measurements of the sensor mechanism (60), additionally storing situational parameters and / or environmental parameters with the associated time information.

35. Method according to claim 33 or 34, wherein, Upon activation of the input element (80), the measurement value of the sensor device (60) is additionally detected at the time of activation of the input element (80) independently of the time control.

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