Surveillance system

Abstract

A monitoring system (100) is described for an aircrew (99), such as an airplane pilot, aircraft operator, pilot, co-pilot, or passenger, of an aircraft or flight device, for example, an airplane or helicopter in civil or military aviation, a passenger aircraft in scheduled or charter flights, and especially including ultrafast aircraft, in which a sensor system (60) is used for metrological detection of gas concentrations.

Description

[Technical field]

[0001] The present invention relates to a monitoring system for pilots or passengers of an aircraft or flight device. By aircraft or flight device is meant airplanes or helicopters in civil or military aviation, for example scheduled or charter passenger aircraft, as well as very fast aircraft approaching or exceeding the supersonic range. In particular, jet flight at supersonic speed and / or at flight altitudes of more than 15,000 m above the seabed imposes great demands on pilots, especially jet pilots, in terms of flying aptitudes, such as strength, energy, attention, concentration and vigilance. In addition to reliable equipment of the aircraft, it is also very important to ensure that the pilot is always provided with satisfactory and health-free breathing air, in order to guarantee the strength, energy and vigilance required to operate the flight device, in rapid flight maneuvers or flight attitudes, such as turns, dives, inverted flight, at high altitudes, for example with high speeds (more than Mach 1) and accelerations exceeding or several times the acceleration of gravity, as well as in air refueling. To supply breathing air or breathing gas to the aircraft pilot, pilot, co-pilot or passengers, systems are used that use, for example, fresh air (mainly treated or air-conditioned filtered) from the surrounding environment as the breathing gas source, but also systems that add additional oxygen to the breathing air or breathing gas. In this case, oxygen can be brought onto the aircraft under high pressure (less than 200 bar), for example using pressurized oxygen cylinders and reduced to a breathable pressure using suitable pressure reducing devices, or it can be produced by a chemical process, for example from sodium chlorate brought onto the aircraft by a chemical oxygen generator, for direct consumption during use. Here, it is often possible for the aircraft pilot, pilot or co-pilot to independently activate the metering or supply of oxygen and / or to independently adjust or pre-set the amount and / or concentration of oxygen and / or the composition of the breathing gas. The supply of breathing air / breathing gas can in this case also be made directly from the cabin or cockpit air, but it is also possible to use a hose system with a mouth / nose mask to directly supply and / or exhaust breathing air / breathing gas to the aircraft pilot, pilot or co-pilot.In any case, the on-board technology of the aircraft or flight equipment requires that the pilot, pilot or co-pilot in use is supplied with a breathing gas that is satisfactory and does not pose health concerns. This includes, on the one hand, 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 within ranges that do not pose health concerns. In natural air, in addition to nitrogen and the noble gases, oxygen (O. 2 ) accounts for 21% by volume. 2 The current global average of CO2 emissions is less than 0.05% by volume, but the US Federal Aviation Administration (FAA) recommends that passengers on aircraft be at least 30,000 ppm (CO2). 2 The American Society of Heating, Cooling and Air-Conditioning Engineers (ASHRAE) recommends an upper limit of 1,000 ppm (CO 2 Therefore, the provision of breathing gas for pilots, co-pilots, or passengers should at least follow the recommendations of the Federal Aviation Administration (FAA) or the American Society of Heating, Cooling, and Air-Conditioning Engineers (ASHRAE), with a concentration of more than 21% vol. for the oxygen ratio and 0.1% vol. for the carbon dioxide ratio. 2 An upper limit of 0.1% vol. of oxygen should be achieved during use. It has been scientifically proven that carbon dioxide concentrations exceeding 1%-3% vol. can cause carbon dioxide poisoning, characterized by, for example, nausea, headache, and dizziness. Carbon dioxide concentrations exceeding 12% are immediately fatal. Insufficient oxygen supply can also be a health hazard, especially for airplane pilots, pilots, or co-pilots, because in the case of insufficient oxygen supply, the partial pressure of oxygen in the blood can decrease, resulting in the so-called hypoxic state (hypoxia). Such a decrease in arterial partial pressure of oxygen in the blood (also called hypoxemic hypoxia (hypoxemia)) is likely to occur frequently during stays at high altitudes. Symptoms of hypoxia are, for example, anxiety and restlessness, dyspnea, cyanosis, tachycardia, elevated blood pressure, confusion, dizziness, bradycardia, and even cardiac arrest. [Background technology]

[0002] A device and a method for monitoring the inhaled gases are known from EP 3287173 A1. Here, the pressure level of the total inhaled breathing air while the breathing air flows into the person's face mask and the partial oxygen pressure in the inhaled breathing air are determined, from which the partial oxygen pressure in the person's lungs is deduced. From US 2007 / 181129 A1, a breathing mask is known with a display device that is configured to visually provide data and / or information to the aircraft pilot, pilot or co-pilot. The display device is configured as a so-called head-up display. Here, a projection of data and / or information on the inside of the visor is performed in the field of view of the aircraft pilot, pilot or co-pilot. From US 7391574 A1, a further head-up display is known. From US 2016 / 253561 A1, a face mask is known with a device for detecting the ambient temperature and its display or visualization. US 2019 / 118008 A1 discloses a display device for a face mask in the embodiment as a so-called in-mask display. US 8210175 A1 discloses an apparatus for oxygen supply for airplanes, for example according to the pressure swing adsorption principle. In addition, oxygen is provided from an oxygen reservoir. The air is treated with a molecular sieve bed, which is flushed with oxygen from the oxygen reservoir at the start of operation. US 7407528 A1, US 2004 / 245390 A1 and US 7264647 A1 disclose further apparatuses for oxygen supply in airplanes. DE 102010014222 A1 discloses a compressed air monitoring device for monitoring compressed air, which comprises 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.As sensors for continuously detecting at least one parameter of the compressed air, sensors for detecting the carbon dioxide concentration, the nitrogen dioxide concentration, the carbon monoxide concentration, the sulfur dioxide concentration, the oxygen concentration, and a sensor for detecting the relative air humidity in the measurement air line are mentioned. EP 2148616 A1 shows a measurement system with multiple sensor systems, such as a flow sensor system, a temperature sensor system, a pressure sensor system, a humidity sensor system, a gas sensor system for measuring oxygen, carbon dioxide, carbon monoxide, nitrogen, nitrogen oxides, anesthesia gases, gas components in the exhaled air, and further gases. DE 102006030242 A1 shows a configurable measurement system with multiple gas sensors. In this measurement system, electrochemical, infrared optical, and catalytic gas sensors can be configured as gas sensors. US 2013 / 0167843 A1 shows a pump for delivering a defined volume of air. The pump has a piezoelectric function mode. Such a pump is suitable for the delivery of a defined gas quantity from a measurement point to a sensor system point and / or metrological detection by means of a measurement line, e.g. for use in side stream measurements for the analysis of gas components (including in particular carbon dioxide and oxygen) near the mouth / nose of a person or patient, for the analysis of inspired and / or expired air. Many different embodiments and configurations of gas delivery devices, pumps or gas conveying devices for supplying a person with a breathing gas, in some configurations suitable for breathing by a person, as well as many different embodiments and configurations comprising such devices are known from the patent documents WO 2018 / 033224 A1, US 2018 / 0163712 A1, WO 2018 / 033225 A1, US 2018 / 0133420 A1, US 2018 / 0110957 A1, WO 2019 / 072606 A1, DE 102017009605 A1, DE 102017009606 A1, DE 102018004341 A1 and DE 202012013442 A1.Further configurations of gas delivery devices, pumps or gas conveying devices for supplying a person with a breathing gas suitable for breathing in some configurations are known from the (previously undisclosed) German patent applications Nos. 102019003643.3, 102019003607.7, 102019004450.9 and 102019004451.7. Many different embodiments and configurations of gas delivery devices, pumps or gas conveying devices for supplying a measurement gas to a gas measurement device are known from the patent literature, German patent application No. 102016013756, US patent application No. 2018 / 0143171, US patent application No. 2018 / 0143170 and US patent application No. 2018 / 0335410. US 2008 / 264418 A1 discloses a connection element, a so-called Y-piece, for connecting a ventilation tube to the mouth / nose area of ​​a person or patient, which comprises sensor system components, components for measuring measured values, signal processing, signal evaluation and display. The sensor system components include a respiratory flow sensor system with a pressure sensor system, a sensor system for measuring partial oxygen pressure, a temperature sensor system, a flow sensor system configured as a hot wire anemometer or ultrasonic flow sensor, as well as connection elements for ECG and blood pressure measurement. US 7897109, US 7335164, US 6616896, US 5789660 and US 6312389 disclose oxygen sensors based on the so-called luminescence quenching measurement principle, which can be arranged in the path of the patient's breathing gas or in a side stream on the path. From DE 102010037923 an oxygen sensor with a bioreactor array is known. From US 9867563 a system for identifying a reduction in oxygen supply in a pilot and for reducing the reduction in oxygen supply in the pilot is known. From US 2003194351 a galvanic cell for oxygen measurement is known. From DE 102004062052 and DE 19726453 electrochemical oxygen sensors are known.German Patent Application No. DE 2155935 A1 discloses an electrochemical sensor for measuring gaseous components in a gas mixture. From US 5958200 A1, German Patent Application No. DE 102009010773 A1, German Patent Application No. DE 102005026491 A1, German Patent Application No. DE 102005026306 A1 and US 8496795 A1, various configurations of electrochemical gas sensors suitable for metrological detection of oxygen or other gases are known. German Patent Application No. DE 102005007539 A1 shows an electrochemical gas sensor for quantitatively measuring redox-active substances in the very low concentration range. Depending on the configuration of the electrodes and electrolyte, this electrochemical measuring principle is suitable for detecting a wide variety of gases, such as, for example, oxygen, ammonia, sulfur dioxide, hydrogen peroxide, hydrogen sulfide, nitrogen dioxide, nitric oxide, arsine, silane, formaldehyde, acetylene, carbon monoxide, phosgene, phosphine, etc. From DE 19912100 A1 an electrochemical carbon monoxide sensor is known. From US 4851088 A1 an electrochemical carbon dioxide sensor is known. In US 5473304 A1 and DE 4020385 A1 real calorimeter sensors are shown which are produced in ceramic film technology. In US 7875244 A1, GB 2210980 A1 and DE 19610912 A1 real calorimeter sensors are shown in a pellistor configuration. US Patent Application Publication No. 2010 / 221148, US Patent Application Publication No. 5902556 show catalytic gas sensors with a semiconductor chip as a measuring element. US Patent Application Publication No. 2816863, US Patent Application Publication No. 2019 / 178827, US Patent Application Publication No. 8425846, US Patent Application Publication No. 9625406, US Patent Application Publication No. 6756016, US Patent Application Publication No. 2016 / 178412, US Patent Application Publication No. 6344174 disclose catalytic gas sensors. This catalytic measurement principle, also known as the actual calorific value principle, is particularly suitable for the detection of combustible and / or explosive gases, in particular hydrocarbon compounds, as well as for determining residual components of combustion processes.For example, toluene, ammonia, benzene, propane, methane, methanol, octane, butane, ethylene can be metrologically detected using the principle of actual calorific value. Catalytic sensors are often used for monitoring limit values, for example UEG (lower explosion limit). US Pat. No. 4,175,422 shows a gas sensor with a semiconductor element as the measuring element. US Pat. No. 9,958,305 discloses a gas sensor arrangement with a semiconductor sensor system of chip technology for monitoring the combustion process in internal combustion engines of motor vehicles. DE Pat. Nos. 102004,048,979 and 4,902,138 disclose miniaturized semiconductor gas sensors. DE Pat. No. 102012,022,136 discloses a semiconductor carbon monoxide sensor. US Pat. Nos. 9,818,937 and 9,234,876 disclose miniaturized semiconductor oxygen sensors which are constructed with microstructuring technology, so-called MEMS technology. Furthermore, gas sensors with solid electrolytes, for example based on zirconium dioxide, are known. Thus, for example, in DE 102008056279 A1, an array with a heated solid electrolyte oxygen sensor and an ultrasonic sensor is shown for indirect detection of the carbon dioxide concentration. In US 5026992 A1, a gas sensor is shown for the optical detection of methane. In US 8399839 A1, a gas sensor is shown for the optical detection of carbon dioxide. From EP 0149619 A1, a device with a lambda probe for detecting the amount of residual oxygen in the exhaust gas of an internal combustion engine is known. From US 4667157 A1, a Hall effect oxygen sensor is known.US Patent No. 8,596,109, US Patent No. 9,360,441, US Patent No. 4,808,921, US Patent No. 6,430,987, US Patent No. 6,952,947, US Patent No. 6,895,802, US Patent No. 6,405,578, US Patent No. 4,683,426, US Patent No. 4,173,975, US Patent No. 3,646,803, US Patent No. 3,584,499, US Patent No. 294,448 and WO 16 / 162,287 show devices for measuring the concentration of paramagnetic gases. With such devices, it is possible to perform not only a qualitative metrological detection of oxygen, but also a quantitative metrological detection, in particular because oxygen has paramagnetic properties. US Patent No. 9,360,441 discloses a measuring element for a paramagnetic gas sensor, in particular for an oxygen sensor. The paramagnetic gas sensor or oxygen sensor may be conveniently located in a side stream in or on the patient's breathing gas path. Gas measurement devices are described in German Patent No. 102010047159 and US Patent Publication No. 2004 / 238746. An infrared optical gas measurement device is described in US Patent No. 5,739,535. US Patent No. From DE 8399839 an infrared optical carbon dioxide sensor, so-called IR carbon dioxide sensor, is known. From DE 102010047159 and US 6895802 a device is known for determining the carbon dioxide concentration in a breathing gas by measuring the thermal conductivity. In the embodiment according to DE 102010047159 a carbon dioxide sensor is shown which comprises a semiconductor chip as measuring element for detecting changes in the thermal conductivity. From US 5696379, US 2004 / 203169 and US 4050823 an infrared optical carbon dioxide sensor is known. US Patent No. 8,448,642, US Patent No. 5,095,900, US Patent No. 5,067,492, WO 2010 / 9115, US Patent Application Publication No. 2019 / 105457, US Patent No. 6,095,986, US Design Patent No. D727,492 and US Patent No. 5,942,755 disclose infrared optical carbon dioxide sensors that can be arranged in the main stream of the patient's respiratory gas path. Gas measuring devices or sensors for the metrological detection of carbon dioxide, particularly also suitable for the metrological detection of carbon dioxide in respiratory gases, are known from US Patent Application Publication No. 2002 / 036266, US Patent Application Publication No. 2004 / 238746, US Patent Application Publication No. 2018 / 0120224 and US Patent Application Publication No. 2018 / 0116555. Further gas measuring devices or sensors for metrological detection of carbon dioxide are known from the (previously undisclosed) German patent applications 102020114972.7 and 102020114968.9. From US 6,571,622 a combined sensor is known consisting of an infrared optical carbon dioxide sensor and a flow sensor which can be arranged in the main stream in the path of the patient's breathing gas. From US 2004 / 238746 and US 2002 / 036266 an infrared optical carbon dioxide sensor is known which can be arranged in a side stream in or on the path of the patient's breathing gas.US Patent No. 6,954,702, US Patent No. 7,606,668, US Patent No. 8,080,798, US Patent No. 7,501,630, US Patent No. 7,684,931, US Patent No. 7,432,508, US Patent No. 7,183,552 show gas measurement systems for detecting gas concentrations in side and main streams. US Patent No. 9,939,374 and US Patent No. 7,705,991 describe interferometers in the configuration of gas measurement devices. US Patent No. 6,274,879 and EP Patent No. 2,788,739 disclose laser-based arrays for the detection of gas components. US Patent No. 9,459,235 discloses gas sensors in the form of photoionization detectors. A further aspect regarding the qualitative and quantitative composition of the breathing gas is that the breathing gas should be substantially free of impurities, for example foreign bodies or particles such as soot, dust, pollen or vapors of materials that pass through the breathing gas on its way to the aircraft pilot, pilot, co-pilot or passengers. Furthermore, the breathing gas should be at least slightly or substantially free of gases or gas mixtures of health concern, for example carbon monoxide (CO), ozone, traces of further gases or traces of aviation fuel or kerosene, possibly exhaust gases or combustion residues or further air pollutants. These include, for example, hydrocarbons, benzene, nitrogen oxides (NO. 2 , NO x ), sulfur oxides, (SO 2 , SOx), dioxins, furans, particles, such as soot, fine dust, ultrafine particles, and various compositions. In addition to carbon dioxide poisoning, mentioned above, carbon monoxide poisoning should also be mentioned among the related poisons. At concentrations above 200 ppm (0.02%), it already causes headaches and loss of judgement, and at concentrations above 800 ppm (0.08%), it can cause dizziness, restlessness, nausea, anxiety, convulsions within 45 minutes, and loss of consciousness and even death within 2 hours. In the case of carbon monoxide poisoning, the blood's oxygen-carrying capacity is reduced due to a decrease in the hemoglobin content (anemia) or an impairment of the blood's oxygen-binding capacity, leading to anemic hypoxia. Summary of the Invention [Problem to be solved by the invention]

[0003] Therefore, there is a need to ensure that the on-board technology of an aircraft or flight device always provides an impeccable high-quality breathing gas during flight operations and can be administered to the aircraft pilot, pilot, co-pilot and passengers of the aircraft or flight device. As a result, one object of the present invention is to provide a monitoring system for the aircraft pilot, pilot, co-pilot and passengers of an aircraft or flight device or to provide a method that allows metrological monitoring of breathing gas or breathing air in an aircraft or flight device. As a result, a further object of the present invention is to provide a method for metrological monitoring of breathing gas or breathing air in an aircraft or flight device. [Means for solving the problem]

[0004] These problems are solved by the attached independent claims. This problem is solved in particular by a monitoring system for monitoring the gas composition of a breathing gas in an aircraft or flight device having the features of independent claim 1.

[0005] The problem is also solved by a method for operating a monitoring system for monitoring the gas composition of a respiratory gas in an aircraft or flight device, which has the features of independent claim 33. Further features and details of the invention as well as preferred embodiments are evident from the dependent claims, the description and the drawings. References used herein indicate further developments of the subject matter of the independent claims by the features of the respective dependent claims and should not be understood as waiving the achievement of independent objective protection for the combination of features of the incorporated dependent claims. Furthermore, with regard to the interpretation of the claims and the description in the case of more detailed realizations of the features in the dependent claims, it is to be started from the fact that such limitations are not present in the preceding claims as well as in the more general embodiments of the system or method. Any relation in the description to the aspects of the dependent claims should therefore be explicitly read as a description of optional features, even if there is no specific indication thereto. Finally, it is pointed out that the monitoring system proposed herein may be developed according to method claims and the method proposed herein may be developed according to monitoring system claims, for example by the monitoring system comprising means determined and / or installed for the execution of one or more method steps or by the method comprising steps executable by means of the monitoring system or suitable for operating the monitoring system. To that extent, the features and details explained in relation to the proposed monitoring system and possibly the configuration for the pilots or passengers of an aircraft or flight device are of course also valid in relation to the method executed during the operation of the monitoring system and vice versa. Cross reference is therefore or can always be made with respect to the disclosure relating to the individual aspects of the invention.

[0006] Embodiments provide a means for metrologically monitoring the gas composition of air, breathing air or breathing gas in an aircraft or flight device. At least some embodiments of the present invention relate to a monitoring system for monitoring the gas composition of air, breathing air or breathing gas in an aircraft or flight device. At least some embodiments of the present invention relate to a method of operating a monitoring system for monitoring the gas composition of air, breathing air or breathing gas in an aircraft or flight device. At least some embodiments may allow metrological detection of at least one property of the gas using a sensor system of the monitoring system. Gas properties include, for example, pressure, density, viscosity, thermal conductivity, electrical and magnetic properties, temperature, gas composition, humidity, toxicity, heating value, flammability, ability to bind with other gases, or physical and other properties of liquids, such as water or blood. At least some embodiments may allow qualitative metrological detection of at least one gas. At least some embodiments may allow quantitative metrological detection of at least one gas and / or concentration of the gas. At least some embodiments may allow qualitative and quantitative metrological detection of at least one gas. At least some embodiments may allow for qualitative and quantitative metrological detection of oxygen. At least some embodiments may allow for qualitative and quantitative metrological detection of carbon dioxide. At least some embodiments may allow for qualitative and quantitative metrological detection of further gases, in particular carbon monoxide.

[0007] In at least some embodiments, a control unit is arranged in or assigned to the monitoring system. It is envisaged that this control unit is configured to organize, control, open-loop or closed-loop control the sequence of metrological monitoring of the gas composition of air, breathing air or breathing gas in an aircraft or flight device. This control unit is preferably composed of components (μC, μP, PC) with an associated operating system (OS), data memory (RAM, ROM, EEPROM) and SW code, sequence control software, control software, open-loop control software, closed-loop control software. In at least some embodiments, further electronic elements are assigned to the control unit or connected to it, such as, for example, components for signal detection (ADμC), 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 sensor system may be used to enable qualitative and quantitative metrological detection of the concentration of oxygen. The concentration of oxygen may be metrologically determined, for example, in this case in the form of a partial pressure in a gas mixture, such as, for example, breathing air or breathing gas, or in the form of a volume concentration, or in the form of a mass concentration. In at least some embodiments, the sensor system may be used to enable qualitative and quantitative metrological detection of the concentration of carbon dioxide. The concentration of carbon dioxide may be metrologically determined, for example, in this case in the form of a partial pressure in a gas mixture, such as, for example, breathing air or breathing gas, or in the form of a volume concentration, or in the form of a mass concentration. In at least some embodiments, the sensor system may be used to enable qualitative and quantitative metrological detection of the concentration of carbon monoxide. The concentration of carbon monoxide may be metrologically determined, for example, in this case in the form of a partial pressure in a gas mixture, such as, for example, breathing air or breathing gas, or in the form of a volume concentration, or in the form of a mass concentration. In at least some embodiments, the sensor system may have at least one sensor. In this case, the at least one sensor is preferably configured as an oxygen sensor, a carbon dioxide sensor or at least one further gas sensor, in particular a carbon monoxide sensor. In at least some embodiments, a paramagnetic oxygen sensor or a measurement module with a paramagnetic oxygen sensor can be used for the qualitative and quantitative metrological detection of the concentration of oxygen. In a further preferred manner, an electrochemical oxygen sensor or a measurement module with an electrochemical oxygen sensor can be used in this case. In a further preferred manner, an oxygen sensor that functions according to the principle of luminescence quenching or fluorescence quenching or a measurement module with an oxygen sensor can be used in this case. In a further preferred manner, a semiconductor oxygen sensor can be used in this case, preferably a so-called MEMS oxygen sensor or a semiconductor oxygen sensor in the form of a measurement module with a semiconductor oxygen sensor or a MEMS oxygen sensor. In a further preferred manner, an electrochemical oxygen sensor and / or a paramagnetic oxygen sensor or a measurement module with an electrochemical oxygen sensor and / or a paramagnetic oxygen sensor can be used in this case.In a further preferred manner, in this case, an electrochemical oxygen sensor and / or a semiconductor oxygen sensor or a measurement module with an electrochemical oxygen sensor and / or a semiconductor oxygen sensor can be used. In a further preferred manner, in this case, a paramagnetic oxygen sensor and / or a semiconductor oxygen sensor and / or an electrochemical oxygen sensor or a measurement module with a paramagnetic oxygen sensor and / or a semiconductor oxygen sensor and / or an electrochemical oxygen sensor can be used. In a further preferred manner, in this case, a paramagnetic oxygen sensor and / or a semiconductor oxygen sensor or a measurement module with a paramagnetic oxygen sensor and / or a semiconductor oxygen sensor can be used. In at least some embodiments, preferably for the qualitative and quantitative metrological detection of the carbon dioxide concentration, 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, a so-called IR sensor, can be used. In a further preferred manner, in this case, preferably a so-called MEMS carbon dioxide sensor or a semiconductor carbon dioxide sensor in the form of a measurement module with a MEMS carbon dioxide sensor can be used. In a further preferred approach, 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 equipped with a semiconductor carbon dioxide sensor or a MEMS carbon dioxide sensor and / or an optical carbon dioxide sensor or an IR carbon dioxide sensor can be used.

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

[0010] The oxygen measuring module and / or the carbon dioxide measuring module may in some embodiments have further sensors or may in some embodiments be assigned further sensors and / or arranged on the module. In some embodiments, the oxygen measuring module and / or the carbon dioxide measuring module may be implemented in combination with possibly further gas sensors and possibly further sensors for metrological detection of measurement variables or material variables, such as, for example, pressure, ambient pressure, breathing passage pressure, mask pressure, density, temperature, thermal conductivity, heat capacity, volumetric flow rate, mass flow rate, flow rate, volume, etc., and may be configured as a gas measuring module, a measuring module or as a module for ambient or environmental analysis. Thus, a pressure sensor may be arranged in the monitoring system, for example in the oxygen measuring module or the carbon dioxide measuring module, as an element configured for pressure level detection in the measurement gas line. Furthermore, a flow sensor or a flow sensor may be arranged in the monitoring system, for example in the oxygen measuring module or the carbon dioxide measuring module, as an element configured for detection of the flow rate or flow in the measurement gas line. The measurements of the flow sensor, the flow rate sensor, as well as the pressure sensor may also be provided to the control unit.

[0011] In some embodiments, the monitoring system or such modules, 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. This gas transport module comprises for this purpose a gas delivery device (preferably a pump) with a gas connection, which is configured to deliver a predetermined amount of gas from a sensor system or a measuring point remote from 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 an oxygen sensor, a carbon dioxide sensor, in order to enable metrological detection of the oxygen concentration and / or the carbon dioxide concentration. The pump or gas transport module is configured to draw in a predetermined or partial amount of breathing gas or breathing air from a measuring point, in particular a breathing mask, and / or from the passenger cabin or the cockpit, and deliver it to the monitoring system or the oxygen measuring module and / or the carbon dioxide measuring module, or to the sensor system, in particular an oxygen sensor and / or a carbon dioxide sensor. The breathing mask can be configured, for example, 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 completely or completely prevent backflow or to prevent undesired throughflow or throughflow, a valve may additionally be arranged at the inlet upstream of the pump or at the outlet downstream of the pump. The gas-carrying module is preferably pneumatically and / or fluidically connected to a measuring point by means of a sample line. To monitor the breathing gas supply of an aircraft pilot, pilot or co-pilot, a component that directs gas to the face area, i.e. in the vicinity of the mouth / nose area of ​​the aircraft pilot, pilot or co-pilot, is preferably used as measuring point. One end of the measuring gas line is preferably arranged in the mouth / nose area, e.g. in a breathing mask, in order to allow the flow of a quantity of gas from the mouth / nose area to the gas-carrying module of the monitoring system.The other end of the measurement gas line is preferably pneumatically or fluidically connected to a gas connection for inflow into the gas conveying module, so that the gas conveying module allows for the delivery of a defined or partial amount of breathing gas with a flow rate, for example, in the range of 25 ml / min to 250 ml / min, to the oxygen measuring module and / or carbon dioxide measuring module. For this purpose, the gas conveying module is pneumatically and / or fluidically connected to a further gas connection for outflow or delivery to the oxygen measuring module and / or carbon dioxide measuring module. By means of a flow sensor or a flow sensor, the control unit can control the gas conveying module and control, open-loop-controlled, closed-loop-controlled or set a defined amount of gas to be delivered or drawn in the measurement gas line. By means of a pressure sensor, the control unit can also monitor the pressure level in the measurement gas line and control, open-loop-controlled, closed-loop-controlled or set by means of the gas conveying module. If the flow sensor is configured as a differential pressure sensor (ΔP sensor) that measures the difference between two pressure measurement points upstream of the flow restrictor, it may be possible to measure the pressure level in the measurement gas line by using this sensor to detect one of the two pressure measurement points related to the surroundings.

[0012] In a preferred embodiment, the gas conveying module may be arranged in the form of a pump at the gas inlet of the monitoring system. In such an exemplary configuration, the gas conveying module draws a quantity of gas from the pilot's breathing mask through the measurement gas line into the monitoring system and then expels this quantity of gas through a sensor system for determining the gas concentration. After flowing through the sensor system, the quantity of gas reaches the surroundings through a gas outlet.

[0013] In a further preferred embodiment, the gas-carrying module may be arranged at the gas outlet of the monitoring system in the form of a pump. In such an exemplary configuration, the gas-carrying module draws a given amount of gas from the pilot's breathing mask through the measurement gas line through a sensor system for determining the gas concentration into the monitoring system. After flowing through the pump, the given amount of gas reaches the surroundings through the gas outlet. Possible impurities that may pass through the pump cannot reach the sensor system due to the arrangement of the pump on the gas outlet. A conveyance of a given or partial amount of breathing gas to the oxygen measuring module and / or the carbon dioxide measuring module or to the oxygen sensor and / or the carbon dioxide sensor can be carried out via the gas-carrying module, in particular the pump, via a pneumatic and / or fluidic connection, thereby enabling metrological detection of the concentrations of oxygen and / or carbon dioxide passing through. The monitoring system is designed in a structural form that can be worn in or on the clothing of the pilot, pilot or co-pilot. The measurement gas line has a corresponding length that allows such wearing. In particular, it is advantageous to store or wear the monitoring system in a breast pocket, leg pocket or thigh pocket of a pilot suit (pilot overalls). The gas delivery module is designed and configured to deliver a gas volume from the measurement point to a mounting point, preferably in a chest, leg or thigh pocket of the pilot suit. The gas delivery module may be configured, for example, as a centrifugal, axial, radial, piston or diaphragm pump. Pumps with low energy consumption are particularly advantageous for use in monitoring systems for portable and energy-self-sufficient use. For example, piezoelectrically operated pumps, often also called piezo pumps, allow energy-saving use for gas concentration measurements in monitoring systems. Such pumps are available, for example, from Murata Manufacturing Co., Kyoto, Japan, under the model numbers MZB1001T02 as well as MZB1001, as so-called "piezo blowers" or "micro blowers".These pumps do not block the flow even without an electrical drive control or activation, so that for reproducible blocking or release of the flow into and through the measurement gas line, it is advantageous in the use of the monitoring system to provide a valve that reliably, reproducibly and unambiguously guarantees the flow through the measurement gas line in two states: "open" and "blocked". For the embodiment with a pump at the gas outlet as well as the embodiment with a pump at the gas inlet, a shut-off valve, a so-called "Flow-Lock-Valve", is suitable, which may be preferably arranged at the gas outlet. The arrangement of the shut-off valve on the gas outlet of the monitoring system allows the use of a pressure sensor arranged inside the monitoring system for determining the pressure in the breathing mask of the airplane pilot by means of a measurement operation that determines the breathing mask pressure, since in the case of a closed shut-off valve in the no-flow state, the pressure level inside the monitoring system corresponds to the pressure level in the measurement gas line as well as to the pressure level in the breathing mask. Alternatively, for the embodiment with a pump at the gas inlet, a switching valve, a so-called "three-port / two-way valve", which may be preferably arranged at the gas inlet, is suitable. This switching valve may, on the one hand, allow the supply of a quantity of gas from the measurement gas line to the monitoring system, and, on the other hand, allow the supply of a quantity of gas from the surroundings, i.e. from the cabin of the flight device. During the supply of the quantity of gas from the cabin, the control unit can simultaneously determine the pressure level in the breathing mask by means of a measurement operation that determines the breathing mask pressure.

[0014] In a preferred embodiment, a further gas connection with a switching valve is arranged in the monitoring system. In a further preferred embodiment, a further gas connection with a switching valve is arranged in or on the gas-conveying module. This switching valve allows switching between the supply of a given amount of gas from the measurement gas line and the supply of a gas amount from the surroundings, for example from the cabin of the flight device, by means of a further gas connection. In a further preferred embodiment, a further pump is arranged in or on the further gas connection. This allows the supply of a gas amount from the surroundings, for example from the cabin of the flight device, by means of a further gas connection. For embodiments with a pump at the gas outlet, in addition to the shut-off valve at the gas outlet, an optional switching valve may be arranged at the gas inlet for switching between monitoring the gas amount from the measurement gas line of the breathing mask and monitoring the gas amount from the cabin. This therefore makes it possible for the control unit to be able to switch at any time between the supply of a given amount of breathing gas from the breathing mask of the airplane pilot and the supply of gas from the cabin, independent of the time of the mask pressure determination.

[0015] In some embodiments, the control unit may be configured to determine respiratory phase information, i.e., inspiration duration over time, expiration duration over time, the ratio of inspiration duration to expiration duration (I:E-ratio), and the breathing frequency of the aircraft pilot, pilot, or co-pilot from the carbon dioxide sensor measurements.

[0016] In at least some embodiments, the sensor system and the control unit may be configured to detect at least one peripheral parameter and / or at least one operational parameter. The operational parameters may be, for example, parameters from flight operations, parameters from the supply of breathing gas to the aircraft pilot, pilot or co-pilot, parameters from the control of a flight device or a component of the flight device, open-loop control, closed-loop control. In at least some embodiments, the sensor system and the control unit may be configured to take into account and / or include in the control of a metrological monitoring sequence the at least one peripheral parameter.

[0017] In a preferred embodiment, the control unit is configured to connect together with the pressure sensor to determine the current pressure level in the breathing mask. During flight operations of a jet aircraft, the supply to the pilot (pilot, co-pilot) is provided by means of a breathing mask placed in the mouth / nose area. Therefore, in this case, it is particularly beneficial to monitor the current pressure level in the breathing mask of the pilot (pilot) or co-pilot. This allows the pilot (pilot) or co-pilot to be provided with a sufficient pressure level of breathing gas by means of the breathing mask during flight operations.

[0018] The embodiment shows a means for configuring the detection of the pressure level in the breathing mask by means of the sensor system and the control unit, and thus for monitoring, providing, outputting and / or documenting the pressure level in the breathing mask. The control unit detects the pressure level in the measurement gas line by means of a pressure sensor, which is arranged in the monitoring system and is pneumatically and fluidly connected in the pneumatic system with the components breathing mask, the measurement gas line, the connection element and optionally the HME filter element arranged in series connection in the measurement gas line to detect a pressure measurement value indicative of the pressure level in the pneumatic system. In a further preferred embodiment for detecting the current pressure level, the pressure measurement by the control unit is started in a measurement situation during operation of the monitoring system, in which, under the shutdown of the gas-transporting module or the pump, no predetermined amount of gas is supplied from the breathing mask to the sensor system, i.e. the gas concentration measurement by the sensor system is temporarily interrupted or paused. In such a measurement situation, the measurement value indicative of the pressure level in the pneumatic system corresponds to the current pressure level in the breathing mask. In addition to the shutdown of the pump, the shutoff valve can be replaced in a closed state in order to prevent any gas exchange between the pneumatic system and the surroundings. According to such an embodiment, the realization of measuring and checking the pressure level in the respirator can be performed discontinuously in the event of an interruption in the pumped gas supply during a predetermined time interval.

[0019] In a further preferred embodiment for detecting the current pressure level, the pressure measurement is initiated by the control unit during the continuous operation of the monitoring system, in which a predetermined amount of gas is continuously supplied from the breathing mask to the sensor system by means of the gas conveying module or by means of the activated pump. According to such an embodiment, the realization of the measurement and checking of the pressure level in the breathing mask can be performed continuously if the adaptation or calibration to the pressure drop that changes during the operation of the pneumatic system with the components breathing mask, measuring gas line, connection element and HME filter element is performed discontinuously at predetermined time intervals. In such a preferred embodiment, the adaptation or calibration that can be performed discontinuously at predetermined time intervals can be constituted by a measurement operation that is adjusted and performed by the control unit in cooperation with the gas conveying module or pump, the shutoff valve and the data memory. Such a measurement operation can be performed from time to time during flight operation in order to continuously determine the changes in or on the pneumatic system at predetermined times during the operation of the monitoring system while it is used by the airplane pilot. The measurement operation includes metrological detection of the pressure level relative to zero or offset calculation at two working points. The measurement operation is divided into pressure measurement of a static pressure level at a working point without gas flow in the pneumatic system and metrological detection of a dynamic pressure level in the form of a measurement at a further predefined working point with a defined flow in the pneumatic system. In the metrological detection of a static pressure level, a pressure measurement value is detected without gas flow in a pneumatic system having the components breathing mask, the measurement gas line, the connection element and optionally an HME filter element arranged in series connection in the measurement gas line. When there is no gas flow, i.e. when the pump is switched off and the resulting flow rate is 0.00 ml / min, no pressure drop due to components occurs in the pneumatic system between the breathing mask and the pressure sensor in the monitoring system or the pump.The HME filter element is used to prevent moisture from the breathing gas supply with breathing hose and breathing mask, which is introduced into the measurement gas line by the pilot's breath during operation, from reaching the monitoring system for monitoring the gas composition of the breathing gas. Such an HME (Heat Moisture Exchange) filter element is configured to retain a certain amount of moisture. In a preferred embodiment, the HME filter element is arranged in the measurement gas line, in the gas inlet or in the gas conveying module. During operation, a certain amount of moisture or liquid (due to the pilot's breath of moist breathing gas) is continuously accumulated in the HME filter element. As a result, the operation of the monitoring system causes a change in the flow resistance over the time course of the duration of use during flight operation. Besides the pump shutoff, the shutoff valve is closed in a suitable manner to prevent any gas exchange between the pneumatic system and the surroundings. The pressure measurement value detected in the measurement gas line without gas flow corresponds to an instantaneous recording of the current pressure in the breathing mask when the shutoff valve is closed and is stored in the data memory as the static pressure of the pneumatic system. In metrological detection of dynamic pressure levels, a pressure measurement with a defined amount of gas flow is detected in a component of a pneumatic system having a measurement gas line, a connection element and an optional HME filter element, with a corresponding pressure drop for said gas flow. The detected pressure with the defined amount of gas flow is stored in a data memory as the dynamic pressure of the pneumatic system. A suitable and defined amount of gas flow in the measurement gas line, ranging from 10 ml / min to 400 ml / min, can be activated and controlled by the control unit, and controlled in an open-loop or closed-loop manner. The pressure measurement with flow corresponds to the dynamic current total pressure drop of the pneumatic system. This pressure measurement thus corresponds to the sum of the pressure drops in the pneumatic system, i.e. across components such as the respirator, the HME filter element, the measurement gas line and the connection element.The control unit can determine the pressure drop traceable to the component as the offset pressure level of the pneumatic system from the difference between the previously determined static pressure level and the sum of the dynamic pressure drop. The change in the difference determined between the dynamic pressure measurement and the static pressure measurement between two or more times when the measurement operation is performed allows the control unit to inversely reason about the change in the pressure drop in the pneumatic system during operation and the change in the offset pressure level. These offset pressure levels in the pneumatic system, their differences and their changes are continuously detected or determined by the control unit during flight operation and stored in a data memory (e.g. in the form of a data set or table or as a log file). The control unit is configured in this preferred embodiment to use the measurement operation to determine and subsequently provide, output and / or store in the form of a data set or table the offset pressure levels determined by metrological detection of the static and dynamic pressure drops across the pneumatic system as calibration values ​​for the determination of the current mask pressure. The measurement operation thereby provides trends and changes in the offset pressure levels during operation of the monitoring system in use by the airplane pilot, pilot or co-pilot. In this way, it is possible to determine and monitor the currently occurring respective mask pressure of the pilot, even with components of the pneumatic system that change during flight operations. In particular, by continuous repetition of the measurement operation, an increase in the pressure drop across the HME filter element caused by humidity saturation can be detected as a change in the offset pressure level and compensated for in the calculation of the current pressure level in the respirator. Such repetition of the test can be performed, for example, every 15 to 60 minutes, but more frequent execution is not preferred, since the monitoring of the gas concentration is temporarily interrupted or paused for the execution of the operation.The determination of the current pressure in the breathing mask can be performed during operation with the activated pump, also between metrological measurements of oxygen and / or carbon dioxide, and possibly further gases or cabin air, etc., based on the use of the last determined offset pressure level in the measurement operation of the components of the pneumatic system by the control unit. The pressure level currently occurring in the breathing mask is obtained by subtracting the last determined offset pressure level stored in and provided in the data memory from the current measured pressure value, which indicates the pressure level of the pneumatic system during the flow through of the measurement gas line. In the following, the measurement operation already described above for determining the pressure in the breathing mask will be described with reference to its inclusion in the measurement operation of the monitoring system for metrological detection of gas concentrations, preferably carbon dioxide and oxygen, together with the functions of the components involved in this case. The measurement operation can be activated or started at a predetermined time from the continuous measurement operation of the monitoring system. The following steps are activated and started in a step sequence from start to finish by the control unit and are performed as follows: In a first step, the pump is stopped, In a second step, the shutoff valve is closed, in a third step, a first measurement process is carried out by means of a pressure sensor, with the pressure measurement determining a static pressure level, In a fourth step, the opening of the shutoff valve is performed, In the fifth step, a pump is started to discharge a predetermined amount of gas from the breathing mask through the measurement gas line to a sensor system in the monitoring system at a specified discharge rate in the range of 50 ml / min to 100 ml / min, and the discharge rate is controlled and monitored by flow measurement using a flow sensor; in a sixth step, a further measurement process is carried out by the pressure sensor, i.e. a pressure measurement to determine the dynamic pressure level, In a seventh step, a difference value calculation is carried out using the first pressure measurement and the further pressure measurement.

[0020] The difference value so determined indicates an offset pressure level and can be provided and used as a calibration value for the determination of the mask pressure in further operation of the monitoring system during use of the flight device. In an optional configuration of the step sequence of the measurement operation, the control unit can perform metrological detection of static and dynamic pressure levels and / or flow in the third, fifth and sixth steps in synchronization with the breathing of the airplane pilot, pilot or co-pilot. Thus, the pressure and / or flow measurements can preferably be performed during the inspiration pause or the expiration pause.

[0021] In a preferred embodiment, the control unit may be configured to take into account information about the pilot's respiratory phase during metrological detection and / or determination of the static and / or dynamic pressure measurements during the performance of the measurement operation for determining the pressure in the breathing mask. The detection of pressure measurements in synchronization with breathing, which involves performing the measurement detection in a pause between inspiration and expiration, is advantageous because in such a pause the pressure effects superimposed by breathing on the static and / or dynamic pressure levels cannot disturb or affect the pressure measurements. The synchronization with breathing can be performed by the control unit using respiratory phase information based on metrologically detected carbon dioxide and / or oxygen concentration changes in the monitoring system. The physiological concentration difference between inspiration (21%) and expiration (16%) in the oxygen content of the breathing gas as well as the concentration difference between expiration (~5%) and inspiration (<1%) in the carbon dioxide content can be used by the control unit to determine the respiratory phase. Without this type of synchronization of the pressure measurements, for signal processing, appropriate signal filtering, for example using a low-pass filter, or formation of a (preferably moving) average value of the pressure sensor measurement values ​​in order to remove respiratory or respiratory frequency components from the pressure measurement values, would be significant.

[0022] It may therefore be envisaged in a particularly preferred embodiment that the control unit is adapted to determine static and / or dynamic pressure measurements with signal processing using suitable signal filtering, while removing signal components induced by the pilot's breathing using signal filtering. Advantageously, a gas analysis of the cabin air can be performed using a switching valve during the mask pressure determination period. From the external system, a set value (target value), a reference value as a threshold for the breathing mask pressure, for example via a data interface, can be provided. Based on such values, the monitoring system can then determine an alarm situation in case of exceeding or falling below the threshold and provide a corresponding alarm signal and / or data. Such provision can be made to the external system, for example by wire, wireless using radio transmission, wireless using infrared transmission. Further means of issuing an alarm to the pilot of the aircraft are made possible by visual, optical or acoustic signalling systems, for example elements such as lamps, light emitting diodes, display units, speakers, buzzers, horns etc. Further means of issuing an alarm to the pilot of the aircraft may also be given tactilely, for example in the form of a vibration alarm.

[0023] Further embodiments may show how, in addition to the mask pressure, further peripheral parameters may be determinable by the control unit. Peripheral parameters during operation of the aircraft or flight device may include, for example: - Ambient pressure outside the cockpit or cabin of an aircraft or flight device -The ambient temperature in the cockpit or cabin of an aircraft or flight device -Gas composition in the cockpit or cabin of an aircraft or flight vehicle -The absolute and / or relative humidity in the cockpit or cabin of an aircraft or flight vehicle -Density and / or ambient pressure within the cockpit or cabin of an aircraft or flying device -The ambient temperature in the cockpit or cabin of an aircraft or flight device -Gas composition in the cockpit or cabin of an aircraft or flight vehicle - Ambient pressure outside the cockpit or cabin of an aircraft or flight device -The ambient temperature outside the cockpit or cabin of the aircraft or flight device -Gas composition outside the cockpit or cabin of an aircraft or flight device -The absolute and / or relative humidity outside the cockpit or cabin of an aircraft or flight device -Density and / or ambient pressure outside the cockpit or cabin of an aircraft or flight device -The ambient temperature outside the cockpit or cabin of the aircraft or flight device -Gas composition outside the cockpit or cabin of an aircraft or flight device - pressure levels, pressure progression, pressure time progression, pressure differentials and pressure variations in breathing gases, breathing gas mixtures or in breathing air supplied to an aircraft pilot, pilot or co-pilot; -Pressure levels, pressure progressions, pressure differences and pressure fluctuations in the provision of breathing gas, breathing gas mixtures or breathing air on-board technology (e.g. gas tanks, compressed oxygen cylinders, intake, gas treatment, filtering).

[0024] In at least some embodiments, the control unit may be configured to take into account and / or include in the metrological monitoring sequence at least one situation parameter, where situation parameter or current situation parameter is understood to mean an operational situation of the aircraft or flight device and / or a condition resulting from the situation. This includes, for example: -Flight direction -Flight altitude -Flight axis attitude -Flight posture, e.g. inverted flight, turning flight, diving flight, descending flight, ascending flight, etc. -Airspeed -Flight direction -Horizontal acceleration -Vertical acceleration - Yaw or roll angle -Residual stock of oxygen or air -Residual stocks of compressed oxygen gas or compressed air.

[0025] In some embodiments, the monitoring system can have a data interface. The data interface can be configured as a unidirectional or bidirectional data interface, for example, for providing data, receiving data, exchanging data, or communicating with components of the aircraft or flight equipment. In at least some examples, the status and / or environmental parameters can be received by and / or provided to the monitoring system and / or control unit using the data interface. In at least some examples, the status and / or environmental parameters can be metrologically detected using additional sensors of the sensor system arranged in or on the monitoring system and provided to the control unit. In this regard, in the sensor system, in addition to the sensor system that metrologically detects oxygen and / or carbon dioxide, it is possible to use additional gas sensors, such as, for example, additional gas sensors that metrologically detect carbon monoxide, as well as additional gas sensors, such as, for example, electrochemical gas sensors, catalytic gas sensors, optical, infrared optical gas sensors, photoionization gas sensors, solid electrolyte gas sensors, or semiconductor gas sensors, so that the respiratory gas can be monitored in addition to the metrological detection of the concentrations of oxygen and carbon dioxide, as well as additional substances, such as, for example, hydrocarbons, residues, or products of the combustion process. As further sensors in the sensor system, pressure sensors may be provided, which may be configured to metrologically detect an ambient pressure from the surroundings, in particular a pressure or density inside and / or outside the cockpit or cabin of the aircraft or flight device, and provide it to the control unit. Further sensors in the sensor system may be configured as temperature sensors, which may be configured and provided for metrologically detecting an ambient temperature from the surroundings, in particular a temperature inside and / or outside the cockpit or cabin of the aircraft or flight device, and provide it to the control unit.These further sensors in the sensor system may be configured as humidity sensors for detecting the ambient absolute or relative humidity, and these humidity sensors may be configured and provided for metrologically detecting the humidity in the surroundings, in particular the humidity inside and / or outside the cockpit or cabin of the aircraft or flying device, and providing it to the control unit.

[0026] In some embodiments, further sensors may be provided on / in or assigned to the sensor system in the monitoring system to detect data for determining situation parameters, which enable the control unit to determine the current flight situation, including flight altitude, flight direction, flight speed, flight acceleration, flight attitude with orientation in space and flight status or flight maneuver (e.g. climb, descent, turning, landing approach, takeoff). For this purpose, for example pressure sensors, acceleration sensors, altitude sensors, compass sensors, gyro sensors, humidity sensors, temperature sensors are arranged on or in or assigned to the sensor system.

[0027] In some embodiments, the sensor system may be located in the immediate vicinity of the mouth / nose area in or on the breathing mask. In such cases, depending on the flow-technical givens in the mouth / nose area, active transport of the breathing gas to the sensor system may be omitted. The breathing gas reaches the sensor system passively, i.e. by diffusion from the mouth / nose area in the mask. In certain configurations, the integration of the sensor system in or on a part of the breathing mask may be possible. Due to progressive technological developments in the field of chip and / or MEMS technology, a miniaturization of the elements of electrochemical, catalytic or semiconductor sensor systems can be expected in the near future, which therefore allows the integration of sensor systems, preferably oxygen sensor systems, carbon dioxide sensor systems and further gas sensors, and additionally and optionally pressure and / or temperature sensor systems, directly at the measurement point.

[0028] In some embodiments, the gas-carrying module may be provided with an additional gas connection, which allows a predetermined or partial amount of gas or ambient air from the cabin or cockpit to be connected and supplied to the monitoring system. Via a switching valve (e.g. a 3-port / 2-way valve) or a valve system, the pump or gas-carrying module can selectively supply a predetermined or partial amount of gas from ambient air or from the mouth / nose area of ​​the pilot, co-pilot, for example from a breathing mask.

[0029] In some embodiments, further pumps may be provided, one pump provided and arranged to deliver a quantity or partial amount of gas from the ambient air to the oxygen measuring module and / or the carbon dioxide measuring module or to the oxygen sensor and / or the carbon dioxide sensor, and the further pump provided and arranged to deliver a quantity or partial amount of gas from the pilot's, pilot's or co-pilot's mouth / nose area, e.g. from a breathing mask, to the oxygen measuring module and / or the carbon dioxide measuring module or to the oxygen sensor and / or the carbon dioxide sensor. Thus, in such embodiments, a switching valve (e.g. a 3-port / 2-way valve) or a valve system for switching between the quantities or partial amounts of breathing gas may be omitted.

[0030] In some embodiments, the control unit may be configured to control the gas conveying module, which in this case includes starting, stopping, setting, open-loop or closed-loop control of the gas conveying module. This setting may in particular include setting the rotation 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, a decision can be made regarding the presence of a leak in the measurement gas line based on the detection of the gas concentration measurements and / or pressure measurements (for example also based on the pressure difference between the mask and the cockpit).

[0031] In some embodiments, the control unit may further be configured to take into account and / or include in the control at least one ambient or situation parameter during the control of the gas delivery module. Such considerations may include, in particular, the adaptation of the start, stop, speed, delivery rate and / or pressure level of the gas delivery module. This may make it possible to stop the gas delivery module during certain flight maneuvers, for example during ascent, descent, turning, etc., and / or start it after completion of the maneuver, possibly with a higher delivery rate.

[0032] In at least some embodiments, the monitoring system and / or the control unit may be configured to determine and / or identify an alarm situation, organize an alarm or alarm generation, and / or provide an alarm signal. The control unit may determine and / or identify an alarm situation, trigger an alarm, and / or provide an alarm signal, for example to a data interface or other interface, based on measurements of the sensor system and / or information provided by means of the data interface. The alarm may be performed as a visual and / or acoustic and / or tactile alarm. A visual alarm may be performed, for example, in the form of white and / or colored light emitting means (LED, stroboscope) or text output (LCD, LED, display). Such an alarm may also be performed in a visual manner, using a device suitable for visualization, on or in a face mask or respiratory mask, for example as a representation on an in-mask display or a head-up display. An acoustic alarm may be performed, for example, in the form of a voice output or by means of an acoustic alarm generation (horn, siren). Tactile warnings can be provided, for example, in the form of vibration alarms, on flight equipment such as seats, control elements (foot pedals, handles), and on the equipment (breathing mask, breathing hose) or clothing (suit, vest, parachute, shoes) of the aircraft operator, pilot, or co-pilot.

[0033] In some embodiments, the control unit can take into account and / or include in the composition of the warning or alarm generation and / or in the provision of the warning signal the ambient and / or situation parameters. This makes it possible in an advantageous manner to provide the aircraft pilot, pilot or co-pilot with relevant alarm information prioritized according to relevance in an organized or compact manner regarding the status of metrological detections in the breathing gas related to the status in the surroundings (temperature, gas composition in the outside air) and the aircraft usage or operation status (takeoff phase, landing approach, air refueling, descent, circling, climb). In a particular configuration, the control unit can take into account and / or include in the adaptation of the signal processing the ambient and / or situation parameters when performing the signal processing and / or signal filtering of the measured values ​​of the sensor system.

[0034] In some embodiments, the control unit can use predefined thresholds, which may be stored in the data memory of the monitoring system, for values ​​of particular gas concentrations, in particular oxygen or carbon dioxide or carbon monoxide concentrations, when formulating an alarm.

[0035] In some embodiments, the control unit can apply a kind of early warning system for hypoxia identification with an alarm management adapted to the possible onset of hypoxia, using a suitable decision matrix or problem-specific, learning-capable or self-learning algorithms (SVM, Random Forest, AI, Deep Learning, PCA) based on current and past concentration measurements in the form of trend monitoring of oxygen and carbon dioxide. In a particular configuration, the control unit can in this case take into account ambient and / or situation parameters. In a particular configuration, the control unit can in this case also take into account and store in the early warning system for hypoxia identification physiological data of the aircraft pilot, pilot, co-pilot, for example ECG, heart rate, heart rate variability, oxygen saturation in blood, body temperature, etc., provided, for example, by means of a data interface or by a measurement system assigned to the monitoring system.

[0036] In some embodiments, modules such as gas measurement modules, measurement modules, and modules for ambient or environmental analysis can have at least one energy storage device, such as a primary battery or a rechargeable battery. Rechargeable battery types include, for example, lithium-ion, nickel-metal hydride, or nickel-cadmium batteries. Primary battery types include, for example, alkaline manganese, silver oxide, lithium, and aluminum-air batteries.

[0037] In embodiments having a rechargeable battery, the monitoring system may additionally include a battery charging system and / or a battery management system for at least monitoring the charging and / or status of the battery, and an interface for providing charging energy to the battery charging system and / or the battery management system. Most battery management systems have an interface for external communication, e.g., to be able to provide data or information on the status of the battery, and such an interface may be configured as wired (e.g., CAN bus), contactless (e.g., RFID, NFC), wireless (e.g., Bluetooth), or infrared optical (e.g., IrDA). Additionally, modules such as gas measurement modules, measurement modules, modules for ambient or environmental analysis can have further components, for example components for signal detection (ADμC), 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), components for control, open-loop control, closed-loop control (μC, μP), components for sequence control of operations and user interaction (μC, μP), and can have a user interface (User-Interface) with an input / output interface, at least one operating element and / or at least one display element. The at least one operating element and the at least one display element can be arranged in or on the monitoring system or assigned to the monitoring system.

[0038] By using at least one operating element, a user may, in some embodiments, be able to operate the monitoring system by initiating (starting, activation) or terminating (stopping, termination), select between different operating modes of the monitoring system, or perform maintenance, adjustment or calibration methods.

[0039] By means of at least one display element it may be possible in some embodiments to provide the user with information about events, situations, current and / or past measured values, which are metrologically detected and provided by means of a sensor or a measurement module, in particular an oxygen sensor and / or a carbon dioxide sensor or an oxygen measurement module and / or a carbon dioxide measurement module. By means of the display element the user can furthermore be provided with measurement variables derived from the measured values, such as maximum or minimum values, average values, trends, statistics, events, alarm situations, etc. Furthermore, by means of the display element the user can be given general information on the current operating state of the monitoring system, such as battery charge state, battery time remaining, maintenance information, information on the monitoring system itself, such as type, name, variant, version, serial number, initial commissioning, upcoming maintenance intervals, status data, operating state (Ready, In-OP, Stand-by), information on error functions, error memory, as well as operating instructions, etc.

[0040] The display elements may, in some embodiments, be configured as a Graphical User Interface (GUI).

[0041] In addition to the display elements, in some embodiments, input elements may be provided. The input elements may be configured as mechanical or touch-sensitive buttons or switches, rotary or slide controllers, or may be configured in the form of a Graphical User Interface (GUI). In some embodiments, the display elements may be implemented in combination with the input elements. For example, embodiments with a touch-sensitive display (touch screen) provide versatile configuration means of display and manipulation means, such as the use of gestures (swipes, drags) to change the display type, e.g. to enlarge or reduce the display elements (zoom function). The combination of the display elements and the input elements may preferably be configured as a Graphical User Interface (GUI, touch pad).

[0042] In some embodiments, input elements may be provided that allow a occupant or user of the surveillance system to initiate, annotate, trigger, initiate or complete a particular situation, defined action or state in the surveillance system. Such input elements may be configured, for example, as an annotation button and / or a panic button that are preferably operable by manual actuation. Alternatively, operation by voice commands may be possible, in which case the annotation button and / or the panic button are accordingly configured with means for voice recognition involving voice detection, voice processing and command recognition.

[0043] The input element may also be supplemented by an acceleration sensor or may be constituted by such a sensor in a further alternative embodiment. For this purpose, the control unit may use, for example, data or measurements of an acceleration sensor, which is provided on / in a sensor system in the monitoring system as a component of a further sensor system that detects data for determining situation parameters in order to metrologically detect in the monitoring system the current flight situation, including flight altitude, flight direction, flight speed, flight acceleration, flight attitude with orientation in space and flight situation or flight maneuver (e.g. ascent, descent, turning flight, landing approach, takeoff). Alternatively, an additional two- or three-axis acceleration sensor may be arranged in or on the monitoring system, which acceleration sensor represents the function of an input element in connection with the control unit. By using the acceleration sensor, movements or displacements of the monitoring system, movements or displacements of the housing of the monitoring system as well as mechanical, tactile stimuli or tactile excitations acting on the acceleration sensor can be detected sensorily and provided to the control unit as measurements or data. A mechanical or tactile stimulus or excitation is provided to the acceleration sensor in the form of a push, hit, tapping by the airplane pilot, pilot or co-pilot acting on the monitoring system with a hand movement as a force action, energy or force supply in at least one of the directions or axes that are sensorily detectable by the acceleration sensor. This can be realized particularly advantageously for the airplane pilot, pilot or co-pilot if the monitoring system is arranged as a mobile module in a closed pocket, in or on a garment, for example on or in a vest, jacket or suit. This force supply can thereby be performed as an actuation through the garment to the acceleration sensor in the monitoring system. The use of the acceleration sensor as an input means or input element can enable the actuation or operation of the monitoring system by the airplane pilot, pilot or co-pilot when a separate input element on the monitoring system configured as a mobile module is not reachable during use.This is the case, for example, when the monitoring system is arranged as a mobile module in a pocket, in or on clothing. The acceleration sensor thereby provides an alternative to operating the monitoring system by means of a manual button or a manual switching element. For the evaluation of the acceleration sensor measurements or data, the control unit can be used, but additional units equipped to detect and evaluate the acceleration sensor data may also be provided in the monitoring system. Such evaluation of the acceleration sensor data is substantially based on a time measurement. By using the time measurement in combination with a threshold value for the acceleration sensor measurements or data, an evaluation can be made regarding the duration of a tactile excitation of the acceleration sensor as well as the duration between two or more tactile excitations. In an exemplary configuration, the control unit may be configured to identify a first force application or force supply to the acceleration sensor based on the acceleration sensor measurements or data by means of a comparison with a threshold value. If the acceleration sensor measurements are above a first predetermined duration with respect to one predetermined threshold value, the control unit interprets this situation as a first force application in at least one of the directions or axes sensorily detectable by the acceleration sensor. This gives an indication for the start of the pilot's input activation with the hand movement as an input process. If the acceleration sensor measurement value then again exceeds the second predetermined threshold value for a second predetermined duration, the control unit interprets this situation as the end of the first force application. If within a third predetermined duration, an exceedance of the acceleration sensor measurement value relative to the first predetermined threshold value occurs for a first predetermined duration, the control unit interprets this situation as a further force application in at least one of the directions or axes sensorily detectable by the acceleration sensor. This gives an indication for the continuation of the pilot's input activation. If the acceleration sensor measurement value or data then falls below the second predetermined threshold value for a second predetermined duration, the control unit interprets this situation as the end of the further force application.If no further detection and identification of further force application on the acceleration sensor continues within the fourth predetermined duration, an indication for the termination of the pilot's input activation is given. By using this type of evaluation, the control unit is configured to detect and identify a "double tap" input activation by the pilot's hand movement during the monitoring operation using the evaluation of the acceleration sensor measurements with respect to the first, second thresholds and the first, second, third and fourth durations, and thus can trigger further actions in or on the monitoring system based thereon. Such actions can functionally correspond to the functions of, for example, an annotation button and / or a panic button.

[0044] In some embodiments, the configuration of the control unit can be expanded with respect to the evaluation so that, in addition to a "double tap", a "triple tap" or "quadruple tap" input is also possible. In this way, a simple coding for the operation input using the acceleration sensor is provided, so that the control unit can distinguish between various input situations using the tap difference between a "double tap", a "triple tap" or a "quadruple tap". In principle, it is also possible to configure the input of a single tap, but in that case the duration of the excitation indicating a single tap should be specified so that there is no possibility of confusion with another excitation by the aircraft pilot, the flight device or the equipment.

[0045] In some embodiments, the control unit may be configured to include in the evaluation of the duration of the tactile excitation the difference in duration between the tactile excitations of the acceleration sensor in the evaluation. These differences can then be used by the control unit in addition to the evaluation of the "multiple tap" form by increasing the number of mutually distinguishable events, for example by distinguishing between "short pauses" and "long pauses" as durations between the tactile excitations of the acceleration sensor. Such changes in pause length thereby provide a kind of Morse code in the evaluation of the tactile excitations, which is a further means for event coding with the acceleration sensor as input element.

[0046] That is, the use of the acceleration sensor as an input element provides the means and advantage that during flight operations, the pilot, pilot or co-pilot can, for example, manually initiate a measurement operation, set an entry (annotation) or a time mark in the logbook or mark a special health situation, such as a feeling of dizziness, during differentiation of various input situations with their assignment to a process or action triggered by the input, without the need to look at the monitoring system and operate a button or switch on the monitoring system. The measurement operation can be provided, for example, by a measurement operation for determining static and dynamic pressure levels in a pneumatic system or by a measurement operation for the activation of a switching valve for detecting gas concentrations in the cabin.

[0047] In some embodiments, a data memory for storing measurements of measurement variables derived from the measurements, e.g. maximum or minimum values, average values, trends, statistics, events, alarm situations, etc., may be located in or on the monitoring system or may be assigned to the monitoring system. Such a data memory may be configured as a volatile or non-volatile memory (RAM, ROM, EEPROM), as a fixed component of the monitoring system or as a removable and / or transportable memory module (USB stick, SD card). The data memory is used for data recording or data storage of the inputs made with the input elements and for this purpose may provide the functionality of a logbook, flight recorder. The logbook, in this case, preferably in embodiments with tables, lists, data sets, may record the evaluation of gas concentration measurements, flow measurements, pressure measurements, temperature measurements over time with chronological assignment and marking (annotation), further events or manual inputs with the input elements and may retain or provide them for simultaneous or subsequent evaluation. When plotting the events, the measured values ​​or measurement signals of the acceleration sensor can be taken into account in order to set, for real-time or retroactive evaluation, the respective points of time of markings / annotations made by the pilot in the logbook depending on the flight situation or flight maneuvers. When plotting the events, the measured values ​​or measurement signals of the altitude sensor can be taken into account in order to set, for real-time or retroactive evaluation, the respective points of time of markings / annotations made by the pilot in the logbook depending on the flight situation (flight altitude). When plotting the events, the measured values ​​or measurement signals of the gas supply (CO 2 , O 2 ) can be taken into account in order to set up for real-time or retrospective evaluation each time a marking / annotation made by the pilot in the logbook in response to the

[0048] In certain configurations of some embodiments, the control unit may be configured to take ambient and / or situation parameters into account when performing signal processing and / or signal filtering of the measurement values ​​of the sensor system and / or to include them in the adaptation of the signal processing.

[0049] In some embodiments, the control unit may be configured to use predefined threshold values, which may be stored in the data memory of the monitoring system, for certain gas concentration, in particular oxygen or carbon dioxide, carbon monoxide concentration values, when formulating an alarm.

[0050] In some embodiments, the control unit may provide an early warning system for hypoxia identification, for example based on current and past measurements of the sensor system in the form of trend monitoring of oxygen and / or carbon dioxide concentrations. -Using the decision matrix, -or using specially adapted algorithms -or may be configured to apply learning or self-learning algorithms (e.g., SVM, Random Forest, AI, Deep Learning, ICA, PCA).

[0051] In certain configurations of some embodiments, the control unit may in this case take into account ambient and / or situation parameters.

[0052] In a further particular configuration of some embodiments, the control unit can apply an adapted alarm management to the early warning system. In a particular configuration of some embodiments, the control unit can be configured to take into account further physiological data of the aircraft pilot, flight attendant, pilot, co-pilot, such as ECG, heart rate, heart rate variability, oxygen saturation in the blood, body temperature, etc., provided, for example, by means of the data interface or by a measurement system assigned to the monitoring system, in the early warning system for hypoxia identification.

[0053] A further embodiment provides a method for operating a surveillance system.

[0054] In some embodiments of the method for operating a monitoring system, the control unit performs a first step of activating the sensor system of the monitoring system and a second step of preparing the data storage with initialization of the data memory. In a third step, metrological detection of the measured values ​​of the sensor system of the monitoring system is performed using time control. In a fourth step, data storage of the measured values ​​in the data memory together with the associated time information is performed. The third and fourth steps are continued successively by the control unit until the completion of the method for operating a monitoring system.

[0055] In some embodiments of the method for operating a monitoring system, when storing the measurement values ​​of the sensor system in a data memory together with the associated time information, additional storage of situation parameters and / or environmental parameters may be possible.

[0056] In some embodiments of a method for operating a monitoring system, upon activation of an input element by a user, additional detection (not dependent on time control) of measurement values ​​of the sensor system may be possible at the time of activation of the input element.

[0057] Further means for improving the invention will become apparent from the following description of several embodiments of the invention as illustrated in the drawings. All features and / or advantages, including constructional details and spatial arrangements, arising from the claims, the specification or the drawings may be essential to the invention both by themselves and in various combinations. [Brief description of the drawings]

[0058] [Figure 1a] FIG. 1 is a schematic diagram of a monitoring system including a sensor system. [Figure 1b] FIG. 1 is a schematic diagram of a monitoring system including a sensor system. [Figure 2a] FIG. 1 shows a schematic diagram of a monitoring system according to FIGS. 1a, 1b with measurement functions for oxygen and carbon dioxide. [Figure 2b] FIG. 1 shows a schematic diagram of a monitoring system according to FIGS. 1a, 1b with measurement functions for oxygen and carbon dioxide. [Diagram 3] FIG. 2 shows a schematic enlarged view of a variant of the monitoring system according to FIGS. 1a, 1b, 2a and 2b. [Figure 4] FIG. 4 shows a schematic representation of a variant of the monitoring system according to FIGS. 1a, 1b, 2a, 2b and 3 with a further sensor system; [Diagram 5] FIG. 4 shows a schematic representation of a variant of the monitoring system according to FIGS. 1a, 1b, 2a, 2b and 3 with a further sensor system; [Figure 6] FIG. 4 shows a schematic representation of a variant of the monitoring system according to FIG. [Figure 7] FIG. 4 shows a schematic diagram of a further variant of the monitoring system according to FIG. [Figure 8] FIG. 7 shows a schematic representation of an alternative variant of the monitoring system according to FIG. 6. [Figure 9] FIG. 13 is a schematic diagram illustrating a flow chart for determining breathing mask pressure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0059] 1a, 1b show a monitoring system 100, which is connected by means of a measurement gas line 10 to a breathing mask 20 of a person 99. Identical elements in fig. 1a, 1b are provided with the same references as in fig. 1a, 1b. The person 99 in fig. 1 represents an airplane pilot (pilot, co-pilot) or a passenger of an airplane, in particular a jet plane (Jet). The breathing mask 20 has a gas connection 21, a connection element 23 as well as hose lines 24, 25. The hose lines 24, 25 are used for the discharge and supply of breathing gas to the person 99. In this fig. 1a, these hose lines are shown as two separate hose lines 24, 25. However, as shown in Fig. 1b, an embodiment is also possible with a connection element 23' in which there is only one hose line 25 for the inhalation of the respiratory gas supply, and exhalation takes place towards the surroundings 5 ​​via an exhalation valve 29 in the breathing mask 20. Further measures are provided by the realization of a coaxial hose system with two hose lines 24, 25 as a common element. Means or elements necessary for the maintenance or supply of the respiratory gas and for providing the respiratory gas in the aircraft or flying device are not shown in this Fig. 1a and in the remaining figures for reasons of clarity. The monitoring system 100 comprises an operating element 40, a display element 44, at least one gas conveying module 50 and a sensor system 60 with at least one sensor 66. The gas conveying module 50 is preferably connected to a pump P M and more preferably a piezoelectric actuated pump P M The monitoring system 100 further includes a control unit 70.

[0060] The operating element 40, the display element 44, the sensor system 60 and the gas conveying module 50 are connected to the control unit 70 via signal and data lines or control lines. These control lines or signal and data lines can be configured, for example, as a bus system (CAN) or a network. These control lines or signal and data lines are not shown in FIG. 1a and in the further figures for reasons of clarity. The control unit 70 is configured and provided for controlling and / or driving the gas conveying module 50 so that a discharge of the breathing gas from the breathing mask 20 through the measurement gas line 10 and the gas inlet 51 to the sensor system 60 is realized. A predetermined amount or a partial amount of the breathing gas is thus available to at least one sensor 66 of the gas sensor system 60 for metrological detection and / or analysis thereof and for providing it to the control unit 70 as a measured value. By means of the control unit 70, it is possible to evaluate, process and display the measured value at least on a partial element of the display element 44.

[0061] 2a, 2b show a monitoring system 100, 110 according to Fig. 1a, 1b, characterized in that the sensor 66 in the sensor system 60 is configured as an oxygen sensor 68 and a further sensor is also arranged in the sensor system 60 as a carbon dioxide sensor 64. Identical elements in Fig. 1a, 1b, 2a, 2b are provided with the same references as in Fig. 1a, 1b, 2a, 2b. Fig. 2b shows a variant 110 of the monitoring system according to Fig. 2a with an oxygen sensor 68 and a carbon dioxide sensor 64, which in this case is arranged directly on the breathing mask 20 without the measurement gas line 10 or is configured as part of the breathing mask 20. A pump P as in the variant according to Fig. 1a, 1b, 2a for transporting a predetermined amount of breathing gas from the breathing mask 20 to the sensor system 60 is used. Mcan possibly be omitted here. If an optional amount of gas is also to be discharged from the passenger compartment or the cockpit to the sensor system, then also in the arrangement according to FIG. 2b an optional pump 56 is arranged in or on the sensor system. The arrangement of such an optional pump 56 in the monitoring system 110 is not shown for reasons of clarity. In FIG. 2b an energy accumulator 85 is exemplarily shown (also in analogous arrangements as an optional component of the arrangements according to FIGS. 1a, 2a, 3, 4, 5). Such an energy accumulator 85 is configured as a primary battery or a rechargeable or rechargeable battery (rechargeable battery, accumulator) and is configured to be suitable for supplying the various components (60, 70, 40, 44, 75) of the monitoring systems 110, 108 (FIG. 4), 109 (FIG. 5), 100 (FIG. 1a, 1b, 2a, 3). In Fig. 2b an optional configuration is shown with a further display element 45 arranged on or in the mask 20 (also to be understood as an optional component of the configurations according to Figs. 1a, 2a, 3, 4, 5 in a similar configuration). This further display element 45 is connected to the control unit 70 by means of signal or data lines (not shown for reasons of clarity). This further display element 45 can be used additionally or alternatively to the display element 44. The configuration of the further display element can be realized, for example, in the form of an in-mask display or a head-up display. Fig. 2a additionally shows a data interface 90. This data interface 90 can be arranged, on the one hand, to receive data from the outside and then provide these data to the control unit 70. The data lines belonging to the data interface are not shown in Fig. 2a as well as in the further figures for reasons of clarity. On the other hand, the data interface 90 can be used to provide, for example, measured values ​​of the monitoring system 100 or the sensor system 60 to the outside.For this purpose, current ambient or status parameters for the status of the aircraft or flight equipment are received via this data interface 90 (eg from components of the aircraft or flight equipment) and are used during the processing of the measured values ​​and / or the pump P. M 50 to the control unit 70 to be taken into account in the control of the aircraft or flight equipment. Furthermore, the measured values ​​and / or the measured variables or parameters derived therefrom, as well as information or status data from the control unit 70 can be provided for the aircraft or flight equipment components by means of a data interface. In this way, it is possible, for example, to have the measured values ​​and / or the measured variables or parameters derived therefrom, as well as information or status data displayed on an external display element of the aircraft or flight equipment. The data interface may be, for example, wired (CAN bus, LAN, Ethernet, RS485, NMEA183) or wireless (WLAN, Bluetooth, NFC), unidirectional or bidirectional. Current ambient parameters for the ambient situation of the aircraft or flight equipment include, for example: - Ambient pressure outside the cockpit or cabin of an aircraft or flight device -The ambient temperature in the cockpit or cabin of an aircraft or flight device -Gas composition in the cockpit or cabin of an aircraft or flight vehicle -The absolute and / or relative humidity in the cockpit or cabin of an aircraft or flight vehicle -Density and / or ambient pressure within the cockpit or cabin of an aircraft or flying device -The ambient temperature in the cockpit or cabin of an aircraft or flight device -Gas composition in the cockpit or cabin of an aircraft or flight vehicle - Ambient pressure outside the cockpit or cabin of an aircraft or flight device -The ambient temperature outside the cockpit or cabin of the aircraft or flight device -Gas composition outside the cockpit or cabin of an aircraft or flight device -The absolute and / or relative humidity outside the cockpit or cabin of an aircraft or flight device -Density and / or ambient pressure outside the cockpit or cabin of an aircraft or flight device -The ambient temperature outside the cockpit or cabin of the aircraft or flight device -Gas composition outside the cockpit or cabin of an aircraft or flight device - pressure levels, pressure progression, pressure time progression, pressure differentials and pressure variations in the breathing gas, breathing gas mixture or breathing air supplied to an aircraft pilot, pilot or co-pilot; -Pressure levels, pressure progressions, pressure differences and pressure fluctuations in the provision of breathing gas, breathing gas mixtures or breathing air on-board technology (e.g. gas tanks, compressed oxygen cylinders, intake, gas treatment, filtering, gas discharge).

[0062] Status parameters or current status parameters for the status of the aircraft or flight device include, for example: -Flight direction -Flight altitude -Flight axis attitude -Flight posture, e.g. inverted flight, turning flight, diving flight, descending flight, ascending flight, etc. -Airspeed -Flight direction -Horizontal acceleration -Vertical acceleration - Yaw or roll angle -Residual stock of oxygen or air -Residual stocks of compressed oxygen gas or compressed air.

[0063] 3 shows a monitoring system 100 according to FIGS. 1a, 1b, 2a, characterized in that an input element 80 in signal or data connection with the control unit 70 is arranged in the monitoring system. Identical elements in FIGS. 1a, 1b, 1c, 2, 3 are provided with the same references as in FIGS. 1a, 1b, 1c, 2, 3. Via this input element 80, the aircraft pilot, pilot or co-pilot can mark certain events or situations of the flight operations as well as certain personal, for example health events, situations or symptoms, such as fever, tachycardia or dizziness, in the time course of the inputs. These markings can be used by the control unit 70 to combine the events or situations with time information and then store these combinations of time information and events or situations in the data memory 75. The data memory 75 may be configured as a volatile or non-volatile memory (RAM, ROM, EEPROM) and may be arranged as a fixed component in or on the monitoring system 100, 110 (FIG. 2b) or as a removable memory module (USB stick, SD card). It may also be possible to provide and / or exchange data with an external evaluation unit (not shown in the figures), for example by means of a data interface 90 of a similar configuration as shown and described in FIG. 2b. This input element 80 can thereby be used to supplement the detected measurements of the sensor system 60 and the events and situations of the flight operation with further information provided by the aircraft pilot, pilot or co-pilot using the input element, for example to include time information in the form of a time stamp. However, it is also possible to configure the input element as a panic button, to which the aircraft pilot, pilot or co-pilot can immediately draw the attention of the aircraft pilot, pilot or co-pilot in a particular situation from his perceptual senses, for example a situation involving a particular dangerous attitude or risk situation felt objectively or subjectively.The marked measured values ​​and / or events, situations and specific situations can also be provided to the outside, for example directly using the data interface 90, and possibly even transmitted (likewise directly (online)) to a ground station or to another aircraft or flying device via a communication system of the aircraft or flying device. Furthermore, an evaluation of the marked measured values ​​and / or events, situations and specific situations can be performed afterwards (offline) using the data memory 75 and / or the data interface 90 after launch.

[0064] Figures 4 and 5 show variants of the monitoring system 100, 110 according to Figures 1a, 1b, 2a, 2b, 3 with further components of the sensor system 60. The associated control lines or signal and data lines for the further sensors of the sensor system 60 are not shown in Figures 4 and 5 for reasons of clarity. Identical elements in Figures 1a, 1b, 1c, 2, 3, 4, 5 are provided with the same references as in Figures 1a, 1b, 1c, 2, 3, 4, 5. These further sensors of the sensor system 60 can be used to determine current ambient parameters inside and / or outside the cockpit or cabin of the aircraft or flight device and / or to determine current situation parameters and situations, as well as to determine physical properties and further the composition of the breathing gas. As further components of the sensor system 60, the monitoring system 108 in FIG. 4 exemplarily shows the following further sensors, which are also to be understood as optional means of the arrangement for FIGS. 1a, 1b, 2a, 2b, 3, 5: at least one acceleration sensor 61 in the form of a two-axis or three-axis acceleration sensor (Accelerometer); at least one compass sensor 62, such as an electronic compass, a gyro compass or a fluxgate compass; - at least one altitude sensor58 at least one gyro sensor 63;

[0065] As further components of the sensor system 60, in FIG. 5 the following further sensors are exemplarily shown, which are also to be understood as optional means of the arrangement for FIGS. 1a, 1b, 2a, 2b, 3, 4: at least one temperature sensor 69, 69' at least one pressure sensor 67, 67' at least one humidity sensor 59,59'

[0066] Further sensors in the sensor system 60 may be configured as pressure sensors, which may be configured and provided for metrologically detecting the ambient pressure from the surroundings, in particular the pressure or density inside and / or outside the cockpit or cabin of the aircraft or flight device, and providing it to the control unit 70. Further sensors in the sensor system 60 may be configured as temperature sensors, which may be configured and provided for metrologically detecting the ambient temperature of the surroundings, in particular the temperature inside and / or outside the cockpit or cabin of the aircraft or flight device, and providing it to the control unit 70. Further sensors in the sensor system 60 may be configured as humidity sensors, which may be configured and provided for metrologically detecting the humidity in the surroundings, in particular the humidity inside and / or outside the cockpit or cabin of the aircraft or flight device, and providing it to the control unit 70. Further sensors in the sensor system 60 may be configured as humidity sensors, which may be configured and provided for metrologically detecting the humidity in the surroundings, in particular the humidity inside and / or outside the cockpit or cabin of the aircraft or flight device, and providing it to the control unit 70. The further sensor in the sensor system 60 may be configured as at least one further gas sensor 65 for detecting the gas composition in the surroundings, which may be configured and provided for metrologically detecting the gas composition in the surroundings, in particular inside and / or outside the cockpit or cabin of the aircraft or flight device, and providing it to the control unit 70. As further gas sensor, 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 monitor the breathing gas in addition to metrological detection of the concentrations of oxygen and carbon dioxide, further with respect to further substances, such as carbon monoxide, hydrocarbons, residues or products of the combustion process. For example, the switching valve 55 shown in FIG. 4 configured as a valve module or as part of a valve module allows the switching of a given or partial amount of the gas sample between the gas inlet 51 and the further gas connection 52. This allows, on the one hand, the pump P M50 allows the respiratory gas from the respiratory mask 20 to be delivered to the sensor system 60, and further includes a pump P M It is also possible to use the switching valve 55 to deliver a defined amount of gas or gas mixture from the surroundings 5 ​​to the sensor system 60 and to metrologically detect it by means of the sensor system 60. The switching valve 55 is controlled by the control unit 70. Thus, it is possible to supply fresh air from outside the aircraft or flying device or internal air from the cabin or cockpit of the aircraft or flying device via the further gas connection 52, and it may be possible alternately to monitor the gas concentration in the breathing mask 20, in the cockpit, in the cabin or in the outside air (under the control of the control unit 70).

[0067] The further sensors 59′, 64′, 68′, 69′ and at least one further gas sensor 65′ are shown in addition to the further gas sensor 65 and the sensors 59, 67, 69 in the monitoring system 109 in FIG. A 56. Identical elements in Figures 1a, 1b, 1c, 2, 3, 4 and 5 are provided with the same reference numerals as in Figures 1a, 1b, 1c, 2, 3, 4 and 5. This further pump P A 56 allows the supply of gas from the surroundings 5 ​​via a further gas connection 53, for example a supply of fresh air from the outside of the aircraft or flight device or a supply of internal air from the cabin or cockpit of the aircraft or flight device. A56 is controlled by the control unit 70. Thus, fresh air from outside the aircraft or flight device or internal air from the cabin or cockpit of the aircraft or flight device can be supplied via the further gas connection 53. This allows simultaneous monitoring of the gas concentration in the breathing mask 20 and the gas concentration in the cockpit, cabin or external air. Further sensors of the sensor system 60 may be configured to metrologically detect the current situation of the aircraft or flight device. Thus, using data from an acceleration sensor 61, preferably configured as a 3-axis-accelerometer, in combination with information from an altitude sensor 58 (Altimeter), a gyro sensor 63 and an optionally considered compass sensor 62, the control unit (70) can determine the current flight situation, including flight altitude, flight direction, flight speed, flight acceleration, flight attitude with orientation in space (XYZ-Orientation) and flight situation or flight maneuver (e.g. climb, descent, turning flight, landing approach, takeoff).

[0068] FIG. 6 shows a variant of the variant of FIG. 3, in which the pump P M 50 or a gas conveying module is arranged at the gas outlet 49 of the monitoring system 100'. This means that the pump P M 50 cannot reach the monitoring system 100', in particular the sensor system 60 having the carbon dioxide sensor 64 and the oxygen sensor 68. Identical elements in Figures 1a, 1b, 1c, 2, 3, 4, 5 and 6 are provided with the same reference numerals as in Figures 1a, 1b, 1c, 2, 3, 4, 5 and 6. Preferably, the pump P M Components that may be required to control 50 and deliver a given amount of gas include pump P M 50. For this purpose, a pressure sensor 47, a flow sensor 48 and a shutoff valve 57 are provided in close proximity to the pump P MThe flow rate sensor 48 is disposed near the pump P M It is used for metrological control of the flow rate delivered by pump P M After flowing through the flow sensor 50 and the flow sensor 48, the discharged amount of gas reaches the environment 5 towards the outside of 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 in the closed state of the shut-off valve 57 can thus detect the mask pressure in the breathing mask 20 in the flow-free state, which is therefore identical to the pressure level at the gas inlet 51 and in the measurement gas line 10. Alternatively, the pressure sensor can be arranged in the gas flow near the gas inlet, in the measurement gas line 10 or near the gas sensors 60, 64, 68. The gas inlet 51 is provided with a switching valve 55, which allows switching of an amount or a part of the gas sample between the gas inlet 51 and the further gas connection 52 (in a manner equivalent to the switching valve 55 described in FIG. 4). The switching valve 55 is preferably configured as a 3-port / 2-way valve. With this arrangement, at the gas inlet 51, the pump P M 50, on the one hand, makes it possible to deliver the breathing gas from the breathing mask 20 to the sensor system 60, but also to pump P M By using the pump P it is also possible to discharge a defined amount of gas or gas mixture from the surroundings 5 ​​through a further gas inlet 52 to the sensor system 60 and to detect metrologically by means of the sensor system 60. The switching valve 55 is controlled by the control unit 70. Thus, it is possible to supply fresh air from outside the aircraft or flight device or internal air from the cabin or cockpit of the flight device via the further gas connection 52, and it may be possible alternately to monitor the gas concentration in the breathing mask 20, in the cockpit, in the cabin or in the outside air (under the control of the control unit 70). MIn order to protect the sensor system 60 from moisture and condensation water supplied to the sensor system 60 through the measurement gas line 10 from the respiratory mask 20 using 50, a filter element (HME filter) 54 may be arranged in series in the measurement gas line 10 or at the outlet of the switching valve 55.

[0069] Instead of an input element 80 configured in the form of a switching element as in the arrangement 100 according to FIG. 3, in this arrangement 100′ according to FIG. 6 an acceleration sensor 61 is provided as an input element, which is configured as and provided for an alternative operation or input element for detecting manual operations of the airplane pilot. Via this alternative operation or input element or acceleration sensor 61, the airplane pilot, pilot or co-pilot can mark certain events or situations of the flight operations as well as certain personal, for example health events, situations or symptoms, such as fever, tachycardia or dizziness, in the time course of the inputs. These markings can be utilized by the control unit 70 to combine the events or situations with time information and then store these combinations of time information and events or situations in the data memory 75. The data memory 75 may be configured as a volatile or non-volatile memory (RAM, ROM, EEPROM) and may be arranged as a fixed component in or on the monitoring system 100′ or as a removable memory module (USB stick, SD card). It may also be possible to provide and / or exchange data with an external evaluation unit (not shown in the figures), for example by means of a data interface 90 of a similar configuration as shown and described in Fig. 2b. This alternative operation or input element or acceleration sensor 61 can thereby be used to supplement the detected measured values ​​of the sensor system 60 and the events and situations of the flight operations with further information provided by the aircraft pilot, pilot or co-pilot by means of the alternative operation or input element or acceleration sensor 61, for example to include time information in the form of a time stamp. However, it is also possible for the alternative operation or input element or acceleration sensor 61 to be configured as a panic button, to which the aircraft pilot, pilot or co-pilot can immediately draw his attention in a particular situation from his perceptual senses, for example in a situation involving a particular dangerous attitude or risk situation felt objectively or subjectively.The marked measured values ​​and / or events, situations and specific situations can also be provided directly to the outside, for example by means of the data interface 90, and possibly even transmitted to a ground station or to another aircraft or flying device (also directly (online) via the aircraft's or flying device's communication system). Furthermore, the evaluation of the marked measured values ​​and / or events, situations and specific situations can be performed afterwards (offline) by means of the data memory 75 and / or the data interface 90 after the launch.

[0070] FIG. 7 (which differs in part from FIG. 6 as a detailed view of the area around the gas inlet 51) shows the filter element (HME filter) 54, pump P, and the like in an arrangement in which the gas inlet 51 does not have a changeover valve for switching between monitoring the pilot's breathing gas and monitoring the cabin air. M 50, a sensor system 60, a pressure sensor 47, a flow sensor 48 and a shutoff valve 57. The same elements in Fig. 1a, 1b, 1c, 2, 3, 4, 5, 6 and 7 are given the same reference numerals as in Fig. 1a, 1b, 1c, 2, 3, 4, 5, 6 and 7. The pressure sensor 47 is arranged upstream in the gas flow relative to the shutoff valve 57 so that by measuring the pressure when the shutoff valve 57 is closed, a mask pressure in the respirator 20, which is the same as the pressure level at the gas inlet 51 and in the measurement gas line 10 in the subsequent no-flow state, can be detected. The pressure sensor 47 may alternatively be arranged in the gas flow near the gas inlet 51, in the measurement gas line 10 or near the sensor system 60 with the gas sensor.

[0071] FIG. 8 (which differs in part from FIGS. 6 and 7 as a detailed view of the area around the gas inlet 51) shows the filter element (HME filter) 54, the pump P M50, a sensor system 60, a pressure sensor 47 at the gas inlet 51 and a switching valve 55 in the configuration of a 3-port / 2-way valve are shown. Identical elements in FIGS. 1a, 1b, 1c, 2, 3, 4, 5, 6, 7, 8 are provided with the same references as in FIGS. 1a, 1b, 1c, 2, 3, 4, 5, 6, 7, 8. The switching valve 55 can open the path for the gas quantity from the surroundings 5, for example the passenger cabin, to the sensor system 60, so that monitoring of the cabin air is possible. At the same time, the switching valve closes the path for the gas quantity from the breathing mask 20. In this configuration according to FIG. 8, the switching valve 55, besides switching between the measurement of the breathing gas and the measurement of the cabin air, also has the functionality as a shut-off valve for carrying out a measurement operation for determining the pressure in the breathing mask. The pressure sensor 47 is arranged in gas inlet 51 in relation to the switching valve 55 and the measurement gas line 10 so that a pressure measurement in the state of the switching valve 55 with cabin air monitoring can detect a mask pressure in the breathing mask 20 which is the same as the pressure level at the gas inlet 51 and in the measurement gas line 10. The switching valve 55 is capable of switching between monitoring the pilot's breathing gas and monitoring the cabin air.

[0072] FIG. 9 shows a schematic sequence 200 of measurement operations for determining the pressure level in the respiratory mask 20 (FIG. 6) using the monitoring system 100′ according to FIG. 6. Identical elements in FIGS. 1a, 1b, 1c, 2, 3, 4, 5, 6, 7, 8, 9 are provided with the same references as in FIGS. 1a, 1b, 1c, 2, 3, 4, 5, 6, 7, 8, 9. The measurement operations in the step sequence starting with START 201 up to STOP 210 are performed by the control unit 70 (FIG. 6) in the configuration with the shutoff valve (Flow-Lock-Valve) 57 (FIG. 6). After START 201, the pump P M50 is stopped 202 (FIG. 6) and, at the same time or after a slight time delay, the shut-off valve 57 (FIG. 6) is closed 203. As a result, the flow stops in the measurement gas line 10 (FIG. 6) and the sensor system 60 (FIG. 6) is brought to a quiescent state. A measurement step 204 of a first pressure measurement is carried out to determine the static pressure level. Then, the shut-off valve 57 (FIG. 6) is opened 205 and the pump P M 50 (FIG. 6) is started 206. M 50 (FIG. 6) starts to draw a volume of gas from the breathing mask 20 (FIG. 6) through the measurement gas line 10 (FIG. 6) and the sensor system 60 (FIG. 6) with a defined volume of gas in the range of 50 ml / min to 100 ml / min. A flow measurement 207 is then performed by means of the flow sensor 48 (FIG. 6) for controlling and monitoring the volume of the gas. A further measurement process 208 of pressure measurement is then performed for determining the dynamic pressure level. From the pressure measurements of the first pressure measurement 204 and the pressure measurements of the further pressure measurement 208, a calculation 209 of a difference value is performed, which difference value indicates the current pressure drop for the pneumatic system. In this way, the sequence of measurement operations is ended 210. The difference value thus determined can thus be provided and used for the determination of the mask pressure in further operation of the monitoring system during use of the flying device. [Explanation of symbols]

[0073] 5 Surroundings, atmosphere, outside air, cockpit, or passenger cabin 10. Measurement gas line 20 Respiratory Mask 21 Gas connection to breathing mask 24,25 Hose line 23,23' Connection element 29 Exhalation valve 40 Operational Elements 44,45 Display elements 46 Wireless Interfaces, Radio Interfaces 47 Pressure Sensor 48 Flow sensor (Flowsensor, ΔP-Sensor) 49 Gas outlet 50 Gas transport module, pump P M 51 Gas inlet 52,53 Further gas connections 54 Filter Element (HME-Filter) 55 Switching valve (3-port / 2-way valve), valve module 56 More Pumps P A 57 Flow-Lock-Valve 58 Altimeter 59,59' Humidity Sensor 60 Sensor System 61 Acceleration Sensor 62 Compass Sensor 63 Gyro sensor 64,64' Carbon Dioxide Sensor 65 More Gas Sensors 66 Sensors 67,67' Pressure Sensor 68,68' Oxygen Sensor 69,69' Temperature sensor 70 Control Unit 80 input elements 90 Data Interface 99 Personnel, pilots, flight attendants 100,100' Surveillance System 108,109,110,111,112 Surveillance systems 200 Sequence of measurement operations 201 Start, start 202 Pump: Stopped 203 Shut-off valve: Valve closed 204 First Pressure Measurement: Static Pressure Level 205 Shut-off valve: Valve open 206 Pump: Start 207 Flow measurement 208 Further Pressure Measurements: Dynamic Pressure Levels 209 Determining the current pressure drop value 210 End, stop

Claims

1. A monitoring system (100, 108, 109, 110) for monitoring the gas composition of air, breathing air or breathing gas in an aircraft or flight device, said monitoring system (100, 108, 109, 110) comprising: A control unit (70) and a sensor system (60) are provided. said control unit (70) being configured to organize, control, open-loop or closed-loop control a sequence of metrological monitoring of the gas composition of air, breathing air or breathing gas in said aircraft or flight device; said sensor system (60) being capable of metrological detection, both qualitative and quantitative, of the concentration of carbon monoxide; The monitoring system (100) is connected to a breathing mask (20) using a measurement gas line (10); A pump (50) is arranged in the monitoring system (100) having at least one gas connection (51) for delivering a predetermined amount or a portion of the breathing gas or breathing air from the breathing mask (20) to the sensor system (60) by means of the measuring gas line (10), said control unit (70) being configured to control said pump (50) and the further pump (56) so that fresh air from outside the aircraft or flight vehicle or internal air from the cabin or cockpit of the aircraft or flight vehicle can be supplied via a further gas connection (53); The sensor system (60) includes a paramagnetic oxygen sensor. A monitoring system (100, 108, 109, 110).

2. The sensor system (60) allows for the metrological detection of the concentration of oxygen, both qualitative and quantitative. The monitoring system (100, 108, 109, 110) of claim 1.

3. The sensor system (60) allows for qualitative and quantitative metrological detection of the concentration of carbon dioxide. The monitoring system (100, 108, 109, 110) of claim 1.

4. The sensor system (60) further comprises a carbon dioxide sensor (64) or a carbon monoxide sensor (65, 65'). The monitoring system (100) of claim 1.

5. the control unit (70) is configured to take into account and / or include in the metrological monitoring sequence at least one peripheral parameter and / or at least one situation parameter when controlling said sequence, The monitoring system (100, 108, 109, 110) of claim 1.

6. The monitoring system (100, 108, 109, 110) has a data interface (90). The monitoring system (100, 108, 109, 110) of claim 1.

7. said monitoring system (100, 108, 109, 110) having a data interface (90) for receiving and / or providing ambient and / or situation parameters; The monitoring system (100, 108, 109, 110) of claim 1.

8. the sensor system (60) comprises further sensors (61, 62, 63, 64, 64', 65, 67, 67', 58, 58') for determining and / or metrologically detecting an ambient parameter and / or for determining and / or metrologically detecting a situation parameter, the sensor system (60) being configured to provide the environmental parameter and / or the situation parameter, The monitoring system (100, 108, 109, 110) of claim 1.

9. The pump (50) is disposed at a gas inlet of the monitoring system (100). The monitoring system (100) of claim 1.

10. The pump (50) is arranged at a gas outlet (49) of the monitoring system (100'). The monitoring system (100) of claim 1.

11. a further gas connection (52) having a switching valve (55) is arranged in the monitoring system (100, 100', 108, 109, 110, 111, 112) or in or on the pump (50); A monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1.

12. At the further gas connection (52) another pump (56) is arranged, A monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 11.

13. the control unit (70) is configured to take into account and / or include in the control of the pump (50) at least one peripheral parameter and / or at least one state parameter. A monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 1.

14. the monitoring system (100, 100', 108, 109, 110, 111, 112) and / or the control unit (70) are configured to determine and / or identify an alarm situation, organize an alarm or alarm generation, and / or provide an alarm signal, A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 13.

15. the control unit (70) is configured to take into account and / or include in the organization of the alarm or the generation of the alarm and / or in the provision of the alarm signal ambient and / or situational parameters. A monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 14.

16. The monitoring system (100, 100', 108, 109, 110, 111, 112) comprises at least one energy accumulator (85), A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims.

17. at least one operating element (44) for operating said monitoring system (100, 100', 108, 109, 110, 111, 112) is arranged in or on said monitoring system (100, 108, 109, 110) or is assigned to said monitoring system (100, 108, 109, 110); A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims.

18. In or on said monitoring system (100, 100', 108, 109, 110, 111, 112), - Events, situations, status data, current measurements, - past measurements, - measurement variables, maximum or minimum values, averages, trends, statistics, events and alarm conditions derived from measurements; at least one display element is arranged on or assigned to the monitoring system (100, 108, 109, 110) for displaying A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims.

19. an input element (80) disposed in or on said monitoring system (100, 100', 108, 109, 110, 111, 112), said input element (80) configured to allow a user to initiate, annotate, trigger, initiate or complete a particular situation, defined action or state on said monitoring system; A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims.

20. The input element (80) is constituted by an acceleration sensor (61). A monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 19.

21. a data memory is arranged in or on said monitoring system (100, 100', 108, 109, 110, 111, 112) or is assigned to said monitoring system (100, 108, 109, 110) for storing measured values ​​of measurement variables, maximum or minimum values ​​derived from the measured values, average values, trends, statistics, events and alarm situations, A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 20.

22. the control unit (70) is configured to take into account environmental and / or situation parameters when performing signal processing and / or signal filtering of the measured values ​​of the sensor system and / or to include them in the adaptation of the signal processing, A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 21.

23. the control unit (70) is configured to use predefined threshold values ​​for oxygen, carbon dioxide or carbon monoxide concentration when generating an alarm, the threshold values ​​may be stored in a data memory of the monitoring system. A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 22.

24. The control unit (70) determines, based on current and past measurements of the sensor system (60), - decision matrix, - or an adapted algorithm, or configured to apply an early warning system for hypoxia identification using a learning or self-learning algorithm, A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 23.

25. The control unit (70) is configured to take physiological data into account in an early warning system for hypoxia identification. A monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 24.

26. an HME filter element (54) is arranged in the measurement gas line (10), in the gas inlet (51) or in the pump (50); A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of claims 1 to 25.

27. said control unit (70), together with a pressure sensor (47), a shutoff valve (57) and a data memory (75), configured to determine a current pressure level within the respiratory mask (20); A monitoring system (100, 100', 108, 109, 110, 111, 112) according to any one of the preceding claims.

28. The control unit uses a measurement operation (200) to - determining the static and dynamic pressure levels; - determining an offset pressure level based on said static pressure level and said dynamic pressure level; - configured to take said dynamic pressure level into account when determining the current pressure level in said respiratory mask (20); A monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 27.

29. The control unit is adapted to control the aircraft operation during metrological detection and / or determination of static and / or dynamic pressure measurements during the performance of the measurement operation (200). and configured to take into account information regarding the respiratory phase of the user. A monitoring system (100, 100', 108, 109, 110, 111, 112) according to claim 28.

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