50 results about "Air data computer" patented technology

A deicing system includes dual deice system components to provide a redundant deice system. Each redundant portion of the system generally includes a controller, an air data computer, an ice rate controller, and an ice rate probe. The controller communicating a heating cycle which defines a multiple of electric pulse trains to sequentially provides power to a multiple of heating elements in a designated blade set. Each electric pulse train is defined by an element on-time, a null time between the element on-time for this element and the next element, and an off-time between repetition of the heating cycle for the first heater element. The element on-time is a function of outside air temperature (OAT). The off-time is a function of liquid water content. The tail rotor heating cycle is a more straightforward version of the main rotor heating cycle as each of the tail rotor blade are activated simultaneously and there is only a single heating element on each tail rotor blade.

A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information or in lieu of the ADC information when the ADC information is unreliable or unavailable.

The invention discloses a forward-looking forecast warning system in a ground proximity warning system and a method, which is characterized in that the forward-looking forecast warning system comprises a forward-looking forecast warning processor. The input end of the forward-looking forecast warning processor is connected with an air data computer, a navigation system, radio equipment, and a terrain memory, the aircraft speed and the flight path angle information are received, a warning domain based on the current aircraft position is calculated on the basis of built-in warning domain calculation method, a warning domain on the basis of the geographic coordinate system is calculated in combination with aircraft position information, query is carried out in a terrain database, warning is generated if a terrain invades the warning domain, and the warning information is outputted. The system and the method have the advantages of reducing false alarms and missing alarms to the maximal degree, improving warning performances and ensuring flying security.

A method of accounting for errors in the altitude reporting of a terrain alert and warning system (TAWS) is disclosed wherein errors due to non-standard atmospheric conditions, incorrect altimeter setting and air data computer (ADC) sensor error are detected and corrected for by compensating ADC altitudes for cold temperatures as well as using global positioning system (GPS) altitude data to confirm the accuracy of the ADC altitude information at all times.

A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information or in lieu of the ADC information when the ADC information is unreliable or unavailable.

The invention discloses an information fusion method which has multiple targets and multiple sensors and is based on a convex optimization algorithm, and relates to an information fusion method of a combined navigation system of strapdown inertia, a GPS, an atmospheric data computer and a three-shaft magnetometer. Firstly, the information fusion method uses the speed and posture data of the atmospheric data computer and the three-shaft magnetometer for stabilizing an inertia navigation system, thus forming a combined internal navigation system of the strapdown inertia, the atmospheric data computer and the three-shaft magnetometer with high reliability and high independence; secondly, according to the optimal control idea of the modern control theory, the information fusion method uses the convex optimization algorithm for designing a robust multi-target filter for the fusion of high-precision position of the GPS and speed measurement information, thus forming an external system to implement the hybrid H2/H infinity/performance guarantee multi-target filtering on the internal system, thus improving the navigation precision of the whole system. The information fusion method completely exerts high reliability and usability of traditional navigation means and high precision of satellite navigation, and finally achieves the combined navigation technique with high reliability and high precision based on multiple sensors.

An aerodynamic state estimation system includes a real-time actual measurement device, an air data computer, and a plurality of sensors. The measurement device receives laser scatter energy indicative of one or more atmospheric data parameters and outputs one or more truth measurements. The air data computer module receives the one or more truth measurements, calculates one or more state parameter estimations based on a plurality of functional parameters, and outputs at least one of the one or more truth measurements and the one or more state parameter estimations as one or more high accuracy state parameters, The plurality of sensors, located at the air data computer module, measure the plurality of functional parameters.

The invention discloses a comprehensive avionics system for a small-sized general aircraft. The comprehensive avionics system comprises a comprehensive display, a data processing and interface computer and a sensor function module, wherein the comprehensive display is connected with the data processing and interface computer; the data processing and interface computer is respectively provided with the sensor function module, the sensor function modulecomprises an attitude heading unit, an air data computer, a GPS (Global Positioning System) navigation satellite receiver, an ultrashort wave radio, a multi-mode receiver, an air traffic-control responder, a motor parameter acquirer and an audio controller; the comprehensive display is connected with the data processing and interface computerthrough a high-speed data bus; and the data processing and interface computer is connected with the sensor function module through a point-to-point data bus. The comprehensive avionics system disclosed by the invention has the characteristics of high integration level, capability of improving flight experience, flexibility for configuration and extension, high reliability, low cost, and capability of meeting requirements of general aircrafts on comprehensive performances.

The present invention discloses a method for modifying the position error of the total static pressure pick-up. The method uses a wind tunnel experiment to obtain a simple modifying method for modifying the flight speed of the unmanned plane and the atmosphere static pressure data. When the modifying method provided by the invention is applied, the designing of the total static pressure pick-up and the general arrangement of the plane do not need modifying; besides the provided modifying formula is simple and definite formulated, the inner algorithm of the air data computer does not need modifying and the data can be automatically modified in the flight control software; and a higher modifying precision is provided to the typical flight condition.

The invention belongs to the technical field of aviation atmosphere data detection and discloses a digital atmosphere data computer and an implementation method thereof. The digital atmosphere data computer comprises a pitot tube and a temperature sensor, and a total pressure tube and a static pressure tube are arranged on the pitot tube. A first digital barometric sensor is arranged at an outlet of the total pressure tube, and a second digital barometric sensor is arranged at an outlet of the static pressure tube. The digital atmosphere data computer further comprises an operation amplifier, an analog-digital converter and a signal processing circuit, the input end of the operation amplifier is electrically connected with the signal output end of the temperature sensor, and the output end of the operation amplifier is electrically connected with the input end of the analog-digital converter. The signal processing circuit comprises an FPGA chip and a DSP chip, the input end of the FPGA chip is electrically connected with the first digital barometric sensor, the second digital barometric sensor and the analog-digital converter, and the FPGA chip is electrically connected with the DSP chip.

The invention discloses an atmosphere data computer based on a Kalman filtering algorithm and an implementing method of the atmosphere data computer. The computer comprises a sensor module, a time sequence control module and a digital signal processing module. The sensor module comprises a digital pressure sensor and an analog temperature sensor. The time sequence control module communicates with the digital signal processing module through controlling a time sequence signal. The digital signal processing module is connected with the time sequence control module through an address bus and a data bus to finish data transmission. The method includes the steps that initialization is performed; an interrupt signal is transmitted; whether the interrupt signal is received or not is judged; data are received; whether temperature data exceed the range or not is judged; the data are preprocessed; atmosphere data are calculated; Kalman filtering is performed; the data and fault codes are transmitted; whether the data and the fault codes are received or not is judged. The atmosphere data computer has the advantages of being high in precision, small in error, good in stability and suitable for sudden changes of the barometric height and can serve as an airborne device to be placed on an airplane.

The invention relates to an air data computer testing device, and belongs to the technical field of simulation. The air data computer testing device is used for testing and analog simulation of air data computers and air data indicating instruments. The testing device comprises a computer, a DC power supply module, a power supply control module, an adapter module and a signal conditioning box module, wherein the computer is connected with the DC power supply module and the adapter module; the DC power supply module is provided with the power supply control module and connected with the adapter module; and the adapter module is provided with the signal conditioning box module and connected with the air data computer and the air data indicating instrument. The invention has the advantages of simple structure, compact assembly, economy and practicality, high testing speed, accurate data, high simulation degree and the like.

The invention discloses an atmospheric data computer detection system. The system comprises a control system, a signal modulation unit, a power control unit and a program control pressure source. Thecontrol system comprises an industrial control computer and various function board card inlaid into the main board of the industrial control computer as a whole control center and an operation platform; the signal modulation unit comprises a discrete signal input module, a discrete signal output module and a high-precision controllable resistor network for modulation of two types of discrete signals consisting of 'ground/overhang' and '28V/overhang' signals to achieve level conversion, control of the total temperature simulation device and output of different total temperature resistances andcontrol a digital multimeter by a relay to achieve the power source monitoring and measurement of output resistance. The problems are solved that a traditional atmospheric data computer test device istedious in operation and use steps and poor in operability and versatility.

The invention, which belongs to the technical field of avionics display controlling, relates to a ground velocity measurement method based on an instrument landing system. According to vertical acceleration outputted by an attitude heading reference system, an aircraft height outputted by an air data computer/radio altimeter, and an airport altitude outputted by an aircraft management system, a vertical speed of the aircraft is calculated by complementary filtering; on the basis of a geometrical relationship, a ground velocity based on an instrument landing system is calculated; and then the ground velocity is filtered by using the acceleration along a runway direction to obtain a smooth available ground velocity. According to the ground velocity measurement method based on an instrument landing system, while the ground velocity that can not be outputted by the attitude heading reference system is calculated by using the vertical acceleration, the aircraft height, the airport height, the glide slope offset, and the reference glide slope angle comprehensively, noises caused by the glide slope offset are suppressed by acceleration complementary filtering, so that the obtained groundvelocity is smooth and has high integrity; and high-safety application like head-up flight guidance is supported.

A system includes an air data computer (ADC) having a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output. The ADC can transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals. In a further example embodiment, the system includesa first pressure sensing probe discrete from the ADC and a pneumatic connection joining a pressure sensing port of the first probe to the pneumatic input of the ADC. Second and third pressure sensingprobes pneumatically coupled to respective pressure modules, which output electrical signals to the ADC, the electrical signals being representative of pressures sensed by the second and third pressure sensing probes, respectively.

Inertial/atmospheric data combined hardware-in-the-loop simulation system belongs to the technical field of aircraft navigation/control simulation, and is characterized in that it consists of a dynamics/kinematics simulation module, an inertial measurement component simulator, an angle of attack/sideslip angle simulator, an inertial/atmospheric data Combination filter computer and error real-time display/record module are composed of five parts. Through the real-time calculation of aircraft dynamics simulation computer, matching angular velocity signals and angle of attack/sideslip angle signals are generated as input to inertial/atmospheric data combination filter computer. The invention provides fast and low-cost simulation test means for the verification of the inertial/atmospheric data combined filter computer and its combined filter algorithm, and has the advantages of high test precision, convenient use and the like.

The invention discloses a turbo-propeller aircraft power control method. The turbo-propeller aircraft power control method involves a power rod, a throttle table, an engine controller, a propeller controller, an electromechanical data computer and an atmospheric data computer, wherein the engine power rod is provided with a plurality of control gears in an engine maximum propeller reversing power-to-maximum take off power full-activity stroke, the engine controller controls the working state of an engine, the propeller controller controls the working state of a propeller, the power rod performs control over the engine controller through the throttle table, and the engine controller is in linkage with the propeller controller.

The invention relates to a multifunctional atmosphere data sensor. The sensor provided by the invention is mounted on the outer wall of an air vehicle and integrates total pressure, static pressure, attack angle and static temperature detection. The sensor provided by the invention is compact in structure, convenient to mount and low in weight. The sensor provided by the invention can make primarytreatment on collected atmosphere data and then the atmosphere data subjected to treatment can be transmitted to an atmosphere data computer or a flight control computer through a bus directly, so that a problem of pressure pipeline transmission delay is avoided. The sensor provided by the invention can be used for deicing through heating and the heating temperature can be controlled through a built-in sensor, so that use reliability in rainy, snowy and frost weather can be ensured.

The invention discloses an instruction and warning system of a water rudder control system of a large amphibious aircraft. The instruction and warning system is characterized in that a water rudder control computer (101) acquires the water rudder deflection angle acquired by a feedback sensor in real time, the feedback sensor (102) acquires the deflection angle of a water rudder, a GPS (103) acquires a ground speed signal of the aircraft in real time, an atmosphere data computer (105) acquires an air speed signal, a radio altimeter (106) acquires the height of the aircraft away from the groundor the water surface, a take-off and landing wheel load annunciator (107) acquires an undercarriage front take-off wheel load signal, a warning lamp (108) is used for giving a warning visual instruction, a displayer (109) displays a water rudder deflection angle instruction and the maximum deflection limit angle, an intra-aircraft verbal system (110) is used for giving an auditory instruction, acombined hydraulic valve (111) is used for driving the water rudder to act and providing power, a control actuator (112) is used for controlling collection, release and deflection of the water rudder,and a system processor (104) receives data of the water rudder control computer (101) and obtains the water rudder deflection angle and the water rudder deflection angle limit angle at the current speed.

The invention provides an atmosphere data ground testing system. The invention aims to provide a testing system which can test the dynamic characteristics of optical atmosphere speed sensors in a ground environment and has low requirements for environments. The technical solution of the invention is characterized in that an atmosphere data computer, a GPS/Beidou resolver and an inertial navigationapparatus are integrated in a case; a combined wind speed measurement apparatus measures the wind speed and direction of relative airflow in the horizontal direction and the vertical direction at measurement points to provide benchmark data of the true airspeed, angle of attack and angle of sideslip for an optical atmosphere speed sensor; a rotating platform changes the included angle between theoptical atmosphere speed sensor and the relative airflow by rotating a stipulated angle; the optical atmosphere speed sensor makes emitted laser beams converge at a focus, and the projection speed ofthe macroscopic atmosphere relative movement speed Vc in the axis direction of each laser beam at the focus is detected according to the principle of laser scattering; the projection speeds of more than three different directions are combined to obtain testing data.