23 results about "Air data computer" patented technology

Disclosed in the present invention are a method and system for estimating an airspeed, an angle of attack, and a sideslip angle of an aircraft. The method comprises: modeling the full six-degree-of-freedom dynamics, the aerodynamics, a force, and a moment of an aircraft in a nonlinear state-space form; using an inertial measurement unit to measure the body angular rate and body acceleration of the aircraft; using a global navigation satellite system to measure a ground speed; using data of systems of the aircraft other than an air data system to determine air data measurement; and using a plurality of Kalman filters to estimate the airspeed and / or the angle of attack and / or the sideslip angle from all measured data. The method and the system provided by the present invention solve the problem in the prior art of inability to improve the safety and reliability by installing a redundant air data computer / sensor on a size-, weight-, and power-constrained aircraft, and the problem in the prior art of being not independent of a conventional air data system at the measurement principle level.

An aircraft airflow sensor includes one or more pitot inlets, ports, and / or static ports and a calibration data memory physically storing calibration data with the aircraft airflow sensor probe. The aircraft airflow sensor moreover includes where the calibration data is configured to be implemented in an air data computer (ADC).

The invention provides an atmosphere data system. The atmosphere data system comprises four distributed atmosphere data computers, four static pressure sensors, two total temperature sensors, four attack angle sensors, a sideslip angle sensor, two sets of heating control boxes and a backup instrument, the reliability is greatly improved; the functions are integrated, pressure signals are transmitted through a bus, laying of pipelines on the machine is omitted, complex pipelines on the original machine and corresponding airtightness inspection work of the pipelines can be omitted, and maintenance work on the machine is reduced.

The utility model discloses a calibration test fixing device for an atmosphere data computer, which is characterized in that two sides of an upper cover plate and a lower cover plate are respectively supported by a right side plate and a left side plate to form a frame structure, at least three groups of slots are symmetrically arranged on opposite surfaces of the right side plate and the left side plate, the slots are horizontally arranged, and one end of each slot is provided with an opening for inserting a support plate; one end of each slot is open, the other end of each slot is sealed, a supporting plate is selectively inserted into each pair of slots, the supporting plates are used for placing an atmosphere data computer, and the atmosphere data computer is connected with external equipment through a test cable. The device can effectively and absolutely safely lock equipment, has enough bearing and protecting capabilities, is matched with a guide rail structure, locks a hardware plate, stably locks the equipment in a test fixing device, supports multi-equipment access test calibration, greatly saves equipment calibration test cost, reduces calibration time, and improves test efficiency. And the space utilization in the testing process can be increased.

The utility model discloses atmosphere parameter monitoring equipment based on wireless Bluetooth communication, which comprises a signal conversion function board and a DB9 female joint which are connected with each other, and the DB9 female joint is connected with an atmosphere data computer. Wherein the signal conversion function board comprises a wireless Bluetooth module and a current source driver which are connected with each other, the wireless Bluetooth module is connected with the user side equipment, and when the atmosphere data computer is used for external field ground joint test or troubleshooting, the user side equipment can directly receive the air pressure height and the atmosphere parameters indicating the air speed sent by the atmosphere data computer; and analyzing according to a sending parameter protocol. Whether data output of the atmosphere data computer is normal or not can be directly judged through the user side equipment, fault inspection and maintenance of the atmosphere data computer by external field maintenance personnel are facilitated, and the advantages of being easy to operate and convenient to maintain are achieved. And the selected modules and devices belong to general equipment, so that the system has the advantages of low cost, small size, light weight, simplicity in operation and convenience in maintenance.

The application discloses a kind of 1553B bus data's air data computer test system, it is related to air data computer test technical field, power module and analog signal equipment are connected with the input end of XSC-5 air data computer test platform;XSC-5 air data computer test platform output end is connected with XSC-5 air data computer;Air data tester is connected with XSC-5 air data computer;XSC-5 air data computer is realized communication with industrial computer by data line and 1553B bus data box;Test software is installed in industrial computer, for obtaining the data protocol of 1553B data when XSC-5 air data computer is output to different atmospheric parameters, and built-in integrated preset parameter, based on data protocol and preset parameter, 1553B data is interpreted, and corresponding atmospheric parameter is obtained.The application is manually tested by the test software and XSC-5 air data computer test platform of independent research and development, not only simple structure, production cost and maintenance cost are low, and maintenance, test and adjustment are also more convenient and fast.

The invention provides an atmosphere data system and method with an enhanced heating monitoring function, and belongs to the field of aircraft airborne avionics, and the atmosphere data system comprises a three-channel atmosphere data computer subsystem, a three-channel atmosphere data heating controller subsystem, an aircraft flight management subsystem and an atmosphere data probe subsystem. The three channels are cross-linked, and the communication architecture of the atmosphere data system with the enhanced heating monitoring function and the heating monitoring method are provided. The method solves the problem that according to an existing civil aircraft atmosphere data system, due to the fact that a communication link between an atmosphere data computer and an atmosphere data heating controller breaks down, single-channel atmosphere parameter output errors are caused.

The application belongs to the technical field of atmospheric data system, and particularly relates to a system and method for heating total pressure sensor and static pressure sensor. The system comprises: a total pressure sensor connected with an atmospheric data computer through a total pressure pipeline; a static pressure sensor connected with the atmospheric data computer through a static pressure pipeline; a first control pipeline connected with an on-board air source system at one end and connected with the total pressure sensor at the other end, and a second control pipeline connected with the on-board air source system at one end and connected with the static pressure sensor at the other end; a first electric control one-way valve arranged on the first control pipeline, and a second electric control one-way valve arranged on the second control pipeline; and the atmospheric data computer is used for controlling the opening or closing of the first electric control one-way valve according to the signal of the total pressure sensor received, and for controlling the opening or closing of the second electric control one-way valve according to the signal of the static pressure sensor received. The application can provide a backup heating measure, improve the system safety, and ensure the flight task and flight safety.

The application provides a kind of helicopter L-shaped air speed pipe gas path water accumulation abnormality detection method, belongs to helicopter L-shaped air speed pipe gas path water accumulation abnormality detection field, the method includes: using metal pipeline, constructs air speed pipe gas path, air speed pipe gas path is connected with atmosphere data computer, and metal probe sensor is installed in total pressure gas path and static pressure gas path;Metal probe sensor is connected with atmosphere data computer, and the down pull resistance formed by rain is obtained using metal probe sensor and metal pipeline;Based on the down pull resistance formed by rain, water accumulation abnormality detection is carried out using the signal acquisition circuit of atmosphere data computer, and the air speed pipe gas path water accumulation abnormality detection result is obtained;The application solves the problem that the existing aircraft air speed pipe cannot carry out gas path water accumulation detection.

An aircraft airflow sensor includes one or more pitot inlets, ports, and / or static ports and a calibration data memory physically storing calibration data with the aircraft airflow sensor probe. The aircraft airflow sensor moreover includes where the calibration data is configured to be implemented in an air data computer (ADC).

The present invention discloses an air data probe support arm and an air data detection system, belonging to the field of aerospace. An air data probe is installed through an installation interface, and through the cooperation of a bistable structure and a steady-state transition driving mechanism, the bistable structure is switched between various steady-state structures, thereby driving the installation interface to communicate with the air data probe for reciprocating movement, achieving the effects of ice breaking and de-icing. The structure of the air data probe support arm is novel and reasonable. Compared with the traditional anti-icing method of welding heating wires inside the air data probe, this support arm supports the air data probe externally and will not affect the structure and performance of the air data probe itself. It has the advantages of simple processing and manufacturing, convenient use, strong ice-breaking ability of the support arm, and good insulation. The anti-icing ability of the air data probe support arm can be adjusted by the pilot or the air data computer according to the actual situation, ensuring the service life of the air data probe and reducing the energy consumption of the bistable structure at the same time.

The application provides an atmospheric data system and method with strengthened heating monitoring function, belonging to the field of airborne avionics of an airplane, comprising: a three-channel atmospheric data computer subsystem, a three-channel atmospheric data heating controller subsystem, an airplane flight management subsystem and an atmospheric data probe subsystem; the three channels have crosslinking, and a communication architecture of the atmospheric data system with the strengthened heating monitoring function and a heating monitoring method are provided.The application solves the problem of single-channel atmospheric parameter output error caused by the communication link fault between the atmospheric data computer and the atmospheric data heating controller of the existing civil airplane atmospheric data system.

The invention belongs to the technical field of atmosphere data systems, and particularly relates to a total and static pressure sensor heating system and method. According to the system, a total pressure sensor is connected with an atmosphere data computer through a total pressure pipeline; the static pressure sensor is connected with an atmosphere data computer through a static pressure pipeline; one end of the first loop control pipeline is connected with the onboard air source system, the other end of the first loop control pipeline is connected with the total pressure sensor, one end of the second loop control pipeline is connected with the onboard air source system, and the other end of the second loop control pipeline is connected with the static pressure sensor; the first electric control one-way valve is arranged on the first loop control pipeline, and the second electric control one-way valve is arranged on the second loop control pipeline; the atmosphere data computer is used for controlling opening or closing of the first electric control one-way valve according to the received signals of the total pressure sensor and used for controlling opening or closing of the second electric control one-way valve according to the received signals of the static pressure sensor. According to the invention, standby heating measures can be provided, the system safety is improved, and the flight mission and flight safety are ensured.

An aircraft airflow sensor includes one or more pitot inlets, ports, and / or static ports and a calibration data memory physically storing calibration data with the aircraft airflow sensor probe. The aircraft airflow sensor moreover includes where the calibration data is configured to be implemented in an air data computer (ADC).

The invention belongs to the technical field of airplane atmospheric sensor heating abnormal opening alarm design, and particularly relates to an airplane atmospheric sensor heating abnormal opening alarm system which comprises an atmospheric sensor, a wheel load information acquisition device, an inertial navigation device, an atmospheric data computer, a central alarm computer and a display control unit. Existing equipment on an airplane is utilized, no additional equipment is needed, implementation is easy, when automatic heating of the atmospheric sensor is started abnormally, warning can be conducted in time, a unit or ground crew is prompted to disconnect heating of the atmospheric sensor, and damage to the atmospheric sensor or personnel injury caused by untimely finding is avoided.

The present invention relates to the field of aviation test flight technology, and discloses a test flight platform suitable for robot pilots, which is formed by modifying a retired aircraft, that is, removing some mechanical components, some electrical components and some radio components in the retired aircraft. A flight control subsystem, a measurement and control subsystem, an electrical subsystem and a ground test subsystem are installed. The flight control subsystem includes an optical fiber attitude and heading, an atmospheric data computer, a flight control computer, an elevator servo, an aileron servo, a steering servo, auxiliary equipment and a throttle motor. The optical fiber attitude and heading are connected to the flight control computer for two-way communication; the ground test subsystem is connected to the flight control computer for two-way communication, and is used to send route information and initial parameters to the flight control computer, and receive the working status information of each device included in the retired aircraft, the information cross-linking status of the flight control subsystem and other subsystems, and the binding parameters. The present invention has the advantages of high technical feasibility, low cost, and strong scalability.

An aircraft ground parking atmospheric sensor temperature abnormity alarm system comprises a total pressure sensor, a static pressure sensor, a total temperature sensor, an atmospheric data computer, a central alarm computer and a display control unit. The abnormal high temperature condition of the atmospheric sensor in the ground state can be effectively and automatically detected, an alarm is given out in time, and intelligent diagnosis and early warning of the temperature abnormal risk of the atmospheric sensor parked on the ground of an airplane are achieved.

The application provides an airborne intelligent heating control system, and belongs to the technical field of airborne sensor / inductor heating control. Specifically, a heating control box receives wheel load state, indicated airspeed, atmospheric total temperature and other information sent by an airborne probe atmospheric data computer, and a forced heating signal of an on-board top control panel, and judges accordingly. The first heating control box and the second heating control box jointly realize heating control of each component of the atmospheric data system, monitor the heating state of each component in real time, and send the heating state information of each component to the airborne probe atmospheric data computer. On the basis of time-sharing starting, in order to avoid the heating power acting on the same load at the same time, rigorous theoretical proof is carried out, various fault conditions are considered, the two heating control boxes on the aircraft are reasonably and efficiently used, the double-redundancy advantage is exerted, and the safety of the aircraft is ensured.

The utility model relates to the technical field of airborne circuit board detection, in particular to a detection device for a digital quantity interface board of a certain type of air data computer, which comprises a test platform provided with a programmable power supply and a first signal array interface, and the programmable power supply is connected with the first signal array interface; the industrial personal computer is connected with the programmable power supply, the discrete IO module is connected with the industrial personal computer, the ARINC429 bus interface module is connected with the industrial personal computer, and the switching adapter board comprises a second signal array interface connected with the first signal array interface, a discrete IO module plug connected with the discrete IO module, an ARINC429 interface module plug connected with the ARINC429 bus interface module and a test board plug. According to the utility model, the performance test and fault rapid positioning of the digital quantity interface board can be realized, the operation is simple, fault diagnosis information is displayed in a report form, maintenance and troubleshooting are easy, and the troubleshooting time is greatly shortened; potential faults and hidden dangers can be blocked in time in a daily plate process test, and the repair quality of products is improved.

The present invention proposes a non-similar dual-redundancy atmospheric data processing system and processing method for civil aircraft, which adopts redundancy design to ensure its safety and reliability, as well as the fault tolerance requirements of fault operation. Aiming at the performance requirements and technical indicators of the atmospheric data computer, the redundant parallel non-similar dual-redundancy CPU working mode architecture is adopted to effectively suppress the possible common mode failures of software and hardware to ensure the reliability and safety requirements of the atmospheric data computer, and the fault tree is used to evaluate and analyze its safety.

The invention discloses an atmosphere data computer test system for 1553B bus data, and relates to the technical field of atmosphere data computer test, a power supply module and analog signal equipment are connected with the input end of an XSC-5 atmosphere data computer test board; the output end of the XSC-5 atmosphere data computer test board is connected with the XSC-5 atmosphere data computer; the atmosphere data tester is connected with the XSC-5 atmosphere data computer; the XSC-5 atmosphere data computer communicates with the industrial personal computer through a data line and the 1553B bus data box; test software is installed in the industrial personal computer, and the industrial personal computer is used for obtaining a data protocol of 1553B data when the XSC-5 atmosphere data computer outputs different atmosphere parameters, internally integrating preset parameters, and interpreting the output 1553B data based on the data protocol and the preset parameters to obtain corresponding atmosphere parameters. Manual testing is carried out through independently researched and developed testing software and an XSC-5 atmosphere data computer testing table, the structure is simple, the manufacturing cost and the maintenance cost are low, and maintenance, testing and adjustment are more convenient and faster.

The application provides an air data system, comprising four pieces of distributed air data computers, four pieces of static pressure sensors, two pieces of total temperature sensors, four pieces of attack angle sensors, one piece of sideslip angle sensor, two sets of heating control boxes and backup instruments; the reliability is greatly improved; functions are integrated, a bus is used for transmitting pressure signals, the laying of on-board pipelines is cancelled, the original on-board complex pipelines and the corresponding air tightness inspection work of the pipelines can be cancelled, and on-board maintenance work is reduced.

An aircraft airflow sensor includes one or more pitot inlets, ports, and / or static ports and a calibration data memory physically storing calibration data with the aircraft airflow sensor probe. The aircraft airflow sensor moreover includes where the calibration data is configured to be implemented in an air data computer (ADC).