CN105136196A - Distributed air data system by adopting multifunctional probe - Google Patents
Distributed air data system by adopting multifunctional probe Download PDFInfo
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- CN105136196A CN105136196A CN201510445324.0A CN201510445324A CN105136196A CN 105136196 A CN105136196 A CN 105136196A CN 201510445324 A CN201510445324 A CN 201510445324A CN 105136196 A CN105136196 A CN 105136196A
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Abstract
The invention discloses a distributed air data system by adopting a multifunctional probe, which comprises a flight control computer, an air data computer, an attack angle solver, a left multifunctional probe sensor, a right multifunctional probe, a left L-shaped pressure receptor assembly, a right L-shaped pressure receptor assembly, an upper pressure difference attack angle sensor, a lower pressure difference attack angle sensor and a sideslip angle sensor, wherein the attack angle solver receives pressure signals of the upper pressure difference attack angle sensor and the lower pressure difference attack angle sensor for solution; the sideslip angle sensor is used for providing sideslip angle signals for the attack angle solver and the air data computer; and the attack angle solver provides the solved air parameters to an electromechanical management computer and a backup parameter collector. According to the multifunctional probe sensor adopted by the invention, in the condition of not reducing system redundancy, two pieces of equipment can be reduced compared with an independent sensor scheme, projections on the surface of the body can be reduced, the difficulty that sensors select positions for arrangement can be reduced, system integration is improved, and the system weight is reduced.
Description
Technical field
The present invention relates to a kind of distributed air data system adopting Multi-functional probe.Belong to the measurement to atmospheric parameter in instrument and apparatus field.
Background technology
Air data system is system very important on a kind of aircraft, gathers and provides air speed, Mach number, barometer altitude, rising or falling speed and the atmospheric parameter such as the angle of attack, yaw angle to aircraft.Air data system is made up of pick-up, sensor and air data computers etc. such as total static pressure pick-up, incidence vane, sideslip sensor and total temperature probe usually.Air data system has centralized and distributed dividing, and the core of centralized air data system is air data computer, and the signal that all the sensors, pick-up are experienced all is sent to air data computer and processes; Sensor, pick-up and microprocessor integrate by distributed air data system, namely an equipment achieve atmospheric parameter impression and calculate the comprehensive of functions such as revising, compare the centralized pipeline eliminated needed for conducting pressure, reduce the delay of pressure, reduce system weight.
Usual air data system should provide the atmospheric parameter of multiple remaining to aircraft, this just needs to arrange multiple air data sensor (pick-up) aboard.Air data sensor is substantially all be arranged in the less region of aircraft surfaces flow field characteristic change, and aircraft surfaces limited available space, and also arranged apart with the device of the outstanding body surface such as antenna, this just causes the bit selecting of sensor to there is larger difficulty.For reducing the quantity of the atmosphere data probe of outstanding aircraft surfaces, occur that lump static pressure measurement and air flow deflector angular measurement are in the Multi-functional probe sensor of one in the world, but domestic not yet organic type application at present.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
Summary of the invention
For solving a difficult problem for body surface air data sensor layout bit selecting, there is provided the atmosphere data parameter of 4 remainings to aircraft, the technical issues that need to address of the present invention are to provide a pair lump static pressure measurement and air flow deflector angular measurement in the air data system of the Multi-functional probe sensor of one.
For solving technical matters of the present invention, the technical solution used in the present invention is:
Adopt a distributed air data system for Multi-functional probe, it comprises air data computer, angle of attack solver, left and right Multi-functional probe sensor, left and right L shape pressure tube assembly, upper and lower pressure reduction incidence vane and sideslip sensor;
Described left and right Multi-functional probe sensor provides one group of total, static pressure and local angle of attack's signal to air data computer and angle of attack solver, and dynamic and static pressure signal and two groups of angle of attack signals of one group of analog quantity form are provided separately to flight control computer, the mutual communication of described left and right Multi-functional probe sensor, meanwhile, the left and right Multi-functional probe sensor yaw angle signal received from air data computer is used for the correction of parameter;
Described left and right L shape pressure tube assembly provides one group of total, static pressure signal respectively towards air data computer and angle of attack solver, and the dynamic and static pressure signal of one group of analog quantity form is provided separately to flight control computer, meanwhile, left and right L shape pressure tube assembly receives the correction being used for parameter from the angle of attack of angle of attack solver, yaw angle signal;
The pressure signal that described angle of attack solver receives upper and lower pressure reduction incidence vane resolves;
Described sideslip sensor provides yaw angle signal to angle of attack solver and air data computer;
Described angle of attack solver is supplied to Electromechanical Management computing machine and backup parameter acquisition unit by resolving the atmospheric parameter drawn.
Beneficial effect of the present invention: present invention employs one-to-many function probe sensor, when not reducing system margin, compare standalone sensor scheme and can reduce by 2 equipment, reduce engine surface protrusion, reduce the difficulty that sensor bit selecting is arranged, improve level of integrated system, reduce system weight.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
1, air data computer, 2, angle of attack solver, 3, left Multi-functional probe sensor, 4, right Multi-functional probe sensor, 5, left L shape pressure tube assembly, 6, right L shape pressure tube assembly, 7, upper pressure reduction incidence vane, 8, lower pressure reduction incidence vane, 9, sideslip sensor, 10, total temperature probe, 11, field press-fits and order, 12, Electromechanical Management computing machine, 13, parameter acquisition unit is backed up, 14, airborne answering machine, 15, inertial navigation system, 16, avionics system, 17, flight control computer.
Embodiment
Below in conjunction with the drawings and specific embodiments, the invention will be further described.Following examples, only for illustration of the present invention, are not used for limiting the scope of the invention.
Shown in Fig. 1, a kind of distributed air data system adopting Multi-functional probe of the present invention, it comprise air data computer 1, angle of attack solver 2, left and right Multi-functional probe sensor 3,4, left and right L shape pressure tube assembly 5,6, upper and lower pressure reduction incidence vane 7,8 and sideslip sensor 9; Left and right Multi-functional probe sensor 3,4 provides one group of total, static pressure and local angle of attack's signal each via RS-422A interface to air data computer 1 and angle of attack solver 2, and dynamic and static pressure signal and two groups of angle of attack signals of one group of analog quantity form are provided separately to flight control computer 17, left and right Multi-functional probe sensor 3,4 is mutually by RS-422A interface communication, meanwhile, left and right Multi-functional probe sensor 3, the 4 RS-422A yaw angle signal received from air data computer 1 is used for the correction of parameter; Left and right L shape pressure tube assembly 5,6 provides one group of total, static pressure signal each via RS-422A interface to air data computer 1 and angle of attack solver 2, and the dynamic and static pressure signal of one group of analog quantity form is provided separately to flight control computer 17, meanwhile, left and right L shape pressure tube assembly 5,6 receives the correction being used for parameter from the angle of attack of angle of attack solver 2, yaw angle signal; The pressure signal that angle of attack solver 2 receives upper and lower pressure reduction incidence vane resolves; Sideslip sensor 9 provides yaw angle signal to angle of attack solver 2 and air data computer 1; Angle of attack solver 2 is supplied to Electromechanical Management computing machine 12 and backup parameter acquisition unit 13 by resolving the atmospheric parameter drawn by RS-422A interface.
Air data computer 1 is supplied to airborne answering machine 14, inertial navigation system 15 and Electromechanical Management computing machine 12 system by resolving the atmospheric parameter drawn by ARINC429 bus, provides avionics system 16(FADEC by 1553B bus simultaneously) etc. regarding system.
Present invention employs one-to-many function probe sensor and pair of L-shaped pressure tube assembly, the angle of attack signal of total, the static pressure signal of 4 remainings and 2 mechanical remainings, 4 electric remainings is provided.Meanwhile, have employed a set of differential incidence vane, a sideslip sensor and a total temperature probe.System uses two pieces independently to resolve parts (" angle of attack solver " and " air data computer ") the reception numeral that provides of the sensor and analog signals and field to press-fit and order signal, calculate the atmospheric parameters such as air speed, Mach number, barometer altitude, rising or falling speed, the angle of attack, yaw angle after voting, export to regarding system on machine respectively by different buses.
The process such as Multi-functional probe sensor and L shape pressure tube component internal all have microprocessor to change the atmospheric parameter experienced, compensate, correction, are exported to relevant equipment by RS-422A or other digital communication interfaces.Meanwhile, total, the static pressure signal of analog quantity form and the fault of discrete magnitude form and status signal is also had to be supplied to system in need.
Present invention employs one-to-many function probe sensor, when not reducing system margin, comparing standalone sensor scheme and can reduce by 2 equipment, reduce engine surface protrusion, reduce the difficulty that sensor bit selecting is arranged, improve level of integrated system, reduce system weight.
Claims (1)
1. adopt a distributed air data system for Multi-functional probe, it is characterized in that: it comprises air data computer, angle of attack solver, left and right Multi-functional probe sensor, left and right L shape pressure tube assembly, upper and lower pressure reduction incidence vane and sideslip sensor;
Described left and right Multi-functional probe sensor provides one group of total, static pressure and local angle of attack's signal to air data computer and angle of attack solver, and dynamic and static pressure signal and two groups of angle of attack signals of one group of analog quantity form are provided separately to flight control computer, the mutual communication of described left and right Multi-functional probe sensor, meanwhile, the left and right Multi-functional probe sensor yaw angle signal received from air data computer is used for the correction of parameter;
Described left and right L shape pressure tube assembly provides one group of total, static pressure signal respectively towards air data computer and angle of attack solver, and the dynamic and static pressure signal of one group of analog quantity form is provided separately to flight control computer, meanwhile, left and right L shape pressure tube assembly receives the correction being used for parameter from the angle of attack of angle of attack solver, yaw angle signal;
The pressure signal that described angle of attack solver receives upper and lower pressure reduction incidence vane resolves;
Described sideslip sensor provides yaw angle signal to angle of attack solver and air data computer;
Described angle of attack solver is supplied to Electromechanical Management computing machine and backup parameter acquisition unit by resolving the atmospheric parameter drawn.
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| CN105953816A (en) * | 2016-04-28 | 2016-09-21 | 江西洪都航空工业集团有限责任公司 | Distributed atmosphere data system |
| CN106248139A (en) * | 2016-07-29 | 2016-12-21 | 成都凯天电子股份有限公司 | Atmosphere parameter measurement is popped one's head in |
| CN106950002A (en) * | 2017-02-24 | 2017-07-14 | 中国航天空气动力技术研究院 | A kind of Flush Airdata Sensing System |
| CN107132376A (en) * | 2017-04-21 | 2017-09-05 | 陕西飞机工业（集团）有限公司 | A kind of acquisition methods of aircraft angle of attack fair curve |
| CN110608766A (en) * | 2018-06-15 | 2019-12-24 | 罗斯蒙特航天公司 | Advanced atmospheric data system architecture with atmospheric data computer |
| CN111856074A (en) * | 2020-06-04 | 2020-10-30 | 中国人民解放军国防科技大学 | Combined type atmospheric data measurement experiment cabin section and flight data measurement method thereof |
| WO2022179278A1 (en) * | 2021-02-25 | 2022-09-01 | 成都凯天电子股份有限公司 | Rotor blade downwash impact correcting method for helicopter atmospheric data system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106950002A (en) * | 2017-02-24 | 2017-07-14 | 中国航天空气动力技术研究院 | A kind of Flush Airdata Sensing System |
| CN107132376A (en) * | 2017-04-21 | 2017-09-05 | 陕西飞机工业（集团）有限公司 | A kind of acquisition methods of aircraft angle of attack fair curve |
| CN110608766A (en) * | 2018-06-15 | 2019-12-24 | 罗斯蒙特航天公司 | Advanced atmospheric data system architecture with atmospheric data computer |
| CN111856074A (en) * | 2020-06-04 | 2020-10-30 | 中国人民解放军国防科技大学 | Combined type atmospheric data measurement experiment cabin section and flight data measurement method thereof |
| WO2022179278A1 (en) * | 2021-02-25 | 2022-09-01 | 成都凯天电子股份有限公司 | Rotor blade downwash impact correcting method for helicopter atmospheric data system |
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