CN109521689B - Design method of airplane double-redundancy quick-pressure adjustment type control surface angle control system - Google Patents
Design method of airplane double-redundancy quick-pressure adjustment type control surface angle control system Download PDFInfo
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- CN109521689B CN109521689B CN201810218338.2A CN201810218338A CN109521689B CN 109521689 B CN109521689 B CN 109521689B CN 201810218338 A CN201810218338 A CN 201810218338A CN 109521689 B CN109521689 B CN 109521689B
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- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
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Abstract
The invention belongs to the field of aviation flight control, and particularly relates to a design method of a dual-redundancy speed-pressure adjusting type control surface angle control system of an airplane. The invention controls the angle of the control surface according to the trapezoidal regulation rule of the angle of the control surface and the flying speed, and the system is designed in a dual-redundancy closed loop and has a self-checking function. The invention solves the problem of airplane potential safety hazard caused by too large rudder quantity for a pilot, and improves the reliability and safety of the airplane. The method is verified in practice, and has wide application prospect.
Description
Technical Field
The invention belongs to the field of aviation flight control systems, and particularly relates to a design method of an airplane dual-redundancy speed and pressure adjusting type control surface angle control system.
Background
In order to ensure flight safety, when a large-sized transporter does not allow high-speed flight, the deflection angle of a control surface is too large, in order to ensure flight safety and avoid the potential safety hazard of an airplane caused by too large rudder quantity for a driver, a control surface angle control mechanism is required to be arranged in a flight control system to control the angles of the control surface at different speeds. The airplane is still safe and reliable when the rudder using amount of a pilot is large. Therefore, in the development of the airplane, a control surface angle control system is required to be arranged in addition to a main system of a normal flight control system. So as to improve the mission reliability and safety of the airplane.
Disclosure of Invention
The object of the invention is: the invention provides a design method of an airplane double-redundancy speed and pressure adjusting type control surface angle control system. Controlling the angle of the control surface according to the control law of the flight speed and the angle of the control surface, wherein the system is designed in a dual-redundancy closed loop mode; the problem of the aircraft potential safety hazard that the pilot too big with the rudder volume when having solved large-scale cargo airplane high speed flight causes is solved, improved the reliability, the security of aircraft, reached the user satisfaction's service property.
The technical scheme is as follows:
the technical problems to be solved by the invention are as follows:
in order to ensure flight safety, when a large-sized transporter does not allow high-speed flight, the deflection angle of a control surface is too large, and in order to ensure flight safety and avoid the problem of airplane potential safety hazard caused by too large rudder quantity for a driver, a control surface angle control system is required to be arranged in a flight control system to control the angles of the control surface at different speeds.
In order to solve the technical problems, the invention is realized by the following technical scheme:
a design method of a dual-redundancy speed pressure adjustment type control surface angle control system comprises the following steps:
the first step is as follows: according to the requirements of the reliability and safety of the mission of the airplane, the speed-pressure adjusting type control surface angle control system adopts dual-redundancy setting;
the second step is that: designing control surface control angle parameters according to the design requirements of flight control system performance parameters;
the third step: determining the corresponding relation between the output displacement of an execution device in the airplane dual-redundancy speed-pressure adjusting type control surface angle system and the control surface angle according to the transmission ratio distribution relation of a flight control system, a system motion diagram, a pedal stroke and the control surface angle mathematical model simulation calculation result;
the fourth step: determining a step voltage value of a control device in an airplane dual-redundancy speed-pressure adjusting type control surface angle control system according to the corresponding relation between the output voltage signal of the control device and a control surface angle display signal;
the fifth step: according to the redundancy design requirement of a control surface angle system, designing corresponding signal sources, control circuits, control devices, execution devices and the like by adopting a parallel double-channel design, wherein the double channels are mutually hot backed;
and a sixth step: designing fault alarm display according to the safety requirement of the airplane; when the system unit element control device fails, the system moves the automatic control execution device to the maximum displacement;
the seventh step: according to the requirement of fault isolation of the signal source and the control device, when the signal source is in fault, an angle display number is set to turn yellow to remind a driver of paying attention.
Further:
the safety requirement in the step 1 is that according to the requirements of the reliability and the safety of the airplane, the airplane dual-redundancy speed-pressure adjusting type control surface angle control system is provided with automatic and manual control functions;
and 2, correcting the curve according to the design requirement of strength and by combining the control surface limiting angle, correcting the curve of the speed pressure and the control surface angle into a step shape, and setting the corresponding relation between the speed pressure and the control surface angle.
(III) advantageous effects
Compared with the prior art, the invention has the beneficial effects that: according to the invention, the dual-redundancy quick-pressure adjusting type control surface angle control system is arranged in the flight control system, so that the problem of airplane potential safety hazard caused by too large rudder quantity used by a pilot is solved, and the task reliability and safety of the airplane are improved.
Detailed Description
The present invention will be described in further detail with reference to specific embodiments below:
a design method of an aircraft dual-redundancy speed-pressure adjustment type control surface angle control system comprises the following steps:
the first step is as follows: according to the requirements of the reliability and safety of the mission of the airplane, the speed-pressure adjusting type control surface angle control system adopts dual-redundancy setting;
the second step is that: designing control surface control angle parameters according to the design requirements of flight control system performance parameters;
the third step: selecting proper set points of a control device and an execution device on the airplane according to the spatial layout of the airplane;
the fourth step: according to the installation position of the executing device, carrying out transmission ratio distribution on the flight control system;
the fifth step: determining the corresponding relation between the output displacement of an execution device in a dual-redundancy speed-pressure regulation type control surface angle system and a control surface angle according to the transmission ratio distribution relation of a flight control system, a system motion diagram, a pedal stroke and a control surface angle mathematical model simulation calculation result;
and a sixth step: determining a step voltage value of a control device in a dual-redundancy speed-pressure adjusting type control surface angle system according to the corresponding relation between a control surface angle display signal and a control device output voltage signal;
the seventh step: according to the redundancy design requirement of a control surface angle system, designing corresponding signal sources, control circuits, control devices, execution devices and the like by adopting a parallel double-channel design, wherein the double channels are mutually hot backed;
eighth step: designing fault alarm display according to the safety requirement of the airplane; when the system unit element control device fails, the system moves the automatic control execution device to the maximum displacement;
the ninth step: according to the requirement of fault isolation of the signal source and the control device, when the signal source is in fault, an angle display number is set to turn yellow to remind a driver of paying attention.
Claims (3)
1. A design method of an airplane double-redundancy speed-pressure adjustment type control surface angle control system is characterized by comprising the following steps: the method comprises the following steps:
the first step is as follows: according to the requirements of the reliability and safety of the mission of the airplane, the speed-pressure adjusting type control surface angle control system adopts dual-redundancy setting;
the second step is that: designing control surface control angle parameters according to the design requirements of flight control system performance parameters;
the third step: determining the corresponding relation between the output displacement of an execution device in the airplane dual-redundancy speed-pressure adjusting type control surface angle system and the control surface angle according to the transmission ratio distribution relation of a flight control system, a system motion diagram, a pedal stroke and the control surface angle mathematical model simulation calculation result;
the fourth step: determining a step voltage value of a control device in an airplane dual-redundancy speed-pressure adjusting type control surface angle control system according to the corresponding relation between the output voltage signal of the control device and a control surface angle display signal;
the fifth step: designing a corresponding signal source, a control circuit, a control device and an execution device according to the redundancy design requirement of a control surface angle system, wherein the signal source, the control circuit, the control device and the execution device are all designed by adopting parallel double channels, and the double channels are mutually in hot backup;
and a sixth step: designing fault alarm display according to the safety requirement of the airplane; when the system unit element control device fails, the system moves the automatic control execution device to the maximum displacement;
the seventh step: according to the requirement of fault isolation of the signal source and the control device, when the signal source is in fault, an angle display number is set to turn yellow to remind a driver of paying attention.
2. The design method of the aircraft dual-redundancy speed-pressure-adjusting control surface angle control system according to claim 1, is characterized in that: and (3) according to the safety requirement in the step 1, according to the requirements of the task reliability and the safety of the airplane, the airplane dual-redundancy speed and pressure adjusting type control surface angle control system is provided with automatic and manual control functions.
3. The design method of the aircraft dual-redundancy speed-pressure-adjusting control surface angle control system according to claim 1, is characterized in that: and 2, correcting the curve according to the design requirement of strength and by combining the control surface limiting angle, correcting the curve of the speed pressure and the control surface angle into a step shape, and setting the corresponding relation between the speed pressure and the control surface angle.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810218338.2A CN109521689B (en) | 2018-03-16 | 2018-03-16 | Design method of airplane double-redundancy quick-pressure adjustment type control surface angle control system |
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| CN201810218338.2A CN109521689B (en) | 2018-03-16 | 2018-03-16 | Design method of airplane double-redundancy quick-pressure adjustment type control surface angle control system |
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| CN109521689B true CN109521689B (en) | 2022-03-15 |
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| JP5735253B2 (en) * | 2010-10-20 | 2015-06-17 | 住友精密工業株式会社 | Aircraft steering apparatus control method, aircraft steering apparatus, and aircraft equipped with the same |
| CN102001444B (en) * | 2010-11-19 | 2014-06-11 | 陕西飞机工业（集团）有限公司 | Neutral position adjustment device of flight control system and neutral position setting method thereof |
| JP5816019B2 (en) * | 2011-07-29 | 2015-11-17 | Ntn株式会社 | Control device for steer-by-wire steering system with redundancy function |
| CN202632110U (en) * | 2012-05-31 | 2012-12-26 | 西北工业大学 | Dual-redundancy steering engine system |
| CN104590550B (en) * | 2013-10-30 | 2017-06-20 | 北京精密机电控制设备研究所 | A kind of highly reliable dual redundant electric steering engine control device |
| CN104554710B (en) * | 2014-11-19 | 2018-05-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of double remaining aircraft leading edge wing flap servoactuation systems of machinery |
| CN204507246U (en) * | 2014-12-10 | 2015-07-29 | 西安庆安电气控制有限责任公司 | A kind of many rocker arm bodies of variable-speed ratio |
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Inventor after: Che Yibin Inventor after: Xu Jian Inventor after: Shi Zhenliang Inventor after: Luo Liping Inventor after: Chen Fenghua Inventor after: Zhang Jiguang Inventor after: Gao Ming Inventor after: Xu Hongyang Inventor after: Yang Tao Inventor after: Dai Chang Inventor after: Qi Haidong Inventor after: He Zhiguo Inventor after: Cui Jinming Inventor after: Cheng Xinghong Inventor after: Song Juanni Inventor after: Lv Ming Inventor after: Shi Qiangjun Inventor after: Li Xiaoru Inventor after: He Songqing Inventor after: Zhu Yonggang Inventor after: Yang Xi Inventor before: Luo Liping Inventor before: Xu Jian Inventor before: Shi Zhenliang Inventor before: Che Yibin Inventor before: Chen Fenghua Inventor before: Zhang Jiguang Inventor before: Gao Ming Inventor before: Xu Hongyang Inventor before: Yang Tao Inventor before: Dai Chang Inventor before: Qi Haidong Inventor before: He Zhiguo Inventor before: Cui Jinming Inventor before: Cheng Xinghong Inventor before: Song Juanni Inventor before: Lv Ming Inventor before: Shi Qiangjun Inventor before: Li Xiaoru Inventor before: He Songqing Inventor before: Zhu Yonggang Inventor before: Yang Xi |
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