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Method, device and electronic equipment for determining aircraft control capability

A technology of control ability and determination method, which is applied in the direction of ground device, control/regulation system, non-electric variable control, etc., can solve the problems of large structure size of control rudder surface, increase the weight of the whole machine and the energy consumption of the steering gear, so as to reduce the overall The effect of reducing the weight of the steering gear and the energy consumption of the steering gear, reducing the demand for control capability, and reducing the size of the structure

Active Publication Date: 2021-09-03
CHINA ACAD OF LAUNCH VEHICLE TECH
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AI Technical Summary

Problems solved by technology

Due to the high speed of the aircraft in orbit, the re-entry process of the reusable surface-symmetric aircraft has experienced high altitude, high Mach, and high angle of attack flight states. If the control capability of the reusable surface-symmetric aircraft is determined according to the existing methods, due to To meet the requirements of high altitude, high Mach, and high angle of attack flight conditions during reentry, the control surface of the designed aircraft has a large structural size, which increases the weight of the entire aircraft and the energy consumption of the steering gear

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  • Method, device and electronic equipment for determining aircraft control capability
  • Method, device and electronic equipment for determining aircraft control capability
  • Method, device and electronic equipment for determining aircraft control capability

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Embodiment Construction

[0108] The specific implementation manners of the present invention will be further described in detail below in conjunction with the drawings and specific embodiments.

[0109] see figure 1 , an embodiment of the present invention provides a method for determining an aircraft control capability, including:

[0110] Step 101: According to the overall parameters, ballistic data and aerodynamic data of the aircraft, calculate the first parameter and the second parameter corresponding to each flight ballistic state point, wherein the first parameter is the coupling influence evaluation parameter of the aileron control on the heading stability , the second parameter is a lateral-direction coupling dynamic heading stability parameter;

[0111] Specifically, the coupling influence evaluation parameter of the aileron control on the heading stability, denoted as ACATD (aileron control affection to direction), can be determined according to the stability of the heading and the steerin...

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Abstract

The invention discloses an aircraft control capability determination method, device and electronic equipment, belonging to the field of aircraft design. The embodiment of the present invention provides a method for determining the control capability of an aircraft, which determines the evaluation parameters of the coupling influence of aileron manipulation on the heading stability and the lateral heading coupling dynamic heading stability corresponding to each flight ballistic state point through the overall parameters, ballistic data and aerodynamic data. According to the determined parameters, the control capability of each flight trajectory state point that meets the requirements is determined through the coupling control strategy. The coupling control strategy makes full use of the coupling effect between the lateral direction and the heading of the aircraft, which greatly reduces the control capability of the aircraft. Demand, The control potential of the plane-symmetrical aircraft is fully tapped to relax the design constraints of the control capability, thereby reducing the requirements for the structural size of the control rudder surface, reducing the weight of the whole machine and the energy consumption of the steering gear.

Description

technical field [0001] The invention relates to a method and a device for determining the control capability of an aircraft, belonging to the field of aircraft design. Background technique [0002] A plane-symmetric aircraft mainly uses aerodynamic force to realize trajectory and attitude control, that is, by manipulating the aerodynamic rudder surface, a control torque is generated to change the attitude, thereby changing the trajectory. Surface-symmetrical aircraft has a wide range of maneuverability, and has become a hot spot for the development of major countries in the world. In order to perform maneuvers and complete expected tasks, it is necessary to accurately evaluate and design the control capability of the aircraft, that is, the maximum control capability that each axis needs to provide. [0003] At present, the traditional aircraft design method is mainly used in the design of the control capability of the plane-symmetric aircraft at home and abroad, that is, th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10B64F5/00
CPCB64F5/00G05D1/107
Inventor 邵干袁利平海尔瀚蔡巧言赵大海郑宏涛张建英刘刚康建斌李洋步召杰石庆峰郎鹏飞李然邱丰
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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