Aircraft controllability determining method and device and electronic device

Abstract

The invention discloses an aircraft controllability determining method and device and an electronic device, and belongs to the field of aircraft design. The method includes the steps of determining anevaluating parameter of the coupling influence of aileron control on course stability and a transverse course coupling dynamic course stability parameter corresponding to all flight trajectory statepoints through total parameters, trajectory data and aerodynamic data, and determining the controllability of all the flight trajectory state points meeting requirements through a coupling control strategy according to the determined parameters. The coupling effect between the transverse direction and the course of an aircraft is sufficiently used through the coupling control strategy, the requirement for the controllability of the aircraft is greatly reduced, the plane symmetry aircraft control potential is sufficiently mined so as to loosen the controllability design constraint, and therefore the requirement for the structural size of the control plane is lowered, and the weight of the whole aircraft and the energy consumption of a whole steering engine are reduced.

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...

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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