Method for determining using priority of each control surface of multi-control-surface aircraft during over-the-horizon stage

Abstract

The invention provides a method for determining the using priority of each control surface of a multi-control-surface aircraft during an over-the-horizon stage, the formula that J delta i=Rm delta i ((L / D) delta i-(L / D)0) is adopted for determining the using priority of each control surface under the same Mach number flight state, wherein delta Cm delta i is the pitch control effectiveness of theith control surface, delta Cm delta 0 is the pitch control effectiveness of the reference control surface, and the reference control surface can be any control surface in the multi-control-surface aircraft; and CL0 and CD0 are a lift coefficient and a drag coefficient respectively when no control surface of the aircraft deflects, and delta CL delta i and delta CD delta i are an additional lift coefficient and an additional drag coefficient generated after the ith control surface deflects the unit angle. By adopting the method, the requirements of the aircraft on cruising ability during the over-the-horizon air battle stage can be reflected, the requirements can be further combined to determine the using priority of each control surface of the aircraft, the control surface with the high using priority can be selected under the situation that the various control ways exist, the adverse cost during the control process can be reduced and the flight performance of the aircraft during the over-the-horizon stage can be improved.

Description

technical field [0001] The invention relates to the field of flight control, in particular to a method for determining the use priority of each control surface in the over-the-horizon phase of an aircraft with multiple control surfaces. Background technique [0002] The three control surfaces of the traditional layout aircraft, including the elevator, aileron and rudder, respectively correspond to the attitude control in the three directions of pitch, roll and yaw. The number of control surfaces is equal to the number of control expected parameters, and the control method is unique. In order to meet the expected performance requirements, modern new aircraft generally introduce some new control surfaces. For example, in order to obtain maneuverability at high angle of attack, a close-coupled canard is introduced; in order to obtain post-stall maneuverability and maneuverability, thrust vectoring is introduced; in order to improve takeoff and landing performance, a lift device...

AI Technical Summary

Problems solved by technology

The aircraft with multiple control surfaces can use various control methods to meet the control requirements, but the cost of different control methods is also different. This is mainly because, firstly, the deflection of the control surfaces can not only generate the control moment, but also affect the lift-drag characteristics of the aircraft. If the control method that affects the lift-drag characteristics of the aircraft is selected, it will affect the flight performance of the aircraft; secondly, the deflection angle and deflection rate of the steering gear on the control surface are limited, so the control surface The generated control torque is limited, and it will take a certain amount of time to reach the desired control torque. If too many control surfaces with low steering gear deflection rate are selected, although the desired control torque can still be achieved in the end, the control response of the aircraft will be affected. Slower, which affects the flight quality and agility of the aircraft

Images