Method of determining use priority of various control surfaces of multi-control surface plane at close-range stage

Abstract

The invention provides a method of determining a use priority of various control surfaces of a multi-control surface plane at a close-range stage. The method adopts the equation of J delta i=aLD[(L / D) delta i-(L / D)0] +amRm delta i+arlRrl delta i to determine the use priority of various control surfaces at the flight condition of the same mach number and angle of incidence, wherein delta Cm delta i is the pitching control efficacy of the ith control surface; CL0 and CD0 are lift coefficient and resistance coefficient in case of deflection of the plane without the control surface; delta CL delta i and delta CD delta i are additional lift coefficient and additional resistance coefficient after the ith control surface deflects the unit angle; RL delta i is the deflection rate of the ith control surface; and RL delta 0 is the deflection rate of the reference control surface. The method meets the requirements of lift and resistance characteristics, control surface efficacy and deflection capability of a steering engine of the plane at the close-range air war stage, and determines the use priority of various control surfaces of the plane based on the requirements, the control surface with high priority can be selected to use at multiple control ways, the unfavorable cost in the control process is lowered, and the flight performance of the plane at the close-range air war stage is 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 of an aircraft with multiple control surfaces in the short-distance stage. 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 i...

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 agility of the aircraft

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