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A Calculation Method for Minimum Hinge Moment Downward Trajectory Applicable to Gliding Vehicles

A hinge torque, aircraft technology, applied in the direction of calculation, instruments, special data processing applications, etc., can solve the problems of large output torque, servo system can not provide, outstanding hinge torque, etc., to achieve the effect of alleviating contradictions

Inactive Publication Date: 2016-11-16
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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Problems solved by technology

[0003] Hypersonic vehicles rely on aerodynamic force to achieve ballistic downward pressure. In order to improve the penetration capability of the aircraft, the required terminal speed is relatively high, so that the maximum dynamic pressure during the flight can reach the order of one million Pa or even higher, which directly leads to the prominent hinge moment. , put forward harsh conditions for the servo system, the servo system cannot provide a large output torque under the limitation of weight and size, and there is a prominent contradiction between ballistic maneuvering and the maximum capacity of the servo system

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  • A Calculation Method for Minimum Hinge Moment Downward Trajectory Applicable to Gliding Vehicles
  • A Calculation Method for Minimum Hinge Moment Downward Trajectory Applicable to Gliding Vehicles
  • A Calculation Method for Minimum Hinge Moment Downward Trajectory Applicable to Gliding Vehicles

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[0009] Exemplary embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The description of the exemplary embodiments is for the purpose of illustration only, and in no way limits the invention and its application or usage.

[0010] The target calculation method scheme of the minimum hinge moment depressing trajectory is as follows:

[0011] The first step is to assign values ​​to the initial flight state parameters of the aircraft, wherein the flight state parameters include altitude H, longitude θ, latitude φ, velocity V, ballistic inclination Θ, and velocity azimuth ψ;

[0012] The second step, based on the geographic coordinate motion model, uses the fourth-order Runge-Kutta to integrate the time t, calculates the rapid downward flight trajectory until the end of the entire flight process, and records the maximum hinge moment during the entire flight process maximum overload and the terminal velocity V f and ...

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Abstract

The invention relates to a minimum hinge moment pressing-down trajectory calculation method applicable to a glide vehicle. The minimum hinge moment pressing-down trajectory calculation method comprises: step 1, assigning initial flight status parameters of an air vehicle; step 2, based on a geographical coordinate movement model, calculating a rapid pressing-down flight trajectory and recording maximum hinge moments M<-1><max>, M<0><max> and M<+1><max>, a minimum overload N<max><*>, a terminal speed Vf and a terminal inclined angle thetaf in a whole flight process; and step 3, adjusting a flight attack angle alpha of the air vehicle by adopting a direct shooting method, and repeating the step 1 and the step 2 to calculate a rapid pressing-down flight trajectory to obtain a standard trajectory with the minimum hinge moment. According to the method, a technical way is provided for an integrated optimization design of a hypersonic air vehicle trajectory, guidance and a posture control system according to the design of the trajectory; a calculated minimum hinge moment trajectory is traced, so that the index requirements on a servo system can be effectively reduced and the weight of the servo system is reduced; and the design margin of a control system is increased, and the integrity of a hypersonic air vehicle is improved.

Description

technical field [0001] The invention relates to a control method for a hypersonic gliding aircraft, in particular to a method for calculating a minimum hinge moment depressing trajectory suitable for a gliding aircraft. Background technique [0002] The technical background related to the present invention will be described below, but these descriptions do not necessarily constitute the prior art of the present invention. [0003] Hypersonic vehicles rely on aerodynamic force to achieve ballistic downward pressure. In order to improve the penetration capability of the aircraft, the required terminal speed is relatively high, so that the maximum dynamic pressure during the flight can reach the order of millions of Pa or even higher, which directly leads to the prominent hinge moment. , put forward harsh conditions for the servo system, the servo system cannot provide a large output torque under the limitation of weight and size, and there is a prominent contradiction between ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F19/00
Inventor 杨业马卫华包为民黄万伟祁振强禹春梅唐海红吴浩
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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