A frequency management method for hypersonic vehicle attitude stabilization

Abstract

The invention relates to a frequency management method for stable postures of a hypersonic aircraft. The method sequentially comprises the steps that (1), information of various frequencies is collected; (2) when a rigid motion transmission band is larger than first-order elastic vibration frequency by more than 10 times, and an elasticity amplitude stabilizing method is adopted; (3), a rate gyroscope is led in to a place where the vibration mode slope is zero; (4) when shaking zero frequency is larger than pole frequency, shaking stability is improved through feedback of an accelerometer or additional arrangement of an anti-shaking board; (5), a transmission band of a steering engine is 5-10 times of the rigid motion transmission band; (6), an inertia unit transmission band is 10-20 times of rigid motion bandwidth; (7), the structural stiffness of an executing mechanism and a sensitive mechanism is kept to be more than 5 times of a single-engine bandwidth; (8), main frequency of external disturbance is prevented from being coupled with inherent frequency of a structural part; (9), ground tests of various frequency characteristics are carried out, and the stable postures of the hypersonic aircraft are ensured. According to the frequency management method for the stable postures of the hypersonic aircraft, repeated schemes are avoided, development schedule is accelerated, and system interfaces are made to be clear and comprehensively optimum.

Description

technical field [0001] The invention relates to a frequency management method for attitude stabilization of a hypersonic aircraft, in particular to a control system as the core, aiming at improving the overall performance of the aircraft, and performing various motion information and external interference information that affect the attitude stability of the aircraft. Synthesis and allocation, active elimination of unfavorable coupling, optimization of each system to achieve the overall optimal frequency management method of hypersonic vehicle attitude stability. Background technique [0002] The subsystems of a hypersonic vehicle are highly coupled from performance to structural design, the design parameters of each subsystem influence each other, and the overall performance is highly sensitive to the parameters of the subsystems. The development process is a systematic project. At the same time, there are many uncertain factors such as the complex movement mode of the proj...

AI Technical Summary

Problems solved by technology

At the same time, there are many uncertain factors such as the complex movement mode of the missile body, the harsh flight environment, and external interference, which all affect the stable flight of the aircraft.

When the coupling between the subsystems, the movements, the projectile, the environment, and the interference is not effectively controlled, the attitude of the aircraft will be unstable or the structure will be divergent.

[0003] Traditionally, each system generally calculates the transfer characteristics and motion characteristic information of the system first, and inputs the results to the attitude control system, and then the attitude control system designers evaluate the stability of the attitude control system based on the data provided by each system. If the stability design requirements are not met, the control parameters need to be redesigned. When the stability requirements cannot be met by redesigning the parameters, then counter-requirements are made for the structure and other related systems. This design idea is time-consuming, labor-intensive, and more importantly It is easy to cause the repetition of the scheme and delay the development progress. Therefore, it is necessary to adopt a better design method

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