Method for direct force pulse width modulation at aircraft end

A wide modulation, aircraft technology, applied in the direction of torque/mechanical power control, instrumentation, adaptive control, etc., can solve the problem of reducing the energy quality characteristics of the engine

Inactive Publication Date: 2019-08-06
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although reducing the gas temperature can simplify the valve structure, improve reliability and manufacturability, it also reduces the energy quality characteristics of the engine

Method used

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  • Method for direct force pulse width modulation at aircraft end
  • Method for direct force pulse width modulation at aircraft end
  • Method for direct force pulse width modulation at aircraft end

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Embodiment Construction

[0040] The following will combine Figure 1 ~ Figure 2 The method for controlling the direct force impulse of the missile of the present invention is further described in detail. For convenience of description, the longitudinal plane is taken as an example below.

[0041] The direct force pulse width modulation method at the end of the aircraft in the embodiment of the present invention includes the following steps:

[0042] Step 1. The missile-on-board computer is based on the missile-to-target relative information given by the radar seeker, including the line-of-sight angular velocity Projectile-target relative distance R, projectile-target radial relative velocity And according to the missile motion state information obtained by the strapdown solution, the target motion information is estimated by using the missile-target relative motion equation:

[0043]

[0044] where V t is the target speed, is the target velocity inclination velocity, is the missile veloci...

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Abstract

The invention relates to a method for direct force pulse width modulation at an aircraft end. Characteristics of an existing aircraft rail-controlled direct force control mode are analyzed and a direct force pulse width modulation control method is put forward. To be specific, according to the method, direct engine nozzles are distributed in a cross-shaped manner and the direct thrust can not be adjusted; and an objective of controlling direct force lasting time is achieved by turning on an opposite valve. Besides, the direct force control strategy of the control method includes: providing a thrust equivalent principle based on the characteristics of the control method and deducing direct engine startup time; according to the thrust equivalent principle, calculating residual flight time and an estimated miss distance and designing maneuver estimation on the target based on an extended state observer; and designing a zero-miss-distance-based variable structure guidance law to solve a displacement correction limit problem of the thrust equivalent principle.

Description

technical field [0001] The invention relates to a direct force pulse width modulation method at the end of an aircraft, in particular to a direct force impulse control technology with constant direct thrust and adjustable thrust time. Background technique [0002] At present, the existing track-controlled direct force / pneumatic force composite control technology mainly focuses on two thrust methods: one is represented by the European Aster-15 and Aster-30, the direct thrust engine is modulated by the gas switch valve, and the direct thrust Continuously adjustable; the second type is represented by 9M96E and 9M96E2 in the Russian S-400 defense system. A certain number of nozzles are distributed along the circumference of the center of mass of the missile, and the direct thrust is adjusted by switching a certain number of nozzles in a specific direction. The direction and magnitude of the synthetic thrust of this adjustment method have a certain minimum resolution, which canno...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04G05D17/02
CPCG05B13/042G05B13/048G05D17/02
Inventor 赵斌朱传祥
Owner NORTHWESTERN POLYTECHNICAL UNIV
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