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High-speed axisymmetric aircraft composite control method

A composite control, aircraft technology, applied in general control systems, control/regulation systems, instruments, etc., can solve problems such as poor stability

Inactive Publication Date: 2014-07-09
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the shortcomings of the poor stability of the existing direct force and aerodynamic compound control methods for intercepting missiles, the present invention provides a compound control method for high-speed axisymmetric aircraft

Method used

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Embodiment Construction

[0144] The specific steps of the compound control method for high-speed axisymmetric aircraft of the present invention are as follows:

[0145] Step 1: Formulate the instruction distribution strategy under the composite control scheme.

[0146] The variable center of mass maneuver control mainly adjusts the sliding of the internal mass block of the aircraft, so that the position of the center of mass of the aircraft moves according to a certain rule, forming an offset of aerodynamic force relative to the center of mass of the aircraft, thereby generating aerodynamic moment, adjusting the attitude angle of the aircraft and establishing a corresponding Trimming the angle of attack and trimming the sideslip angle finally realizes the maneuver control of the center of mass of the aircraft, making it move according to a certain ballistic trajectory.

[0147] The invention adopts the control mode of the three-axis stable reentry vehicle. For the shape of the aircraft with axisymmet...

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Abstract

The invention discloses a high-speed axisymmetric aircraft composite control method. The high-speed axisymmetric aircraft composite control method is used for solving the technical problem of poor stability in an existing interceptor missile direct force and aerodynamic force composite control method. According to the technical scheme, a varying centroid and pneumatic rudder composite control are adopted, based on defining a varying centroid control mode, an instruct allocation strategy under a composite control scheme is formulated; a dynamical model for control is established through force analysis of a high-speed aircraft; an overall scheme of a varying centroid mechanism is further determined; then ballistic characteristic points are taken to finish design of a control system. According to the high-speed axisymmetric aircraft composite control method, the varying centroid mechanism is introduced, so that the technical problem of poor stability of a background technology control method is effectively avoided, larger control torque is obtained while energy consumption is reduced as much as possible, and reentry flight of the high-speed aircraft for a long time in a large airspace is facilitated; a composite mode with the pneumatic rudder is adopted, so that work pattern of a sliding block executing mechanism is simplified, and system stability is improved.

Description

technical field [0001] The invention relates to a control method for a high-speed axisymmetric aircraft, in particular to a compound control method for a high-speed axisymmetric aircraft. Background technique [0002] Existing high-speed aircraft have the characteristics of high flight speed, large flying airspace, and strong maneuverability. Due to long-term high-altitude flight and low air density, the system efficiency of the aircraft is greatly reduced, and the available overload is greatly reduced. Traditional pneumatic controls present serious challenges. The compound control technology of direct force and aerodynamic force is a kind of aircraft control technology widely used at present. The principle is to generate gas power through a large number of side-injection micro-engines installed on the aircraft, and directly generate torque to the aircraft to quickly change the attitude of the aircraft and quickly establish an aerodynamic angle, so as to achieve large maneu...

Claims

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Application Information

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IPC IPC(8): G05B17/00
Inventor 林鹏周军余晨菲许琦葛振振
Owner NORTHWESTERN POLYTECHNICAL UNIV
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