Hovering flight trajectory guidance law design method and system
A technology of flight trajectory and design method, applied in the field of guidance law, can solve the problems of autopilot anti-interference, large overload, rapid change of attack angle, etc., to achieve the effects of easy engineering implementation, low pressure, and simple algorithm
Active Publication Date: 2015-01-21
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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[0004] Aiming at the defects and technical requirements of the prior art, the present invention provides a guidance law design method and system for the circling flight trajectory, which can solve the problem of large overload and rapid change of the angle of attack in the prior art, which brings unnecessary problems to the autopilot. Deficiencies in anti-jamming requirements
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[0023] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not constitute a conflict with each other.
[0024] The guidance law design method of the present invention mainly obtains the centripetal acceleration guidance instruction after matching the velocity by obtaining the curvature radius of the flight trajectory. The lateral autopilot follows this command to achieve 180° reverse circling flight. The longitudinal autopilot can track the modified proportional guidance command with ballistic in...
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The invention discloses a hovering flight trajectory guidance law design method and system. The method includes the following steps that first, the velocity V of an aircraft, the current transverse position Zt of the aircraft in a launching system, and the transverse position Z of an ending point of the aircraft completing reverse 180-degree hovering in the launching system are acquired, and the midcourse guidance instruction AzO of the aircraft is obtained; second, the terminal guidance instruction Az1 of the aircraft is obtained; third, the final guidance instruction Az of the aircraft is determined according to the midcourse guidance instruction AzO of the aircraft and the terminal guidance instruction Az1 of the aircraft and serves as an input instruction of an automatic pilot so that the aircraft can achieve reverse 180-degree hovering flight. The invention further provides the system for implementing the method. Due to the implementation of the method and system, reverse 180-degree flight of the aircraft can be achieved very conveniently and rapidly, and the method and system have the advantages that an algorithm is simple, engineering realization is easy, and the pressure on the automatic pilot is small.
Description
technical field [0001] The invention belongs to the technical field of guidance laws, and in particular relates to a guidance law design method and system for a circling flight trajectory. Background technique [0002] The current domestic guidance law design for 180-degree reverse circling flight is basically planning the flight trajectory off-line on the ground and loading it into the computer storage body. Then, in the real flight process, the deviation value is obtained by comparing the actual position and speed of the aircraft with the aircraft loaded in the computer storage body, and the deviation value is corrected to realize the hovering flight of the aircraft. [0003] However, this type of traditional method has the following defects: when the initial value of the aircraft control moment is far from the flight trajectory value planned offline on the ground, the flight trajectory planned offline on the ground is no longer the optimal trajectory; if the aircraft is s...
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IPC IPC(8): G05D1/10
Inventor 朱伟
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD