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Hypersonic gliding aircraft linear pseudo-spectrum reentry guidance method and system

A hypersonic, linear pseudo-spectrum technology, applied in control/regulation systems, vehicle position/route/height control, instruments, etc., can solve problems such as low efficiency and poor adaptability, and achieve high numerical accuracy, fast calculation speed, and strong Effects of Adaptability and Robustness

Pending Publication Date: 2021-12-24
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In view of this, the object of the present invention is to provide a hypersonic gliding vehicle linear pseudo-spectrum re-entry guidance method and system, to alleviate the technical problems of poor adaptability and low efficiency in the prior art

Method used

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  • Hypersonic gliding aircraft linear pseudo-spectrum reentry guidance method and system
  • Hypersonic gliding aircraft linear pseudo-spectrum reentry guidance method and system
  • Hypersonic gliding aircraft linear pseudo-spectrum reentry guidance method and system

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Embodiment 1

[0027]figure 1 It is a flow chart of a linear pseudo-spectrum reentry guidance method for a hypersonic glide vehicle according to an embodiment of the present invention. In the embodiment of the present invention, the guidance includes guidance in the descent section and guidance in the gliding section. Among them, such as figure 1 As shown, the glide segment guidance provided by the embodiment of the present invention specifically includes the following steps:

[0028] Step S102, decoupling the longitudinal plane motion and the transverse plane motion of the target aircraft, and establishing the longitudinal plane dynamics model of the target aircraft; the target aircraft is a hypersonic gliding aircraft; the longitudinal plane dynamics model is a dynamics that does not consider the influence of the earth's rotation Model.

[0029] Step S104, converting the state quantities and terminal constraints of the longitudinal planar dynamics model into state quantities and terminal...

Embodiment 2

[0220] Figure 7 It is a schematic diagram of a linear pseudo-spectrum reentry guidance system for a hypersonic glide vehicle according to an embodiment of the present invention. Such as Figure 7 As shown, the system includes: a decoupling module 10 , a conversion module 20 , an establishment module 30 , a solution module 40 , a determination module 50 and a guidance module 60 .

[0221] Specifically, the decoupling module 10 is used to decouple the longitudinal plane motion and the transverse plane motion of the target aircraft, and establish the longitudinal plane dynamics model of the target aircraft; the target aircraft is a hypersonic gliding aircraft; the longitudinal plane dynamics model is not A dynamical model considering the effects of the Earth's rotation.

[0222] The conversion module 20 is used to convert the state quantities and terminal constraints of the longitudinal plane dynamics model into the state quantities and terminal constraints of the differential...

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Abstract

The invention provides a hypersonic gliding aircraft linear pseudo-spectrum reentry guidance method and system. The method comprises the steps of: decoupling longitudinal plane motion and transverse plane motion of a target aircraft, and establishing a longitudinal plane dynamic model of the target aircraft; based on a state equation satisfied by the state quantity of a differential flat system, establishing a target linear state equation set which simultaneously satisfies an optimal solution under an optimal control algorithm and a terminal constraint of the differential flat system; solving the target linear state equation set based on a pseudo-spectral discrete method to obtain a control quantity of longitudinal plane motion of the target aircraft; determining a course angle error control quantity of the target aircraft on a transverse motion plane based on a course angle error corridor, and constructing a heeling angle overturning logic based on the course angle error control quantity; and based on the control quantity of the longitudinal plane motion and roll angle overturning logic, guiding the target aircraft. The hypersonic gliding aircraft linear pseudo-spectrum reentry guidance method and system mitigate the technical problems of poor adaptability and low efficiency in the prior art.

Description

technical field [0001] The invention relates to the technical field of hypersonic vehicle trajectory control, in particular to a linear pseudo-spectrum reentry guidance method and system for a hypersonic gliding vehicle. Background technique [0002] Due to the large airspace and wide speed range of the hypersonic gliding vehicle during the reentry phase, and the attitude and trajectory changes very drastically, it has serious coupling characteristics and uncertainties. In addition, the re-entry process of the aircraft must not only meet the terminal state constraints related to the flight mission, but also take into account the limitations of the aircraft's own materials and structures, and introduce path constraints such as heat flow constraints, dynamic pressure constraints, and overload constraints to ensure the flight process. security, which brings a huge challenge to the design of the reentry guidance law. [0003] With the deepening of reentry guidance control techn...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/107
Inventor 杨良陈万春王冲冲
Owner BEIHANG UNIV
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