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On-line iterative landing guidance method and system and memory including the method

An iterative and storage module technology, applied in the field of landing recovery, which can solve the problems of landing site position, low speed accuracy, and inability to achieve appropriate adjustment, and achieve the effect of accurate landing control

Active Publication Date: 2021-03-16
江苏深蓝航天有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

When the deviation state is large, or the flight time is uncertain, the propellant consumed by the existing technology is not optimal, and moderate adjustment cannot be achieved, and the accuracy of the landing point position and speed is low

Method used

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  • On-line iterative landing guidance method and system and memory including the method
  • On-line iterative landing guidance method and system and memory including the method
  • On-line iterative landing guidance method and system and memory including the method

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Embodiment Construction

[0042] The present disclosure will be further described in detail below with reference to the drawings and embodiments. It can be understood that the specific implementation manners described here are only used to explain relevant content, rather than to limit the present disclosure. It should also be noted that, for ease of description, only parts related to the present disclosure are shown in the drawings.

[0043] It should be noted that, in the case of no conflict, the implementation modes and the features in the implementation modes in the present disclosure can be combined with each other. The present disclosure will be described in detail below with reference to the drawings and embodiments.

[0044] The guidance process model of the present disclosure can be divided into two parts: acceleration and deceleration. According to common knowledge, the required initial point position in the guidance process initial point velocity initial point acceleration Landing tar...

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Abstract

The invention relates to a landing guidance system. The landing guidance system comprises a calculation module, a storage module, an acquisition module and a control output module. By calculating deviation of a current position parameter from a current reference trajectory, the propellant consumption is estimated according to the deviation; the reference trajectory is calculated and adjusted basedon the remaining whole-journey motion time t<f>, the current position parameter and a landing target point position parameter; and if constraint conditions of a propellant are not met, the remainingwhole-journey motion time t<f> is adjusted, the reference trajectory is calculated and adjusted based on the remaining whole-journey motion time t<f>, and the propellant consumption required to perform the adjustment of the reference trajectory is estimated until the constraint conditions of the propellant are met. The invention further provides an on-line iterative calculation method and a memory, and the effects of minimal fuel consumption during landing and more accurate landing control can be achieved.

Description

technical field [0001] The present disclosure relates to the technical field of landing recovery, in particular to an online iterative landing guidance method, a system and a memory including the method. Background technique [0002] The problem of landing trajectory planning in near-Earth space is a very critical technology for reentry and recovery rockets. Improving the guidance accuracy can effectively reduce the scope of the landing field, reduce the design pressure of the landing buffer device, reduce the accuracy level of the inertial measurement device, and effectively improve the landing control performance. Patent "Mars Rover Landing Guidance Method Based on Optimum Fuel" ( [0003] CN201410802923.9) can fit the corresponding path points of the detector in the atypical initial state when the initial state of the detector is not the stored typical initial state, and realize the matching of the path point and the initial state. But in fact, after a fitting, the guid...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/242
Inventor 不公告发明人
Owner 江苏深蓝航天有限公司
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