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Mars rover landing guidance method based on fuel optimization

A technology for Mars probes and probes, applied in the field of deep space exploration, can solve problems such as occupying probes, large storage space, and inability to achieve optimal fuel guidance, reducing online calculation, saving storage space, and high reliability. Effects of Features

Active Publication Date: 2016-06-29
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to propose a fuel-optimized Mars rover landing guidance method to solve the problem that the existing explicit guidance law cannot achieve fuel-optimized guidance and that the optimal guidance law must store the entire trajectory, resulting in the need for occupancy detection. The problem of large storage space

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  • Mars rover landing guidance method based on fuel optimization
  • Mars rover landing guidance method based on fuel optimization
  • Mars rover landing guidance method based on fuel optimization

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specific Embodiment approach 1

[0029] Specific implementation mode one: combine figure 1 , figure 2 , image 3 Illustrate this embodiment, the Mars rover landing guidance method based on fuel optimization described in this embodiment, comprises the following steps:

[0030] Step 1. Obtaining the optimal solution of the detector fuel;

[0031] Step 2. After step 1 is completed, set waypoints and build a waypoint library;

[0032] Step 3. After step 2 is completed, design a linear feedback guidance law. If the initial state information of the detector matches the waypoint information in the waypoint library, implement landing, otherwise proceed to step 4;

[0033] Step 4: The initial state information of the detector does not directly match the waypoint information, and the landing is implemented after waypoint fitting.

[0034] The beneficial effects of this embodiment are:

[0035] 1. The present invention utilizes path point information combined with linear guidance law for guidance. On the premise o...

specific Embodiment approach 2

[0040] Specific implementation mode two: combinationfigure 1 This embodiment is described. The difference between this embodiment and the first embodiment is that the minimum fuel consumption corresponding to different flight times has a convex function property. Therefore, the present invention uses the idea of ​​dichotomy for reference and uses the method of thirds to obtain the global optimal solution. The specific process of obtaining the optimal solution of the detector fuel described in step 1 is as follows:

[0041] Step 11, using the dichotomy method to determine the minimum feasible flight time t l , combined with task requirements and experience to give a feasible flight time interval [t l , t u ], solve the endpoint time t l , t u The fuel optimization problem of , to obtain the optimal endpoint fuel consumption m l and m u ;

[0042] Step one two, the interval described in step one [t l , t u ] into thirds, ie t 1 = t l +(t u -t l ) / 3 , t 2 = t u -(t...

specific Embodiment approach 3

[0045] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is: the solution process of the fuel optimization problem described in step one by one is:

[0046] The optimization software SeDumi is used to solve the problem, and the optimal fuel consumption and acceleration of the detector can be obtained through this software, and then the optimal landing trajectory can be obtained.

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Abstract

The invention relates to a mars soft landing guidance method, in particular to a mars probe landing guidance method based on fuel minimization, and belongs to the technical field of deep space exploration. The mars probe landing guidance method based on fuel minimization solves the problems that fuel minimization guidance can not be achieved through an existing explicit guidance law, and the optimal guidance law must store an entire track, so that a large storage space is occupied. The technical scheme includes the steps that a fuel optimal solution of a probe is acquired; path points are set and a path point library is established; a linear feedback guidance law is designed, if initial state information of the probe is matched with path point information of the path point library, landing is executed, and otherwise, landing is executed after the path points are fitted. Through the guidance strategy of the path points and the linear guidance law, the method can achieve the fuel optimal guidance of a power descent section of the mars probe based on a small storage space. The mars probe landing guidance method based on fuel minimization is suitable for the guidance law of the power descent section of the mars probe.

Description

technical field [0001] The invention relates to a guidance method for a soft landing on Mars, in particular to a landing guidance method for a Mars probe based on optimal fuel, and belongs to the technical field of deep space exploration. Background technique [0002] Key technologies such as deep space exploration and planetary landing sampling have laid the foundation for human beings to study the origin of the universe, develop and utilize space resources. In particular, Mars, the closest neighbor of the earth, has become the first choice for human beings to explore outer space. The successful landing of the US "Curiosity" Mars rover in 2011 set off a new wave of planetary exploration and landing missions. India and the United States launched the "Mars Orbiter" and the "Mars Atmosphere and Volatile Evolution Mission" probes on November 5 and 18, 2013, respectively, and have successfully entered Mars orbit on September 24 and 22, 2014. , will bring new opportunities to s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
Inventor 郭延宁马广富曾添一李传江崔祜涛
Owner HARBIN INST OF TECH
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