Landing control method for small astrophysical probes based on online estimation of model-free interference

A technology for landing control and small celestial bodies, which is applied in the direction of aerospace vehicle landing devices, aerospace vehicle guidance devices, and systems for aerospace vehicles returning to the earth's atmosphere. And other issues

Inactive Publication Date: 2016-04-13
CHANGCHUN UNIV OF TECH
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Problems solved by technology

[0004] In order to solve the problem that the upper bound of model-free interference cannot be obtained and accurate and safe landing control cannot be realized in the existing landing control of small astronomical body detectors, the invention provides an online estimation of small astronomical body detector landing without model interference Control Method

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  • Landing control method for small astrophysical probes based on online estimation of model-free interference
  • Landing control method for small astrophysical probes based on online estimation of model-free interference
  • Landing control method for small astrophysical probes based on online estimation of model-free interference

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specific Embodiment approach 1

[0036] Specific implementation mode 1. Combination Figure 1 to Figure 4 In this embodiment, the method for controlling the landing of small astrophysical probes with online estimation without model interference is described. The specific steps are as follows:

[0037] 1. During the landing process of the small astrophysical probe, the kinetic equation of the probe is established as:

[0038] x · · - 2 ω y · - ω 2 x = F x + f ...

specific Embodiment approach 2

[0081] Specific embodiment two, combine Figure 1 to Figure 4 Describe this embodiment. This embodiment is an embodiment of the method for controlling the landing of a small astronomical body detector without model online estimation described in the first embodiment. The method described in the first embodiment is used for simulation testing to test the landing of small astronomical bodies. The parameters are shown in Table 1, and Table 1 is the parameters related to the landing small celestial body in the simulation test.

[0082] Table 1

[0083] GM (m 3 / s 2 )

ω

a(m)

C 20

C 22

4.842×10 5

1.65×10 -4

1138.5

-0.043

0.058

[0084] The simulation test landing trajectory parameters are shown in Table 2, and Table 2 is the simulation test landing trajectory parameters.

[0085] Table 2

[0086]

[0087] The landing control parameters of the simulation test are shown in Table 3.

[0088] table 3

[0089] Under the ab...

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Abstract

The invention discloses a small celestial body detector landing control method for online estimating non-model interference, relates to the technical field of small celestial body landing control, and solves the problems of incapability of obtaining an upper bound of the non-model interference and incapability of realizing precise and safe landing control in traditional small celestial body detector landing control. The method comprises the following steps: firstly, a trajectory capable of guaranteeing safe landing in time tau is designed, and anticipant descending positions, descending speeds and descending accelerations in three directions of X axis, Y axis and Z axis are determined; then, the non-model interference is estimated online in real time by designing an estimation function based on present position, speed and acceleration operation state information of a detector in the process of realizing the small celestial body detector landing; and finally, a control law is obtained based on the stability theorem of Lyapunov second method to obtain control accelerations of the detector in three directions, and the detector is controlled to track a nominal trajectory to guarantee precise and safe landing of the small celestial body detector.

Description

technical field [0001] The invention relates to the technical field of small celestial body landing control, in particular to a landing control method for a small celestial body probe with online estimation without model interference. Background technique [0002] In recent years, the world's space powers have set off an upsurge in deep space exploration of the solar system, and the deep space exploration of small celestial bodies has also attracted people's attention. The deep-space exploration of small celestial bodies began in the 1990s. The Galileo probe of the United States flew by two small celestial bodies on the way to detect Jupiter. On February 12, 2001, NASA's NEAR (NearEarthAsteroidRendezvous) probe successfully landed on the Eros asteroid; on May 9, 2003, Japan's MUSESC small asteroid probe was launched into space, beginning the first detection of a small celestial body in the history of human spaceflight. The rock sample sampling return mission; in September 2...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/62B64G1/24
Inventor 谢慕君李元春崔平远刘克平李岩李慧王宏王茜茜
Owner CHANGCHUN UNIV OF TECH
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