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Parachute evasion method for Mars lander based on off-line analysis of parachute landing point

An off-line analysis and parachute technology, applied in the direction of aerospace vehicles, aerospace vehicle landing devices, aircraft, etc., can solve the problem of covering landers, achieve conservative and reliable results, and reduce evasive maneuvering energy.

Active Publication Date: 2022-05-20
BEIJING INST OF SPACECRAFT SYST ENG +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The purpose of the present invention is: to solve the problem that the parachute back cover assembly will cover the lander when the parachute back cover assembly is separated after the separation of the lander and the parachute back cover assembly in the prior art, a method for avoiding the parachute of the Mars lander based on the off-line analysis of the parachute landing point is proposed

Method used

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  • Parachute evasion method for Mars lander based on off-line analysis of parachute landing point
  • Parachute evasion method for Mars lander based on off-line analysis of parachute landing point
  • Parachute evasion method for Mars lander based on off-line analysis of parachute landing point

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specific Embodiment approach 1

[0063] Specific implementation mode one: refer to figure 1 Specifically illustrate this embodiment, the method for avoiding the parachute of the Mars lander based on the off-line analysis of the parachute landing point described in this embodiment includes:

[0064] Step 1: Use the Monte Carlo simulation method to determine the parachute landing point p for n times of simulation by offline simulation on the ground before the landing mission is implemented i , where the subscript i=1,2,…,n, indicates the landing point result corresponding to the i-th simulation, and indicates that when Mars enters the ground coordinate system Σ m Down;

[0065] Step 2: Construct the separated instantaneous reference coordinate system Σ s , drop the parachute in step 1 to point p i Transform to Σ s in, expressed as

[0066] Step 3: Count the mean value of n times of simulated landing points and the covariance matrix σ s , giving the separated instantaneous reference frame Σ s The stat...

Embodiment

[0149] In order to verify the parachute evasive maneuvering strategy provided by the present invention, 1020 Monte Carlo simulations have been carried out, and the distribution of the parachute drop point under the instantaneous reference coordinate system after applying the evasive maneuver is as follows: Figure 6 shown. The simulation results show that the number of trajectories with the distance between the parachute back cover assembly and the landing point of the lander is less than 100m, and the probability of the landing point distance being less than 100m is only 0.29%. Among the 1020 trajectories, 99.73% of the relative distances between the landing points are greater than 90.74m. The minimum distance is 68.73m, and the statistical histogram of the relative distance of the landing point is as follows Figure 7 shown.

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Abstract

A parachute evasion method for a Mars lander based on off-line analysis of parachute landing points, involves the field of guidance and control technology, and aims at the problem that the parachute back cover assembly will cover the lander when the lander is separated from the parachute back cover assembly in the prior art. Problem, this application uses the Monte Carlo simulation method to determine the distribution of the landing point of the parachute back cover assembly offline, and uses the aerodynamic parameters to pull the deviation to ensure that the shortest and longest empty time of the parachute and the combination of different wind directions are included in the simulation In the above, the parachute scatter ellipse covers various extreme conditions, and the results are more conservative and reliable. During the landing process, the landing point of the lander is predicted based on polynomial guidance, and the maneuvering is only applied to the situation where the parachute falls within the scattered area of ​​the parachute, and the maneuvering goal is to make the lander move the shortest distance to reach outside the parachute scattered area.

Description

technical field [0001] The invention relates to the technical field of guidance and control, in particular to a parachute avoidance method for a Mars lander based on off-line analysis of parachute drop points. Background technique [0002] After the Mars lander leaves the orbit and starts the landing process, it generally needs to use the Martian atmosphere to perform aerodynamic deceleration, and go through the stages of atmospheric entry, descent, and landing (EDL) to achieve a soft landing on the surface of Mars. During the atmospheric entry phase, the initial speed of the lander is about 25 times the speed of sound, and it is decelerated to about 2 times the speed of sound by using the aerodynamic force of the Martian atmosphere. Then the lander ejected the parachute, further using Martian atmospheric resistance to reduce the speed of the lander to tens of meters per second. During the landing phase, the lander is about a few kilometers above the surface of Mars. The la...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/62B64G1/24
CPCB64G1/62B64G1/242Y02T90/00
Inventor 董捷饶炜王闯崔祜涛田阳陈正缪远明谭志云
Owner BEIJING INST OF SPACECRAFT SYST ENG
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