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Method for determining safe separation condition of heatproof outsole

A technology for determining methods and separation conditions, which is applied in the field of aerospace and can solve problems such as the lack of safety conditions for determining the separation of the large bottom

Active Publication Date: 2021-11-05
BEIJING INST OF SPACECRAFT SYST ENG +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the invention is to propose a method for determining the safe separation conditions of the heat-proof large bottom in view of the lack of methods for determining the safe separation conditions of the large bottom in the prior art

Method used

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  • Method for determining safe separation condition of heatproof outsole
  • Method for determining safe separation condition of heatproof outsole
  • Method for determining safe separation condition of heatproof outsole

Examples

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specific Embodiment approach 1

[0061] Specific implementation mode one: refer to figure 1 Specifically explain this embodiment, a method for determining the safety separation conditions of a heat-proof outsole described in this embodiment, including:

[0062] Step 1: According to the ballistic coefficient analysis of the detector and the outsole, determine the minimum separation speed for the safe separation of the outsole;

[0063] Step 2: According to the minimum separation speed of the safe separation of the large bottom, analyze the safety of the large bottom separation at different heights, and determine the minimum height of the safe separation of the large bottom;

[0064] Step 3: According to the phase relationship between the angular velocity and the attitude angle when the outsole is separated, and the minimum separation speed and minimum height for the safe separation of the outsole, analyze the angular velocity and attitude angle of different phases to determine the phase requirements for the sa...

Embodiment

[0110] In order to verify the method for determining the safe separation conditions of the large bottom provided by the application, the steps described in the application have been carried out in an embodiment, 1. According to the ballistic coefficient analysis of the detector and the large bottom, determine the minimum separation speed of the safe separation of the large bottom;

[0111] Analyze the ballistic coefficient of the detector and the outsole, and obtain the aerodynamically unsafe Mach number range of [0.8,1.0]. The outsole separation simulation is carried out in the aerodynamically unsafe Mach number range, and the outsole separation is performed every 0.1Ma. Plot the velocity difference between the outsole and the probe / parachute system, as in Figure 4 shown. Figure 4 It is the speed difference between the outsole and the detector / parachute system corresponding to the outsole separation trigger condition 0.8~1.0Ma. The curves from left to right correspond to th...

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Abstract

The invention relates to the technical field of aerospace, and relates to the technical field of aerospace. Aiming at the problem that in the prior art, the method for determining the safety condition of the large bottom separation is lack, the method comprehensively considers the ballistic coefficient of the outsole and the detector and the effect of the fire (by explosion) to push the two connected objects away, such as the two stages of the rocket, the anti-thermal outsole and the detector, the separation speed, the height, the separation phase, the angular velocity and the Mach number required by the large-bottom safe separation can be determined by step-by-step analysis on each separation condition, and the method is suitable for Mars detectors with different configurations.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method for determining safe separation conditions of a heat-resistant outsole. Background technique [0002] The key stage for the successful landing of the Mars rover is the process of entry, deceleration, and landing. During this process, the Mars rover will reduce its speed from kilometers per second to 0 in about 7 minutes. During the entry process, the Mars rover relies on the Martian atmosphere for aerodynamic deceleration, the speed is reduced by about 90%, and then it is decelerated by a parachute. When the speed drops to about 100 meters per second, it is decelerated by the thrust reverser engine and performs a soft landing. During the deceleration process, the Mars rover needs to overcome high temperature and pressure, and protect the rover through a heat-resistant outsole (outsole for short). When the parachute deploys and the rover slows down, the outsole has do...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/20G06F111/04G06F119/20
Inventor 饶炜董捷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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