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Lander and instrument anchoring system for microgravity environment

An anchoring system and lander technology, applied in the directions of space navigation equipment, space navigation equipment, aircraft, etc., can solve the problems of small anchoring force and non-deformable anchor tip, achieve high anchoring force, reduce the risk of floating away, wear Strong penetrating effect

Active Publication Date: 2015-04-15
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0023] The present invention aims to solve the problem that the anchor tip cannot be deformed in the existing anchoring mechanism, so that the anchoring force is small after being driven into the medium, and further provides an anchoring system for landers and instruments in a microgravity environment.

Method used

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  • Lander and instrument anchoring system for microgravity environment
  • Lander and instrument anchoring system for microgravity environment
  • Lander and instrument anchoring system for microgravity environment

Examples

Experimental program
Comparison scheme
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specific Embodiment approach 1

[0036] Specific implementation mode one: as Figures 1 to 5 As shown, the anchoring system for landers and instruments in a microgravity environment in this embodiment consists of an anchoring unit 1, a propulsion unit 2, a vibration damping unit 3 and a winding unit 4;

[0037]The anchor unit 1 includes an anchor tip 1-1, an anchor claw 1-2, an inverted cone 1-3, a stepped push rod 1-4, a piston 1-7, a combustion chamber 1-8, an pyrotechnic device 1-9, an anchor A rod 1-10, an anchor rod end cover 1-11, a plurality of evenly distributed spreading wing pins 1-5 and a plurality of uniformly spreading spreading wings 1-6; the anchor tip 1-1, the combustion chamber 1-8 and the anchor rod 1-10 are all hollow structures, one end of the anchor tip 1-1 is larger and the other end is smaller, the larger end of the anchor tip 1-1 is threadedly connected to one end of the combustion chamber 1-8, and the other end of the combustion chamber 1-8 is connected to the anchor rod 1 One end of...

specific Embodiment approach 2

[0047] Specific implementation mode two: as figure 1 and figure 2 As shown, the small end of the anchor tip 1-1 in this embodiment is conical, and the large end of the anchor tip 1-1 is cylindrical. Such setting can effectively increase the penetration depth. Other compositions and connection methods are the same as those in Embodiment 1.

specific Embodiment approach 3

[0048] Specific implementation mode three: as figure 1 and image 3 As shown, the number of piston rods 2-6 in this embodiment is two to six. With this setting, the initial exit velocity of the anchor body can be adjusted. Other compositions and connection methods are the same as those in Embodiment 1 or 2.

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Abstract

The invention discloses a lander and instrument anchoring system for a microgravity environment, relating to the lander and instrument anchoring system. The invention aims to solve the problem that an anchor bill in the traditional anchoring mechanism is not deformable and leads to smaller anchoring force after being stricken into a medium. The big end of a stepped push rod is fixedly connected with a piston, the stepped push rod is located in the anchor bill and is in sliding connection with the anchor bill, a back taper is arranged in the anchor bill and is arranged adjacent to the small end of the stepped push rod, four anchoring claws are fixed on the small end of the stepped push rod and are arranged in a star shape, each spreading wing is arranged on the big end of the anchor bill through a spreading wing pin, and a plurality of the spreading wings are arranged in the star shape; and the outer wall of a combustion chamber of an anchoring unit is in sliding connection with the inner wall of the end cover of an expansion cylinder, the sliding bearing of a damping unit is sleeved on the outer wall of the expansion cylinder of a pushing unit, the damping unit slides relatively to the expansion cylinder of the pushing unit, and a winding unit is fixed on the sleeve of the damping unit. The lander and instrument anchoring system disclosed by the invention is used for anchoring the lander and instrument under the microgravity environment.

Description

technical field [0001] The invention relates to an anchoring system for a lander and instruments and equipment in a microgravity environment. Background technique [0002] Microgravity is mainly reflected in deep space exploration. The development of space technology has made it possible for humans to launch probes to certain planets in the solar system, land on the surface of some planets to retrieve soil and rock samples, and understand and use planets through scientific experiments. So far, humans have landed on the surface of the moon and Mars, and successfully retrieved lunar soil and rock samples. In addition to the moon and Mars, humans have also launched landers to Venus, Jupiter, asteroids, and comets. With the advent of the 21st century, deep space exploration technology, as an important means for human beings to protect the earth, enter the universe and find new living homes, has attracted great attention from various countries in the world. Deep space explorati...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/66
Inventor 赵志军赵京东王爽刘宏
Owner HARBIN INST OF TECH