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Electromagnetic damping device for spacecraft recovery

A technology of electromagnetic damping and electromagnetic damper, which is applied to the landing device of aerospace vehicles, the system, transportation and packaging of aerospace vehicles returning to the earth's atmosphere, etc., and can solve the problems of occupying spacecraft load resources, heavy weight, and large diameter of the umbrella surface, etc. problems, to achieve the effect of making full use of the ground space and large damping force

Active Publication Date: 2021-11-19
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the most commonly used spacecraft recovery device is a parachute landing system, but it has the disadvantages of large diameter of the umbrella surface, heavy weight, etc., and the problem of occupying the load resources of the spacecraft

Method used

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  • Electromagnetic damping device for spacecraft recovery
  • Electromagnetic damping device for spacecraft recovery
  • Electromagnetic damping device for spacecraft recovery

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specific Embodiment approach 1

[0017] Specific implementation mode one: refer to Figure 1 to Figure 5 Specifically illustrate this embodiment, the spacecraft recovery electromagnetic damping device described in this embodiment, the device includes a plurality of support frames 1, a recovery net 2 and an electromagnetic damping device 3,

[0018] Each support frame 1 is connected with a net angle of the recovery net 2 through an electromagnetic damping device 3, and the recovery net 2 is propped up,

[0019] The electromagnetic damping device 3 includes a mounting plate 3-1, an electromagnetic damper 3-3, a rotating shaft 3-2, a steel cable 3-4, a cable support 3-5 and a cable winding motor 3-6, and an electromagnetic damper 3-3 Including a stator and a rotor, the stator is a plurality of permanent disks 3-3-2, the rotor is a plurality of conductor disks 3-3-1, the permanent disks 3-3-2 and the conductor disks 3-3-1 are alternately arranged to form a multi-layer disk formula structure,

[0020] The rotor ...

specific Embodiment approach 2

[0025] Specific embodiment 2: This embodiment is to further illustrate the spacecraft recovery electromagnetic damping device described in specific embodiment 1. In this embodiment, the permanent magnetic disk 3-3-2 includes a yoke plate 6 and a fan-shaped permanent magnet 5.

[0026] Conductor plates 3-3-1 and yoke plates 6 are alternately arranged, and the two outer sides of the electromagnetic damper 3-3 are yoke plates 6, and the inner sides of the two outer yoke plates 6 are circumferentially arranged with fan-shaped permanent magnets 5, which are located on the two conductor plates. Sector-shaped permanent magnets 5 are arranged on both sides of the yoke plate 6 between 3-3-1 in the circumferential direction, and the sector-shaped permanent magnets 5 are alternately arranged in N-S poles at equal intervals along the circumferential direction.

[0027] In this embodiment, if Figure 5 As shown, the conductor disks 3-3-1 and the yoke plates 6 are alternately arranged. When...

specific Embodiment approach 3

[0028] Specific embodiment three: This embodiment is to further illustrate the spacecraft recovery electromagnetic damping device described in specific embodiment one. In this embodiment, the permanent magnetic disk 3-3-2 includes a yoke plate 6 and a fan-shaped permanent magnet 5.

[0029] The conductor disks 3-3-1 and the yoke plates 6 are alternately arranged, and the two outer sides of the electromagnetic damper 3-3 are conductor disks 3-3-1, and the sector-shaped permanent magnets 5 are circumferentially arranged on both sides of the yoke plate 6, and the sector-shaped permanent magnets The magnets 5 are alternately arranged with N-S poles equidistant along the circumferential direction.

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Abstract

An electromagnetic damping device for spacecraft recovery relates to the field of spacecraft recovery. The purpose of the present invention is to solve the problem that the parachute landing system, which is widely used in the existing spacecraft recovery device, has the disadvantages of large diameter and heavy weight of the umbrella surface, and the problem of occupying the load resources of the spacecraft. The stator is a plurality of permanent disks, and the rotor is a plurality of conductor disks. The permanent disks and conductor disks are alternately arranged to form a multi-layer disk structure. The electromagnetic damper, the rotor of the cable winding motor and the cable support are all passed through and coaxially fixed on the On the rotating shaft, the steel cable is wound on the cable support, and the installation plate is fixed on the top side wall of the support frame. The multiple permanent disks of the electromagnetic damper and the stator of the cable winding motor are all fixed on the installation plate. The mesh angle of the recovery net Connect the head end of the cable. It is used to recover spacecraft.

Description

technical field [0001] The invention relates to an electromagnetic damping device for recovering spacecraft, belonging to the field of spacecraft recovery. Background technique [0002] Spacecraft recovery technology is a technology for a spacecraft to break away from its original orbit and enter the earth's atmosphere and land safely on the ground. Recovering a spacecraft belongs to the final phase of the spacecraft return process, the landing phase. After the spacecraft is decelerated by a special deceleration device, it is called a soft landing at a certain speed. Without special deceleration, it is called a hard landing. The recovery device is an important means to achieve a soft landing. The reliable performance of the spacecraft recovery device It plays an important role in the safe landing of spacecraft. [0003] The recovery of the spacecraft can choose land landing or sea splashing, and there are land recovery systems and sea recovery systems accordingly. At pres...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G5/00B64G1/62
CPCB64G1/62B64G5/00
Inventor 张赫寇宝泉王梦瑶牛旭陈雯
Owner HARBIN INST OF TECH
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