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An ejection-type connection and separation integrated device

A ejection-type and unlocking device technology, which is applied to space vehicle docking devices, transportation and packaging, space navigation equipment, etc., can solve problems such as inability to meet rapid launch, inability to adapt to different configurations of satellites, and satellite size constraints, and achieve improved The effects of space utilization, increased rigidity, and short development cycle

Active Publication Date: 2022-05-31
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem solved by the present invention is: in view of the current existing technology, the traditional satellite-rocket connection and separation device has size constraints on satellites, cannot adapt to different configurations of satellites, and cannot meet the problems of rapid launch, and proposes an ejection-type connection and separation device. Integrated device

Method used

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  • An ejection-type connection and separation integrated device
  • An ejection-type connection and separation integrated device
  • An ejection-type connection and separation integrated device

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Embodiment Construction

[0034] The housing assembly 1 consists of a left skin 1-3, a right skin 1-4, an upper skin 1-5, a lower skin 1-6, a rear end cover 1-7, a door frame

[0037] The door frame 1-8 and the lower skin 1-6 are provided with protrusions, and the front baffle 2-1 of the push plate assembly 2 plays a limiting role,

[0048] As shown in FIG. 1 to FIG. 7, the integrated device for ejection connection and separation consists of a housing assembly 1, a push plate assembly 2, and a telemetry device.

[0055] The present invention has been disclosed as above with specific embodiments, but this embodiment is only used for illustrating the present invention more clearly,

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Abstract

An ejection-type connection and separation integrated device, mainly composed of a housing assembly (1), a push plate assembly (2), a telemetry device (3), and a connection unlocking device (4). In the initial state, the satellite is locked by the connection unlocking device And placed in the shell assembly, when the satellite is in orbit, the unlocking device is connected to unlock, and the push plate assembly used to push the satellite to be ejected from the shell assembly is set in the shell assembly and contacts the satellite. The telemetry device is in the ground control station. Under control, the unlocking signal is sent to the connection and unlocking device, and the separation signal is sent to the push plate assembly, which solves the problem that the traditional satellite-rocket connection and separation device has size constraints on the satellite, cannot adapt to different configurations of satellites, and cannot meet the needs of rapid launch. The structure is stable .

Description

An ejection-type connection and separation integrated device technical field [0001] The present invention relates to an integrated device for ejection-type connection and separation, which belongs to the field of design of star-arrow separation devices. Background technique With the development of space science and technology, domestic and foreign satellite development technology trends are becoming more and more mature, and launch tasks are increasing day by day. In addition, the configuration and size of satellites are also increasingly diversified. In the context of the launch of satellites on launch vehicles, future aerospace The technology has a great impact on the utilization rate of the carrier space, the development cycle of the star-rocket separation device, the less impact on the satellite, and the realization of high-efficiency and reliable separation. The technical requirements for remote and real-time unlocking and separation telemetry are also getting hi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 张哲源江涛康士朋林仁邦任海辽苏新源潘思辰胡励陆江阅
Owner SHANGHAI AEROSPACE SYST ENG INST
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