Locking and unlocking device for satellite docking

A technology for unlocking devices and satellites, applied in docking devices for aerospace vehicles, transportation and packaging, space navigation equipment, etc., can solve vibration excitation, reduce service life, and the docking distance and tolerance of mechanical docking mechanisms cannot be applied to small aerospace device and other issues

Active Publication Date: 2020-10-23
ZHONGBEI UNIV
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Problems solved by technology

Traditional on-orbit docking usually adopts a mechanical docking mechanism, mainly using thrusters to provide docking force. This method is prone to collisions, consumes thruster fuel, reduces service life, and easily produces thruster plume optical pollution and heat emissions. and vibration excitation
The mechanical docking mechanism is not suitable for small spacecraft in terms of docki

Method used

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  • Locking and unlocking device for satellite docking
  • Locking and unlocking device for satellite docking
  • Locking and unlocking device for satellite docking

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Embodiment Construction

[0016] The technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0017] Such as figure 1 As shown, a locking and unlocking device for satellite docking according to the present invention includes four auxiliary electromagnets 1 , a passive system 2 and an active system 3 . The two satellites that need to be docked are the active satellite and the passive satellite. The two auxiliary electromagnets 1 and the active system 3 are fixed on the active satellite, and the two auxiliary electromagnets 1 are symmetrically distributed relative to the axis of the active system 3 . The remaining two auxiliary electromagnets 1 and the passive system 2 are fixed on the passive satellite, and the two auxiliary electromagnets 1 are symmetrically distributed relative to the axis of the passive system 2 . During docking, the auxiliary electromagnet 1 on the active satellite corresponds to the auxiliary electromagnet 1 on...

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Abstract

The invention relates to a locking and unlocking device for satellite docking. The device comprises four auxiliary electromagnets (1), a passive system (2) and an active system (3), wherein the two auxiliary electromagnets and the active system (3) are fixed on the active satellite, the other two auxiliary electromagnets and the passive system (2) are fixed on the passive satellite, the auxiliaryelectromagnets (1) on the active satellite are in one-to-one correspondence with the auxiliary electromagnets of the passive satellite, and the axes of the passive system (2) and the active system (3)coincide; the passive system comprises a locking and unlocking electromagnet (5), a passive system main electromagnet (9), a sliding rail (10), a sliding block (11), a passive system shell (12), a docking sleeve and a passive docking piece (17). The driving system comprises a driving docking piece (18), a fine alignment gear sleeve, a driving system main electromagnet (21) and a driving system shell (22). The docking reliability and the docking precision are improved, and flexible docking and rigid locking are achieved.

Description

technical field [0001] The invention belongs to the technical field of space satellite docking, and in particular relates to a locking and unlocking device for satellite docking. Background technique [0002] Spacecraft docking technology is a prerequisite for on-orbit services such as on-orbit assembly, replenishment, maintenance, and upgrades of modular spacecraft. At the same time, space docking technology is an important means of developing space countermeasure equipment, and it is the core technology that all space powers are competing to develop. Traditional on-orbit docking usually adopts a mechanical docking mechanism, mainly using thrusters to provide docking force. This method is prone to collisions, consumes thruster fuel, reduces service life, and easily produces thruster plume optical pollution and heat emissions. and vibration excitation. The mechanical docking mechanism is not suitable for small spacecraft in terms of docking distance and tolerance; when app...

Claims

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Application Information

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IPC IPC(8): B64G1/64
CPCB64G1/646
Inventor 王菁杨浩王昊东马贺姜金鹏董国玺楼雨涵
Owner ZHONGBEI UNIV
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