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A locking device and square cone technology, which is applied in the docking device of aerospace vehicles, etc., can solve the problems of low reliability, poor maintainability, and low degree of automation, and achieve the effect of reliable rigid locking and ensuring safety
Inactive Publication Date: 2019-05-03
LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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Abstract
Description
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[0003] However, for the exposed load outside the cabin and the exposed platform outside the cabin, the docking and locking interface device in the prior art cannot automatically capture the exposed load outside the cabin, the degree of automation is not high, the operation ability of the astronaut or the mechanical arm is high, and the mechanism is complicated. Poor maintainability and low reliability
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Embodiment 1
[0026] Step 1, fixing the active end 200 to the exposed load, and fixing the passive end 300 on the exposed platform of the aircraft;
[0027] Step 2, the active end 200 and the exposed load assembly are operated by the manipulator or the astronaut, so that the active end 200 and the passive end 300 are docked and captured;
[0028] Step 3, control the motor reducer assembly 21 in the active end 200 to drive the internal mechanism to complete the tightening and fitting of the active end 200 and the passive end 300, insertion of the blind plug electrical connector, rigid locking and anti-loosening.
Embodiment 2
[0030] Step 1, fixing the passive end 300 to the exposed load, and fixing the active end 200 on the exposed platform of the aircraft;
[0031] Step 2, the passive end 300 and the exposed load assembly are operated by the manipulator or the astronaut, so that the active end 200 and the passive end 300 are docked;
[0032] Step 3, control the motor reducer assembly 21 in the active end 200 to drive the internal mechanism to complete the tightening and fitting of the active end 200 and the passive end 300, insertion of the blind plug electrical connector, rigid locking and anti-loosening.
[0033] Among them: the active end 200 includes: micro switch 1, bottom plate 2, tapered guide surface A3, tapered guide surface B4, guide groove 5, rigid locking device 6, frame B9, frame A11, lead screw 14, blind Insert the connector plug 19, the motor reducer assembly 21, and the cover plate 20.
[0034] Wherein: the passive end 300 includes: a frame body 26 , a tapered surface A23 , a tape...
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Abstract
The invention provides a square cone type butt joint locking device, which can realize the guided positioning butt joint, inactive capturing, active tightening-up, plugging of blind plug connector, rigid locking, and manual release of an exposing load and an exposing platform of a spacecraft cabin. The technical support of position supply can be provided to arrange the exposing load outside of thespacecraft cabin. The square cone type butt joint locking device comprises an active end and an inactive end. The active end comprises a microswitch 1, a bottom plate 2, a cone-shaped guiding face A3, a cone-shaped guiding face B4, a rigid locking device 6, a rack B9, a rack A11, a lead screw 14, a blind plug connector 19, a motor decelerator assembly 21, and a cover plate 20. The inactive end comprises a frame body 26, a cone-shaped face A23, a cone-shaped face B24, a blind plug connector socket 27, a capturing locking hole 22, an electric connector rack 29, and an electric connector socket30.
Description
technical field [0001] The invention belongs to the field of space application equipment, and in particular relates to a device suitable for docking and locking interfaces of space loads. Background technique [0002] Space vehicles such as space stations and manned spacecraft have arranged a large number of exposure load test platforms on the outer wall of the cabin to expand the exposure test capabilities of space vehicles. At present, the International Space Station has used various forms of payload docking and locking interface devices to support exposure experiment tasks. [0003] However, for the exposed load outside the cabin and the exposed platform outside the cabin, the docking and locking interface device in the prior art cannot automatically capture the exposed load outside the cabin, the degree of automation is not high, the operation ability of the astronaut or the mechanical arm is high, and the mechanism is complicated. Poor maintainability and low reliabili...
Claims
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Application Information
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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
Inventor 康永李文新马少君张民涛董占敏
Owner LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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