CN111572823A - A cohesion device for satellite cabin is arrested - Google Patents
A cohesion device for satellite cabin is arrested Download PDFInfo
- Publication number
- CN111572823A CN111572823A CN202010482301.8A CN202010482301A CN111572823A CN 111572823 A CN111572823 A CN 111572823A CN 202010482301 A CN202010482301 A CN 202010482301A CN 111572823 A CN111572823 A CN 111572823A
- Authority
- CN
- China
- Prior art keywords
- seat
- sliding
- flange
- finger
- pressing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000003825 pressing Methods 0.000 claims abstract description 79
- 238000000034 method Methods 0.000 claims abstract description 10
- 230000008569 process Effects 0.000 claims abstract description 9
- 230000007246 mechanism Effects 0.000 claims description 28
- 230000000630 rising effect Effects 0.000 claims description 6
- 238000004146 energy storage Methods 0.000 claims description 5
- 230000003139 buffering effect Effects 0.000 claims description 4
- 238000013016 damping Methods 0.000 claims description 4
- 239000002775 capsule Substances 0.000 claims 1
- 230000009471 action Effects 0.000 abstract description 9
- 238000003032 molecular docking Methods 0.000 description 6
- 238000009434 installation Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 238000000926 separation method Methods 0.000 description 4
- 230000001174 ascending effect Effects 0.000 description 3
- 210000001503 joint Anatomy 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 241000251468 Actinopterygii Species 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000005674 electromagnetic induction Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Seats For Vehicles (AREA)
Abstract
The invention discloses a cohesion device for capturing a satellite cabin, which comprises a slide rail and a slide seat arranged above the slide rail in a sliding fit manner; a positioning table matched with the bottom surface of the flange is arranged in the middle of the sliding seat, an anti-bouncing pin which stretches along the length direction of the sliding rail is arranged above the end surface matched with the bottom surface of the flange on the positioning table, and the upper end surface of the positioning table and the anti-bouncing pin are combined to form a limiting space; the sliding seat is provided with a pressing component, and the pressing component axially acts on the flange along the flange in the working process to realize that the flange enters a limiting space; a locking assembly for locking the flange entering the limiting space is arranged on the sliding seat; the pressing component and the locking component are driven by a power component in sliding fit with the sliding rail to complete pressing and locking of the flange; the flange is pressed to the limiting space through the pressing assembly to be locked initially, then the locking assembly is used for locking, and the pressing and locking actions are realized through the matching of the lead screw and the nut.
Description
Technical Field
The invention relates to the technical field of space satellite capture, in particular to a cohesion device for capturing a satellite cabin.
Background
In-orbit service tasks such as in-orbit maintenance and repair, in-orbit filling, in-orbit function expansion, software upgrading and the like increasingly become important tasks for satellite development in China. The space docking mechanism is used for realizing multiple connection, connection keeping and separation between two spacecrafts. The docking mechanism is divided into a central layout type and a peripheral layout type according to the layout form. The peripheral layout type reserves a transfer channel in the center, has a universal interface, and is a common butt joint interface on a manned spacecraft. Li Yongzhen et al proposed a single diameter adaptive WeChat docking device based on cam curves and linkage mechanisms. The 'fish spear' is successfully launched by the 'fragment clearing' project of the European space Bureau, and the target satellite is hit and dragged to a launching platform. Xunfu et al propose a coordination planning and control method for space robot to capture target. The peripheral layout type docking mechanism designed at present only aims at a target satellite with a single diameter, and is poor in universality.
The invention provides a repeated locking and unlocking mechanism applied to a master-slave non-contact double-super satellite platform, which is disclosed by China, wherein the notice number is CN 106184828B, and the notice date is 2018.08.03; wherein, the first mounting body is provided with an electromagnetic locking mechanism and an electrically driven bolt; the second mounting body is provided with another magnetic locking mechanism and an emergency unlocking mechanism; the first mounting body and the second mounting body are mutually adsorbed and locked after being electrified and unlocked after being powered off through an electromagnetic locking mechanism and another magnetic locking mechanism; the emergency unlocking mechanism is provided with a butt nut matched with the electric drive bolt; after the first installation body and the second installation body are locked through an electromagnetic locking mechanism and another magnetic locking mechanism, the electric drive bolt is screwed out to be connected with the butt joint nut. The electromagnetic locking mechanism can realize multiple locking and separating functions through the on-off of the electromagnetic induction coil. The technical scheme adopts an electromagnetic locking framework to realize the locking and the separation of the satellite platform, but the technical scheme of the invention is not involved.
The invention discloses a Chinese invention discloses an open type locking and separating device for a pico-satellite, wherein the notice number is CN 107697321B, and the notice date is 2019.07.16, the invention discloses the open type locking and separating device for the pico-satellite, which comprises a separating bottom plate, a locking and separating module and a pushing module, wherein the locking and separating module comprises: the two sliding parts are symmetrically arranged and are arranged on two sides of the separation bottom plate in a sliding manner; two cutting units respectively mounted on the corresponding sliders; the two elastic units are respectively used for connecting the corresponding sliding parts with the separation bottom plate, the sliding parts deform to provide unlocking driving force when located at the locking position, and the two sliding parts slide to the unlocking positions far away from each other after the driving force is released; the two groups of locking pieces are respectively arranged on the corresponding sliding pieces and tightly press the satellite on the pushing module when the sliding pieces are positioned at the locking positions; the locking rope is wound on the cutting surfaces of the two cutting units at the same time and enables the two sliding parts to slide to locking positions close to each other; the invention has simple structure, convenient installation, stable work and low development cost. The above technical solutions do not relate to the technical solution described in the present invention.
Disclosure of Invention
The invention aims to solve the problems and adopts the technical scheme that:
a cohesion device for capturing a satellite cabin is used for cohesion of a flange on the satellite cabin to achieve capturing and fastening of the satellite cabin and comprises a sliding rail and a sliding seat which is arranged above the sliding rail in a sliding fit mode; a positioning table matched with the bottom surface of the flange is arranged in the middle of the sliding seat, an anti-jumping pin which stretches and retracts along the length direction of the sliding rail is arranged above the end surface matched with the bottom surface of the flange on the positioning table, and the upper end surface of the positioning table and the anti-jumping pin are combined to form a limiting space; a lower pressing assembly is mounted on the sliding seat, and in the working process, the lower pressing assembly axially acts on the flange along the flange to realize that the flange enters a limiting space; a locking assembly for locking the flange entering the limiting space is arranged on the sliding seat; the pressing component and the locking component are driven by the power component in sliding fit with the sliding rail to complete pressing and locking of the flange.
Furthermore, the sliding seat is also provided with dampers used for buffering the flanges and positioned on two sides of the positioning table, and the upper end faces of the dampers are higher than the positioning table in the non-working process.
Furthermore, a pressure spring is arranged between the anti-jumping pin and the positioning table along the length direction of the slide rail, and an inclined surface is arranged on one side of the anti-jumping pin, which is back to the upper end surface of the positioning table.
Further, power component includes the lead screw of being connected with the motor output and first nut, the second nut of normal running fit installation on the lead screw, first nut and second nut are located the both ends of slide below respectively, and first nut is installed on the first nut seat with slide rail sliding fit, and the second nut is installed on the second nut seat with slide rail sliding fit, first nut seat is used for acting on and pushes down the subassembly and realize pushing down the flange, and the second nut seat is used for acting on the locking subassembly and realizes the locking to the flange.
Furthermore, an upright post is arranged on the upper end surface of the sliding seat between the positioning table and the second nut seat; the downward pressing component comprises a rotary seat, a first tension spring is arranged between the upper end of the rotary seat and the upright column, the lower end of the rotary seat is hinged with the positioning table, a cam plate is connected on the sliding seat in a sliding manner, the cam plate acts on the lower end of the rotary seat through a driving mechanism to realize the rotation of the rotary seat, one side of the cam plate, which faces away from the rotary seat, is in contact fit with the first nut seat, a downward pressing finger is arranged at the upper end of the rotary seat, extends out of the rotary seat towards one side of the anti-jumping pin and slides along the axial direction of the flange relative to the sliding seat, a return spring is arranged between the downward pressing finger and the rotary seat along the sliding direction of the downward pressing finger, a pull rope is arranged on the downward pressing finger, the other end of the pull rope penetrates through the bottom end of the rotary seat, passes through a plurality of rope wheels arranged on the sliding seat and slides through the, and a rope seat limiting block is arranged on the sliding seat at one side of the cam plate of the rope seat.
Further, actuating mechanism includes the notch cuttype terminal surface that sets up on the cam plate, the notch cuttype terminal surface includes horizontal terminal surface down and horizontal terminal surface on, connect through connecting the inclined plane between horizontal terminal surface down and the horizontal terminal surface on, the gyration seat lower extreme is equipped with changes positive terminal surface and slope terminal surface, and in operation, slope terminal surface and horizontal terminal surface contact cooperation down, through connecting the inclined plane effect and changeing positive terminal surface for the gyration seat carries out rotary motion, and the terminal surface of going up this moment and changeing positive terminal surface contact cooperation.
Furthermore, a pressing part is further arranged on the pressing finger along the movement direction of the pressing finger, and a damping spring is arranged between the pressing part and the pressing finger.
Furthermore, the locking assembly comprises an inner supporting part and an outer buckling part matched with the inner supporting part to realize locking, a mounting groove used for mounting the inner supporting part and the outer buckling part is reserved on the positioning table, the inner supporting part comprises an inner supporting finger, the middle part of the inner supporting finger is hinged with the positioning table, a second tension spring is mounted between the upper end of the inner supporting finger and the positioning table, and the lower end of the inner supporting finger is hinged with a roller; the outer buckling part comprises an outer buckling finger and a reversing tooth, one end of the outer buckling finger and one end of the reversing tooth are respectively hinged with two ends of the connecting rod, the middle part of the outer buckling finger is hinged with the positioning table, the middle part of the reversing tooth is hinged with the upright post, and the other end of the reversing tooth is provided with a sector tooth for reversing; the sliding rack is characterized in that a rack seat is arranged between the end portion of the stand column and the end portion of the sliding seat in a sliding mode, linear teeth matched with the fan-shaped teeth are arranged at the upper end of the rack seat, an energy storage spring is arranged between the rack seat and the sliding seat along the length direction of the sliding rail, a jacking column matched with the roller in a contact mode is arranged on the rack seat in a sliding mode, and the second nut seat is in contact fit with the rack seat and faces away from one end of the stand column.
Furthermore, a buffer spring is arranged between the top column and the rack seat along the length direction of the sliding rail.
Furthermore, the slide seat is positioned with the slide rail through a positioning component after moving in place; the locating component comprises a stepped locating block arranged on two sides of the sliding rail, a locating pin matched with the stepped locating block is vertically arranged at the lower end of the sliding seat, a pressure spring is axially arranged between the locating pin and the sliding seat along the locating pin, a rising hole is formed in the locating pin along the length direction of the sliding rail, a first nut seat is provided with an oblique push plate matched with the rising hole and arranged on one side of the locating pin, and after work is finished, the oblique push plate acts on the rising hole to realize that the locating pin rises and is separated from the stepped locating block.
The invention has the following beneficial effects:
1. the invention relates to a cohesion device for capturing a satellite cabin, which realizes cohesion of a flange on the satellite cabin by arranging a pressing component and a locking component.
2. The positioning assembly is arranged, so that the positioning can be carried out on the flanges with different diameters on the satellite cabin, then the pressing and locking actions are carried out, and finally the cohesion of the satellite cabin in a catching mode is completed.
Drawings
FIG. 1 is a schematic structural view of the present invention:
FIG. 2 is a top view of the present invention:
FIG. 3 is a cross-sectional view taken along line 2A-A:
FIG. 4 is a cross-sectional view taken along lines E-E of FIG. 2:
FIG. 5 is a perspective view of a portion of the assembly of the present invention:
fig. 6 is a top view of fig. 5:
FIG. 7 is a sectional view taken along line B-B in FIG. 6:
FIG. 8 is a cross-sectional view taken along line C-C of FIG. 6:
FIG. 9 is a schematic view of the present invention in use.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1-9, a cohesion device for capturing a satellite cabin is used for cohesion of a flange 10 on the satellite cabin to capture and fasten the satellite cabin, and comprises a slide rail 2 and a slide seat 1 which is arranged above the slide rail 2 in a sliding fit manner; a positioning table 5 matched with the bottom surface of the flange 10 is arranged in the middle of the sliding seat 1, an anti-bouncing pin 6 which stretches along the length direction of the sliding rail 2 is installed above the end surface matched with the bottom surface of the flange 10 on the positioning table 5, the upper end surface of the positioning table 5 and the anti-bouncing pin 6 are combined to form a limiting space, and the flange 10 is preliminarily locked through the limiting space; a lower pressing component 7 is mounted on the sliding seat 1, and in the working process, the lower pressing component 7 axially acts on the flange 10 along the flange 10 to realize that the flange 10 enters a limiting space and preliminarily locks the flange 10 through the limiting space; the locking assembly 8 for locking the flange 10 entering the limiting space is mounted on the sliding seat 1, and the locking assembly 8 embraces the preliminarily locked flange 10, so that the satellite cabin is caught and fastened subsequently; the pressing component 7 and the locking component 8 are driven by the power component 3 in sliding fit with the sliding rail 2 to complete pressing and locking of the flange 10.
As shown in fig. 1-9, in order to buffer the impact of the satellite flange 10 in motion on the embracing device, dampers 4 for buffering the flange 10 are further installed on the sliding base 1 at two sides of the positioning table 5, and during non-working, the upper end face of each damper 4 is higher than the positioning table 5. After the flange 10 of satellite contacts the upper end face of the damper 4, energy is stored through the deformation of the damper 4, so that the moving speed of the flange 10 is buffered, and the satellite flange 10 is conveniently held by a holding device.
As shown in fig. 1 to 9, in order to realize holding the flange 10 tightly, the flange 10 needs to be initially limited, in this embodiment, a limiting space is formed by combining the upper end surface of the positioning table 5 and the anti-jump pin 6, so as to complete the initial limiting of the flange 10, a pressure spring 91 is installed between the anti-jump pin 6 and the positioning table 5 along the length direction of the slide rail 2, one side of the anti-jump pin 6, which is opposite to the upper end surface of the positioning table 5, is set as an inclined surface, in operation, the flange 10 moves along the axial direction thereof, the flange 10 contacts and extrudes the inclined surface on the anti-jump pin 6, so that the anti-jump pin 6 compresses the pressure spring 91 along the length direction of the slide rail 2 to shrink, when the flange 10 enters the limiting space, the anti-jump pin 6 stretches out along the length direction of the slide rail 2 under the action of the pressure spring 91 to be rapidly reset, at this time, the anti-jump pin 6 limits, therefore, the flange 10 is initially limited, and when the position of the sliding seat 1 is not changed, the target satellite cannot be separated from the butt joint mechanism.
As shown in fig. 1-9, in order to accomplish the pressing and locking actions on the flange 10, a power mechanism is required to drive the pressing assembly 7 and the locking assembly 8 to accomplish the pressing and locking actions, the power assembly 3 includes a lead screw 31, and a first nut 33 and a second nut 34 which are installed on the lead screw 31 in a rotating fit manner, the first nut 33 and the second nut 34 are respectively located at two end portions below the sliding base 1, the first nut 33 is installed on a first nut seat 32 which is in sliding fit with the sliding rail 2, the second nut 34 is installed on a second nut seat 35 which is in sliding fit with the sliding rail 2, the first nut seat 32 is used for acting on the pressing assembly 7 to press the flange 10, the second nut seat 35 is used for acting on the locking assembly 8 to lock the flange 10, in this embodiment, a power input end of the lead screw 31 is connected to a motor through a coupler, the lead screw 31 is driven to rotate by the, the screw 31 cooperates with the first nut 33 and the second nut 34 to drive the first nut seat 32 and the second nut seat 35 to move axially along the screw 31, so as to drive the pressing assembly 7 and the locking assembly 8 to complete pressing and locking of the flange 10.
As shown in fig. 1 to 9, in order to press down the flange 10, in the present embodiment, an upright 11 is disposed on the upper end surface of the sliding base 1 between the positioning table 5 and the second nut seat 35; the pressing assembly 7 comprises a rotary seat 71, a first tension spring 78 is arranged between the upper end of the rotary seat 71 and the upright post 11, the lower end of the rotary seat 71 is hinged to the positioning table 5, a cam plate 77 is connected to the sliding seat 1 in a sliding manner, the cam plate 77 acts on the lower end of the rotary seat 71 through a driving mechanism to realize the rotation of the rotary seat 71, one side of the cam plate 77, which is opposite to the rotary seat 71, is in contact fit with the first nut seat 32, the cam plate 77 is pushed to slide on the sliding seat 1 through the first nut seat 32, and the driving mechanism on the cam plate 77 acts on the lower end of the rotary seat 71 to realize the rotation of the rotary seat 71; a lower pressing finger 72 is mounted at the upper end of the rotary seat 71, the lower pressing finger 72 extends out of the rotary seat 71 towards one side of the anti-tripping pin 6 and slides axially along the flange 10 relative to the sliding seat 1, a return spring 73 is mounted between the lower pressing finger 72 and the rotary seat 71 along the sliding direction of the lower pressing finger 72, and a pull rope 74 is mounted on the lower pressing finger 72, preferably, in the embodiment, the pull rope 74 is a steel wire rope; the other end of the pulling rope 74 penetrates through the bottom end of the rotary seat 71, passes through a plurality of rope pulleys arranged on the sliding seat 1, slides through a cam plate 77 and is installed on a rope seat 75, the rope seat 75 is positioned between the cam plate 77 and the positioning table 5 and is connected with the sliding seat 1 in a sliding fit manner, and a rope seat limiting block 76 is installed on the sliding seat 1, is positioned on one side of the cam plate 77 of the rope seat 75; in the work, the first nut seat 32 pushes the cam plate 77 to slide on the sliding seat 1, the cam plate 77 acts on the lower end of the rotary seat 71 through the driving mechanism to realize that the rotary seat 71 rotates, when the rotary seat 71 rotates in place, the cam plate 77 slides on the pull rope 74 and acts on the rope seat 75 to move towards one side close to the positioning table 5, and the rope seat 75 pulls the pull rope 74 to realize that the pull rope 74 drives the pressing finger 72 to move axially along the flange 10 and complete the pressing work of the flange 10.
As shown in fig. 1 to 9, in order to complete the rotation of the rotary seat 71, ensure that the pressing finger 72 moves axially along the flange 10 and completes the pressing of the flange 10, the driving mechanism includes a stepped end surface provided on the cam plate 77, the stepped end surface includes a lower horizontal end surface 773 and an upper horizontal end surface 771, the lower horizontal end surface 773 and the upper horizontal end surface 771 are connected by a connecting inclined surface 772, and the lower end of the rotary seat 71 is provided with a correcting end surface 712 and an inclined end surface 711; the rotary seat 71 is in an inclined state when in a non-working state, the inclined end face 711 is in contact fit with the lower horizontal end face 773, and the rotary seat 71 is arranged in such a way, so that a holding device is not required to be accurately matched with the flange 10, the pressing finger 72 can be ensured to be in contact with the flange 10 in a large range, and the flange 10 is pressed; when the rotation of the rotary base 71 is to be realized, the inclined end face 711 is firstly in contact fit with the lower horizontal end face 773, the rotating end face 712 is acted by the connecting inclined face 772, so that the rotary base 71 performs the rotation motion, and the rotation of the rotary base 71 is completed when the upper horizontal end face 771 is in contact fit with the rotating end face 712.
As shown in fig. 1 to 9, in order to realize flexible pressing of the pressing finger 72 on the flange 10 and avoid rigid contact, in this embodiment, a pressing portion 721 is further installed on the pressing finger 72 along the moving direction of the pressing finger 72, and a damping spring 722 is installed between the pressing portion 721 and the pressing finger 72, so that the damping spring 722 can play a certain buffering role in the pressing process when the pressing portion 721 is in contact with the flange 10, and avoid rigid contact, thereby realizing flexible pressing of the pressing finger 72 on the flange 10.
As shown in fig. 1 to 9, in order to realize locking of the flange 10 entering the limiting space, the locking assembly 8 includes an inner supporting portion and an outer fastening portion matching with the inner supporting portion to realize locking, and a mounting groove for mounting the inner supporting portion and the outer fastening portion is reserved on the positioning table 5; the inner supporting part comprises an inner supporting finger 82, the middle part of the inner supporting finger 82 is hinged with the positioning table 5, a second tension spring 81 is arranged between the upper end of the inner supporting finger 82 and the positioning table 5, and the lower end of the inner supporting finger 82 is hinged with a roller 821; the outer buckling part comprises an outer buckling finger 84 and a reversing tooth 85, one end of the outer buckling finger 84 and one end of the reversing tooth 85 are respectively hinged with two ends of a connecting rod 83, the middle part of the outer buckling finger 84 is hinged with the positioning table 5, the middle part of the reversing tooth 85 is hinged with the upright post 11, and the other end of the reversing tooth 85 is provided with a sector tooth 851 for reversing; a rack seat 86 is slidably mounted on the sliding seat 1 between the upright post 11 and the end of the sliding seat 1, linear teeth 861 matched with the fan-shaped teeth 851 are arranged at the upper end of the rack seat 86, an energy storage spring 862 is mounted between the rack seat 86 and the sliding seat 1 along the length direction of the sliding rail 2, a top column 87 in contact and matching with the roller 821 is slidably mounted on the rack seat 86, and preferably, a buffer spring 871 is mounted between the top column 87 and the rack seat 86 along the length direction of the sliding rail 2; the second nut seat 35 contacts one end of the matching rack seat 86 back to the upright post 11; in this embodiment, the rack seat 86 is pushed by the second nut seat 35 to move to one side of the positioning table 5, the roller 821 is acted on the jack 87 on the rack seat 86 to enable the inner supporting finger 82 to rotate around the hinge joint, the upper end of the inner supporting finger 82 protrudes out of the upper end face of the positioning table 5 to act on the lower end face of the flange 10, meanwhile, the rack seat 86 moves to one side of the positioning table 5 to drive the reversing tooth 85 to rotate around the hinge joint through the matching of the linear tooth 861 and the fan-shaped tooth 851, the reversing tooth 85 drives the outer buckling finger 84 to rotate around the hinge joint through the connecting rod 83 to act on the upper end face of the flange 10, the inner supporting finger 82 and the outer buckling finger 84 cooperate to lock the flange 10, and the energy storage spring 862 between the rack seat 86 and the sliding base 1 compresses and stores energy in the locking process.
As shown in fig. 1 to 9, in order to lock flanges 10 with different diameters, positioning assemblies 9 need to be arranged on a mounting frame according to the diameters of the flanges 10, and after a sliding seat 1 moves to a position corresponding to the diameter of the flange 10, the sliding seat 1 is positioned with a sliding rail 2 through the positioning assemblies 9; locating component 9 is including installing the notch cuttype locating piece 92 in 2 both sides of slide rail, 1 lower extreme of slide is vertical install with notch cuttype locating piece 92 complex locating pin 93, install pressure spring 91 along locating pin 93 axial between locating pin 93 and the slide 1, 2 length direction on the slide rail of edge on the locating pin 93 is equipped with ascending hole 94, first nut seat 32 towards locating pin 93 one side be equipped with ascending hole 94 complex oblique push pedal 321, after the work finishes, oblique push pedal 321 effect ascending hole 94 realizes that locating pin 93 rises and separates with notch cuttype locating piece 92.
The working process of the invention is as follows:
the docking mechanism acquires the information of the captured satellite and confirms the size of a satellite and rocket flange 10 of the target satellite; when the satellite-rocket flange 10 is confirmed to be 35mm away from the rigid supporting surface of the positioning table 5 of the sliding seat 1, the motor rotates positively to drive the lead screw 31 to rotate, the lead screw 31 is matched with the first nut 33 and the second nut 34 to drive the first nut seat 32 and the second nut seat 35 to move axially along the lead screw 31, the components on the sliding seat 1 and the sliding seat 1 move towards the center of the aircraft under the driving of the first nut seat 32 and the second nut seat 35, the components move to the corresponding step-shaped positioning block 92 to stop moving, and the step groove on the step-shaped positioning block 92 is matched with the positioning pin 93 to limit the sliding seat 1 to move towards one end away from the center of the aircraft.
The motor is controlled to rotate reversely to drive the screw rod 31 to rotate, under the drive of the screw rod 31, the first nut 33 and the second nut 34 are matched to drive the first nut seat 32 and the second nut seat 35 to move towards one end far away from the center of the aircraft, the first nut seat 32 pushes the cam plate 77 to slide on the sliding seat 1, the cam plate 77 acts on the lower end of the rotary seat 71 through the drive mechanism, firstly, the inclined end face 711 is in contact fit with the lower horizontal end face 773, the rotary end face 712 is acted through the connecting inclined face 772, the rotary seat 71 rotates around the hinged position of the rotary seat to the center of the aircraft, and when the upper horizontal end face 771 is in contact fit with the rotary end face 712, the rotary seat 71 is rotated; after the rotary seat 71 rotates to a certain position, the first nut seat 32 and the second nut seat 35 continue to move towards one end far away from the center of the aircraft, the first nut seat 32 continues to push the cam plate 77 to slide on the sliding seat 1, the cam plate 77 slides on the pull rope 74 and starts to contact and push the rope seat 75 to move towards one side close to the positioning table 5, the rope seat 75 pulls the pull rope 74, the other end of the pull rope 74 drives the downward pressing finger 72 to move axially along the flange 10, the downward pressing part 721 installed on the downward pressing finger 72 contacts the end surface of the flange 10, the downward pressing flange 10 is pulled to the upper end surface of the positioning table 5 of the sliding seat 1, when the flange 10 contacts with the anti-jump pin 6 installed on the positioning table 5, the flange 10 contacts and presses the inclined surface on the anti-jump pin 6, so that the anti-jump pin 6 compresses the compression spring 91 along the length direction of the sliding rail 2 to contract and enters the installation surface, the flange 10 continues to press down through the position of the anti-jump pin, at the moment, the anti-jumping pin 6 limits the upper end of the flange 10, the flange 10 is limited in a limiting space formed by the anti-jumping pin 6 and the positioning table 5, so that preliminary limiting of the flange 10 is realized, when the position of the sliding seat 1 is not changed, the target satellite cannot be separated from the docking mechanism, and the pressing finger 72 continues to move along the axial direction of the flange 10 at the moment and completes pressing work on the flange 10.
After the downward pressing is completed, the motor is controlled to rotate forward to drive the screw rod 31 to rotate, under the drive of the screw rod 31, the first nut 33 and the second nut 34 are matched to drive the first nut seat 32 and the second nut seat 35 to move towards one end of the center of the aircraft, the sliding seat 1 cannot move towards one end of the center of the aircraft due to the limiting of the flange 10, the downward pressing finger 72 is reset under the action of the reset spring 73, the downward pressing finger 72 pulls the rope seat 75 to move towards one side far away from the positioning table 5 through the pull rope 74 until the downward pressing finger 72 and the rope seat 75 stop moving after being limited by the rope seat limiting block 76; meanwhile, the rope seat 75 pushes the cam plate 77 to move to the side far away from the positioning table 5 for resetting, when the driving mechanism on the cam plate 77 contacts the lower end of the rotary seat 71 again, along with the movement of the cam plate 77 to the side far away from the positioning table 5, the upper horizontal end face 771 is separated from the turning end face 712, then the connecting inclined face 772 contacts the turning end face 712, the rotary seat 71 gradually rotates under the action of the first tension spring 78, finally the inclined end face 711 is in contact fit with the lower horizontal end face 773, and the rotary seat 71 rotates in place to complete resetting.
When the first nut seat 32 and the second nut seat 35 move to the initial positions, the first nut seat 32 and the second nut seat 35 continue to move towards one end of the center of the aircraft, the second nut seat 35 pushes the rack seat 86 to move towards one side of the positioning table 5, the support pillar 87 on the rack seat 86 acts on the roller 821 to enable the inner supporting finger 82 to rotate around the hinged part, the upper end of the inner supporting finger 82 protrudes out of the upper end face of the positioning table 5 to act on the lower end face of the flange 10, meanwhile, the rack seat 86 moves towards one side of the positioning table 5 and drives the reversing teeth 85 to rotate around the hinged part through the matching of the linear teeth 861 and the sector teeth 851 through the connecting rod 83, the reversing teeth 85 drive the outer buckling finger 84 to rotate around the hinged part to act on the upper end face of the flange 10 through the connecting rod 83, the inner supporting finger 82 and the outer buckling finger 84 cooperate to lock the flange 10, and the energy storage spring 862 between the rack seat 86 and the sliding seat 1 is compressed, at this time, rigid capture and locking of the satellite and rocket flange 10 of the target satellite are completed.
When the target satellite is released, the actions are reversed.
The invention relates to a cohesion device for capturing a satellite cabin, which is provided with a pressing component 7 and a locking component 8 to realize cohesion of a flange 10 on the satellite cabin, the device presses the flange 10 to a limiting space through the pressing component 7 to be primarily locked, then is locked through the locking component 8, and realizes pressing and locking actions through the matching of a lead screw 31 and a nut.
The present embodiment is not intended to limit the shape, material, structure, etc. of the present invention in any way, and any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention are within the scope of the technical solution of the present invention.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be considered as limiting the scope of the present invention.
If the terms "first," "second," etc. are used herein to define parts, those skilled in the art will recognize that: the use of "first" and "second" is merely for convenience in describing the invention and to simplify the description, and unless otherwise stated the above words are not intended to have a special meaning.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: it is to be understood that modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, but such modifications or substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A cohesion device for capturing a satellite cabin is used for cohesion of a flange on the satellite cabin to achieve capturing and fastening of the satellite cabin and is characterized by comprising a sliding rail and a sliding seat which is arranged above the sliding rail in a sliding fit mode;
a positioning table matched with the bottom surface of the flange is arranged in the middle of the sliding seat, an anti-jumping pin which stretches and retracts along the length direction of the sliding rail is arranged above the end surface matched with the bottom surface of the flange on the positioning table, and the upper end surface of the positioning table and the anti-jumping pin are combined to form a limiting space; a lower pressing assembly is mounted on the sliding seat, and in the working process, the lower pressing assembly axially acts on the flange along the flange to realize that the flange enters a limiting space;
a locking assembly for locking the flange entering the limiting space is arranged on the sliding seat; the pressing component and the locking component are driven by the power component in sliding fit with the sliding rail to complete pressing and locking of the flange.
2. The embracing device for catching the satellite cabin according to claim 1, wherein dampers for buffering flanges are further mounted on the sliding seat at two sides of the positioning table, and the upper end faces of the dampers are higher than the positioning table in a non-working process.
3. The embracing device for catching the satellite cabin according to claim 2, wherein a pressure spring is installed between the anti-bouncing pin and the positioning table along the length direction of the slide rail, and one side of the anti-bouncing pin, which is back to the upper end face of the positioning table, is provided with an inclined surface.
4. The embracing device for capturing the satellite capsule of claim 3, wherein the power assembly comprises a screw connected with the output end of the motor, and a first nut and a second nut which are arranged on the screw in a rotating fit manner, the first nut and the second nut are respectively arranged at two end parts below the sliding seat, the first nut is arranged on a first nut seat in a sliding fit manner with the sliding rail, the second nut is arranged on a second nut seat in a sliding fit manner with the sliding rail, the first nut seat is used for acting on the pressing assembly to press the flange downwards, and the second nut seat is used for acting on the locking assembly to lock the flange.
5. The embracing device for catching the satellite cabin according to claim 4, wherein a stand column is arranged on the upper end face of the sliding seat between the positioning table and the second nut seat; the pressing component comprises a rotary seat, a first tension spring is arranged between the upper end part of the rotary seat and the upright post, the lower end part of the rotary seat is hinged with the positioning table, a cam plate is connected on the sliding seat in a sliding way, the cam plate acts on the lower end of the rotary seat through a driving mechanism to realize the rotation of the rotary seat, one side of the cam plate, which is back to the rotary seat, is in contact fit with the first nut seat,
the utility model discloses a rope seat, including the swing seat, rope seat, slip seat, flange, return finger, stay cord, rope seat, cam plate, relative slide, the swing seat upper end is installed and is pressed down the finger, press down the finger and stretch out the swing seat outside and relative slide along flange endwise slip towards anti-bouncing pin one side, press down and indicate and install the reset spring along pressing down finger slip direction between the finger and the swing seat, press down and install the stay cord on the finger, the stay cord other end is worn out the swing seat bottom and is passed the cam plate through a plurality of rope sheaves that set up on the slide and install on the rope seat, the rope seat is located between cam plate and.
6. The embracing device for capturing the satellite cabin, according to claim 5, wherein the driving mechanism comprises a stepped end surface arranged on the cam plate, the stepped end surface comprises a lower horizontal end surface and an upper horizontal end surface, the lower horizontal end surface and the upper horizontal end surface are connected through a connecting inclined surface, the lower end of the rotary seat is provided with a righting end surface and an inclined end surface, in operation, the inclined end surface is in contact fit with the lower horizontal end surface, the righting end surface is acted through the connecting inclined surface, so that the rotary seat performs rotary motion, and at the moment, the upper horizontal end surface is in contact fit with the righting end surface.
7. The embracing device for catching the satellite cabin according to claim 6, wherein a pressing part is further mounted on the pressing finger along the movement direction of the pressing finger, and a damping spring is mounted between the pressing part and the pressing finger.
8. The embracing device for catching the satellite cabin according to claim 7, wherein the locking assembly comprises an inner supporting portion and an outer buckling portion matched with the inner supporting portion to realize locking, a mounting groove for mounting the inner supporting portion and the outer buckling portion is reserved on the positioning table,
the inner supporting part comprises an inner supporting finger, the middle part of the inner supporting finger is hinged with the positioning table, a second tension spring is arranged between the upper end of the inner supporting finger and the positioning table, and the lower end of the inner supporting finger is hinged with a roller;
the outer buckling part comprises an outer buckling finger and a reversing tooth, one end of the outer buckling finger and one end of the reversing tooth are respectively hinged with two ends of the connecting rod, the middle part of the outer buckling finger is hinged with the positioning table, the middle part of the reversing tooth is hinged with the upright post, and the other end of the reversing tooth is provided with a sector tooth for reversing;
the sliding rack is characterized in that a rack seat is arranged between the end portion of the stand column and the end portion of the sliding seat in a sliding mode, linear teeth matched with the fan-shaped teeth are arranged at the upper end of the rack seat, an energy storage spring is arranged between the rack seat and the sliding seat along the length direction of the sliding rail, a jacking column matched with the roller in a contact mode is arranged on the rack seat in a sliding mode, and the second nut seat is in contact fit with the rack seat and faces away from one end of the stand column.
9. The embracing device for catching the satellite compartment as claimed in claim 8, wherein a buffer spring is installed between the top column and the rack seat along the length direction of the sliding rail.
10. The embracing device for capturing the satellite cabin according to claim 9, wherein the sliding base is positioned with the sliding rail through a positioning assembly after being moved to the proper position; the locating component comprises a stepped locating block arranged on two sides of the sliding rail, a locating pin matched with the stepped locating block is vertically arranged at the lower end of the sliding seat, a pressure spring is axially arranged between the locating pin and the sliding seat along the locating pin, a rising hole is formed in the locating pin along the length direction of the sliding rail, a first nut seat is provided with an oblique push plate matched with the rising hole and arranged on one side of the locating pin, and after work is finished, the oblique push plate acts on the rising hole to realize that the locating pin rises and is separated from the stepped locating block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010482301.8A CN111572823B (en) | 2020-05-29 | 2020-05-29 | A cohesion device for satellite cabin is arrested |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010482301.8A CN111572823B (en) | 2020-05-29 | 2020-05-29 | A cohesion device for satellite cabin is arrested |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111572823A true CN111572823A (en) | 2020-08-25 |
| CN111572823B CN111572823B (en) | 2021-11-02 |
Family
ID=72123689
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010482301.8A Expired - Fee Related CN111572823B (en) | 2020-05-29 | 2020-05-29 | A cohesion device for satellite cabin is arrested |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111572823B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104709473A (en) * | 2014-08-08 | 2015-06-17 | 北京宇航系统工程研究所 | Aerospace craft segment separation device |
| CN106742081A (en) * | 2016-11-29 | 2017-05-31 | 航天东方红卫星有限公司 | A kind of separating mechanism based on rotation pressure ring unblock |
| CN107697321A (en) * | 2017-08-28 | 2018-02-16 | 浙江大学 | A kind of open locking separation device of skin satellite |
| US20190023419A1 (en) * | 2017-07-21 | 2019-01-24 | The Aerospace Corporation | Interlocking, reconfigurable, reconstitutable, reformable cell-based system with nested ring structures |
| CN110901962A (en) * | 2019-12-16 | 2020-03-24 | 中国科学院长春光学精密机械与物理研究所 | Space load locking device |
| CN111099043A (en) * | 2020-01-14 | 2020-05-05 | 中国科学院空间应用工程与技术中心 | Load adapter with guide convex block |
-
2020
- 2020-05-29 CN CN202010482301.8A patent/CN111572823B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104709473A (en) * | 2014-08-08 | 2015-06-17 | 北京宇航系统工程研究所 | Aerospace craft segment separation device |
| CN106742081A (en) * | 2016-11-29 | 2017-05-31 | 航天东方红卫星有限公司 | A kind of separating mechanism based on rotation pressure ring unblock |
| US20190023419A1 (en) * | 2017-07-21 | 2019-01-24 | The Aerospace Corporation | Interlocking, reconfigurable, reconstitutable, reformable cell-based system with nested ring structures |
| CN107697321A (en) * | 2017-08-28 | 2018-02-16 | 浙江大学 | A kind of open locking separation device of skin satellite |
| CN110901962A (en) * | 2019-12-16 | 2020-03-24 | 中国科学院长春光学精密机械与物理研究所 | Space load locking device |
| CN111099043A (en) * | 2020-01-14 | 2020-05-05 | 中国科学院空间应用工程与技术中心 | Load adapter with guide convex block |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111572823B (en) | 2021-11-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN212290394U (en) | Locking mechanism for capturing satellite cabin | |
| CN102248880B (en) | Battery box component for electric automobile | |
| CN109538022B (en) | Intelligent lock capable of automatically locking and unlocking and reversing lock tongue | |
| CN106300528A (en) | The device of the automatic charging of a kind of tunnel crusing robot and tunnel crusing robot | |
| CN112319869B (en) | Large-space-tolerance butt joint device and locking method | |
| CN106150199B (en) | Linkage mechanism and emergency gate manual tripper | |
| CN111572823B (en) | A cohesion device for satellite cabin is arrested | |
| CN2891237Y (en) | Linear reciprocating trigger-type quick-release mechanism in on-load tapping switch | |
| CN111993467A (en) | Intelligent robot removes support | |
| CN2864026Y (en) | Electric glass lifter | |
| CN2635519Y (en) | Device for clamping and lifting airplane wheel | |
| CN201687303U (en) | Locking system of sliding plug door | |
| CN116461738A (en) | Unmanned aerial vehicle arresting cable lifting device | |
| CN113084493B (en) | Automatic pin plugging and unplugging system for assembling buffer | |
| CN113998154B (en) | Satellite repeated locking device | |
| CN116021531A (en) | Sleeper spring inclined wedge assembling manipulator | |
| CN211034104U (en) | Rotary conveying mechanism | |
| CN111231684B (en) | Current collector and charging system of rail vehicle | |
| CN114313321A (en) | Center-expanded large-tolerance low-impact space docking mechanism | |
| CN208263983U (en) | A kind of current collection device and a kind of trolleybus | |
| CN215325165U (en) | Follow-up lifting feeding device | |
| CN214301039U (en) | Elasticity pushes down mechanism suitable for multichannel vertical motion simultaneously | |
| CN214446026U (en) | Pin removing device | |
| CN111231682A (en) | Charging system | |
| CN219312751U (en) | Iron wedge brake |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20211102 |