CN106742062A - Rely on positioning guide rail in the Spacecraft Launch cylinder of guiding piece - Google Patents
Rely on positioning guide rail in the Spacecraft Launch cylinder of guiding piece Download PDFInfo
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- CN106742062A CN106742062A CN201710014727.9A CN201710014727A CN106742062A CN 106742062 A CN106742062 A CN 106742062A CN 201710014727 A CN201710014727 A CN 201710014727A CN 106742062 A CN106742062 A CN 106742062A
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- guide rail
- guiding piece
- spacecraft
- traction
- block
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
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Abstract
The invention discloses positioning guide rail in a kind of Spacecraft Launch cylinder for relying on guiding piece, mainly solve existing Spacecraft Launch cylinder positioning guide rail cause spacecraft to enter a flow is cumbersome, low production efficiency, it is necessary to it is special enter the problem put of wound packages.It includes guiding piece (1), pedestal (2), guide rail (3), two positioning sliding blocks (4) and hauling rope (5).Pedestal is arranged on the inwall of accumulating launching tube, its length direction and accumulating launching tube diameter parallel；Guide rail is arranged on pedestal, and two positioning sliding blocks are separately mounted to tail end and the middle part of spacecraft；Spacecraft is arranged on guide rail by positioning sliding block, and guiding piece is located at the inside of guide rail, and the tail end of guiding piece is connected with hauling rope；Sliding block is dragged by guiding piece to be moved along guide rail, drive spacecraft to be completed into cylinder to movement in launching tube.The present invention has simple structure, easy to use, it is not necessary to the advantage of special equipment, can be used for location and installation of the variety classes spacecraft in launching tube.
Description
Technical field
The invention belongs to field of mechanical technique, more particularly to a kind of positioning guide rail, can be used for spacecraft.
Background technology
For the flow for simplifying production and use, modern a part of spacecraft such as guided missile and rocket etc. are all sent out using accumulating
Shooting cylinder is stored, transported and launched.In order to ensure the reliability for using, spacecraft is sent out by guide rails assembling in accumulating mostly
In shooting cylinder.The guide precision is higher, to ensure stabilization, the reliability of emission process.Yet with guide rail and spacecraft positioning sliding block
Between cooperation it is more tight, tin process of being loaded into of spacecraft needs the larger thrust spacecraft could to be pushed away along positioning guide rail
Deliver to specified location in launching tube.And for some spacecrafts, its main part is using material systems such as fiberglass, aluminium alloys
Into its main body major part position can not bear above-mentioned thrust, therefore in practical operation, the process needs to use complex
Mechanism pushing tow is carried out to the hard point of spacecraft can complete into a process.Therefore, it is improved by correlation technique, is dropped
It is low enter a process difficulty, raising is loaded into the convenient degree of a process, the raising to the spacecraft production efficiency such as guided missile, rocket
Suffer from extremely important meaning.
At present, the spacecraft that studies in China relates to enter an operation to spacecraft enters wound packages and puts, and it is full to a certain extent
Foot spacecraft enters the demand of cylinder.
Authorization Notice No. is CN 204165512U, and the utility model of entitled " accurate columnar member is rotated into a platform " is special
Profit, discloses a kind of accurate columnar member and is rotated into a platform, including leveling underframe, rail brackets, chain-wales, body bracket, cylinder support
Frame, preceding portal frame, back gantry, it is preceding shore, after shore, laser level device, distance detection device, angle detection device.Should
Utility model patent is positioned by front and rear portal frame to cylinder, adjusts columnar member highly by body bracket, the preceding protection shored
Head-shield is protected to columnar member head；The laser level device can real-time detection columnar member outer surface and cylinder inwall away from
From, angle detection device it is detectable before shore exit when, the angle of protection head-shield and columnar member, in order to avoid when head-shield is exited and cylindricality
Part frangible section collides.The utility model patent can meet spacecraft enter cylinder required precision and can be by spacecraft to be assembled
Specified location in launching tube is delivered to, but the equipment mechanism is cumbersome, huge, enters a process whole process and is completed by manpower, using more
Inconvenience.And the equipment does not have expansion, a set of equipment enters cylinder requirement only for a kind of model spacecraft.For longer dimension
Spacecraft for, it is necessary to process the rail brackets and bracket of equal length, which increases the difficulty of device fabrication.
The content of the invention
It is an object of the invention to overcome the shortcomings of existing for foregoing prior art, propose in a kind of Spacecraft Launch cylinder
Positioning guide rail, a flow is entered to simplify spacecraft, improve production efficiency, and improve equipment structure.
Concrete thought of the invention is, improves the positioning guide rail in former accumulating launching tube, and install one thereon can be with
With the guiding piece for treating to be engaged into a spacecraft positioning sliding block, the positioning sliding block of spacecraft afterbody is dragged by the guiding piece, will
In treating reversely to draw in accumulating launching tube from transmitting nozzle into a spacecraft.After spacecraft in place after, free guiding piece and spacecraft
Between cooperation, by guiding piece from accumulating launching tube afterbody pull out, completion be loaded into a process.And the guiding piece can be circulated and made
With improve the versatility and economy of a whole set of production line.
To achieve the above object, the present invention includes pedestal 2, guide rail 3 and two positioning sliding blocks 4, wherein, pedestal 2 is installed
On the inwall of Spacecraft Launch cylinder；Guide rail 3 is installed in parallel on pedestal 2；Two positioning sliding blocks 4 are separately positioned on spacecraft
Tail end and middle part, spacecraft by positioning sliding block 4 be arranged on guide rail 3 on, it is characterised in that also including guiding piece 1；Guide rail
The top surface of body 3 is provided with traction groove 31 along longitudinal direction, and two side is provided with guiding groove 32；Positioning sliding block 4 is located on traction groove 31
Side, bottom both sides are provided with raised 41, and the two positioning convex 41 insert both sides and are oriented in groove 32 respectively, for positioning sliding block
4 are oriented to and are positioned；
The guiding piece 1 is located at the lower section inside traction groove 31, and its tail end is connected with hauling rope 5, and the dragging of hauling rope 5 is led
Draw block 1 to be moved in traction groove 31；The motion of guiding piece 1 drags sliding block 4 in the top of traction groove 31 along the length of guide rail 3 again
Direction is moved, and drives spacecraft to being moved inside launching tube.
Positioning guide rail in the Spacecraft Launch cylinder of above-mentioned support guiding piece, it is characterised in that guiding piece 1 includes traction block
11st, cylinder unblock swing arm 15, cam limit block 16 and hook 17 are gone out, wherein：
The traction block 11, its front end face is provided with into a hook knob 12, and middle part is symmetrically arranged on two with two tractions
Hook 13, lower surface is provided with mechanism grooves 112, and positioning and guiding block 111 is respectively arranged at two ends with from beginning to end；
Two back-moving springs 14, one end of the two back-moving springs are arranged with the mechanism grooves 112 along its length
It is fixed on traction block 11, the other end is connected with the bottom of draw hook 13 respectively；
The upper end of described two draw hooks 13 is inserted both sides and is oriented in groove 32 respectively, for catching on two positioning convex
41；
Cam limit block 16 is located on the central axis of mechanism grooves 112, and the leading portion of cam limit block 16 is respectively against two
The bottom of draw hook 13；
The one end for going out cylinder unblock swing arm 15 is inserted into the tail end of cam limit block 16, and the other end is by screw thread and traction block 11
Connection；
One end of hook 17 is connected by hinge with the afterbody of traction block 11, and the other end is connected with hauling rope 5.
Positioning guide rail in the Spacecraft Launch cylinder of above-mentioned support guiding piece, it is characterised in that the upper end of draw hook 13 is traction
Hook arm 131, lower end is cam 133, and traction hook arm 131 and cam 133 are connected to become an entirety by rotating shaft 132；Draw hook
Arm 131 is located at the upper surface of traction block 11, and cam 133 is located in mechanism grooves 112；
Above-mentioned support guiding piece Spacecraft Launch cylinder in positioning guide rail, it is characterised in that the width of positioning and guiding block 111 with
The width for drawing groove 31 is equal.
Positioning guide rail in the Spacecraft Launch cylinder of above-mentioned support guiding piece, it is characterised in that guiding piece 1 leads in spacecraft
After guiding to position, taken out from the end of guide rail 3, for future use.
The present invention compared with prior art, with advantages below：
The present invention by improving original guide rail, on the premise of equipment performance is not influenceed on guide rail integrated guiding piece
Auxiliary completes spacecraft and enters a process, with existing use bracket and push rod by scheme phase in spacecraft push in cylinder
Than, simplify the structure put into wound packages and enter an operation, so that the arrangement of the arrangement of equipment and production procedure is more flexible, carry
Production efficiency high.
The present invention enters a process by hauling rope pulling guiding piece completion spacecraft, and the process can be used rotary machine, liquid
The mechanically aided completion such as cylinder pressure, compared with existing manpower shake crank promotes the technical scheme that spacecraft enters cylinder, is easy to implement
Automation.
Completed into after a process in spacecraft in the present invention, can taken out guiding piece from guide rail end, be easy to circulation to make
With having saved the use cost of equipment.
Brief description of the drawings
Fig. 1 is overall structure figure of the invention.
Fig. 2 is positioning sliding block in the present invention and guide rail cooperation schematic cross-section.
Fig. 3 is the traction block structural diagram in the present invention.
Fig. 4 is the draw hook schematic diagram in the present invention.
Fig. 5 is workflow schematic diagram of the invention.
Specific embodiment
Below in conjunction with the accompanying drawings, the invention will be further described：
Reference picture 1 and reference picture 2, the present invention include guiding piece 1, pedestal 2,3, two positioning sliding blocks 4 of guide rail and traction
Rope 5.To ensure the accuracy of explanation, cutting treatment is made to outside accumulating launching tube 7 herein, and specify accumulating launching tube 7
Port direction is front portion, and tail end direction is rear portion.Wherein, pedestal 2 is arranged on the inwall of accumulating launching tube 7, its length direction
With the diameter parallel of accumulating launching tube 7, to the fixing guide rail 3 on accumulating launching tube inwall and spacecraft to be assembled 6 is adjusted
Position, makes it coaxial with accumulating launching tube 7.Guide rail 3 is installed on the base 2, and the two is by some groups of bolt connections.Two fixed
Position sliding block 4 is separately mounted to tail end and the middle part of spacecraft 6, and on the same bus in the external cylindrical surface of spacecraft 6, is used for
Spacecraft 6 is positioned.Guiding piece 1 is located at the inside of guide rail 3, and the tail end of guiding piece 1 is connected with hauling rope 5.
The top surface of guide rail 3 is provided with the traction groove 31 of square-section along longitudinal direction, is used to accommodate guiding piece 1 and can be
Slided in traction groove 31；Guiding groove 32, the bottom two of each positioning sliding block 4 are symmetrically provided with traction groove 31 two side
Side is provided with raised 41, and two positioning convex 41 of each positioning sliding block 4 inserts in the guiding groove 32 for drawing groove both sides respectively,
For positioning sliding block 4 to be oriented to and is positioned on guide rail 3；The lower surface of positioning sliding block 4 is provided with recessed before and after sliding block 4
Groove, so that guiding piece 1 is slipped over from the lower section of positioning sliding block 4.When guiding piece 1 catches on positioning convex 41, hauling rope 5 is pulled to make traction
Block 1 is moved in guide rail 3, while the dragging positioning sliding block 4 of guiding piece 1 is moved in guide rail 3, spacecraft 6 is drawn in into accumulating
In launching tube 7.
The structure of the guiding piece 1 is as shown in figure 3, wherein 3 (a) is the surface structure schematic diagram of guiding piece 1, Fig. 3 (b)
It is the lower surface configuration schematic diagram of guiding piece 1.
Reference picture 3, guiding piece 1 include traction block 11, enter a hook knob 12,13, two back-moving springs 14 of draw hook,
Go out cylinder unblock swing arm 15, cam limit block 16 and hook 17.Wherein, traction block 11 rear and front end is respectively equipped with two positioning and leads
To block 111, the width of positioning and guiding block 111 is equal with the traction width of groove 31, and the positioning and guiding block 111 is used to position, and draws
The lower surface of block 11 is provided with mechanism grooves 112, for placing back-moving spring 14, going out cylinder unblock swing arm 15 and cam limit block 16.
Enter the front end that a hook knob 12 is located at traction block 11.When spacecraft to be assembled 6 enters accumulating launching tube 7 by outside, will
Enter a hook knob 12 and be rotated down 90 degree, guiding piece 1 is locked in the front end of accumulating launching tube 3 so that guiding piece 1 cannot by with
In the push in cylinder of positioning sliding block 4.Draw hook 13 is symmetrically disposed on the middle part both sides of traction block 11, and it can be on guiding piece 1
Rotate, two traction hook arm 131 of the upper end of draw hook 13 are inserted in the guiding groove 32 of both sides respectively, for catching on positioning convex
41, the upper surface for drawing hook arm 131 and the upper surface for being oriented to groove 32 are fitted.Two back-moving springs 14 are along the traction length of block 11
Direction is symmetrically disposed in the traction lower surface of block 11, and one end of each back-moving spring 14 is connected with traction block 11, the other end
The cam 133 with two bottoms of draw hook 13 is connected respectively, by back-moving spring 14, can order about draw hook 13 and rotate
After return to initial position.Cam limit block 16 be located at traction the lower surface of block 11 mechanism grooves 112 in, and respectively with two traction
The bottom of hook 13 is fitted, so as to limit the rotary motion of draw hook 13.Insert cam limit block 16 in the one end for going out cylinder unblock swing arm 15
In the circular groove at rear portion, the other end is connected by screw thread with traction block 11.Rotary cylinder unlocking knob 15, can make cam limit
Block 16 is along the length motion of guiding piece 1.The rotation direction of draw hook 13 can be limited by cam limit block 16, is made at draw hook 13
In bilateral rotation or the state of unilateral rotation.Hook 17 is arranged on the rear portion of traction block 11, its one end and traction by hinge
Block 11 is connected, and the other end is connected with hauling rope 5.
Reference picture 4, draw hook 13 includes traction hook arm 131, rotating shaft 132, cam 133, and three is connected to become an entirety.
Two draw hooks 13 are symmetrically arranged in the two vertically disposed axis holes of middle part of traction block 11 by rotating shaft 132, wherein drawing hook arm
131 are located at traction block 11 upper surface, and cam 133 is located in the mechanism grooves 112 of the traction lower surface of block 11, and draw hook 13 exists
132 axis can be rotated around the shaft on guiding piece 1.
Draw hook 13 has two kinds of motion states, i.e. bilateral rotation status and unilateral rotation status：
When draw hook 13 is in bilateral rotation status, cam limit block 16 does not come in contact with cam body 133, front and rear to push away
Dynamic traction hook arm 131 can be such that draw hook 13 is rotated around its axial bilateral, and reply initial bit in the presence of back-moving spring 14
Put.Now, there are two kinds of relative motion situations：Guiding piece 1 is motionless and positioning sliding block 4 is moved, and the motionless guiding piece of positioning sliding block 4
1 motion.When guiding piece 1 is motionless and positioning sliding block 4 is moved, guiding piece 1 will not stop fortune of the positioning sliding block 4 on guide rail 3
It is dynamic；When the motionless guiding piece 1 of positioning sliding block 4 is moved, guiding piece 1 can the free movement below positioning sliding block 4.Therefore, when leading
When drawing hook 13 in bilateral rotation status, draw hook 13 is unable to load.
When draw hook 13 is in unilateral rotation status, cam limit block 16 withstand two cams 133 limit it can only be to
One lateral movement, now, there is two kinds of relative motion situations, i.e., guiding piece 1 is motionless and positioning sliding block 4 is moved, and positioning sliding block 4 is not
It is dynamic and guiding piece 1 is moved.When guiding piece 1 is motionless and positioning sliding block 4 is moved, positioning sliding block 4 can only be from the front side of guiding piece 1 backward
Side shifting, when the motionless guiding piece 1 of positioning sliding block 4 is moved, then from the front side of positioning sliding block 4, side shifting can be subject to guiding piece 1 backward
The stop of positioning convex 41, i.e. draw hook 13 can be with loads.In this unilateral rotation status, hauling rope 5 pulls guiding piece 1,
Two draw hooks 13 is caught on the positioning convex 41 of the both sides of positioning sliding block 4 respectively, dragging spacecraft 6 to accumulating launching tube 7 inside
Motion.
Reference picture 5, the course of work of the invention includes：Positioning sliding block pulls positioning sliding block, leads into guide rail, guiding piece
Draw block and take out these three processes, each process is described in detail below：
Reference picture 5 (a), positioning sliding block is positioning sliding block 4 and crosses guiding piece 1 to accumulating transmitting into the process of guide rail
The process of 7 internal motions of cylinder：Cylinder unblock swing arm 15 is rotated out of first so that draw hook 13 is in unilateral rotation status, will draw
Block 1 loads in the guiding groove 31 of guide rail 3, and two traction hook arm 131 are inserted in the guiding groove 32 of both sides respectively.Cylinder will be entered
Hook knob 12 is rotated down 90 degree, enters the edge protuberance part of a hook knob 12 and is blocked by the front end face of guide rail 3 so that traction
Block 1 cannot be pushed into accumulating launching tube 7.Adjusted by unwheeling equipment and treated into the position of a spacecraft 6 and determining its tail end
In the push-in guide rail 3 of sliding block 4 of position, the insertion of the positioning convex 41 of positioning sliding block 4 be oriented in groove 32 and promote traction hook arm 131 to
After rotate, positioning sliding block 4 crosses guiding piece 1 to the internal motion of accumulating launching tube 7 from top.In order to clearly describe the process, this
Place omits cylinder to be entered spacecraft 6 to be assembled, only retains the positioning sliding block 4 of spacecraft bottom, while being carried out to accumulating launching tube 7
Cutting treatment, and indicate the direction of motion of component with arrow.
Reference picture 5 (b), guiding piece drawing positioning sliding block process be：After positioning sliding block 4 crosses guiding piece 1, cylinder will be entered
Hook knob 12 rotates up 90 degree, so that guiding piece 1 can be to moving, due to now draw hook inside accumulating launching tube 7
13 in unilateral rotation status, can pull hauling rope 5 with load, and two traction hook arm 131 can be made to catch on positioning sliding block 4 respectively
The positioning convex 41 of both sides, dragging spacecraft 6 is to the internal motion of accumulating launching tube 7.
Reference picture 5 (c), guiding piece takes out process is：When guiding piece 1 drives positioning sliding block 4 to move to the tail end of guide rail 3
When, spacecraft 6 can not continue to move backward due to the effect of the positioner in accumulating launching tube 7, the tail end of rotation traction traction block 1
Go out cylinder unblock swing arm 15 so that bilateral rotation status at draw hook 13, it is impossible to which load, positioning sliding block 4 can not stop that guiding piece 1 exists
Motion in guide rail 3.Drawing hauling rope 5 makes guiding piece 1 be moved backward along guide rail 3, two traction hook arm on guiding piece 1
131 are rotated due to the stop of positioning sliding block 4 to the front end of guiding piece 1, and guiding piece 1 is from the groove of the bottom of positioning sliding block 4 along guide rail
Body 3 is skidded off and is removed from the tail end of accumulating launching tube 7, is completed into an assembling process.
Above description and examples, preferred embodiment only of the invention, not to constituting any limitation of the invention, it is clear that
For those skilled in the art, after present invention and implementation principle has been understood, all may be based on of the invention
In the case of principle and structure, the various amendments and change in form and in details are carried out, but these are based on inventive concept
Amendment and change still within claim of the invention and protection domain.
Claims (5)
1. positioning guide rail in a kind of Spacecraft Launch cylinder for relying on guiding piece, including pedestal (2), guide rail (3) and two are positioned
Sliding block (4), wherein, pedestal (2) is on the inwall of Spacecraft Launch cylinder；Guide rail (3) is installed in parallel on pedestal (2)；
Two positioning sliding blocks (4) are separately positioned on tail end and the middle part of spacecraft, and spacecraft is by positioning sliding block (4) installed in guide rail
(3) on, it is characterised in that also including guiding piece (1)；Guide rail (3) top surface is provided with traction groove (31) along longitudinal direction, on two side
It is provided with guiding groove (32)；Positioning sliding block (4) is provided with raised (41) positioned at traction groove (31) top, bottom both sides, the two
Positioning convex (41) inserts both sides and is oriented in groove (32) respectively, for positioning sliding block (4) to be oriented to and positioned；
The guiding piece (1) is connected with hauling rope (5) positioned at the internal lower section of traction groove (31), its tail end, and hauling rope (5) is dragged
Dynamic guiding piece (1) is moved in traction groove (31)；The motion of guiding piece (1) drags sliding block (4) in traction groove (31) again
Side moves along guide rail (3) length direction, drives spacecraft to being moved inside launching tube.
2. it is according to claim 1 rely on guiding piece Spacecraft Launch cylinder in positioning guide rail, it is characterised in that guiding piece
(1) swing arm (15), cam limit block (16) and hook (17) are unlocked including drawing block (11), going out cylinder, wherein：
Traction block (11), its front end face is provided with into a hook knob (12), and middle part is symmetrically arranged on two with two tractions
Hook (13), lower surface is provided with mechanism grooves (112), and positioning and guiding block (111) is respectively arranged at two ends with from beginning to end；
Two back-moving springs (14), one end of the two back-moving springs are arranged with the mechanism grooves (112) along its length
It is fixed in traction block (11), the other end is connected with draw hook (13) bottom respectively；
The upper end of described two draw hooks (13) is inserted both sides and is oriented in groove (32) respectively, for catching on two positioning convex
(41)；
On mechanism grooves (112) central axis, cam limit block (16) leading portion is respectively against two for cam limit block (16)
The bottom of individual draw hook (13)；
The one end for going out cylinder unblock swing arm (15) is inserted into cam limit block (16) tail end, and the other end is by screw thread and traction block
(11) connect；
The one end for linking up with (17) is connected by hinge with the afterbody of traction block (11), and the other end is connected with hauling rope (5).
3. positioning guide rail in the Spacecraft Launch cylinder of guiding piece is relied on according to claim 1 and 2, it is characterised in that lead
It is traction hook arm (131) to draw hook (13) upper end, and lower end is cam (133), and traction hook arm (131) and cam (133) are by rotating shaft
(132) it is connected to become an entirety；Positioned at the upper surface of traction block (11), cam (133) is positioned at mechanism for traction hook arm (131)
In groove (112).
4. it is according to claim 2 rely on guiding piece Spacecraft Launch cylinder in positioning guide rail, it is characterised in that positioning lead
It is equal with the width of traction groove (31) to block (111) width.
5. it is according to claim 2 rely on guiding piece Spacecraft Launch cylinder in positioning guide rail, it is characterised in that guiding piece
(1) after spacecraft traction in place, taken out from guide rail (3) end, for future use.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710014727.9A CN106742062B (en) | 2017-01-10 | 2017-01-10 | Rely on positioning guide rail in the Spacecraft Launch cylinder of guiding piece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710014727.9A CN106742062B (en) | 2017-01-10 | 2017-01-10 | Rely on positioning guide rail in the Spacecraft Launch cylinder of guiding piece |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106742062A true CN106742062A (en) | 2017-05-31 |
| CN106742062B CN106742062B (en) | 2019-01-08 |
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ID=58948448
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710014727.9A Active CN106742062B (en) | 2017-01-10 | 2017-01-10 | Rely on positioning guide rail in the Spacecraft Launch cylinder of guiding piece |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109483193A (en) * | 2018-11-27 | 2019-03-19 | 上海航天精密机械研究所 | A kind of revolving body space product is into cylinder regulating device and its application method |
| CN110567318A (en) * | 2019-08-02 | 2019-12-13 | 上海航天精密机械研究所 | automatic detection device for launching tube and control method thereof |
| CN111521064A (en) * | 2020-04-02 | 2020-08-11 | 上海机电工程研究所 | Multi-degree-of-freedom constraint auxiliary supporting device for reverse-launched missile |
| CN111551075A (en) * | 2020-04-08 | 2020-08-18 | 上海机电工程研究所 | Disconnected type guide rail sliding block pair capable of continuously sliding |
| CN111717420A (en) * | 2020-07-21 | 2020-09-29 | 哈尔滨工业大学 | Accurate limiting and unfolding device and method for pressing mechanism |
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| CN204165512U (en) * | 2014-09-22 | 2015-02-18 | 上海航天精密机械研究所 | Accurate columnar member rotates into a platform |
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| CN102933932A (en) * | 2010-02-11 | 2013-02-13 | 霍华德·M·钦 | Rocket launch system and supporting apparatus |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109483193A (en) * | 2018-11-27 | 2019-03-19 | 上海航天精密机械研究所 | A kind of revolving body space product is into cylinder regulating device and its application method |
| CN110567318A (en) * | 2019-08-02 | 2019-12-13 | 上海航天精密机械研究所 | automatic detection device for launching tube and control method thereof |
| CN111521064A (en) * | 2020-04-02 | 2020-08-11 | 上海机电工程研究所 | Multi-degree-of-freedom constraint auxiliary supporting device for reverse-launched missile |
| CN111521064B (en) * | 2020-04-02 | 2022-04-01 | 上海机电工程研究所 | Multi-degree-of-freedom constraint auxiliary supporting device for reverse-launched missile |
| CN111551075A (en) * | 2020-04-08 | 2020-08-18 | 上海机电工程研究所 | Disconnected type guide rail sliding block pair capable of continuously sliding |
| CN111717420A (en) * | 2020-07-21 | 2020-09-29 | 哈尔滨工业大学 | Accurate limiting and unfolding device and method for pressing mechanism |
| CN111717420B (en) * | 2020-07-21 | 2023-08-22 | 哈尔滨工业大学 | Accurate limiting and unfolding device and unfolding limiting method for pressing mechanism |
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| Publication number | Publication date |
|---|---|
| CN106742062B (en) | 2019-01-08 |
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