CN108871065A - A kind of space payload compression release device adapting to lunar surface environment - Google Patents
A kind of space payload compression release device adapting to lunar surface environment Download PDFInfo
- Publication number
- CN108871065A CN108871065A CN201810390713.1A CN201810390713A CN108871065A CN 108871065 A CN108871065 A CN 108871065A CN 201810390713 A CN201810390713 A CN 201810390713A CN 108871065 A CN108871065 A CN 108871065A
- Authority
- CN
- China
- Prior art keywords
- firer
- release device
- lunar surface
- adapting
- screw rod
- 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
- 230000006835 compression Effects 0.000 title description 5
- 238000007906 compression Methods 0.000 title description 5
- 230000037452 priming Effects 0.000 claims abstract description 34
- 230000035939 shock Effects 0.000 claims description 16
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 238000005474 detonation Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000003721 gunpowder Substances 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 231100001261 hazardous Toxicity 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
- F16B35/02—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws divided longitudinally
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Geophysics And Detection Of Objects (AREA)
- Emergency Lowering Means (AREA)
Abstract
The invention belongs to lunar surface and field of deep space exploration, in particular to a kind of space payload for adapting to lunar surface environment compresses release device.Including priming system, firer's check lock lever, locking nut and screw rod, wherein priming system is set on the first joint of equipment, one end of firer's check lock lever is connect with priming system by screw rod and is locked by locking nut, the other end of firer's check lock lever is connect with the payload mounting plate on the second joint of the equipment, to realize the locking of payload.The present invention is applied to lunar surface and deep space exploration, and bears the payload of judder, provides fixed, limitation movement in emission state for payload, improves rigidity for it.
Description
Technical field
The invention belongs to lunar surface and field of deep space exploration, in particular to a kind of space for adapting to lunar surface environment effectively carries
Lotus compresses release device.
Background technique
Space payload during the launch process, need to overcome the vibration of rocket launching bring, impact.Therefore payload must
It must be fixed with celestial body, or several moving components are fixed in restraining position restraint, rigidity when so as to improve transmitting.But it is right
Need to act work, and the environment that space is special, without other after reaching predetermined work position in active actions class load
Mechanism or personnel release fixed limits device for it.Therefore, a kind of device assistant officer being automatically separated the fixed limitation of releasing waits solving
Certainly.
Summary of the invention
In view of the above-mentioned problems, the purpose of the present invention is to provide a kind of space payload compressions for adapting to lunar surface environment to release
Device is put, to be applied to lunar surface and deep space exploration, and the payload of judder is born, is mentioned for payload in emission state
For fixation, limitation movement, rigidity is improved for it.
To achieve the goals above, the present invention uses following technical scheme：
A kind of space payload compression release device adapting to lunar surface environment, including priming system, firer's check lock lever, locking
Nut and screw rod, wherein priming system is set on the first joint of equipment, and one end of firer's check lock lever passes through screw rod and fire
Work product connect and pass through locking nut and lock, the other end of firer's check lock lever and having on the second joint of the equipment
The connection of load mounting plate is imitated, to realize the locking of payload.
One end of firer's check lock lever is equipped with cavity, is equipped with firer's protecting against shock part in the cavity, the screw rod passes through
Firer's protecting against shock part is connect with the rectangular interface of the priming system.
Firer's protecting against shock part is using pyramidal structure made of aluminum material.
Firer's check lock lever is A font structure, and the cavity is set to the top of the A font structure.
Two legs of A font structure bottom are connect by screw with the payload mounting plate.
The one side that the cavity and the priming system contact one end is slope, and excess-three is equipped with boss on face.
The nut anti-looseness part for preventing the locking nut rotation is connected on the screw rod.
The nut anti-looseness part is L-type structure, and one end is connect with the screw rod, and the other end connects with the locking nut
Touching.
The nut anti-looseness part is connect by screw with the end of the screw rod.
The invention has the advantages and beneficial effects that：What is selected in the present invention is priming system, after energization, internal gunpowder quilt
It ignites, generates high pressure gas, cut safety pin, the screw rod below priming system can fly out, and realize the release of payload.
The present invention is slowed down by the screw rod that firer's protecting against shock part flies out, and is eventually hung on firer's check lock lever, will not
Flying out influences other equipment.
The present invention is applied to lunar surface and deep space exploration, and bears the payload of judder, is emitting for payload
State provides fixed, limitation movement, improves rigidity for it.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is the connection schematic diagram of priming system and firer's check lock lever in the present invention；
Fig. 3 is the structural schematic diagram of firer's check lock lever in the present invention；
Fig. 4 is the structural schematic diagram that the present invention is in locking state；
Fig. 5 is the structural schematic diagram that the present invention is in discrete state.
In figure：1 is priming system, and 2 be firer's check lock lever, and 3 be firer's protecting against shock part, and 4 be locking nut, and 5 be nut anti-looseness
Part, 6 be cavity, and 7 be boss, and 8 be slope, and 9 be A font structure, and 20 be second joint, and 21 be the first joint, and 22 be pedestal,
24 be payload mounting plate, and 25 be screw rod, and 26 be screw.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention clearer, right in the following with reference to the drawings and specific embodiments
The present invention is described in detail.
As shown in Figs. 1-2, a kind of space payload adapting to lunar surface environment provided by the invention compresses release device, packet
Priming system 1, firer's check lock lever 2, locking nut 4 and screw rod 25 are included, wherein priming system 1 is set on the first joint 21 of equipment,
One end of firer's check lock lever 2 is connect with priming system 1 by screw rod 25 and passes through locking nut 4 and locked, firer's check lock lever 2 it is another
Payload mounting plate 24 on the second joint 20 of one end and equipment connects, to realize the locking of payload.
As Figure 2-3, one end of firer's check lock lever 2 is equipped with cavity 6, is equipped with firer's protecting against shock part 3, screw rod in cavity 6
25 pass through firer's protecting against shock part 3 connect with the rectangular interface of priming system 1.Firer's protecting against shock part 3 is using made of aluminum material
Pyramidal structure.
As shown in figure 3, firer's check lock lever 2 is A font structure 9, design strength height, stable connection.Cavity 6 is set to A
Three faces at the top of font structure 9, one end that cavity 6 is contacted with priming system 1 are equipped with boss 7, can bear the vibration in three directions
Impact passes to power when vibration on payload matrix by priming system ontology.It is on one side slope 8, is able to bear the party
To certain active force, and conveniently after unlocking, pitching joint smooth rotation.Firer's check lock lever 2 and payload are installed
One end that plate 24 connects is A font structure 9, and two legs of 9 bottom of A font structure are connected by screw and payload mounting plate 24
It connects.
The nut anti-looseness part 5 for preventing locking nut 4 from rotating is connected on screw rod 25, nut anti-looseness part 5 is L-type structure,
One end is connect with screw rod 25, and the other end is contacted with locking nut 4, prevents locking nut 4 from rotating.
Further, nut anti-looseness part 5 is connect by screw 26 with the end of screw rod 25.
After the detonation unlock of priming system 1, the screw rod 25 of lower end can be popped up at a high speed, prevent its bullet to catch screw rod 25
Other equipment are damaged out, and reduce its impact to payload, according to the length that it is deviate from, the one of firer's check lock lever 2
End design has a cup type cavity 6 to accommodate the screw rod 25 of abjection.And it is placed with a tower fine aluminium in cup type cavity 6 to be made
Firer's protecting against shock part 3.Under the pressure effect of impact, firer's protecting against shock part 3 of tower can be by from top to bottom in layer
It flattens, to have the function that absorb impact energy.In the lower section of priming system attaching nut, also prevent it from loosening locking
Part.
The locking of the connection type is also key, and during the launch process once loosening, rigidity will be greatly reduced.Therefore,
It in the lower section of screw rod 25, is not only locked with locking nut 4, the nut anti-looseness part for limiting its rotation to be also installed to locking nut 4
5。
It during the launch process, is the rigidity for improving mechanical arm, using itself " folded arm " formula locking mode.Two joints turn
It moves to side extreme position, so that it is exported connecting rod and be tightly attached on the outside of articular shell, and be linked to be one by compressing release device
Body, as shown in Figure 4.
After priming system detonation, equipment enters operating mode, can be with normal rotation.The screw rod to fly out, because of protecting against shock part
Effect, slowed down, eventually hung on firer's check lock lever, will not fly out influences other equipment, as shown in Figure 5.
The present invention is provides locking state when payload transmitting, the purpose for playing and improving rigidity, resist vibration.When effective
When load is in locking state, priming system 1 is mounted below orientation joint by screw, and two of the A type of firer's check lock lever 2
" foot " is mounted on payload one end by screw, is put into firer's protecting against shock part 3 (tower top is in priming system one end) in " rectangular cup ",
Then the screw rod 25 below priming system is penetrated, is buckled on the rectangular interface of priming system 1.Lead between firer's check lock lever 2 and priming system 1
Locking nut 4 is crossed to be connected.Locking nut 4 loosens in order to prevent simultaneously, is equipped with nut anti-looseness part 5, spiral shell in locking screw female end
Female anti-release member 5 is fixed on the lower end of screw rod 25 by screw 26.
What is selected in the present invention is priming system 1, and after energization, internal gunpowder is detonated, and generates high pressure gas, cuts peace
The screw rod 25 of full pin, 1 lower section of priming system can fly out.There is no resistance in space, the object to fly out at a high speed is extremely hazardous, possibility
Other equipment can be damaged.Therefore, another task of this compression release device seeks to slow down and connect for the screw rod 25 to fly out
Other equipment are damaged to prevent it in firmly screw rod 25.
When priming system 1 detonates, screw rod 25 can be detached from inside priming system 1, projected and flattened firer's protecting against shock part 3, hang over
On firer's check lock lever 2.It is detached from locking state from this payload, operating mode operation can be carried out, equipment runs well, and such as schemes
Shown in 5.
Mode the above is only the implementation of the present invention is not intended to limit the scope of the present invention.It is all in the present invention
Spirit and principle within any modification, equivalent replacement, improvement, extension etc., be all contained in protection scope of the present invention
It is interior.
Claims (9)
1. a kind of space payload for adapting to lunar surface environment compresses release device, which is characterized in that including priming system (1), fire
Work check lock lever (2), locking nut (4) and screw rod (25), wherein priming system (1) is set on the first joint (21) of equipment, institute
The one end for stating firer's check lock lever (2) is connect with priming system (1) and is locked by locking nut (4), the fire by screw rod (25)
The other end of work check lock lever (2) is connect with the payload mounting plate (24) on the second joint (20) of the equipment, thus real
The locking of existing payload.
2. the space payload according to claim 1 for adapting to lunar surface environment compresses release device, which is characterized in that institute
The one end for stating firer's check lock lever (2) is equipped with cavity (6), and firer's protecting against shock part (3), the screw rod are equipped in the cavity (6)
(25) firer's protecting against shock part (3) is passed through to connect with the rectangular interface of the priming system (1).
3. the space payload according to claim 2 for adapting to lunar surface environment compresses release device, which is characterized in that institute
Stating firer's protecting against shock part (3) is using pyramidal structure made of aluminum material.
4. the space payload according to claim 2 for adapting to lunar surface environment compresses release device, which is characterized in that institute
Stating firer's check lock lever (2) is A font structure (9), and the cavity (6) is set to the top of the A font structure (9).
5. the space payload according to claim 4 for adapting to lunar surface environment compresses release device, which is characterized in that institute
Two legs for stating A font structure (9) bottom are connect by screw with the payload mounting plate (24).
6. the space payload according to claim 2 for adapting to lunar surface environment compresses release device, which is characterized in that institute
The one side for stating cavity (6) and the priming system (1) contact one end is slope (8), is equipped with boss (7) on excess-three face.
7. the space payload according to claim 1 for adapting to lunar surface environment compresses release device, which is characterized in that institute
State the nut anti-looseness part (5) for being connected on screw rod (25) and preventing the locking nut (4) from rotating.
8. the space payload according to claim 7 for adapting to lunar surface environment compresses release device, which is characterized in that institute
Stating nut anti-looseness part (5) is L-type structure, and one end is connect with the screw rod (25), and the other end connects with the locking nut (4)
Touching.
9. the space payload according to claim 8 for adapting to lunar surface environment compresses release device, which is characterized in that institute
Nut anti-looseness part (5) are stated to connect by screw (26) with the end of the screw rod (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810390713.1A CN108871065B (en) | 2018-04-27 | 2018-04-27 | Space effective load compressing and releasing device suitable for lunar surface environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810390713.1A CN108871065B (en) | 2018-04-27 | 2018-04-27 | Space effective load compressing and releasing device suitable for lunar surface environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108871065A true CN108871065A (en) | 2018-11-23 |
| CN108871065B CN108871065B (en) | 2023-08-22 |
Family
ID=64327266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810390713.1A Active CN108871065B (en) | 2018-04-27 | 2018-04-27 | Space effective load compressing and releasing device suitable for lunar surface environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108871065B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110793793A (en) * | 2019-09-26 | 2020-02-14 | 上海宇航***工程研究所 | Ground unfolding test system of large-scale load platform |
| CN114802813A (en) * | 2022-03-17 | 2022-07-29 | 齐鲁空天信息研究院 | Fire compressing and releasing device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050045771A1 (en) * | 2003-08-28 | 2005-03-03 | Caldwell Douglas W. | Compact external launcher for small space payloads |
| CN103659834A (en) * | 2013-11-21 | 2014-03-26 | 上海宇航***工程研究所 | Multifunctional small-sized mechanical arm |
| CN105474775B (en) * | 2011-12-14 | 2014-06-25 | 上海宇航***工程研究所 | A kind of locking relieving mechanism |
| CN104276294A (en) * | 2014-09-16 | 2015-01-14 | 上海卫星工程研究所 | Compression releasing device of satellite micro-vibration vibration isolation system |
| CN105425513A (en) * | 2015-12-01 | 2016-03-23 | 中国科学院沈阳自动化研究所 | Interface board structure used for connecting panorama cameras on space probe with rotary table |
| CN208108928U (en) * | 2018-04-27 | 2018-11-16 | 中国科学院沈阳自动化研究所 | The space payload for adapting to lunar surface environment compresses release device |
-
2018
- 2018-04-27 CN CN201810390713.1A patent/CN108871065B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050045771A1 (en) * | 2003-08-28 | 2005-03-03 | Caldwell Douglas W. | Compact external launcher for small space payloads |
| CN105474775B (en) * | 2011-12-14 | 2014-06-25 | 上海宇航***工程研究所 | A kind of locking relieving mechanism |
| CN103659834A (en) * | 2013-11-21 | 2014-03-26 | 上海宇航***工程研究所 | Multifunctional small-sized mechanical arm |
| CN104276294A (en) * | 2014-09-16 | 2015-01-14 | 上海卫星工程研究所 | Compression releasing device of satellite micro-vibration vibration isolation system |
| CN105425513A (en) * | 2015-12-01 | 2016-03-23 | 中国科学院沈阳自动化研究所 | Interface board structure used for connecting panorama cameras on space probe with rotary table |
| CN208108928U (en) * | 2018-04-27 | 2018-11-16 | 中国科学院沈阳自动化研究所 | The space payload for adapting to lunar surface environment compresses release device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110793793A (en) * | 2019-09-26 | 2020-02-14 | 上海宇航***工程研究所 | Ground unfolding test system of large-scale load platform |
| CN114802813A (en) * | 2022-03-17 | 2022-07-29 | 齐鲁空天信息研究院 | Fire compressing and releasing device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108871065B (en) | 2023-08-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108871065A (en) | A kind of space payload compression release device adapting to lunar surface environment | |
| CN108928489B (en) | Remote throwing device for carrying hand throwing grenade and knocking grenade by unmanned aerial vehicle | |
| CN105043166B (en) | Low-impact integral ejection type launch box front cover | |
| CN109229431A (en) | A kind of non-firer's tripper and locking unlocking method | |
| CN108371767A (en) | A kind of police multi-functional flight rescue system of fire-fighting | |
| CN208108928U (en) | The space payload for adapting to lunar surface environment compresses release device | |
| RU2388508C2 (en) | Device for fire extinguishing in building | |
| CN109850151A (en) | A kind of unmanned plane arrest net device and unmanned plane | |
| CN108180795A (en) | A kind of non-firer's separator of electromagnetic drive based on scroll spring transmission component | |
| CN216348112U (en) | Gun shooting fuse mechanism | |
| CN209889115U (en) | Unmanned aerial vehicle catches net device and unmanned aerial vehicle | |
| KR101338156B1 (en) | Separation structures for ejection apparatus of portable guided missile | |
| CN112061428B (en) | Self-adaptive penetration expansion attachment device for attaching space target surface | |
| CN105783614B (en) | A kind of mechanical timing type throws bullet | |
| CN209479991U (en) | The cold hairdo multitube bomb rack control of unmanned plane | |
| CN108332622A (en) | A kind of throwing bullet that comprehensive shock is opened | |
| CN108870034B (en) | Robotic panoramic camera turntable adapting to lunar environment | |
| CN212332973U (en) | Unmanned aerial vehicle throwing type energy-gathering destroying equipment | |
| CN208107592U (en) | Adapt to the robotization panorama camera turntable of lunar surface environment | |
| CN208488012U (en) | A kind of shock resistance hood for MISSILE LAUNCHING | |
| CN107031874B (en) | A kind of space non-cooperative target instantaneously triggered grabs adsorption device | |
| CN111559502B (en) | Unmanned aerial vehicle throwing type energy-gathering destroying equipment and destroying method | |
| CN110155307A (en) | A kind of inertia unlock rudder face device for ejecting | |
| KR101879944B1 (en) | Concussion fuse that ensures alignment between armoring part and firing part | |
| CN210057222U (en) | Filling-up burst fire extinguishing bomb with recovery device |
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 |