CN108871065B - Space effective load compressing and releasing device suitable for lunar surface environment - Google Patents
Space effective load compressing and releasing device suitable for lunar surface environment Download PDFInfo
- Publication number
- CN108871065B CN108871065B CN201810390713.1A CN201810390713A CN108871065B CN 108871065 B CN108871065 B CN 108871065B CN 201810390713 A CN201810390713 A CN 201810390713A CN 108871065 B CN108871065 B CN 108871065B
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- CN
- China
- Prior art keywords
- explosive device
- initiating explosive
- screw
- nut
- locking
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- 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.)
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- 239000002360 explosive Substances 0.000 claims abstract description 81
- 230000000977 initiatory effect Effects 0.000 claims abstract description 80
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 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 4
- 238000001514 detection method Methods 0.000 abstract description 2
- 230000009471 action Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 239000003721 gunpowder Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 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
- 230000002265 prevention 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
Abstract
The invention belongs to the technical field of lunar surface and deep space exploration, and particularly relates to a space effective load compressing and releasing device suitable for lunar surface environments. Including initiating explosive device, initiating explosive device locking lever, lock nut and screw rod, wherein the initiating explosive device sets up on the first joint of equipment, the one end of initiating explosive device locking lever passes through the screw rod and is connected with the initiating explosive device, and locks through lock nut, the other end of initiating explosive device locking lever with the payload mounting panel on the second joint of equipment is connected to realize the locking of payload. The invention is applied to lunar surface and deep space detection and bears the effective load of strong vibration, and provides fixed and limited movement for the effective load in a transmitting state, thereby improving the rigidity of the effective load.
Description
Technical Field
The invention belongs to the technical field of lunar surface and deep space exploration, and particularly relates to a space effective load compressing and releasing device suitable for lunar surface environments.
Background
During the launching process, the space payload needs to overcome the vibration and impact caused by rocket launching. The payload must therefore be fixed to the star or several moving parts can be immobilized in a limited position, thus increasing the rigidity during firing. However, when the movable action type load reaches the predetermined working position, the movable action is required, and the space is special, and there is no restriction device for releasing the fixation by other mechanisms or personnel. Therefore, a device for automatically separating and releasing the fixation restriction is to be solved.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a space payload compression and release device adapted to lunar environments, so as to be applied to lunar and deep space exploration, and to bear a payload of intense vibration, to provide a fixed and limited movement for the payload in a transmitting state, and to improve rigidity thereof.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the utility model provides a space payload compresses tightly release of adaptation lunar surface environment, includes initiating explosive device, initiating explosive device locking lever, lock nut and screw rod, and wherein the initiating explosive device sets up on the first joint of equipment, the one end of initiating explosive device locking lever is connected with the initiating explosive device through the screw rod, and locks through lock nut, the other end of initiating explosive device locking lever with the payload mounting panel on the second joint of equipment is connected to realize the locking of payload.
One end of the initiating explosive device locking rod is provided with a cavity, a initiating explosive device anti-impact piece is arranged in the cavity, and the screw rod penetrates through the initiating explosive device anti-impact piece and is connected with a square interface of the initiating explosive device.
The initiating explosive device anti-impact piece is of a tower-shaped structure made of aluminum materials.
The initiating explosive device locking rod is of an A-shaped structure, and the cavity is formed in the top of the A-shaped structure.
The two legs at the bottom of the A-shaped structure are connected with the effective load mounting plate through screws.
One surface of the cavity, which is in contact with one end of the initiating explosive device, is a slope surface, and the other three surfaces are provided with bosses.
And a nut locking piece for preventing the lock nut from rotating is connected to the screw rod.
The nut locking piece is of an L-shaped structure, one end of the nut locking piece is connected with the screw, and the other end of the nut locking piece is in contact with the locking nut.
The nut locking piece is connected with the end part of the screw rod through a screw.
The invention has the advantages and beneficial effects that: the explosive material is selected as the initiating explosive device, and after the initiating explosive device is electrified, the gunpowder in the initiating explosive device is detonated to generate high-pressure gas, so that the safety pin is sheared off, and a screw below the initiating explosive device flies out to release the effective load.
The screw rod which flies out through the initiating explosive device anti-impact piece is decelerated, and finally the screw rod can be hung on the initiating explosive device locking rod, so that other equipment cannot be influenced.
The invention is applied to lunar surface and deep space detection and bears the effective load of strong vibration, and provides fixed and limited movement for the effective load in a transmitting state, thereby improving the rigidity of the effective load.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic diagram of the connection of an initiating explosive device and an initiating explosive device locking lever in the invention;
FIG. 3 is a schematic view of the structure of the firelock lever of the present invention;
FIG. 4 is a schematic view of the present invention in a locked state;
fig. 5 is a schematic view of the structure of the present invention in a separated state.
In the figure: 1 is a initiating explosive device, 2 is a initiating explosive device locking rod, 3 is a initiating explosive device anti-impact piece, 4 is a locking nut, 5 is a nut locking piece, 6 is a cavity, 7 is a boss, 8 is a slope surface, 9 is an A-shaped structure, 20 is a second joint, 21 is a first joint, 22 is a base, 24 is a payload mounting plate, 25 is a screw, and 26 is a screw.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1-2, the space payload compressing and releasing device suitable for lunar surface environment provided by the invention comprises an initiating explosive device 1, an initiating explosive device locking rod 2, a locking nut 4 and a screw rod 25, wherein the initiating explosive device 1 is arranged on a first joint 21 of equipment, one end of the initiating explosive device locking rod 2 is connected with the initiating explosive device 1 through the screw rod 25 and locked through the locking nut 4, and the other end of the initiating explosive device locking rod 2 is connected with a payload mounting plate 24 on a second joint 20 of the equipment, so that the payload is locked.
As shown in fig. 2-3, one end of the initiating explosive device locking rod 2 is provided with a cavity 6, a initiating explosive device anti-impact member 3 is arranged in the cavity 6, and a screw 25 penetrates through the initiating explosive device anti-impact member 3 to be connected with a square interface of the initiating explosive device 1. The initiating explosive device anti-impact member 3 is of a tower-shaped structure made of aluminum materials.
As shown in fig. 3, the initiating explosive device locking rod 2 is of an a-shaped structure 9, and the design strength is high and the connection is stable. The cavity 6 is arranged at the top of the A-shaped structure 9, and three sides of one end of the cavity 6, which is contacted with the initiating explosive device 1, are provided with bosses 7, so that vibration impact in three directions can be born, and force during vibration is transmitted to a payload matrix through the initiating explosive device body. One surface is a slope surface 8, which can bear a certain acting force in the direction, and the pitching joint can smoothly rotate after unlocking conveniently. One end of the initiating explosive device locking rod 2 connected with the effective load mounting plate 24 is an A-shaped structure 9, and two legs at the bottom of the A-shaped structure 9 are connected with the effective load mounting plate 24 through screws.
The screw rod 25 is connected with a nut locking piece 5 for preventing the locking nut 4 from rotating, the nut locking piece 5 is of an L-shaped structure, one end of the nut locking piece is connected with the screw rod 25, and the other end of the nut locking piece is contacted with the locking nut 4 to prevent the locking nut 4 from rotating.
Further, the nut lock 5 is connected to an end of the screw 25 by a screw 26.
Considering that the screw 25 at the lower end pops up at a high speed after the initiating explosive device 1 is detonated and unlocked, in order to catch the screw 25, prevent the screw 25 from being popped up to damage other equipment, and reduce the impact on the payload, according to the length of the popped-up screw, a cup-shaped cavity 6 is designed at one end of the initiating explosive device locking lever 2 to accommodate the popped-up screw 25. And a tower-type pure aluminum fire work impact-proof member 3 is arranged in the cup-type cavity 6. Under the impact pressure, the tower-type initiating explosive device impact prevention piece 3 can be flattened from top to bottom, so that the impact energy absorption effect is achieved. And a locking piece for preventing loosening of the initiating explosive device connecting nut is arranged below the initiating explosive device connecting nut.
The locking of this connection is also critical, and once loosened during firing, the stiffness will drop greatly. Therefore, below the screw 25, not only the lock nut 4 is used for locking, but also a nut lock 5 for restricting the rotation thereof is attached to the lock nut 4.
In the process of launching, in order to improve the rigidity of the mechanical arm, a self arm-holding locking mode is adopted. Both joints are rotated to one side limit position, so that the output connecting rods are clung to the outer side of the joint shell, and are connected into a whole through the compression release device, as shown in fig. 4.
After initiating explosive device detonates, equipment enters a working mode and can normally rotate. The flying screw, due to the impact-resistant member, is decelerated and eventually hangs on the firer locking lever without flying to affect other equipment, as shown in fig. 5.
The invention provides a locking state for the effective load during transmitting, and achieves the purposes of improving rigidity and resisting vibration. When the effective load is in a locking state, the initiating explosive device 1 is arranged below the azimuth joint through screws, two 'feet' of the A type of the initiating explosive device locking rod 2 are arranged at one end of the effective load through screws, an initiating explosive device anti-impact piece 3 (the tower top is arranged at one end of the initiating explosive device) is placed in a 'square cup', and then the initiating explosive device is penetrated into a screw rod 25 below the initiating explosive device and buckled on a square interface of the initiating explosive device 1. The initiating explosive device locking rod 2 is connected with the initiating explosive device 1 through a locking nut 4. Meanwhile, in order to prevent the locknut 4 from loosening, a nut locking piece 5 is mounted at the locknut end, and the nut locking piece 5 is fixed at the lower end of the screw 25 through a screw 26.
In the invention, the initiating explosive device 1 is selected, and after being electrified, gunpowder in the initiating explosive device is detonated to generate high-pressure gas, so that a safety pin is sheared, and a screw rod 25 below the initiating explosive device 1 can fly out. There is no resistance in the space and objects flying at high speed are extremely dangerous and may damage other equipment. Thus, another task of the present compression release device is to slow down the flying screw 25 and catch the screw 25 to prevent it from damaging other equipment.
When initiating explosive device 1, screw 25 will separate from the inside of initiating explosive device 1, eject and flatten the impact-proof member 3 of initiating explosive device, and hang on the locking rod 2 of initiating explosive device. From this payload, the locked state, the work mode operation can be performed and the device is operating normally as shown in fig. 5.
The foregoing is merely an embodiment of the present invention and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, expansion, etc. made within the spirit and principle of the present invention are included in the protection scope of the present invention.
Claims (6)
1. The space effective load compressing and releasing device suitable for the lunar surface environment is characterized by comprising an initiating explosive device (1), an initiating explosive device locking rod (2), a locking nut (4) and a screw rod (25), wherein the initiating explosive device (1) is arranged on a first joint (21) of a mechanical arm, one end of the initiating explosive device locking rod (2) is connected with the initiating explosive device (1) through the screw rod (25) and is locked through the locking nut (4), and the other end of the initiating explosive device locking rod (2) is connected with an effective load mounting plate (24) on a second joint (20) of the mechanical arm, so that effective load locking is realized;
one end of the initiating explosive device locking rod (2) is provided with a cavity (6), a initiating explosive device anti-impact piece (3) is arranged in the cavity (6), and the screw (25) penetrates through the initiating explosive device anti-impact piece (3) to be connected with a square interface of the initiating explosive device (1); the initiating explosive device anti-impact piece (3) is of a tower-shaped structure made of aluminum materials;
one surface of the cavity (6) contacting with the initiating explosive device (1) is a slope surface (8), and the other three surfaces are provided with bosses (7).
2. The space payload compression release device adapted to lunar environment according to claim 1, characterized in that the initiating explosive device locking lever (2) is an a-shaped structure (9), and the cavity (6) is arranged at the top of the a-shaped structure (9).
3. The lunar environment compliant space payload compression release of claim 2 wherein the two legs at the bottom of the a-shaped structure (9) are connected to the payload mounting plate (24) by screws.
4. The lunar environment compatible space payload compression release of claim 1 wherein the screw (25) has a nut lock (5) attached thereto that prevents rotation of the lock nut (4).
5. The lunar surface environment adapting space payload compression release of claim 4, wherein the nut lockers (5) are L-shaped structures with one end connected to the screw (25) and the other end in contact with the locknut (4).
6. The lunar environment compatible space payload compression release of claim 5, wherein the nut lock (5) is connected to an end of the screw (25) by a screw (26).
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 CN108871065A (en) | 2018-11-23 |
| CN108871065B true CN108871065B (en) | 2023-08-22 |
Family
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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) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110793793B (en) * | 2019-09-26 | 2022-04-19 | 上海宇航系统工程研究所 | Ground unfolding test system of large-scale load platform |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103659834A (en) * | 2013-11-21 | 2014-03-26 | 上海宇航系统工程研究所 | Multifunctional small-sized mechanical arm |
| CN105474775B (en) * | 2011-12-14 | 2014-06-25 | 上海宇航系统工程研究所 | 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7036773B2 (en) * | 2003-08-28 | 2006-05-02 | Ecliptic Enterprises Corporation | Compact external launcher for small space payloads |
-
2018
- 2018-04-27 CN CN201810390713.1A patent/CN108871065B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105474775B (en) * | 2011-12-14 | 2014-06-25 | 上海宇航系统工程研究所 | A kind of locking relieving mechanism |
| CN103659834A (en) * | 2013-11-21 | 2014-03-26 | 上海宇航系统工程研究所 | 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 |
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| Publication number | Publication date |
|---|---|
| CN108871065A (en) | 2018-11-23 |
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