CN110143298A - Subtract and rushes single machine seat structure - Google Patents
Subtract and rushes single machine seat structure Download PDFInfo
- Publication number
- CN110143298A CN110143298A CN201910291109.8A CN201910291109A CN110143298A CN 110143298 A CN110143298 A CN 110143298A CN 201910291109 A CN201910291109 A CN 201910291109A CN 110143298 A CN110143298 A CN 110143298A
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- CN
- China
- Prior art keywords
- single machine
- rush
- subtract
- seat structure
- rubber pad
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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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- 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
-
- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Bolts, Nuts, And Washers (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The present invention relates to it is a kind of subtract rush technical field of structures be suitable for subtracting for spacecraft rush single machine seat structure；It is described subtract rush single machine seat structure include fastening screw, packing washer, on subtract rush rubber pad, groove type single machine support, under subtract rush rubber pad and connection embedded part；The fastening screw is used for the fixation of single machine installation foot and provides pretightning force；The packing washer is for compressing and making its upper surface uniform stressed；On subtract and rush the top that rubber pad is set to groove type single machine support, under subtract and rush rubber pad and be set in the groove of groove type single machine support；The connection embedded part, which is located in cellular board, provides hickey for single machine.Of the invention subtract rushes single machine seat structure and solves the problems, such as that single machine shock response is excessive on star, subtracts and rushes that high-efficient, weight is small and applied widely.
Description
Technical field
The present invention relates to subtract to rush technical field of structures, and in particular to one kind, which subtracts, rushes single machine seat structure, is suitable for spacecraft
The upper larger single machine of heat conduction amount demand subtracts punching.
Background technique
When the separation of device arrow or bay section separate, temporary impact overload can be generated.It is issued and is instructed by ground before the separation of device arrow, make to connect
The blasting bolt detonation of band is connect, system for unlocking unlock, band unclamps, to realize separation.Launch separating mechanism mainly by
Blasting bolt, cut spring or pneumatic actuator composition.During rocket flight, satellite, bullet or spacecraft are usually used quick-fried
Fried bolt is reliably connected together with final-stage rocket, and cut spring (or pneumatic actuator) is in compression (or pending) state.
When control system issues separation command by preset program, blasting bolt is ignited, star, arrow connection are cut off, while cut spring (or
Pneumatic actuator) separating force is released, satellite, bullet or other spacecrafts are launched away, realize the separation with final-stage rocket.
Braking rocket separating mechanism is mainly made of blasting bolt and retro-rocket.The work of blasting bolt as hereinbefore, is exploded
When bolt unlocks, retro-rocket is lighted.Since retro-rocket generates the unlock delay of thrust ratio blasting bolt, so generation is counter to push away fire
When arrow thrust, star, arrow have been disengaged.As retro-rocket thrust increases, satellite, bullet or other spacecrafts are gradually fiery with final stage
Arrow spaces out, and realizes star, arrow reliable separation.As it can be seen that impact meeting caused by blasting bolt is so that single machine generates one on star
Temporary impact overload, the impact acceleration may make standalone architecture generate destruction.It is responded to reduce the impact acceleration of single machine on star,
It needs to research and develop and rushes structure suitable for subtracting for the larger single machine of heat conduction amount demand on spacecraft.
The retrieval discovery of the prior art is coped with, Chinese patent application 201810093881.4 discloses a kind of for space flight
The modularization standalone architecture of device, including rack, pedestal, baffle and screw rod；Rack uses frame structure, and pedestal and baffle are all made of
Plate structure, the boss for the connection rack being respectively provided on pedestal and the flange for the baffle that is spirally connected；Several racks according to
It is secondary it is stacked after be mounted on the base, baffle is bonded to form closed structure and pass through screw rod with outermost rack in several racks
It is fixedly connected, baffle edge is spirally connected with pedestal.The technical solution compensates for the light-duty single machine knot of the high-intensitive three-dimensional of Traditional Space
Structure assembly is complicated and haves the defects that security risk, but can not solve impact acceleration simultaneously causes the correlation of standalone architecture to be asked
Topic.
Summary of the invention
In view of the drawbacks of the prior art, single machine support knot is rushed suitable for subtracting for spacecraft the object of the present invention is to provide a kind of
Structure.Of the invention subtract rushes single machine seat structure and solves the problems, such as that single machine shock response is excessive on star, subtracts and rushes that high-efficient, weight is small
With it is applied widely.Structure of the present invention underlay on single machine installation foot, which subtracts, rushes rubber pad, has to subtract and rushes high-efficient spy
Point；The design of groove type single machine support makes the spy without increasing heat-conducting plate between single machine and mounting plate, with lightweight construction
Point；This kind can be used to the thermally conductive single machine for having demand subtract and rush single machine seat structure, has the characteristics that applied widely.
Single machine seat structure is rushed suitable for subtracting for spacecraft the present invention relates to a kind of, described subtract rushes single machine seat structure and include
Fastening screw, packing washer, on subtract rush rubber pad, groove type single machine support, under subtract rush rubber pad and connection embedded part；The fastening
Screw is used for the fixation of single machine installation foot and provides pretightning force；The packing washer for compress and make its upper surface uniformly by
Power；On subtract and rush the top that rubber pad is set to groove type single machine support, under subtract and rush rubber pad and be set to groove type single machine support
In groove；The connection embedded part, which is located in cellular board, provides hickey for single machine.
Preferably, the fastening screw and packing washer are national standard part.
Preferably, the material of the fastening screw is titanium alloy.
Preferably, the material of the packing washer is stainless steel.
Preferably, the packing washer overall diameter, which is greater than, above subtracts the overall diameter for rushing rubber pad.
Preferably, subtract that rush rubber pad be column structure on described, wound and suppressed by stainless steel wire, be mounted on single machine
Between installation foot and packing washer.
Preferably, the groove type single machine support is specially provided with a groove in the lower surface position of single machine installation foot,
Rubber pad is rushed for subtracting under installing.
Preferably, subtract that rush rubber pad be column structure under described, wound and suppressed by stainless steel wire, be mounted on groove
In formula single machine support.
Preferably, the connection embedded part is double-vane screw hole embedded part, is embedded in honeycomb mounting plate, provides installation for single machine and connect
Mouthful.
Preferably, the connection embedded part is magnesium alloy.
Compared with prior art, the present invention have it is following the utility model has the advantages that
It is 1, of the invention to be suitable for subtracting to rush single machine seat structure underlay on single machine installation foot and subtract and rushing rubber pad for spacecraft,
Have the characteristics that subtract rush it is high-efficient；
2, it is of the invention be suitable for spacecraft subtract the design for rushing the groove type single machine support of single machine seat structure use, make
Without increasing heat-conducting plate between single machine and mounting plate, has the characteristics that lightweight construction；
3, the subtracting for spacecraft that be suitable for of the invention can be used to the thermally conductive single machine for having demand and rushes single machine seat structure, have
Have the characteristics that applied widely.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature mesh of the invention
And advantage will become more apparent upon.
Fig. 1 subtracts for the present invention rushes single machine seat structure scheme of installation；
Fig. 2 is to subtract to rush rubber pad scheme of installation under the present invention.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
Embodiment
In the present embodiment, of the present invention to rush single machine seat structure suitable for subtracting for spacecraft, described subtract rushes single machine branch
Holder structure include fastening screw, packing washer, on subtract rush rubber pad, groove type single machine support, under subtract and rush rubber pad and connection is buried
Part；The fastening screw is used for the fixation of single machine installation foot and provides pretightning force；The packing washer is for compressing and making thereon
Surface uniform stressed；On subtract and rush the top that rubber pad is set to groove type single machine support, under subtract and rush rubber pad and be set to groove type
In the groove of single machine support；The connection embedded part, which is located in cellular board, provides hickey for single machine.
Next the present invention is described in detail.
The present invention subtract rush embedded parts structure include: connection embedded part 3, fastening screw 4, packing washer 5, on subtract and rush rubber pad 6, recessed
Slot type single machine support 7 subtracts under rushes rubber pad 8, as shown in Figure 1.Under subtract and rush rubber pad 8 in the installation side of groove type single machine support 7
Formula, as shown in Figure 2.
Under subtract rush rubber pad 8 thickness outline be higher than groove type single machine support 7 depth of groove, as shown in Fig. 2, this height
Difference can be adaptively adjusted according to screwing force.The circumferential direction for subtracting and rushing rubber pad 8 can be effectively suppressed down in groove type single machine support 7
Expansion, can promote the connective stability of screw.In addition, directly padding rubber pad up and down compared in single machine installation foot, it is single that this subtracts punching
The groove design of machine seat structure make between the biggish single machine of heat conduction amount demand 1 and cellular board 2 without increasing heat-conducting padding plate,
It can effectively mitigate and rush construction weight.
Subtract rush rubber pad 6 and 8 be stainless steel wire winding, suppress, surface tension is weaker, rushes rubber pad 6 in upper subtract
Packing washer 5 is installed on upper surface can make its uniform stressed, improve stability.Single machine installation foot is installed to subtract up and down rushes rubber pad 6
With 8, cellular board 2 can be effectively reduced and embedded part 3 is transmitted to the shock loading of single machine, have the characteristics that subtract rush it is high-efficient.
In addition to this, this subtract rush single machine seat structure component it is easy to process, have thermally conductive demand for various on spacecraft
Single machine or there is the structure for subtracting the demand of punching and can be used such subtract to rush single machine seat structure and carry out subtracting punching design.Therefore, this subtracts punching
Single machine seat structure also has the characteristics that applied widely.
Single machine seat structure is rushed in of the invention subtracting, by fastening screw, packing washer, on subtract and rush rubber pad, groove type single machine
Support, under subtract rush rubber pad and connection embedded part composition；On subtract and rush rubber pad and packing washer is located above single machine installation foot；Under subtract
It rushes rubber pad to be located in the groove of groove type single machine support, thickness is slightly larger than depth of groove；The single machine that installation subtracts flushing device passes through
Fastening screw connect embedded part with cellular board and is connected.It is of the invention subtract to rush single machine seat structure underlay on single machine installation foot and subtract rush rubber
Rubber mat, have the characteristics that subtract rush it is high-efficient；The subtracting for spacecraft that be suitable for of the invention rushes the groove type that single machine seat structure uses
The design of single machine support makes have the characteristics that lightweight construction without increasing heat-conducting plate between single machine and mounting plate；Have to thermally conductive
The single machine of demand can be used the subtracting for spacecraft that be suitable for of the invention and rush single machine seat structure, have spy applied widely
Point.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. one kind, which subtracts, rushes single machine seat structure, which is characterized in that described to subtract that rush single machine seat structure include fastening screw, clamping pad
Circle, on subtract rush rubber pad, groove type single machine support, under subtract rush rubber pad and connection embedded part；The fastening screw is pacified for single machine
It fills the fixation of foot and pretightning force is provided；The packing washer is for compressing and making its upper surface uniform stressed；On subtract and rush rubber pad
Be set to the top of groove type single machine support, under subtract and rush rubber pad and be set in the groove of groove type single machine support；The connection
Embedded part, which is located in cellular board, provides hickey for single machine.
2. subtracting as described in claim 1 and rushing single machine seat structure, characterized in that the fastening screw and packing washer are country
Standard component.
3. subtracting rush single machine seat structure as described in claim 1, characterized in that the material of the fastening screw is titanium alloy.
4. subtracting rush single machine seat structure as described in claim 1, characterized in that the material of the packing washer is stainless steel.
5. subtracting rush single machine seat structure as described in claim 1, characterized in that the packing washer overall diameter, which is greater than, above subtracts punching
The overall diameter of rubber pad.
6. subtracting as described in claim 1 and rushing single machine seat structure, characterized in that subtract that rush rubber pad be column structure on described,
It is wound and is suppressed by stainless steel wire, be mounted between single machine installation foot and packing washer.
7. subtracting rush single machine seat structure as described in claim 1, characterized in that the groove type single machine support is specially in list
The lower surface position of machine installation foot is provided with a groove, rushes rubber pad for subtracting under installing.
8. subtracting as described in claim 1 and rushing single machine seat structure, characterized in that subtract that rush rubber pad be column structure under described,
It is wound and is suppressed by stainless steel wire, be mounted in groove type single machine support.
9. subtracting rush single machine seat structure as described in claim 1, characterized in that the connection embedded part is double-vane screw hole embedded part,
It is embedded in honeycomb mounting plate, provides installation interface for single machine.
10. subtracting rush single machine seat structure as described in claim 1, characterized in that the connection embedded part is magnesium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910291109.8A CN110143298B (en) | 2019-04-11 | 2019-04-11 | Support structure of single impact reducing machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910291109.8A CN110143298B (en) | 2019-04-11 | 2019-04-11 | Support structure of single impact reducing machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110143298A true CN110143298A (en) | 2019-08-20 |
| CN110143298B CN110143298B (en) | 2020-10-09 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910291109.8A Active CN110143298B (en) | 2019-04-11 | 2019-04-11 | Support structure of single impact reducing machine |
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| CN (1) | CN110143298B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4002120A (en) * | 1975-07-31 | 1977-01-11 | The United States Of America As Represented By The Secretary Of The Navy | Missile stage coupler |
| KR100659303B1 (en) * | 2006-04-05 | 2006-12-20 | 국방과학연구소 | Missile fixing apparatus of missile launching system |
| RU2341423C1 (en) * | 2007-06-22 | 2008-12-20 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" | Attachment device |
| CN103292641A (en) * | 2013-05-10 | 2013-09-11 | 北京宇航系统工程研究所 | Explosive separation device used for longitudinal separation of fairing |
| CN104058107A (en) * | 2014-05-23 | 2014-09-24 | 北京空间飞行器总体设计部 | Connecting device capable of reducing impact during satellite-rocket separation |
| KR101864047B1 (en) * | 2016-12-07 | 2018-06-04 | 국방과학연구소 | Low-shock separation device |
-
2019
- 2019-04-11 CN CN201910291109.8A patent/CN110143298B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4002120A (en) * | 1975-07-31 | 1977-01-11 | The United States Of America As Represented By The Secretary Of The Navy | Missile stage coupler |
| KR100659303B1 (en) * | 2006-04-05 | 2006-12-20 | 국방과학연구소 | Missile fixing apparatus of missile launching system |
| RU2341423C1 (en) * | 2007-06-22 | 2008-12-20 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" | Attachment device |
| CN103292641A (en) * | 2013-05-10 | 2013-09-11 | 北京宇航系统工程研究所 | Explosive separation device used for longitudinal separation of fairing |
| CN104058107A (en) * | 2014-05-23 | 2014-09-24 | 北京空间飞行器总体设计部 | Connecting device capable of reducing impact during satellite-rocket separation |
| KR101864047B1 (en) * | 2016-12-07 | 2018-06-04 | 국방과학연구소 | Low-shock separation device |
Non-Patent Citations (1)
| Title |
|---|
| 丁继锋: "星箭分离缓冲设计方法及试验验证研究", 《强度与环境》 * |
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| CN110143298B (en) | 2020-10-09 |
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