CN110092012A - Satellite engine mounting bracket - Google Patents
Satellite engine mounting bracket Download PDFInfo
- Publication number
- CN110092012A CN110092012A CN201910223950.3A CN201910223950A CN110092012A CN 110092012 A CN110092012 A CN 110092012A CN 201910223950 A CN201910223950 A CN 201910223950A CN 110092012 A CN110092012 A CN 110092012A
- Authority
- CN
- China
- Prior art keywords
- strut
- connector
- hole
- chassis
- mounting bracket
- 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.)
- Pending
Links
- 238000010276 construction Methods 0.000 claims abstract description 7
- 238000009434 installation Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims 1
- 229910052719 titanium Inorganic materials 0.000 claims 1
- 239000010936 titanium Substances 0.000 claims 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 239000000956 alloy Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000004836 Glue Stick Substances 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary 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
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Connection Of Plates (AREA)
Abstract
The present invention provides a kind of satellite engine mounting brackets, which is characterized in that including chassis (1), strut (2) and connector (3)；Described strut (2) one end is connected with chassis (1), and the other end is connected with connector (3).Chassis (1) includes chassis body, through-hole, the first strut mounting hole and the first connector through-hole；Chassis body uses hollow design, and is provided with support construction.Strut (2) is designed using hollow round bar；Connector (3) includes adapter body, the second strut mounting hole and the second connector through-hole.The present invention uses split-type design, and structure type is simple, realizes structural function using a small amount of part, overall weight is low, safety, reliability are higher, have good mechanical characteristic, have the advantages that intensity is high, density is low, anticorrosive, low temperature resistant, high temperature resistant and thermal deformation are small.
Description
Technical field
The present invention relates to field of stents, and in particular, to satellite engine mounting bracket more particularly to a kind of novel light weight
Change satellite engine mounting bracket.
Background technique
It needs to install on satellite for providing the engine of power when satellite orbit shifts, engine is needed by one
Mounting bracket is mounted on satellite body, and the examination of the ground environments such as various tests, test, transport is undergone with whole star, is being sent out
The stage of penetrating need to undergo various vibrations, impact and the examination of thermal environment, will also undergo on planned orbit after eventually entering into space
Very long space environment examination.Therefore the mounting bracket of engine is one of satellite important feature, in-orbit normal to satellite is guaranteed
Operation etc. plays an important role.
With the development of space industry technology, the function of satellite, performance requirement are higher and higher, special to the weight of satellite structure
Property, functional characteristic, security feature have more harsh design requirement so that satellite engine support need have lighter weight
Amount higher bears acceleration, better high/low temperature stability and radiation resistance.Existing engine mounting bracket
Using all-metal material, number of parts is more, and structure type is complicated, is largely connected by screw bolts, and connector quantity is more, and bracket is whole
Preponderance, load-carrying efficiency is low, is unable to satisfy above-mentioned satellite function, property development demand.
Therefore, satellite engine mounting bracket is mitigating weight, is simplifying manufacturing process, raising load-carrying efficiency and increase just
Degree etc. needs to make further to be promoted.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of satellite engine mounting brackets.
A kind of satellite engine mounting bracket provided according to the present invention, including chassis, strut and connector；The strut
One end is connected with chassis, and the other end is connected with connector.
Preferably:
Chassis includes chassis body, middle through-hole, the first strut mounting hole and the first connector through-hole；Chassis body is adopted
With hollow design, and it is provided with support construction；
Strut is designed using hollow round bar；
Connector includes adapter body, the second strut mounting hole and the second connector through-hole；
One end of the strut is installed on the first strut mounting hole, and the other end of the strut is installed on the installation of the second strut
Hole.
Preferably:
The chassis quantity is 1；First connector number of openings is 6, is evenly distributed on around through-hole；The installation of first strut
Hole has 3 groups, is evenly distributed on chassis body, and every group of the first strut installation hole number is 2；
The strut quantity is 6；
The connector quantity is 1；It is 2 that second strut, which installs hole number,；Second connector number of openings is 9, is uniformly distributed
In adapter body.
Preferably, the chassis uses titanium alloy material；The strut and connector use carbon fibre composite.
Preferably, the first strut mounting hole, the second strut mounting hole internal diameter are identical as strut outer diameter, the first strut peace
Dress hole, the second strut mounting hole are connect with strut using bonding mode.
Preferably, the connector further includes pin hole；The pin hole is protrusively provided portion within a fitting.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, split-type design is used between satellite engine mounting bracket component provided by the invention, is connected using connector,
Have the advantages that structure is simple, realize structural function using a small amount of part, safety, reliability are higher, have good
Mechanical characteristic, material use is abundant；
2, satellite engine mounting bracket multiple portions provided by the invention use hollow structure, pass through the auxiliary of support construction
It helps, under the premise of not reducing the mechanical strength and extreme environment stability of structure, effectively reduces overall weight；
3, satellite engine mounting bracket provided by the invention has intensity height, low, anticorrosive, low temperature resistant, the resistance to height of density
Warm and small thermal deformation advantage.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the schematic top plan view of satellite engine mounting bracket provided by the invention；
Fig. 2 is the schematic front view of satellite engine mounting bracket provided by the invention；
Fig. 3 is the top cross-sectional view of satellite engine mounting bracket provided by the invention；
Fig. 4 is the perspective diagram of satellite engine mounting bracket center tap provided by the invention；
Fig. 5 is the perspective diagram on chassis in satellite engine mounting bracket provided by the invention.
It is shown in figure:
Chassis 1
Strut 2
Connector 3
Chassis body 11
Middle through-hole 12
First strut mounting hole 13
First connector through-hole 14
Support construction 15
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.
A kind of satellite engine mounting bracket provided according to the present invention, including chassis 1, strut 2 and connector 3；It is described
2 one end of strut is connected with chassis 1, and the other end is connected with connector 3.Chassis 1 includes chassis body 11, the support of middle through-hole 12, first
Bar mounting hole 13 and the first connector through-hole 14；Chassis body 11 uses hollow design, and is provided with support construction 15.Strut
2 are designed using hollow round bar；Connector 3 includes adapter body, the second strut mounting hole and the second connector through-hole.
Specifically, 1 quantity of chassis is 1；First connector number of openings is 6, is evenly distributed on around through-hole；First
Strut mounting hole has 3 groups, is evenly distributed on chassis body, and every group of the first strut installation hole number is 2；The number of strut 2
Amount is 6；3 quantity of connector is 1；It is 2 that second strut, which installs hole number,；Second connector number of openings is 9, is evenly distributed on
In adapter body.The chassis 1 uses titanium alloy material；The strut 2 and connector 3 use carbon fibre composite.Described
One strut mounting hole, the second strut mounting hole internal diameter are identical as 2 outer diameter of strut, the first strut mounting hole 13, the installation of the second strut
Hole is connect with strut 2 using bonding mode；Wherein, the splicing refers to that strut 2 is inserted into connector 3 or chassis 1, and uses glue
Stick connection.The connector 3 further includes pin hole；The pin hole is protrusively provided at 3 middle part of connector.
More specifically, as shown in Figure 1, a kind of satellite engine mounting bracket provided by the invention include chassis 1, strut 2,
Connector 3, chassis 1 are connect with strut 2, and one group of strut 2 connects a connector 3；The one of one connector 3 and one group of strut 2 and chassis 1
Part forms a Partial frame, and totally three Partial frames, which are distributed in around chassis, forms bracket entirety, wherein one group of support
Bar 2 includes two struts.Strut 2 and connector 3 are all carbon fibre composite, have in this way rigidity height, density it is low, it is corrosion-resistant,
The small advantage of thermal deformation.Chassis 1 is titanium alloy material, has the advantages that intensity height, high temperature resistant, low temperature resistant, erosion-resisting in this way.Bottom
1 appearance profile of disk is the leakage bowl shape of a curl hexagon, external thicker, and internal relatively thin, there is a circular through hole at center, this
Make chassis that there is good mechanical property, while lighter in weight.
Further, as shown in figure 3, the inside of chassis 1 is there are six hollow cavity, there is dot matrix support construction in hollow cavity,
So that chassis is reduced material utilization amount while there is high rigidity, high stability, reduces own wt.Strut 2 is Hollow circular beam, in this way
With good mechanical property and craftsmanship, stability is high and is easily installed.The present invention is for installing engine on satellite, and three
Connector 3 includes the installation interface of bracket and satellite, and bracket is mounted on satellite by connector, and chassis includes the installation with engine
Interface, engine are mounted on chassis；Bracket has good mechanical property and adaptability, provides for engine safe and reliable steady
Fixed working environment.
In conclusion structure of the invention form is simple, structural function is realized using a small amount of part, safety, can
By property height, and topology layout form is reasonable, and own material is utilized sufficiently, is born using a small amount of material compared with big load, whole
It is light-weight.
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 (6)
1. a kind of satellite engine mounting bracket, which is characterized in that including chassis (1), strut (2) and connector (3)；The support
Bar (2) one end is connected with chassis (1), and the other end is connected with connector (3).
2. satellite engine mounting bracket according to claim 1, it is characterised in that:
Chassis (1) includes chassis body (11), middle through-hole (12), the first strut mounting hole (13) and the first connector through-hole
(14)；Chassis body uses hollow design, and is provided with support construction (15)；
Strut (2) is designed using hollow round bar；
Connector (3) includes adapter body, the second strut mounting hole and the second connector through-hole；
One end of the strut (2) is installed on the first strut mounting hole, and the other end of the strut (2) is installed on the second strut peace
Fill hole.
3. satellite engine mounting bracket according to claim 2, it is characterised in that:
Chassis (1) quantity is 1；First connector number of openings is 6, is evenly distributed on around through-hole；The installation of first strut
Hole has 3 groups, is evenly distributed on chassis body, and every group of the first strut installation hole number is 2；
Strut (2) quantity is 6；
Connector (3) quantity is 1；It is 2 that second strut, which installs hole number,；Second connector number of openings is 9, is evenly distributed on
In adapter body.
4. satellite engine mounting bracket according to claim 2 or 3, which is characterized in that the chassis (1) is closed using titanium
Golden material；The strut (2) and connector (3) use carbon fibre composite.
5. satellite engine mounting bracket according to claim 2 or 3, which is characterized in that the first strut mounting hole,
Second strut mounting hole internal diameter is identical as strut (2) outer diameter, and the first strut mounting hole, the second strut mounting hole and strut (2) are adopted
It is connected with bonding mode.
6. satellite engine mounting bracket according to claim 1, which is characterized in that the connector (3) further includes pin hole；
The pin hole is protrusively provided in the middle part of connector (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910223950.3A CN110092012A (en) | 2019-03-22 | 2019-03-22 | Satellite engine mounting bracket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910223950.3A CN110092012A (en) | 2019-03-22 | 2019-03-22 | Satellite engine mounting bracket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110092012A true CN110092012A (en) | 2019-08-06 |
Family
ID=67444033
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910223950.3A Pending CN110092012A (en) | 2019-03-22 | 2019-03-22 | Satellite engine mounting bracket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110092012A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202124120U (en) * | 2011-05-24 | 2012-01-25 | 航天东方红卫星有限公司 | Ion thruster support |
| CN105659788B (en) * | 2011-02-22 | 2013-11-27 | 北京空间飞行器总体设计部 | A kind of metal mold orbit maneuver motor support for spacecraft |
| RU2621221C1 (en) * | 2015-12-22 | 2017-06-01 | Российская Федерация, от имени которой выступает Федеральное космическое агентство | Service system module |
| CN107701859A (en) * | 2017-08-30 | 2018-02-16 | 上海空间推进研究所 | Truss-like orbit maneuver motor frame |
| CN108082501A (en) * | 2017-12-13 | 2018-05-29 | 荆州市江汉众力实业有限公司 | A kind of portable engine support |
| CN208004202U (en) * | 2018-02-24 | 2018-10-26 | 秦皇岛兴龙轮毂有限公司 | Multi-purpose composite pallet |
-
2019
- 2019-03-22 CN CN201910223950.3A patent/CN110092012A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659788B (en) * | 2011-02-22 | 2013-11-27 | 北京空间飞行器总体设计部 | A kind of metal mold orbit maneuver motor support for spacecraft |
| CN202124120U (en) * | 2011-05-24 | 2012-01-25 | 航天东方红卫星有限公司 | Ion thruster support |
| RU2621221C1 (en) * | 2015-12-22 | 2017-06-01 | Российская Федерация, от имени которой выступает Федеральное космическое агентство | Service system module |
| CN107701859A (en) * | 2017-08-30 | 2018-02-16 | 上海空间推进研究所 | Truss-like orbit maneuver motor frame |
| CN108082501A (en) * | 2017-12-13 | 2018-05-29 | 荆州市江汉众力实业有限公司 | A kind of portable engine support |
| CN208004202U (en) * | 2018-02-24 | 2018-10-26 | 秦皇岛兴龙轮毂有限公司 | Multi-purpose composite pallet |
Non-Patent Citations (5)
| Title |
|---|
| 王扬: "《飞行器制造工艺与装备》", 30 June 2015 * |
| 苑世剑: "《精密热加工新技术》", 31 May 2016 * |
| 苑世剑: "《轻量化成形技术》", 30 September 2010 * |
| 陆新征: "《第24届全国结构工程学术会议论文集 第1册》", 31 October 2015 * |
| 马海泉: "复合材料桁架式发动机支架改进型设计分析", 《强度与环境》 * |
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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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190806 |
|
| RJ01 | Rejection of invention patent application after publication |