CN106864773A - A kind of instrument cabin structure of vehicle - Google Patents
A kind of instrument cabin structure of vehicle Download PDFInfo
- Publication number
- CN106864773A CN106864773A CN201710210857.XA CN201710210857A CN106864773A CN 106864773 A CN106864773 A CN 106864773A CN 201710210857 A CN201710210857 A CN 201710210857A CN 106864773 A CN106864773 A CN 106864773A
- Authority
- CN
- China
- Prior art keywords
- instrument
- frame
- jet pipe
- instrument room
- room shell
- 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
- 238000005422 blasting Methods 0.000 claims abstract description 12
- 238000009434 installation Methods 0.000 claims abstract description 11
- 238000010146 3D printing Methods 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 4
- 238000007493 shaping process Methods 0.000 claims description 2
- 238000010276 construction Methods 0.000 description 3
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The invention discloses a kind of instrument cabin structure of vehicle, including instrument room shell, covering is provided with the outside of instrument room shell, the top and bottom of instrument room shell are respectively equipped with upper end frame and lower end frame, some upper blasting bolt boxes and lower blasting bolt box are respectively equipped with the outside of the outside of upper end frame and lower end frame, some hinge seats are also associated with the outside of the frame of upper end, pan is equipped with each hinge seat, the inside of instrument room shell is respectively equipped with Nei Lu upper ends Kuang Henei roads lower end frame, Nei Lu upper ends frame is connected by some support beams with instrument room shell, the upper end of support beam is provided with instrument and installs version, Nei Lu lower ends frame is connected by stringer with instrument room shell, the lower end of instrument room shell is provided with some big jet pipe mounting interfaces, small jet pipe mounting interface and gas cylinder installation position and bearing.Instrument cabin structure of the present invention alleviates the stability of weight holding structure on the premise of bearing requirements are ensured of structure while integrally improving shell section carrying capacity.
Description
Technical field
The present invention relates to vehicle instrument room technical field, it particularly relates to a kind of instrument cabin structure of vehicle.
Background technology
Common carrier rocket shell segment structure is mostly a segment structure, middle without the requirement of other design objectives, may only be realized
The requirement of carrying, it is not possible to which the installation of instrument and equipment and the bearing requirements of middle part are provided；In addition, in General Instrument cabin structure
Instrument and equipment is side hanging or cantilevered, therefore can not meet the requirement to load environment condition, and with structure bulky
Shortcoming.
The content of the invention
For the above-mentioned technical problem in correlation technique, the present invention proposes a kind of instrument cabin structure of vehicle, Neng Gouke
Take the above-mentioned deficiency of prior art.
To realize above-mentioned technical purpose, the technical proposal of the invention is realized in this way：
A kind of instrument cabin structure of vehicle, including instrument room shell, are provided with covering, the instrument on the outside of the instrument room shell
The top and bottom of device shell out of my cabin are respectively equipped with upper end frame and lower end frame, the outside of the upper end frame and the outside difference of lower end frame
Some upper blasting bolt boxes and lower blasting bolt box are provided with, some hinge seats are also associated with the outside of the upper end frame, it is described every
Pan is equipped with one hinge seat, the inside of the instrument room shell is respectively equipped with Nei Lu upper ends Kuang Henei roads lower end frame,
Nei Lu upper ends frame is connected by some support beams with instrument room shell, and the upper end of the support beam is provided with instrument and installs version,
Nei Lu lower ends frame is connected by stringer with instrument room shell, and the lower end of the instrument room shell is provided with some big jet pipe peaces
Attaching mouthful, small jet pipe mounting interface and gas cylinder installation position and bearing.
Further, the support beam has eight, is trapezoidal support beam.
Preferably, some lightening holes are equipped with described each support beam.
Further, big jet pipe mounting interface and small jet pipe mounting interface have 20, respectively along instrument room shell
Axially, radially and tangentially set.
Further, the big jet pipe mounting interface and small jet pipe mounting interface pass through aluminum alloy forge piece with instrument out of my cabin
The stringer of shell, covering or lower end frame are connected.
Further, described big jet pipe mounting interface and small jet pipe mounting interface are using titanium alloy 3D printing shaping.
Further, described each hinge seat includes 2 hinge plates being separated by, and is equipped with hinge on each hinge plate
Hole.
Beneficial effects of the present invention：Instrument room shell mechanism uses covering, stringer semi-monocoque construction form, overall to improve shell
The weight of structure is alleviated while section carrying capacity；Centre supports engine and satellite using trapezoidal backbar support structure
Load weight, ensure bearing requirements on the premise of holding structure stability.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
The accompanying drawing for needing to use is briefly described, it should be apparent that, drawings in the following description are only some implementations of the invention
Example, for those of ordinary skill in the art, on the premise of not paying creative work, can also obtain according to these accompanying drawings
Obtain other accompanying drawings.
Fig. 1 is a kind of structural representation of the instrument cabin structure of vehicle described according to embodiments of the present invention；
Fig. 2 is a kind of structural representation of the instrument room structure bottom point of the vehicle described in the embodiment of the present invention；
In figure：1st, covering；2nd, upper end frame；3rd, lower end frame；4th, Nei Lu upper ends frame；5th, upper blasting bolt box；6th, lower blasting bolt box；
7th, Nei Lu lower ends frame；8th, hinge seat；9th, stringer；10th, small jet pipe mounting interface；11st, bearing；12nd, big jet pipe mounting interface；13、
Gas cylinder installation position；14th, support beam.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained belongs to present invention protection
Scope.
As shown in Figure 1-2, the instrument cabin structure of a kind of vehicle described according to embodiments of the present invention, including instrument is out of my cabin
Shell, is provided with covering 1 on the outside of the instrument room shell, the top and bottom of the instrument room shell are respectively equipped with the He of upper end frame 2
Lower end frame 3, the outside of the upper end frame 2 and the outside of lower end frame 3 are respectively equipped with some upper blasting bolt boxes 5 and lower blasting bolt
Box 6, is also associated with some hinge seats 8 on the outside of the upper end frame, pan is equipped with described each hinge seat 8, described
The inside of instrument room shell is respectively equipped with Nei Lu upper ends frame 4 and Nei Lu lower ends frame 7, and Nei Lu upper ends frame 4 is by some supports
Beam 14 is connected with instrument room shell, and the upper end of the support beam is provided with instrument and installs version, and Nei Lu lower ends frame 7 passes through stringer 9
It is connected with instrument room shell, the lower end of the instrument room shell is provided with some big jet pipe mounting interfaces 12, the installation of small jet pipe and connects
Mouth 10, gas cylinder installation position 13 and bearing 11.
In one embodiment, the support beam 14 has eight, is trapezoidal support beam.
In one embodiment, some lightening holes are equipped with described each support beam 14.
In one embodiment, big jet pipe mounting interface 12 and small jet pipe mounting interface 10 have 20, respectively edge
The axial direction of instrument room shell, radially and tangentially set.
In one embodiment, the big jet pipe mounting interface 12 and small jet pipe mounting interface 10 are forged by aluminium alloy
The stringer 9 of part and instrument room shell, covering 1 or lower end frame 3 are connected.
In one embodiment, described big jet pipe mounting interface 12 and small jet pipe mounting interface 10 use titanium alloy
3D printing is molded.
In one embodiment, described each hinge seat 8 includes 2 hinge plates being separated by, and on each hinge plate
It is equipped with pan.
Understand above-mentioned technical proposal of the invention for convenience, below by way of in specifically used mode to of the invention above-mentioned
Technical scheme is described in detail.
When specifically used, according to a kind of vehicle instrument cabin structure of the present invention, covering 1 is carried in overall structure
During play a part of antitorque and increase stability, upper end frame 2 and lower end frame 3 be distributed with blasting bolt box 5 and under
Blasting bolt box 6 and hinge seat 8, play a part of and the connection of rocket other section structures and separate；Stringer 9 is instrument room knot
The main load bearing component of structure, assume responsibility in structure about 90% load, Nei Lu upper ends frame 4 and the composition instrument room knot of Nei Lu lower ends frame 7
Gou Nei roads carry branch, carry the load of satellite and engine, and eight supports are had between interior road-load lotus and from outside load
Beam 14, plays a part of connection and carries, and it is also each other that instrument installation and operation provide installing space, in shell section
Lower end is that bearing 11, big jet pipe mounting interface 12, small jet pipe mounting interface 10 and gas cylinder installation position 13 provide installation site, office
Portion's structure strengthen for increasing the stiffness characteristics around attitude control.
Wherein, vehicle instrument room bearing capacity aspect, instrument room shell mechanism uses covering, stringer semi-monocoque construction shape
Formula, alleviates the weight of structure while overall raising shell section carrying capacity；Centre is using the support of trapezoidal backbar support structure
The load weight of engine and satellite, from outside branched structure will hold the load of rocket radome fairing, interior road bifurcation load is carried
The load of engine and satellite is carried, two-way load is merged and collected, is delivered in the substructure of rocket by this kind of structure,
The stability of holding structure on the premise of bearing requirements are ensured.
Attitude control mounting structure is designed, and instrument cabin structure has the important function for attitude control will to provide installing space and expire
The control requirement of sufficient attitude control, has 20 mounting interfaces of attitude control jet pipe, respectively along the axle of shell section in the instrument cabin structure
To, radial direction, tangential distribution.According to the high-precision requirement of posture control system, big rigidity, highly reliable installation site are provided for it,
High-strength aluminum alloy forging is used in this structure by attitude control nozzle carrier and instrument room shell segment structure stringer, covering, hypomere frame phase
Even, local stiffness characteristics are improve, and the tube-in-tube structure of attitude control jet pipe is molded using with titanium alloy 3D printing, not only reduces
Structure takes weight, and improves the anti-thermal characteristics of whole shell section.
Instrument cable mounting structure is designed, and structure of the present invention devises instrument installing plate in the upper end of support beam, i.e., rationally
The narrow and small installing space of rocket body structure be make use of again for accurate instrument and equipment provides good load environment condition, the present invention
Instrument cabin structure, by medial fascicle and external shell connection rational in infrastructure, creative utilization support beam structure sets for instrument
It is standby that mounting platform and follow-up operative space are provided.
In sum, instrument room shell mechanism uses covering, stringer semi-monocoque construction form, overall to improve shell section delivery energy
The weight of structure is alleviated while power；Centre supports the load weight of engine and satellite using trapezoidal backbar support structure
Amount, the stability of holding structure on the premise of bearing requirements are ensured.
Presently preferred embodiments of the present invention is the foregoing is only, is not intended to limit the invention, it is all in essence of the invention
Within god and principle, any modification, equivalent substitution and improvements made etc. should be included within the scope of the present invention.
Claims (7)
1. the instrument cabin structure of a kind of vehicle, including instrument room shell, it is characterised in that set on the outside of the instrument room shell
There is covering（1）, the top and bottom of the instrument room shell are respectively equipped with upper end frame（2）With lower end frame（3）, the upper end frame
（2）Outside and lower end frame（3）Outside be respectively equipped with some upper blasting bolt boxes（5）With lower blasting bolt box（6）, it is described on
Some hinge seats are also associated with the outside of the frame of end（8）, described each hinge seat（8）On be equipped with pan, the instrument room
The inside of shell is respectively equipped with Nei Lu upper ends frame（4）With Nei Lu lower ends frame（7）, Nei Lu upper ends frame（4）By some supports
Beam（14）It is connected with instrument room shell, the upper end of the support beam is provided with instrument and installs version, Nei Lu lower ends frame（7）By purlin
Bar（9）It is connected with instrument room shell, the lower end of the instrument room shell is provided with some big jet pipe mounting interfaces（12）, small jet pipe
Mounting interface（10）, gas cylinder installation position（13）And bearing（11）.
2. a kind of instrument cabin structure of vehicle according to claim 1, it is characterised in that the support beam（14）It is total
Eight, it is trapezoidal support beam.
3. a kind of instrument cabin structure of vehicle according to claim 2, it is characterised in that described each support beam（14）
On be equipped with some lightening holes.
4. a kind of instrument cabin structure of vehicle according to claim 1, it is characterised in that big jet pipe mounting interface（12）
With small jet pipe mounting interface（10）Have 20, respectively along instrument room shell axial direction, radially and tangentially set.
5. a kind of instrument cabin structure of vehicle according to claim 1, it is characterised in that the big jet pipe mounting interface
（12）With small jet pipe mounting interface（10）By aluminum alloy forge piece and the stringer of instrument room shell（9）, covering（1）Or lower end
Frame（3）It is connected.
6. the instrument cabin structure of a kind of vehicle according to claim 5, it is characterised in that described big jet pipe is installed and connect
Mouthful（12）With small jet pipe mounting interface（10）Using titanium alloy 3D printing shaping.
7. a kind of instrument cabin structure of vehicle according to claim 1, it is characterised in that described each hinge seat
（8）Including 2 hinge plates being separated by, and pan is equipped with each hinge plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710210857.XA CN106864773B (en) | 2017-03-31 | 2017-03-31 | A kind of instrument cabin structure of vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710210857.XA CN106864773B (en) | 2017-03-31 | 2017-03-31 | A kind of instrument cabin structure of vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106864773A true CN106864773A (en) | 2017-06-20 |
| CN106864773B CN106864773B (en) | 2018-05-22 |
Family
ID=59159883
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710210857.XA Active CN106864773B (en) | 2017-03-31 | 2017-03-31 | A kind of instrument cabin structure of vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106864773B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108725844A (en) * | 2018-06-26 | 2018-11-02 | 北京蓝箭空间科技有限公司 | The control cabin structure of space launch vehicle |
| CN109050983A (en) * | 2018-08-31 | 2018-12-21 | 上海宇航系统工程研究所 | It is a kind of to support that big quality bilayer propulsion die is installed and the freighter of carrying promotes cabin structure |
| CN111846290A (en) * | 2020-08-06 | 2020-10-30 | 北京中科宇航技术有限公司 | Carrier rocket and launching support tail section thereof |
| CN114659415A (en) * | 2022-03-01 | 2022-06-24 | 航天科工火箭技术有限公司 | Lightweight cabin section structure of carrier |
| CN114812290A (en) * | 2022-05-24 | 2022-07-29 | 湖北航天技术研究院总体设计所 | Integrated structure of fairing and rocket adapter and carrier rocket |
| CN116428077A (en) * | 2023-03-16 | 2023-07-14 | 大连理工大学 | Main frame structure of carrier rocket engine with I-shaped section load beam |
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| JP3979456B2 (en) * | 1998-07-24 | 2007-09-19 | 独立行政法人 宇宙航空研究開発機構 | Bundling control device for deployable frame structure |
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| CN102303710A (en) * | 2011-06-08 | 2012-01-04 | 航天东方红卫星有限公司 | General propelling module for small satellites |
| CN104260903A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Propelling module structure with independent high-rail satellite platform function |
| CN206926839U (en) * | 2017-03-31 | 2018-01-26 | 北京蓝箭空间科技有限公司 | A kind of instrument cabin structure of vehicle |
-
2017
- 2017-03-31 CN CN201710210857.XA patent/CN106864773B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3979456B2 (en) * | 1998-07-24 | 2007-09-19 | 独立行政法人 宇宙航空研究開発機構 | Bundling control device for deployable frame structure |
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| CN102303710A (en) * | 2011-06-08 | 2012-01-04 | 航天东方红卫星有限公司 | General propelling module for small satellites |
| CN104260903A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Propelling module structure with independent high-rail satellite platform function |
| CN206926839U (en) * | 2017-03-31 | 2018-01-26 | 北京蓝箭空间科技有限公司 | A kind of instrument cabin structure of vehicle |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108725844A (en) * | 2018-06-26 | 2018-11-02 | 北京蓝箭空间科技有限公司 | The control cabin structure of space launch vehicle |
| CN109050983A (en) * | 2018-08-31 | 2018-12-21 | 上海宇航系统工程研究所 | It is a kind of to support that big quality bilayer propulsion die is installed and the freighter of carrying promotes cabin structure |
| CN111846290A (en) * | 2020-08-06 | 2020-10-30 | 北京中科宇航技术有限公司 | Carrier rocket and launching support tail section thereof |
| CN114659415A (en) * | 2022-03-01 | 2022-06-24 | 航天科工火箭技术有限公司 | Lightweight cabin section structure of carrier |
| CN114659415B (en) * | 2022-03-01 | 2024-02-09 | 航天科工火箭技术有限公司 | Light cabin section structure of carrier |
| CN114812290A (en) * | 2022-05-24 | 2022-07-29 | 湖北航天技术研究院总体设计所 | Integrated structure of fairing and rocket adapter and carrier rocket |
| CN116428077A (en) * | 2023-03-16 | 2023-07-14 | 大连理工大学 | Main frame structure of carrier rocket engine with I-shaped section load beam |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106864773B (en) | 2018-05-22 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20170704 Address after: 100085, C, No. 28, No. two, information road, Beijing, Haidian District, 02B-492 Applicant after: BEIJING LANDSPACETECH Co.,Ltd. Address before: 100085, C, No. 28, No. two, information road, Beijing, Haidian District, 02B-492 Applicant before: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. |
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| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181024 Address after: 710077 East Building, four floor, aerospace science and technology, civil and integration innovation center, 32 United South Road, Xi'an, Shaanxi Patentee after: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. Address before: 100085 02B-492, information block C, seat 28 (two level), Haidian District, Beijing. Patentee before: BEIJING LANDSPACETECH Co.,Ltd. |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240517 Address after: 100076 H1, AVIC International Plaza, No.13 Ronghua South Road, Daxing District, Beijing Economic and Technological Development Zone Patentee after: Blue Arrow Space Technology Co.,Ltd. Country or region after: China Address before: 710077 East Building, four floor, aerospace science and technology, civil and integration innovation center, 32 United South Road, Xi'an, Shaanxi Patentee before: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. Country or region before: China |