CN106382861A - Carrier rocket supporting cabin side wall carrying structure for installation of satellites of hundreds-of-kilogram grade - Google Patents
Carrier rocket supporting cabin side wall carrying structure for installation of satellites of hundreds-of-kilogram grade Download PDFInfo
- Publication number
- CN106382861A CN106382861A CN201611046440.6A CN201611046440A CN106382861A CN 106382861 A CN106382861 A CN 106382861A CN 201611046440 A CN201611046440 A CN 201611046440A CN 106382861 A CN106382861 A CN 106382861A
- Authority
- CN
- China
- Prior art keywords
- supporting cabin
- carrying
- side wall
- carrier rocket
- reinforcement
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Buildings Adapted To Withstand Abnormal External Influences (AREA)
Abstract
The invention discloses a carrier rocket supporting cabin side wall carrying structure for installation of satellites of a hundreds-of-kilogram grade. The carrier rocket supporting cabin side wall carrying structure comprises a supporting cabin, a carrying support, a mounting plate, a support reinforcement structure and a cabin body reinforcement structure, wherein the carrying support is connected with the outer side wall of the supporting cabin, the mounting plate is connected with the upper end face of the carrying support, the support reinforcement structure is installed inside the carrying support, and the cabin body reinforcement structure is installed on the inner side wall of the supporting cabin. The carrier rocket supporting cabin side wall carrying structure can carry satellites of the hundreds-of-kilogram grade for launching, and the beneficial effects that the form of the carrying structure is simplified, cost is reduced, and the carrying capacity is improved are achieved.
Description
Technical field
The present invention relates to a kind of carrier rocket supporting cabin side wall carrying structure, it is particularly suited for carrying and launch hundred feather weight left sides
Right satellite.
Background technology
At present, about hundred feather weight, moonlet lift-launch task gets more and more.Implement the transmitting of many stars in the past, have series connection and
Two kinds of layout type in parallel.Series connection transmitting, need to develop special carrying nacelle, conventional model be generally to increase transfer chamber and
Supporting cabin, then satellite is installed by adapter.Transmitting in parallel, needs to arrange " well " cabinet frame in supporting cabin upper end, both sides are respectively arranged
One satellite.
Because increased transfer chamber, supporting cabin and " well " cabinet frame etc. occupy the payload of rocket, therefore, reduce
The carrying capacity of rocket.And, series connection can increase the total height of rocket, unfavorable shadow can be produced to aspects such as its stability contorting
Ring.
Currently without the explanation finding technology similar to the present invention or report, also not yet collect the money being similar to both at home and abroad
Material.
Content of the invention
Carry and launch problem to solve moonlet, improve the useful space utilization rate of trouserss, present invention aim at
A kind of hundred feather weight Seeds of First Post-flight dischargers are provided.This apparatus structure is lightweight, and installation operation is convenient, and has higher
Structural strength and rigidity.
In order to reach foregoing invention purpose, the present invention provides a kind of carrier rocket to install the supporting cabin side of hundred feather weight satellites
Wall carrying structure, including：Supporting cabin, carrying bracket, installing plate, support reinforcement structure and nacelle reinforcement structure；Described carrying is propped up
Frame is connected with the lateral wall in supporting cabin；Described installing plate is connected with the upper surface of described carrying bracket；Described support reinforcement structure
It is installed on the inside of described carrying bracket；Described nacelle reinforcement structure its be installed on supporting cabin medial wall.
Further, described supporting cabin is semi-monocoque riveted structure, by front and back ends frame, middle boxes, stringer, eyelid covering etc. zero
Part rivets into frustum, and frustum has gathering hole, and supporting cabin cabin body sidewall is riveted with carrying bracket.
Further, described carrying bracket forms for the 2A12 aluminum alloy sheet metal component bending of 2.5mm thickness.Carrying bracket surrounding
Reserve flange for riveting with cabin body sidewall；All it is connected with nacelle stringer about carrying bracket, upper limb is connected with nacelle middle boxes,
Under because of nacelle reinforcement connect.Carrying bracket front and two sides have lightening core, and described mitigation bore edges make 8mm's
Flange is with strengthen rigidity；Each carrying bracket region all has 3 nacelle stringers to extend there through, and in order to avoid interfering, carries
On support, respective regions are opened stringer breach and are avoided.Stringer indentation, there rivets " L " shape gusset plate, by carrying bracket and stringer
Web connects.
Further, described installing plate is 7A09 aluminium sheet machined piece, and thickness is 5mm.Described installing plate and carrying bracket
The bolt connection by M6 for the upper surface；The installed surface flatness of installing plate reaches 0.1mm, and installed surface is flat with supporting cabin lower surface
Row degree reaches 20 '.
Further, described support reinforcement structure is the bar shaped reinforcement that section is " C " shape, using the 2A14 of 2mm thickness
Aluminium alloy panel beating bending forms；Described reinforcement is crisscross, horizontal 3, longitudinally 2, between reinforcement and reinforcement with
Pass through rivet interlacement between carrying bracket.
Further, described nacelle reinforcement structure is the bar shaped reinforcement that section is " L " shape, using the 7A09 of 3mm thickness
Aluminium alloy panel beating bending forms, and inside reinforcement riveting and supporting cabin eyelid covering, arranges 3 reinforcements along short transverse, for right
Supporting cabin carrying region carries out structural strengthening.
The supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket of the present invention, above-mentioned due to taking
Technical scheme, overcomes many star transmitting series, parallel layouts in prior art and takies rocket payload, satellite fairing utilization
The deficiency such as rate is low and operating process is complicated.Compared with prior art, the invention has the beneficial effects as follows：Simplify Seeds of First Post-flight transmitting
Version, improves carrying capacity and the space availability ratio of satellite fairing.
Brief description
Fig. 1 is the supporting cabin side wall carrying structure schematic diagram that hundred feather weight satellites installed by a kind of carrier rocket of the present invention；
Fig. 2 installs the supporting cabin side wall carrying structure skeleton schematic diagram of hundred feather weight satellites for carrier rocket.
Specific embodiment
In order to be fully clear from disclosing present invention, below in conjunction with the accompanying drawings the present invention is further elaborated.
Accompanying drawing 1,2 is the supporting cabin side wall carrying structure signal that hundred feather weight satellites installed by a kind of carrier rocket of the present invention
Figure.As shown in the embodiment of accompanying drawing, this device includes：Supporting cabin 1, carrying bracket 2, installing plate 3, support reinforcement structure 4, nacelle
Reinforcement structure 5.
Described supporting cabin 1 be semi-monocoque riveted structure, by front and back ends frame, middle boxes, stringer, joint, mouth frame these zero
Part rivets into frustum, and frustum has gathering hole.Described carrying bracket 2 is the 2A12 aluminum alloy sheet metal component bending of 2.5mm thickness
Form, support surrounding reserves flange for riveting with cabin body sidewall.Carrying bracket 2 provides mounting platform for Process of Piggyback Satellite, and will
Load is effectively delivered on supporting cabin 1.Described installing plate 3 is 7A09 aluminium sheet machined piece, and thickness is 5mm.Installing plate 3 is used for
The installation operation realizing Process of Piggyback Satellite requires, and provides higher morpheme size precision.
Described support reinforcement structure 4 is the bar shaped reinforcement that section is " C " shape, using the 2A14 aluminium alloy metal plate of 2mm thickness
Golden bending forms.This reinforcement structure is arranged at the enclosure interior of carrying bracket 2, and is connected with supporting cabin 1 load bearing frame, thus having
The reaching load of effect supports cabin 1.Described nacelle reinforcement structure 5 is the bar shaped reinforcement that section is " L " shape, using 3mm thickness
7A09 aluminium alloy panel beating bending form.Nacelle reinforcement structure 5 is arranged at internal carrying bracket 2 region of nacelle eyelid covering, will
The uniform load that carrying bracket 2 passes over is diffused into nacelle stringer nearby, effectively improves the bearing capacity of this device.
From the above mentioned, the present invention replaces existing many stars series, parallel layout due to carrying layout using supporting cabin side wall,
Not only reduce construction weight, carrying capacity is greatly improved, and simplify operating process, save the one-tenth newly grinding nacelle
This.Compared with prior art, this invention simplifies many stars carrying structure, improve the carrying capacity of rocket and satellite fairing
Space availability ratio, achieves and significantly improves.
Claims (10)
1. a kind of carrier rocket installs the supporting cabin side wall carrying structure of hundred feather weight satellites it is characterised in that including：Supporting
Cabin, carrying bracket, installing plate, support reinforcement structure and nacelle reinforcement structure；
Described carrying bracket is connected with the lateral wall in supporting cabin；
Described installing plate is connected with the upper surface of described carrying bracket；
Described support reinforcement structure is installed on the inside of described carrying bracket；
Described nacelle reinforcement structure its be installed on supporting cabin medial wall.
2. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 1, and it is special
Levy and be：Described supporting cabin is semi-monocoque riveted structure, is riveted into by parts such as front and back ends frame, middle boxes, stringer, eyelid coverings
Frustum, frustum has gathering hole, and supporting cabin cabin body sidewall is riveted with carrying bracket.
3. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 1, and it is special
Levy and be：Carrying bracket is that the 2A12 aluminum alloy sheet metal component bending of 2.5mm thickness forms.
4. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 1, and it is special
Levy and be：Described carrying bracket surrounding reserves flange for riveting with cabin body sidewall；About carrying bracket all with nacelle stringer even
Connect, upper limb is connected with nacelle middle boxes, under because of nacelle reinforcement connect.
5. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 4, and it is special
Levy and be：Described carrying bracket front and two sides have lightening core, and described mitigation bore edges make the flange of 8mm to strengthen
Rigidity；Each carrying bracket region all has 3 nacelle stringers to extend there through, in order to avoid interfering, corresponding on carrying bracket
Region is opened stringer breach and is avoided.
6. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 5, and it is special
Levy and be：Described stringer indentation, there rivets " L " shape gusset plate, and carrying bracket is connected with stringer web.
7. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 1, and it is special
Levy and be：Described installing plate is 7A09 aluminium sheet machined piece, and thickness is 5mm.
8. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 1, and it is special
Levy and be：Described installing plate and the bolt connection by M6 for the carrying bracket upper surface；The installed surface flatness of installing plate reaches
0.1mm, installed surface reaches 20 ' with the depth of parallelism of supporting cabin lower surface.
9. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 1, and it is special
Levy and be：Described support reinforcement structure is the bar shaped reinforcement that section is " C " shape, using the 2A14 aluminium alloy metal plate of 2mm thickness
Golden bending forms；Described reinforcement is crisscross, horizontal 3, longitudinally 2, between reinforcement and reinforcement and carrying bracket
Between pass through rivet interlacement.
10. the supporting cabin side wall carrying structure of hundred feather weight satellites installed by a kind of carrier rocket as claimed in claim 1, and it is special
Levy and be：Described nacelle reinforcement structure is the bar shaped reinforcement that section is " L " shape, using the 7A09 aluminium alloy metal plate of 3mm thickness
Golden bending forms, and inside reinforcement riveting and supporting cabin eyelid covering, arranges 3 reinforcements along short transverse, for taking to supporting cabin
Carry region and carry out structural strengthening.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611046440.6A CN106382861B (en) | 2016-11-23 | 2016-11-23 | A kind of carrier rocket installs the supporting cabin side wall carrying structure of hundred feather weight satellites |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611046440.6A CN106382861B (en) | 2016-11-23 | 2016-11-23 | A kind of carrier rocket installs the supporting cabin side wall carrying structure of hundred feather weight satellites |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106382861A true CN106382861A (en) | 2017-02-08 |
| CN106382861B CN106382861B (en) | 2018-04-06 |
Family
ID=57957713
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611046440.6A Active CN106382861B (en) | 2016-11-23 | 2016-11-23 | A kind of carrier rocket installs the supporting cabin side wall carrying structure of hundred feather weight satellites |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106382861B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791953A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | A kind of trapezoidal moonlet structure for adapting to carry |
| CN109466798A (en) * | 2018-11-19 | 2019-03-15 | 首都航天机械有限公司 | A kind of the arrow five-pointed star satellite bracket and assembly method of thin-wall construction |
| CN110887406A (en) * | 2019-10-25 | 2020-03-17 | 上海宇航系统工程研究所 | Transmitting device with multi-satellite parallel layout |
| CN112061421A (en) * | 2020-09-24 | 2020-12-11 | 上海宇航系统工程研究所 | Multi-satellite parallel transmitting device based on auxiliary support |
| CN116518795A (en) * | 2023-07-03 | 2023-08-01 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2636040A1 (en) * | 1988-09-06 | 1990-03-09 | Matra | Space vehicle for a mission in microgravity and method of experimentation using such a vehicle |
| US5566909A (en) * | 1993-09-08 | 1996-10-22 | Hughes Aircraft Company | System and method for deploying multiple probes |
| US5816539A (en) * | 1994-02-18 | 1998-10-06 | Lockheed Martin Corporation | Orbital assist module and interstage |
| RU2141436C1 (en) * | 1998-10-14 | 1999-11-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им.С.П.Королева" | Space vehicle for cleaning space from passive space vehicles and their fragments |
-
2016
- 2016-11-23 CN CN201611046440.6A patent/CN106382861B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2636040A1 (en) * | 1988-09-06 | 1990-03-09 | Matra | Space vehicle for a mission in microgravity and method of experimentation using such a vehicle |
| US5566909A (en) * | 1993-09-08 | 1996-10-22 | Hughes Aircraft Company | System and method for deploying multiple probes |
| US5816539A (en) * | 1994-02-18 | 1998-10-06 | Lockheed Martin Corporation | Orbital assist module and interstage |
| RU2141436C1 (en) * | 1998-10-14 | 1999-11-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им.С.П.Королева" | Space vehicle for cleaning space from passive space vehicles and their fragments |
Non-Patent Citations (1)
| Title |
|---|
| 陈振知 等: "长征四号乙/丙运载火箭多星发射技术现状与展望", 《上海航天》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791953A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | A kind of trapezoidal moonlet structure for adapting to carry |
| CN108791953B (en) * | 2018-06-15 | 2020-07-24 | 上海卫星工程研究所 | Trapezoidal minisatellite structure suitable for carrying |
| CN109466798A (en) * | 2018-11-19 | 2019-03-15 | 首都航天机械有限公司 | A kind of the arrow five-pointed star satellite bracket and assembly method of thin-wall construction |
| CN110887406A (en) * | 2019-10-25 | 2020-03-17 | 上海宇航系统工程研究所 | Transmitting device with multi-satellite parallel layout |
| CN110887406B (en) * | 2019-10-25 | 2022-04-01 | 上海宇航系统工程研究所 | Transmitting device with multi-satellite parallel layout |
| CN112061421A (en) * | 2020-09-24 | 2020-12-11 | 上海宇航系统工程研究所 | Multi-satellite parallel transmitting device based on auxiliary support |
| CN116518795A (en) * | 2023-07-03 | 2023-08-01 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
| CN116518795B (en) * | 2023-07-03 | 2023-09-15 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106382861B (en) | 2018-04-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106382861A (en) | Carrier rocket supporting cabin side wall carrying structure for installation of satellites of hundreds-of-kilogram grade | |
| US8915470B2 (en) | Aircraft nose and nose landing gear bay structure | |
| US10343768B2 (en) | Landing gear well roof | |
| RU2622304C2 (en) | Platform power structure of the spacecraft | |
| CN102015442A (en) | Method for attaching an aircraft floor module | |
| CN103879541A (en) | Aircraft Nose With Cockpit And Avionics Bay Modules Integrated Therein | |
| CN107651221A (en) | The strong maneuverable spacecraft configuration of hollow big carrying | |
| CN105667836B (en) | A kind of satellite pole structure | |
| CN105235916A (en) | Integration satellite compact in layout | |
| CN204776080U (en) | Double star parallels emitter of asymmetric overall arrangement | |
| CN205819334U (en) | A kind of lightweight automobile body-in-white | |
| CN107985560A (en) | A kind of aircraft main landing gear reinforced frame structure | |
| CN103192979B (en) | Aircraft tail beam transition section structure | |
| CN103112581B (en) | Based on the airtight cover cabin of Y8 freighter aircraft | |
| CN211543907U (en) | Water tank support structure | |
| CN107672778A (en) | A kind of unmanned plane forebody structure | |
| US20120074261A1 (en) | Fuselage arrangement, aircraft or spacecraft and method | |
| CN110887406B (en) | Transmitting device with multi-satellite parallel layout | |
| CN205916207U (en) | Automobile -used central channel divides assembly structure | |
| CN209382290U (en) | A kind of structure for pod for installing test equipment | |
| CN205952322U (en) | Civil aviation aircraft cabin luggage rack extends end | |
| CN110920872A (en) | Nose landing gear module for an aircraft and aircraft | |
| CN205574056U (en) | Chassis skeleton of car | |
| CN105620717B (en) | A kind of tilt rotor aircraft wing tip load diffusion structure | |
| CN109323837A (en) | A kind of adjustable interface load vibration test tooling |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |