CN106628252B - It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter - Google Patents
It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter Download PDFInfo
- Publication number
- CN106628252B CN106628252B CN201610887759.5A CN201610887759A CN106628252B CN 106628252 B CN106628252 B CN 106628252B CN 201610887759 A CN201610887759 A CN 201610887759A CN 106628252 B CN106628252 B CN 106628252B
- Authority
- CN
- China
- Prior art keywords
- payload adapter
- mounting plate
- cross beam
- orbit
- face
- 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.)
- Active
Links
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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Photovoltaic Devices (AREA)
- Details Of Aerials (AREA)
Abstract
It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter, including：Payload adapter (2), separated structure (4)；Payload adapter (2) includes satellite holder (5) etc.；Cross beam (10) is mounted on one end end face of support cabin (7), instrument mounting plate (9) is located at cross beam (10) center lower end face, installation solar cell array mounting plate (6) in cross beam (10) " mouth " shape frame of instrument mounting plate (9) both sides, satellite holder (5) is along solar cell array mounting plate (6) edge；Support cabin (7) the other end face frame is circumferentially distributed separated structure (4), and the realization of the separator (11) by being mounted on separated structure (4) connects or separates.Using payload adapter as staying, orbit aerocraft is in-orbit to carry out expansion task to the present invention, realizes and expands required by task function, reduces to main launch mission influence degree, form and stay orbit aerocraft structure.
Description
Technical field
The present invention relates to one kind staying orbit aerocraft structure.
Background technology
The basic model that the mankind explore the outer space is by spacecrafts such as satellites by vehicles such as carrier rockets by earth surface
It is transported to planned orbit, spacecraft is detached with vehicle, and spacecraft starts to carry out operation on orbit.Under normal circumstances, carrier rocket
By plural serial stage tandem type structure composition, the flight of what rocket before afterbody (i.e. final stage) relay of carrier rocket, by spacecraft
Emit to planned orbit.Under traditional disposable space launch use pattern, vehicle final stage transmitting spacecraft is i.e. useless after entering the orbit
It abandons, there is a situation where using insufficient.
Transition connecting structure of the payload adapter as spacecraft and vehicle final stage, has light weight, is born
The preferable feature of flight environment of vehicle.By the way that payload holder is transformed, orbit aerocraft platform is stayed as one kind, can fully be sent out
The in-orbit effect of vehicle final stage is waved, vehicle life cycle is extended.
By staying orbit aerocraft, it can be achieved that task is expanded based on parallel configuration's payload adapter.As shown in Figure 1,
After two transmittings of spacecraft 1 are entered the orbit and detached by vehicle final stage, payload adapter 2 is detached with vehicle final stage ontology 3,
Payload adapter 2, which is used as, stays orbit aerocraft is in-orbit to carry out expansion task.It therefore, need to be to parallel configuration's payload adapter
Structure restructuring is carried out, stays orbit aerocraft task to expand to realize.
Invention content
The technical problem to be solved by the present invention is to：Overcome the deficiencies in the prior art, it is proposed that one kind is had based on parallel configuration
Effect load adapter stays orbit aerocraft structure, and using payload adapter as staying, orbit aerocraft is in-orbit carries out expansion task,
It realizes and expands required by task function, reduce to main launch mission influence degree, payload adapter is restructured, shape
At staying orbit aerocraft structure.
The technical solution adopted in the present invention is：It is a kind of that orbit aerocraft knot is stayed based on parallel configuration's payload adapter
Structure, including：Payload adapter, separated structure；Payload adapter includes satellite holder, solar battery array strake, branch
Support cabin, communication antenna, instrument mounting plate, cross beam；Cross beam is mounted on one end end face in support cabin, and instrument mounting plate is located at
Cross beam center lower end face, cross beam " mouth " the shape frame of instrument mounting plate both sides is interior to install solar cell array mounting plate, satellite
Holder is along solar cell array mounting plate edge and vertical with cross beam " mouth " shape frame；Communication antenna is installed on payload adaptation
Device supports in cabin；Cabin the other end face frame is circumferentially distributed separated structure for support, and by separated structure
Separator realization connects or separates.
The separated structure is box-like structure, including two parts, a part be installed on payload adapter lower face side
Outer frame side, a part are installed on the outside of vehicle final stage ontology upper surface, by coordinating Planar realization docking, separator installation
At cooperation plane, two parts of separated structure are connected.
The support cabin is taper type.
The supporting beam is mounted on the small one end of support cabin diameter, and both sides stretch out end face and by supporting rod and support cabin cone
Support construction is formed between face.
The separator is blasting bolt or separation nut.
The advantages of the present invention over the prior art are that：
(1) present invention staying orbit aerocraft platform as one kind, can give full play to by the way that payload holder is transformed
The in-orbit effect of vehicle final stage extends vehicle life cycle；It makes full use of payload adapter to have more than needed installation space, passes through
Integrated electric device realizes and stays orbit aerocraft basic function.
(2) present invention subtracts 104 connection bolts cancellations between payload adapter and vehicle final stage in original structure
Light weight 1.8kg is changed to 8 blasting bolts or separation nut and corresponding mounting structure, and increase weight 5.1kg, and increase weight 3.3kg altogether, still
Meet the requirement of final stage carrying capacity, does not influence former main task, risk is controllable.
(3) present invention includes two aspects for the change of structure：One, by payload adapter support cabin lower face change
For separated structure；Two, it is laid out electrical equipment in body structure surface, it is small to the change of original effect load adapter main force support structure, for
Former main task influence is smaller, and risk is controllable.
Description of the drawings
Fig. 1 is that orbit aerocraft is stayed to detach schematic diagram；
Fig. 2 is the device layout axis side view 1 of the present invention effectively adapter；
Fig. 3 is the device layout axis side view 2 of the present invention effectively adapter.
Fig. 4 is the connection structure vertical view of original effect load adapter and vehicle final stage ontology；
Fig. 5 is original effect load adapter and the positions A-A sectional view in the connection structure vertical view of vehicle final stage ontology；
The separated structure vertical view of Fig. 6 payload adapter of the present invention and vehicle final stage ontology；
Fig. 7 is that payload adapter of the present invention is cutd open with the positions A-A in the separated structure vertical view of vehicle final stage ontology
View.
Specific implementation mode
Payload adapter 2 and 3 technique joint face of vehicle final stage ontology are changed to parting surface；It is adapted in payload
Layout expansion task device in 2 structure bay section of device.
It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter, including effective load adapter 2, point
From structure 4；As shown in Figure 2 and Figure 3, according to mission requirements, layout electrical equipment is needed on payload adapter 2.Payload is suitable
Orchestration 2 includes satellite holder 5, solar battery array strake 6, support cabin 7, communication antenna 8, instrument mounting plate 9, cross beam 10；Well
Word beam 10 is mounted on the upper surface in taper type support cabin 7, and both sides stretch out upper surface and by forming branch between supporting rod and the conical surface
Support structure, the small end face of support 7 diameter of cabin are upper surface, and the big one end of diameter is lower end；In 2 cross beam of payload adapter
10 center lower end faces, the instrument mounting plate 9 of one piece of installation, for installing electrical system equipment；The well word of 9 both sides of instrument mounting plate
Installation solar cell array mounting plate 6 in " mouth " shape of beam 10 frame, satellite holder 5 is along 6 edge of solar cell array mounting plate and well
Word beam 10 " mouth " shape frame is vertical, and solar cell array is mounted on solar cell array mounting plate 6, is located at 5 lower section of satellite holder；
Communication antenna 8 is installed in payload adapter support cabin 7.7 lower end frame of cabin is circumferentially distributed separated structure 4 for support,
And connection and separation are realized by separator 11.The separated structure 4 is box-like structure, is consisted of two parts, part installation
On the outside of 2 lower face frame of payload adapter, a part is installed on the outside of 3 upper surface of vehicle final stage ontology, when effective
After load adapter 2 is docked with vehicle final stage ontology 3, separator 11 is installed at box-like mechanism, and box-like structure is fastened
Installation, and then payload adapter 2 is made to be connect with vehicle final stage ontology 3.After separator 11 unlocks, box-like knot is released
Structure is connected, and then payload adapter 2 is made to be detached with vehicle final stage ontology 3.Separator 11 is blasting bolt or separation
Nut.
As shown in Figure 4, Figure 5, in original structure scheme, pass through spiral shell between payload adapter 2 and vehicle final stage ontology 3
It tethers and connects, parting surface between the two is production breakdown interface, i.e., the two is only to realize individually to transport to carry out dismounting point on the ground
From being connected by bolt after heaven, cannot achieve separation.To realize structure separation, cancellation is original to be bolted, such as Fig. 6, Fig. 7
8 separators 11 are replaced with, realize that payload adapter and the connection of vehicle final stage ontology unlock, point between the two
Be task parting surface from face, that is, the former two to enter the orbit is connected by 8 separators 11, after entering the orbit, 11 Explosive Solutions of separator
Lock, the two separation.To adapt to separator 11, near payload adapter 2 and 3 parting surface of vehicle final stage ontology respectively
Box-like structure is designed, as separated structure 4.
In addition, since production breakdown interface is changed to task parting surface, former vehicle final stage ontology 3 and payload adapter 2
Between electric connector must be changed to separate connector, electricity is carried out when payload adapter 2 detaches and is fallen off or mechanical detachment.
Description of the invention unspecified part belongs to technology well known to those skilled in the art.
Claims (5)
1. a kind of staying orbit aerocraft structure based on parallel configuration's payload adapter, which is characterized in that including：Payload
Adapter (2), separated structure (4)；Payload adapter (2) include satellite holder (5), solar cell array mounting plate (6),
Support cabin (7), communication antenna (8), instrument mounting plate (9), cross beam (10)；Cross beam (10) is mounted on the one of support cabin (7)
It holds on end face, instrument mounting plate (9) is located at cross beam (10) center lower end face, the cross beam (10) of instrument mounting plate (9) both sides
Installation solar cell array mounting plate (6) in " mouth " shape frame, satellite holder (5) along solar cell array mounting plate (6) edge and
It is vertical with cross beam (10) " mouth " shape frame；Communication antenna (8) is installed in payload adapter support cabin (7)；It supports cabin (7)
The other end face frame is circumferentially distributed separated structure (4), and the separator (11) by being mounted on separated structure (4)
Realization connects or separates.
2. it is according to claim 1 it is a kind of orbit aerocraft structure is stayed based on parallel configuration's payload adapter, it is special
Sign is：The separated structure (4) is box-like structure, including two parts, a part be installed on payload adapter (2) lower end
On the outside of the frame of face, a part is installed on the outside of vehicle final stage ontology (3) upper surface, by coordinating Planar realization docking, separation
Device (11) is mounted at cooperation plane, two parts of connection separated structure (4).
3. it is according to claim 1 or 2 it is a kind of orbit aerocraft structure is stayed based on parallel configuration's payload adapter,
It is characterized in that：The support cabin (7) is taper type.
4. it is according to claim 3 it is a kind of orbit aerocraft structure is stayed based on parallel configuration's payload adapter, it is special
Sign is：The cross beam (10) is mounted on the small one end of support cabin (7) diameter, and both sides stretch out end face and by supporting rod and branch
Support construction is formed between support cabin (7) conical surface.
5. it is according to claim 1 or 2 it is a kind of orbit aerocraft structure is stayed based on parallel configuration's payload adapter,
It is characterized in that：The separator (11) is blasting bolt or separation nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610887759.5A CN106628252B (en) | 2016-10-11 | 2016-10-11 | It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610887759.5A CN106628252B (en) | 2016-10-11 | 2016-10-11 | It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106628252A CN106628252A (en) | 2017-05-10 |
| CN106628252B true CN106628252B (en) | 2018-11-02 |
Family
ID=58855166
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610887759.5A Active CN106628252B (en) | 2016-10-11 | 2016-10-11 | It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106628252B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050989B (en) * | 2018-08-29 | 2021-07-27 | 上海宇航系统工程研究所 | Double-star point type adapter |
| CN109969431A (en) * | 2019-02-28 | 2019-07-05 | 北京空间飞行器总体设计部 | A kind of integrated bracket of embedded device layout installation |
| CN110749463B (en) * | 2019-10-08 | 2021-06-15 | 上海宇航系统工程研究所 | Rocket final-stage utilization platform system and rail-remaining measuring and utilizing method thereof |
| 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 |
| CN112061421B (en) * | 2020-09-24 | 2022-07-01 | 上海宇航系统工程研究所 | Multi-satellite parallel transmitting device based on auxiliary support |
| CN113148241B (en) * | 2021-04-28 | 2023-08-11 | 北京星途探索科技有限公司 | Series load adapter |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101687553A (en) * | 2006-12-11 | 2010-03-31 | 迈克尔·D·约翰逊 | modular spacecraft |
| KR20100047530A (en) * | 2008-10-29 | 2010-05-10 | 한국항공우주연구원 | Supporting body for propulsion module of satellite |
| CN102372094A (en) * | 2010-08-17 | 2012-03-14 | 上海卫星工程研究所 | Shell type adapter |
| 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 |
| CN204223195U (en) * | 2014-10-31 | 2015-03-25 | 北京宇航系统工程研究所 | Discrete point type satellite adapter |
| CN204776080U (en) * | 2015-06-01 | 2015-11-18 | 上海宇航系统工程研究所 | Double star parallels emitter of asymmetric overall arrangement |
| CN105711856A (en) * | 2016-04-13 | 2016-06-29 | 中国人民解放军国防科学技术大学 | Multifunctional star arrow adapter |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050109878A1 (en) * | 2002-03-28 | 2005-05-26 | Dutch Space B.V. | Spacecraft and method for building such a spacecraft and an adapter to be used in such a spacecraft |
-
2016
- 2016-10-11 CN CN201610887759.5A patent/CN106628252B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101687553A (en) * | 2006-12-11 | 2010-03-31 | 迈克尔·D·约翰逊 | modular spacecraft |
| KR20100047530A (en) * | 2008-10-29 | 2010-05-10 | 한국항공우주연구원 | Supporting body for propulsion module of satellite |
| CN102372094A (en) * | 2010-08-17 | 2012-03-14 | 上海卫星工程研究所 | Shell type adapter |
| 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 |
| CN204223195U (en) * | 2014-10-31 | 2015-03-25 | 北京宇航系统工程研究所 | Discrete point type satellite adapter |
| CN204776080U (en) * | 2015-06-01 | 2015-11-18 | 上海宇航系统工程研究所 | Double star parallels emitter of asymmetric overall arrangement |
| CN105711856A (en) * | 2016-04-13 | 2016-06-29 | 中国人民解放军国防科学技术大学 | Multifunctional star arrow adapter |
Non-Patent Citations (1)
| Title |
|---|
| 运载火箭加速级复合材料载荷承力结构优化设计;汪玮;《中国学位论文全文数据库》;20111230;第8-9页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106628252A (en) | 2017-05-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106628252B (en) | It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter | |
| US9957068B2 (en) | Multiple space vehicle launch system | |
| US5350138A (en) | Low-cost shuttle-derived space station | |
| CN110525688B (en) | On-orbit reconfigurable extensible satellite system | |
| CN111003211B (en) | Spacecraft configuration capable of being assembled and expanded in orbit | |
| JP2014530144A (en) | Propulsion bay | |
| US20080149777A1 (en) | Piggyback equipment panel payload arrangement, a device for and method of attaching a hosted secondary piggyback payload and adapter to be used for a piggyback secondary payload arrangement for launching the piggyback equipment panel secondary | |
| CN106374995A (en) | Space application communication platform based on rail retaining last stage of carrier rocket | |
| US12017804B2 (en) | Satellite launch system | |
| CN103612774A (en) | Separable micro and nano-satellite configuration | |
| WO2009148625A2 (en) | Space station, launch vehicle, and method of assembly | |
| CN109927936B (en) | Static orbit satellite with load isolated from platform thermal deformation | |
| US9796484B2 (en) | Satellite system comprising two satellites attached to each other and method for launching them into orbit | |
| CN111619827A (en) | Inflatable expansion type living cabin for spacecraft | |
| CN102717901B (en) | Separation type many device combinations Mars probes structure and forming method thereof | |
| US5813632A (en) | Salvage hardware apparatus and method for orbiting objects | |
| CN105775166A (en) | I-shaped satellite platform | |
| US20050109878A1 (en) | Spacecraft and method for building such a spacecraft and an adapter to be used in such a spacecraft | |
| RU2627904C2 (en) | Method and device for collecting objects in space with rings and lattice surfaces and method of conclusion of objects in space with flexible, for example, mesh-membrane surfaces | |
| CN107792395B (en) | Radome fairing main satellite integrated large-caliber deployable spacecraft | |
| CN210942315U (en) | Carrier rocket fairing | |
| CN110887406B (en) | Transmitting device with multi-satellite parallel layout | |
| CN114771874A (en) | Nuclear power satellite configuration | |
| CN114735248A (en) | Conical top cover pull type recovery suborbital carrier rocket | |
| CN111559519B (en) | Ultra-long wave astronomical observation satellite and array configuration thereof |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |