CN106628252A - In-orbit aircraft structure of effective load adapter based on parallel arrangement - Google Patents
In-orbit aircraft structure of effective load adapter based on parallel arrangement Download PDFInfo
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- CN106628252A CN106628252A CN201610887759.5A CN201610887759A CN106628252A CN 106628252 A CN106628252 A CN 106628252A CN 201610887759 A CN201610887759 A CN 201610887759A CN 106628252 A CN106628252 A CN 106628252A
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- payload adapter
- cabin
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- installing plate
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- 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
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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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
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- Aviation & Aerospace Engineering (AREA)
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- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Photovoltaic Devices (AREA)
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Abstract
An in-orbit aircraft structure of an effective load adapter based on parallel arrangement comprises the effective load adapter (2) and separating structures (4); the effective load adapter (2) comprises a satellite support (5) and others; a cross beam (10) is installed on one end face of a supporting cabin (7), an instrument installing plate (9) is located on the lower end face of the center of the cross beam (10), solar cell array installing plates (6) are installed inside cross beam frames, shaped like the Chinese character 'kou', on the two sides of the instrument installing plate (9), and the satellite support (5) is arranged on the edges of the solar cell array installing plates (6); the separating structures (4) are distributed in the circumferential direction of a frame on the other end face of the supporting cabin (7), and connecting or separating is achieved through separating devices (11) installed on the separating structures (4). The effective load adapter serves as the in-orbit aircraft structure to expand tasks in an orbit, functions needed by task expanding are achieved, the degree of influences on a main launching task is decreased, and the in-orbit aircraft structure is formed.
Description
Technical field
The present invention relates to one kind stays orbit aerocraft structure.
Background technology
It is by earth surface by vehicles such as carrier rockets by spacecrafts such as satellites that the mankind explore the basic model of the outer space
Planned orbit is transported to, spacecraft is separated with vehicle, spacecraft starts to carry out operation on orbit.Generally, 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
Launch to planned orbit.Under traditional disposable space launch use pattern, vehicle final stage transmitting spacecraft gives up after entering the orbit
Abandon, exist using insufficient situation.
Payload adapter possesses light weight, is born as spacecraft and the transition connecting structure of vehicle final stage
The characteristics of flight environment of vehicle is preferable.By transforming payload support, orbit aerocraft platform is stayed as one kind, can fully be sent out
The in-orbit effect of vehicle final stage is waved, extends vehicle life cycle.
By staying orbit aerocraft based on parallel configuration's payload adapter, it is capable of achieving task and expands.As shown in figure 1,
After the transmitting of two spacecrafts 1 is entered the orbit and separated by vehicle final stage, payload adapter 2 is separated with vehicle final stage body 3,
As staying, orbit aerocraft is in-orbit to carry out expansion task to payload adapter 2.Therefore, need to be to parallel configuration's payload adapter
The structure transformation of the way is carried out, to realize staying orbit aerocraft task to expand.
The content of the invention
The technical problem to be solved in the present invention is：Overcome the deficiencies in the prior art, it is proposed that one kind is had based on parallel configuration
Imitate load adapter stays orbit aerocraft structure, and using payload adapter, as staying, orbit aerocraft is in-orbit to carry out expansion task,
Realize expanding required by task function, reduce to main launch mission influence degree, payload adapter is changed a social system, shape
Into staying orbit aerocraft structure.
The technical solution adopted in the present invention is：A kind of orbit aerocraft that stays based on parallel configuration's payload adapter is tied
Structure, including：Payload adapter, isolating construction；Payload adapter includes satellite support, solar battery array strake, props up
Support cabin, communication antenna, instrument installing plate, cross beam；Cross beam is arranged on one end end face for supporting cabin, and instrument installing plate is located at
Cross beam center lower end face, cross beam " mouth " the shape inframe of instrument installing plate both sides installs solar cell array installing plate, satellite
Support is along solar cell array installing plate edge and vertical with cross beam " mouth " shape frame；Communication antenna is installed on payload adaptation
Device is supported in cabin；Support cabin other end end face frame is circumferentially distributed isolating construction, and by isolating construction
Separator is realized connection or is separated.
The isolating construction is box-like structure, including two parts a, part is installed on payload adapter lower surface side
Outer frame side a, part is installed on vehicle final stage body upper surface outside, is installed by coordinating Planar realization docking, separator
Coordinating at plane, two parts of connection isolating construction.
The support cabin is taper type.
The support beam is arranged on the one end for supporting cabin diameter little, and end face is stretched out and by support bar and support cabin cone in both sides
Supporting construction is formed between face.
The separator is blasting bolt or separation nut.
Present invention advantage compared with prior art is：
(1) present invention stays orbit aerocraft platform by transforming payload support as one kind, can give full play to
The in-orbit effect of vehicle final stage, extends vehicle life cycle；Make full use of payload adapter to have more than needed installing space, pass through
Integrated electric device, realizes and stays orbit aerocraft basic function.
(2) present invention subtracts 104 connecting bolts are cancelled 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 altogether 3.3kg, still
Meet the requirement of final stage carrying capacity, do not affect former main task, risk is controllable.
(3) present invention is for the change of structure is including two aspects：First, payload adapter is supported into the change of cabin lower surface
For isolating construction；2nd, in body structure surface layout electrical equipment, little is changed to original effect load adapter main force support structure, for
Former main task affects less, and risk is controllable.
Description of the drawings
Fig. 1 separates schematic diagram to stay orbit aerocraft；
Fig. 2 is the device layout axis side view 1 of effectively adapter of the invention；
Fig. 3 is the device layout axis side view 2 of effectively adapter of the invention.
Fig. 4 is the attachment structure top view of original effect load adapter and vehicle final stage body；
Fig. 5 is original effect load adapter and A-A positions sectional view in the attachment structure top view of vehicle final stage body；
The isolating construction top view of Fig. 6 payload adapters of the present invention and vehicle final stage body；
Fig. 7 is that payload adapter of the present invention is cutd open with A-A positions in the isolating construction top view of vehicle final stage body
View.
Specific embodiment
Payload adapter 2 and the technique joint face of vehicle final stage body 3 are changed into parting surface；In payload adaptation
Layout expansion task device in the structure bay section of device 2.
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 fitted
Orchestration 2 includes satellite support 5, solar battery array strake 6, supports cabin 7, communication antenna 8, instrument installing plate 9, cross beam 10；Well
Word beam 10 is arranged on the upper surface that taper type supports cabin 7, and both sides are stretched out upper surface and pass through to be formed between support bar and the conical surface and prop up
Support structure, supports the little end face of the diameter of cabin 7 to be upper surface, and the big one end of diameter is lower end；In the cross beam of payload adapter 2
10 center lower end faces, install one piece of instrument installing plate 9, for installing electrical system equipment；The well word of the both sides of instrument installing plate 9
" mouth " shape of beam 10 inframe installs solar cell array installing plate 6, and satellite support 5 is along the edge of solar cell array installing plate 6 and well
" mouth " shape of word beam 10 frame is vertical, and solar cell array is arranged on solar cell array installing plate 6, positioned at the lower section of satellite support 5；
Communication antenna 8 is installed on payload adapter and supports in cabin 7.Support that the lower end frame of cabin 7 is circumferentially distributed isolating construction 4,
And connection and separation are realized by separator 11.The isolating construction 4 is box-like structure, is made up of two parts, and a part is installed
In the lower surface frame outside of payload adapter 2, a part is installed on the upper surface of vehicle final stage body 3 outside, when effective
After load adapter 2 is docked with vehicle final stage body 3, separator 11 is installed at box-like mechanism, and box-like structure is fastened
Install, and then payload adapter 2 is connected with vehicle final stage body 3.After separator 11 is unlocked, box-like knot is released
Structure is connected, and then payload adapter 2 is separated with vehicle final stage body 3.Separator 11 is blasting bolt or separation
Nut.
As shown in Figure 4, Figure 5, in original structure scheme, spiral shell is passed through between payload adapter 2 and vehicle final stage body 3
Tether and connect, parting surface therebetween is production breakdown interface, i.e., the two is on the ground only to realize that individually transport carries out dismounting and divides
From being connected by bolt after heaven, it is impossible to realize separating.To realize that structure is separated, cancel original bolt connection, such as Fig. 6, Fig. 7
Be replaced with 8 separators 11, the connection for realizing payload adapter and vehicle final stage body is unlocked, therebetween point
It is task parting surface from face, that is, the former two for entering the orbit is connected by 8 separators 11, after entering the orbit, the Explosive Solutions of separator 11
Lock, the two separation.To adapt to separator 11, near payload adapter 2 and the parting surface of vehicle final stage body 3 respectively
Design box-like structure, as isolating construction 4.
Further, since production breakdown interface is changed to task parting surface, former vehicle final stage body 3 and payload adapter 2
Between electric connector must be changed to separate connector, carry out electricity when payload adapter 2 is separated and come off or mechanical detachment.
Description of the invention unspecified part belongs to technology as well known to those skilled in the art.
Claims (5)
1. it is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter, it is characterised in that to include：Payload
Adapter (2), isolating construction (4)；Payload adapter (2) includes satellite support (5), solar battery array strake (6), support
Cabin (7), communication antenna (8), instrument installing plate (9), cross beam (10)；Cross beam (10) is installed in one end end for supporting cabin (7)
On face, instrument installing plate (9) is positioned at cross beam (10) center lower end face, the cross beam (10) " mouth " of instrument installing plate (9) both sides
Shape inframe installs solar cell array installing plate (6), and satellite support (5) is along solar cell array installing plate (6) edge and and well
Word beam (10) " mouth " shape frame is vertical；Communication antenna (8) is installed on payload adapter and supports in cabin (7)；Support cabin (7) another
End end face frame is circumferentially distributed isolating construction (4), and is realized by the separator (11) on isolating construction (4)
Connection is separated.
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
Levy and be：The isolating construction (4) is box-like structure, including two parts, and a part is installed on payload adapter (2) lower end
Face frame outside a, part is installed on vehicle final stage body (3) upper surface outside, by coordinating Planar realization docking, separates
Device (11) connects two parts of isolating construction (4) installed in coordinating at plane.
3. it is according to claim 1 and 2 it is a kind of orbit aerocraft structure is stayed based on parallel configuration's payload adapter, its
It is characterised by：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
Levy and be：The support beam (10) installed in the one end for supporting cabin (7) diameter little, stretch out end face and pass through support bar and prop up by both sides
Supporting construction is formed between support cabin (7) conical surface.
5. it is according to claim 1 and 2 it is a kind of orbit aerocraft structure is stayed based on parallel configuration's payload adapter, its
It is characterised by：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 |
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| 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 |
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| CN106628252A true CN106628252A (en) | 2017-05-10 |
| CN106628252B CN106628252B (en) | 2018-11-02 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050989A (en) * | 2018-08-29 | 2018-12-21 | 上海宇航系统工程研究所 | A kind of 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 |
| CN110749463A (en) * | 2019-10-08 | 2020-02-04 | 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 |
| 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 |
| CN113148241A (en) * | 2021-04-28 | 2021-07-23 | 北京星途探索科技有限公司 | Serial-type load adapter |
Citations (8)
| 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 |
| 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 |
-
2016
- 2016-10-11 CN CN201610887759.5A patent/CN106628252B/en active Active
Patent Citations (8)
| 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 |
| 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 |
|---|
| 汪玮: "运载火箭加速级复合材料载荷承力结构优化设计", 《中国学位论文全文数据库》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050989A (en) * | 2018-08-29 | 2018-12-21 | 上海宇航系统工程研究所 | A kind of 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 |
| CN110749463A (en) * | 2019-10-08 | 2020-02-04 | 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 |
| 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 |
| 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 |
| CN113148241A (en) * | 2021-04-28 | 2021-07-23 | 北京星途探索科技有限公司 | Serial-type load adapter |
| CN113148241B (en) * | 2021-04-28 | 2023-08-11 | 北京星途探索科技有限公司 | Series load adapter |
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| CN106628252B (en) | 2018-11-02 |
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