WO2008147461A1 - Modular spacecraft - Google Patents
Modular spacecraft Download PDFInfo
- Publication number
- WO2008147461A1 WO2008147461A1 PCT/US2007/086451 US2007086451W WO2008147461A1 WO 2008147461 A1 WO2008147461 A1 WO 2008147461A1 US 2007086451 W US2007086451 W US 2007086451W WO 2008147461 A1 WO2008147461 A1 WO 2008147461A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- adapter section
- forward adapter
- interface plane
- spacecraft
- launch vehicle
- Prior art date
Links
- 230000008878 coupling Effects 0.000 claims description 43
- 238000010168 coupling process Methods 0.000 claims description 43
- 238000005859 coupling reaction Methods 0.000 claims description 43
- 230000007246 mechanism Effects 0.000 claims description 31
- 238000000926 separation method Methods 0.000 claims description 6
- 238000003032 molecular docking Methods 0.000 abstract description 14
- 238000010276 construction Methods 0.000 abstract description 6
- 230000008901 benefit Effects 0.000 description 10
- 238000000034 method Methods 0.000 description 6
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 description 1
- 229910052753 mercury Inorganic materials 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- 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
- B64G1/223—Modular spacecraft systems
-
- 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
Definitions
- This disclosure relates in general to the field of spacecraft, and more particularly to modular spacecraft with launch vehicle interfaces that also function as berthing or docking interfaces for the spacecraft.
- spacecraft launch interfaces include some form of a dual ring structure with a separation plane between the rings.
- Some form of releasable clamp or clamp-band is used to hold the two rings together while the launch vehicle is transporting the spacecraft to orbit.
- the releasable clamp or clamp-band releases, and a set of preloaded springs pushes the launch vehicle and spacecraft interface rings apart, thus releasing the spacecraft into orbit.
- a docking or berthing interface is usually provided as a separate subsystem from the launch vehicle interface.
- Centaur upper stage originally flown in the early 1960's, continues to be flown to this day.
- This high performance upper stage has a structural mass fraction of 0.92. In other words, only 8% of the total mass of the vehicle is devoted to structural and propulsion elements.
- An excellent example of the structural efficiency is the mass of the tank dome is less than 200 pounds, yet it supports a load of approximately 46 thousand pounds.
- the Centaur also contains a full avionics suite to operate as an autonomous spacecraft including a three-axis stabilized guidance and control system and monopropellant reaction control system. Many of these Centaur components and subsystems could be further utilized for spacecraft construction.
- the disclosed subject matter provides an improved modular spacecraft launch vehicle interface that also functions as a berthing/docking interface and a secondary payload carrier, utilizing existing spaceflight-qualified hardware to minimize cost and schedule constraints while meeting diverse mission requirements.
- the disclosed subject matter provides a modular spacecraft.
- the modular spacecraft includes a top forward adapter section with a top outer interface plane ring and a top inner interface plane ring; a top tank dome coupled to the top forward adapter section; at least one tank segment coupled to the top tank dome; and a bottom tank dome coupled to the tank segment(s).
- the bottom tank dome has an opening (e.g. a hatch), providing access to a pressurized section of the modular spacecraft.
- the modular spacecraft further includes a bottom forward adapter section, inverted for coupling to the bottom tank dome, comprising a bottom outer interface plane ring and a bottom inner interface plane ring, for coupling to a forward adapter section of a launch vehicle.
- the modular spacecraft includes a bottom coupling mechanism (e.g. a berthing, docking or any other connecting mechanism), coupled to the bottom forward adapter section, located concentrically with both the bottom inner interface plane ring and the bottom outer interface plane ring.
- a bottom coupling mechanism e.g. a berthing, docking or any other connecting mechanism
- An alternative embodiment includes an additional top coupling mechanism coupled to the top forward adapter section.
- Another alternative embodiment includes a truss coupled to the bottom forward adapter section and a rear support plate coupled to the truss. The rear support plate is used as a separation system.
- a separable forward adapter section is included for coupling to the rear support plate along with an adapter for coupling the separable forward adapter section to a forward adapter section of a launch vehicle.
- Alternative embodiments include using the bottom inner interface plane ring or the bottom outer interface plane ring as a launch vehicle interface for coupling the bottom forward adapter section to the launch vehicle.
- alternative embodiments include an additional outer interface plane class satellite payload; standard interface plane (SIP) class satellite payload(s), or Common Cargo Carrier payload(s) coupled to the top forward adapter section.
- Alternative embodiments also include the use of 5- m fairing or 4-m fairing launch vehicles.
- FIGURE Ia is a phantom side view an embodiment of the configuration of a Passive Common Berthing Mechanism (PCBM) with a Standard Interface Plane (SIP) and a 120-inch interface plane;
- PCBM Passive Common Berthing Mechanism
- SIP Standard Interface Plane
- FIGURE Ib is a perspective side view of an embodiment of the configuration of a
- PCBM with a SIP and a 120-inch interface plane
- FIGURE 2a is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter on a Centaur upper stage;
- FIGURE 2b is an exploded component view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter including a Centaur upper stage;
- FIGURE 2c is an exploded view of additional components used with an embodiment of a two pressurized segment spacecraft of the disclosed subject matter;
- FIGURE 2d is a phantom side view of an embodiment of a two pressurized segment spacecraft of the disclosed subject matter installed on a Centaur upper stage;
- FIGURE 3a is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter installed on a 5-m fairing Atlas V/Centaur launch vehicle;
- FIGURE 3b is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter installed on a 4-m fairing Atlas V/Centaur launch vehicle;
- FIGURE 4a is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter in combination with a 120-inch class primary satellite payload on a 5-m fairing launch vehicle;
- FIGURE 4b is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter in combination with a SIP class primary satellite payload on a
- FIGURE 4c is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter in combination with a 120-inch class primary satellite payload on a 4-m fairing launch vehicle;
- FIGURE 4d is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter in combination with a SIP class primary satellite payload on a
- FIGURE 5a is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter in combination with a single segment Common Cargo Carrier (CCC) payload on a 4-m fairing launch vehicle;
- CCC Common Cargo Carrier
- FIGURE 5b is a phantom side view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter in combination with a triple segment CCC payload on a 5-m fairing launch vehicle;
- FIGURE 5c is a phantom side view of an embodiment of a double pressurized segment spacecraft of the disclosed subject matter in combination with a triple segment CCC payload on a 5-m fairing launch vehicle;
- FIGURE 6a is a phantom side view of an embodiment of a double pressurized segment spacecraft of the disclosed subject matter in combination with a triple segment CCC payload berthed to an ISS module;
- FIGURE 6b is a phantom side view of an embodiment of two double pressurized segment spacecraft of the disclosed subject matter berthed together and to an ISS module;
- FIGURE 7a is a phantom side view of an alternate embodiment of a single pressurized segment spacecraft of the disclosed subject matter on a Centaur upper stage; and
- FIGURE 7b is an exploded component view of an alternate embodiment of a single pressurized segment spacecraft of the disclosed subject matter including a Centaur upper stage.
- the disclosed subj ect matter relates to an improved modular spacecraft with launch vehicle interface that also functions as a berthing/docking interface and a secondary payload carrier, utilizing existing spaceflight-qualified hardware in a modular fashion to minimize cost and schedule constraints while meeting diverse mission requirements.
- Existing spaceflight-qualified Atlas V/Centaur components are described in the embodiments below. However, a person of ordinary skill in the art would understand that alternative existing spaceflight-qualified hardware may also be used.
- the disclosed subject matter uses outer interface plane rings and inner interface plane rings.
- a standard interface plane (SIP) ring is used for the inner interface plane rings in the embodiments described below.
- a 120-inch ring is used for the outer interface plane rings in the embodiments described below.
- the disclosed subject matter uses coupling mechanisms.
- the coupling mechanisms may be a passive common berthing mechanism (PCBM) or an active common berthing mechanism (ACBM).
- PCBM passive common berthing mechanism
- ACBM active common berthing mechanism
- a berthing, docking or any other connecting mechanism may be used as the coupling mechanism.
- the disclosed subject matter utilizes existing spaceflight-qualified
- Centaur Forward Adapter Section as well as propellant tank components, avionics and propulsion systems in combination with a Passive Common Berthing Mechanism (PCBM).
- PCBM Passive Common Berthing Mechanism
- SIP interface ring is located within the diameter of the PCBM and a 120-inch interface ring is located outside the diameter of the PCBM.
- the PCBM as well as the SIP and 120-inch interface rings are located on the aft end of the spacecraft.
- the forward end of the spacecraft may include a similar structure where an Active Common Berthing Mechanism (ACBM) is concentrically located with a SIP and 120- inch interface ring set.
- ACBM Active Common Berthing Mechanism
- FIGURE 1 a is a phantom side view of an embodiment of the configuration of coupling mechanism PCBM 100 with inner interface plane ring (SIP ring) 110 and outer interface plane ring (120- inch interface plane ring) 120; while FIGURE Ib is a perspective side view.
- PCBM 100 is attached to the launch vehicle forward adapter section (Centaur Forward Adapter) 130 by a suitable flange, among other alternatives.
- SIP 110 and 120-inch interface plane 120 are part of the off-the-shelf Centaur Forward Adapter 130 and are unaltered.
- a top tank dome (Centaur Tank Dome) 140 may be connected to Centaur Forward Adapter 130 in conventional fashion.
- FIGURE 2a is a phantom side view of an embodiment of a single pressurized segment spacecraft assembly 200 of the disclosed subject matter installed on a Centaur upper stage 210.
- FIGURE 2b is an exploded component view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter including a Centaur upper stage 210.
- a top forward adapter section (Centaur Forward Adapter) 130 is attached to Centaur Tank Dome 140.
- Centaur Tank Dome 140 is attached to a tank segment (in the embodiment shown, a 36-inch long Centaur Tank Segment) 230 which is further attached to a bottom tank dome (Centaur Tank Dome) 240.
- An inverted Centaur Forward Adapter (bottom forward adapter section) 130 forms the rear attach portion of the spacecraft.
- PCBM 100 is concentrically located to SIP 110 and 120-inch interface plane 120.
- Tunnel opening (i.e. hatch) 220 connects PCBM 100 to Centaur Tank Dome 240.
- the entire spacecraft is mounted to a launch vehicle forward adapter section 210 (in the embodiment shown, this is identical in construction to Centaur Forward Adapter 130) via the SIP 110.
- SIP 110 and 120-inch interface plane 120 utilize conventional spacecraft separation systems such as clamp bands, pyrotechnic bolts, etc. as is well known in the art and available off the shelf.
- An additional adapter (e.g. a C-13, C-22, etc.) 280 may be placed between the two SIP planes 110 of the Centaur forward adapter 210 and the aft facing Centaur forward adapter 130 to facilitate ground handling and launch vehicle interface.
- FIGURE 2c is an exploded view of additional components used with an embodiment of a two pressurized segment spacecraft of the disclosed subject matter.
- ACBM 260 forward tunnel 220, Centaur Tank Dome 140, two 36-inch long Centaur Tank Segments 230, Centaur Tank Dome 240 and a
- FIGURE 2d is a phantom side view of an embodiment of a two pressurized segment spacecraft 270 according of the disclosed subject matter installed on a Centaur upper stage 210.
- FIGURE 3a is a phantom side view of an embodiment of a single pressurized segment spacecraft 200 of the disclosed subject matter installed on a 5-m fairing 300 Atlas V/Centaur launch vehicle.
- the launch vehicle Centaur Forward Adapter 210 is essentially emulated on the front of the spacecraft 200 using the methods of construction described earlier. Utilization of a 120-inch payload attach fitting truss enhances the stiffness of the structure in the case of the 5-meter fairing 300.
- FIGURE 3b is a phantom side view of a single pressurized segment spacecraft 200 of the disclosed subject matter installed on a 4-m fairing 310 Atlas V/Centaur launch vehicle.
- the launch vehicle Centaur Forward Adapter 210 is essentially emulated on the front of the spacecraft 200 using the methods of construction described earlier.
- a SIP is used in the case of the 4-meter fairing 310, as the boat tail of fairing 310 interfaces with the 120-inch payload attach fitting.
- FIGURE 4a is a phantom side view of an embodiment of a single pressurized segment spacecraft 200 of the disclosed subject matter in combination with a 120-inch class primary satellite payload 410 on a 5-m fairing launch vehicle. This illustration shows how the spacecraft 200 emulates the forward launch vehicle attach system 210 forward of spacecraft 200. Two 120-inch payload attach fittings 250 and 400 are utilized to maximize stiffness of the assembly.
- FIGURE 4b is a phantom side view of an embodiment of a single pressurized segment spacecraft 200 of the disclosed subject matter in combination with a SIP class primary satellite payload 420 on a 5-m fairing launch vehicle.
- This illustration shows how the spacecraft 200 emulates the forward launch vehicle attach system 210 forward of spacecraft 200.
- One 120-inch payload attach fitting 250 is utilized to maximize stiffness of the assembly.
- SIP class primary satellite payload 420 is attached to the SIP forward of spacecraft 200.
- FIGURE 4c is a phantom side view of an embodiment of a single pressurized segment spacecraft 200 of the disclosed subject matter in combination with a 120-inch class primary satellite payload 410 on a 4-m fairing launch vehicle. This illustration shows how the spacecraft 200 emulates the forward launch vehicle attach system 210 forward of spacecraft 200.
- Spacecraft 400 is used to attach to the 120-inch class primary satellite payload 410 to maximize stiffness of the assembly.
- Spacecraft 200 is attached to the launch vehicle 210 via SIP.
- FIGURE 4d is a phantom side view of an embodiment of a single pressurized segment spacecraft 200 of the disclosed subject matter in combination with a SIP class primary satellite payload 420 on a 4-m fairing launch vehicle.
- This illustration shows how the spacecraft 200 emulates the forward launch vehicle attach system 210 forward of spacecraft 200.
- SIP is used to attach to the SIP class primary satellite payload 420 to spacecraft 200.
- Spacecraft 200 is attached to the launch vehicle 210 via SIP.
- FIGURE 5a is a phantom side view of an embodiment of a single pressurized segment spacecraft 200 of the disclosed subject matter in combination with a single segment Common Cargo
- Carrier (CCC) payload 500 on a 4-m failing launch vehicle The CCC 500 is a modular system designed to carry ISS external Orbital Replacement Units (ORUs) for installation on the outside of the ISS.
- ORUs Orbital Replacement Units
- CCC 500 may also carry any other payload that may be desired.
- Spacecraft 200 is attached to the launch vehicle 210 via SIP.
- FIGURE 5b is a phantom side view of an embodiment of a single pressurized segment spacecraft 200 of the disclosed subject matter in combination with a triple segment CCC payload 500 on a 5-m fairing launch vehicle.
- Spacecraft 200 attaches to the launch vehicle 210 via 120-inch payload attach fitting 250.
- FIGURE 5c is a phantom side view of an embodiment of a double pressurized segment spacecraft 270 of the disclosed subject matter in combination with a triple segment CCC payload 500 on a 5-m fairing launch vehicle.
- Spacecraft 270 attaches to the launch vehicle 210 via 120-inch payload attach fitting 250.
- FIGURE 6a is a phantom side view of an embodiment of a double pressurized segment spacecraft 270 of the disclosed subject matter in combination with a triple segment CCC payload 500 berthed to an ISS module 600.
- PCBM 100 attaches to ACBM 260 and holds spacecraft 270 in position as well as providing crew access to the pressurized section of spacecraft 270.
- FIGURE 6b is a phantom side view of an embodiment of two double pressurized segment spacecraft 270 of the disclosed subject matter berthed together and to an ISS module 600.
- FIGURE 7a is a phantom side view of an embodiment of a single pressurized segment spacecraft assembly 200 of the disclosed subject matter installed on a Centaur upper stage 210. This configuration utilizes attachment at the 120-inch interface plane while the spacecraft assembly 200 is contained under a 4-m fairing.
- FIGURE 7b is an exploded component view of an embodiment of a single pressurized segment spacecraft of the disclosed subject matter including a Centaur upper stage 210. Centaur Forward
- Adapter 130 is attached to Centaur Tank Dome 140. Centaur Tank Dome 140 is attached to a 36-inch Centaur Tank Segment 230 which is further attached to a Centaur Tank Dome 240.
- An inverted Centaur Forward Adapter 130 forms the rear attach portion of the spacecraft.
- PCBM 100 is concentrically located to SIP 110 and 120-inch interface plane 120. Tunnel 220 connects SIP 110 to Centaur Tank Dome 240.
- PCBM 100 is attached to adapter 720 which is attached to SIP 110.
- Truss 700 is attached to rear support plate 710. Rear support plate 710 interfaces via a separation system (e.g. pyrotechnic bolts) with an aft facing Centaur forward adapter 730.
- a separation system e.g. pyrotechnic bolts
- the entire spacecraft is mounted to a launch vehicle forward adapter section 210 (in the embodiment shown, this is identical in construction to Centaur Forward Adapter 130) via the adapter 740 (e.g. a C-13, C-22, etc. adapter ring).
- the 120-inch interface plane at rear support plate 710 utilizes conventional spacecraft separation systems such as pyrotechnic bolts, etc. as is well known in the art and available off the shelf.
- mission requirements are first analyzed to determine the proper configuration of spacecraft required for a specific mission.
- the modular nature of the spacecraft permits mission specific customization. For example, if a large amount of pressurized cargo is required, two 36-in. Centaur Tank segments 230 may be utilized to carry additional pressurized payload. Other mission requirements may result in the utilization of alternative configurations of spacecraft.
- Another advantage in the operation of the spacecraft of the disclosed subject matter is the ability to lower launch costs by maximizing the utilization of the launch vehicle capability.
- a particular satellite may require the use of an Atlas V 401 launch vehicle. If this launch could be combined with a version of the spacecraft of the disclosed subject matter and launched on a larger launch vehicle (for example, an Atlas V 521), the launch cost of the satellite may be reduced by a factor of 30% while simultaneously reducing the launch costs of the spacecraft of the disclosed subject matter.
- Yet another advantage of the operation of the spacecraft of the disclosed subj ect matter is lower costs resulting from a reduction of the amount of engineering and analysis required by utilizing flight proven hardware.
- Non-recurring engineering effort is minimized by using the proven Centaur components. This also has the advantage of using the existing assembly line for the Centaur stage to manufacture spacecraft components without the added capital expense of a new assembly line (e.g. welders, jigs, tooling, etc.).
- a new assembly line e.g. welders, jigs, tooling, etc.
- Yet another advantage of the operation of the spacecraft of the disclosed subj ect matter is the flexibility of launch vehicle utilization provided by the two launch vehicle interfaces. As with the spacecraft, the launch vehicle may be tailored to the specific mission to maximize performance and minimize cost.
- a further advantage of the operation of the spacecraft of the disclosed subject matter is that the modules may be attached to existing space stations and used to increase the overall volume and living space of orbiting laboratories at relatively low cost.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN200780050550A CN101687553A (en) | 2006-12-11 | 2007-12-05 | modular spacecraft |
AU2007354271A AU2007354271A1 (en) | 2006-12-11 | 2007-12-05 | Modular spacecraft |
JP2009540437A JP2011502845A (en) | 2006-12-11 | 2007-12-05 | Modular spacecraft |
CA002672472A CA2672472A1 (en) | 2006-12-11 | 2007-12-05 | Modular spacecraft |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US87410706P | 2006-12-11 | 2006-12-11 | |
US60/874,107 | 2006-12-11 | ||
US11/950,269 | 2007-12-04 | ||
US11/950,269 US7780119B2 (en) | 2006-12-11 | 2007-12-04 | Modular spacecraft |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2008147461A1 true WO2008147461A1 (en) | 2008-12-04 |
Family
ID=40075424
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2007/086451 WO2008147461A1 (en) | 2006-12-11 | 2007-12-05 | Modular spacecraft |
Country Status (7)
Country | Link |
---|---|
US (1) | US7780119B2 (en) |
JP (1) | JP2011502845A (en) |
CN (1) | CN101687553A (en) |
AU (1) | AU2007354271A1 (en) |
CA (1) | CA2672472A1 (en) |
RU (1) | RU2009126595A (en) |
WO (1) | WO2008147461A1 (en) |
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EP4039598A1 (en) * | 2021-02-03 | 2022-08-10 | The Boeing Company | Direct mount of secondary payload adapters to truss structure common to space vehicle payload adapter |
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FR2945515B1 (en) * | 2009-05-12 | 2012-06-01 | Astrium Sas | SYSTEM COMPRISING A MOTHER SPACE PROBE FORMING CARRIER SPACE VEHICLE AND A PLURALITY OF SPATIAL GIRL PROBES |
WO2013015840A1 (en) * | 2011-07-23 | 2013-01-31 | Excalibur Almaz Usa, Inc. | Capsule system, service module, and reuseable reentry payload and docking module |
FR2972423B1 (en) * | 2011-03-09 | 2014-01-31 | Astrium Sas | METHOD AND SYSTEM FOR LAUNCHING A SATELLITE |
KR101353787B1 (en) * | 2011-12-26 | 2014-01-22 | 주식회사 포스코 | Ultra high strength colde rolled steel sheet having excellent weldability and bendability and method for manufacturing the same |
US8720830B1 (en) * | 2012-01-30 | 2014-05-13 | United Launch Alliance, L.L.C. | Efficient solar panel wing-stowage on a space launch vehicle |
US8807485B2 (en) | 2012-06-07 | 2014-08-19 | The Boeing Company | Systems for interconnecting dual manifested spacecraft |
CN103129751A (en) * | 2013-01-18 | 2013-06-05 | 上海卫星工程研究所 | Design method and system of spacecraft based on split-type configuration |
US9434485B1 (en) * | 2013-01-25 | 2016-09-06 | Stephen C. Lehocki | Multi-purpose cargo delivery and space debris removal system |
DE102014104695A1 (en) * | 2014-04-02 | 2015-10-08 | Rheinisch-Westfälische Technische Hochschule (Rwth) Aachen | Androgyne coupling device for connecting modules and corresponding modules |
CN104266856B (en) * | 2014-09-23 | 2016-08-31 | 北京强度环境研究所 | Two grades of band cover free boundaries and radome fairing built-in boundary implementation in vibration tower |
FR3041939B1 (en) * | 2015-10-02 | 2017-10-20 | Airbus Defence & Space Sas | SATELLITE COMPRISING OPTICAL OPTICAL INSTRUMENT |
CN108367816A (en) * | 2015-12-18 | 2018-08-03 | 空中客车防务和空间公司 | Payload adaptation ring |
CN107585330A (en) * | 2016-07-06 | 2018-01-16 | 北京空间技术研制试验中心 | Multi-functional manned lunar surface's lander based on modularized design |
RU2634496C1 (en) * | 2016-08-05 | 2017-10-31 | Акционерное общество "Научно-производственное объединение им. С.А.Лавочкина" | Fuel tank |
US10214303B1 (en) * | 2016-09-27 | 2019-02-26 | Space Systems/Loral, Llc | Low cost launch vehicle fairing |
CN106628252B (en) * | 2016-10-11 | 2018-11-02 | 北京宇航系统工程研究所 | It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter |
US11072441B2 (en) | 2017-03-03 | 2021-07-27 | Northrop Grumman Systems Corporation | Stackable spacecraft |
CN108313334B (en) * | 2018-02-02 | 2021-03-23 | 西北工业大学 | Electromechanical and thermal integrated isomorphic interface for multi-surface butt joint of modular spacecraft |
CN112061423B (en) * | 2020-08-09 | 2022-07-01 | 北京空间飞行器总体设计部 | Modularized quick-change mechanical interface capable of being replaced on track |
CN116534279B (en) * | 2023-07-05 | 2023-09-08 | 北京未来宇航空间科技研究院有限公司 | Satellite orbit deployment device and assembly thereof |
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- 2007-12-04 US US11/950,269 patent/US7780119B2/en not_active Expired - Fee Related
- 2007-12-05 AU AU2007354271A patent/AU2007354271A1/en not_active Abandoned
- 2007-12-05 JP JP2009540437A patent/JP2011502845A/en active Pending
- 2007-12-05 CN CN200780050550A patent/CN101687553A/en active Pending
- 2007-12-05 RU RU2009126595/11A patent/RU2009126595A/en not_active Application Discontinuation
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP4039598A1 (en) * | 2021-02-03 | 2022-08-10 | The Boeing Company | Direct mount of secondary payload adapters to truss structure common to space vehicle payload adapter |
US11827385B2 (en) | 2021-02-03 | 2023-11-28 | The Boeing Company | Direct mount of secondary payload adapters to truss structure common to space vehicle payload adapter |
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JP2011502845A (en) | 2011-01-27 |
CA2672472A1 (en) | 2008-12-04 |
CN101687553A (en) | 2010-03-31 |
US20090127398A1 (en) | 2009-05-21 |
AU2007354271A1 (en) | 2008-12-04 |
US7780119B2 (en) | 2010-08-24 |
RU2009126595A (en) | 2011-01-20 |
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