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WO2013015840A1 - Système de capsule, module de service, charge utile réutilisable pour la rentrée dans l'atmosphère et module d'amarrage - Google Patents

Système de capsule, module de service, charge utile réutilisable pour la rentrée dans l'atmosphère et module d'amarrage Download PDF

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Publication number
WO2013015840A1
WO2013015840A1 PCT/US2012/022799 US2012022799W WO2013015840A1 WO 2013015840 A1 WO2013015840 A1 WO 2013015840A1 US 2012022799 W US2012022799 W US 2012022799W WO 2013015840 A1 WO2013015840 A1 WO 2013015840A1
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WIPO (PCT)
Prior art keywords
module
common
common bulkhead
bulkhead
spacecraft
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.)
Ceased
Application number
PCT/US2012/022799
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English (en)
Inventor
Jon Zelon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Excalibur Almaz USA Inc
Original Assignee
Excalibur Almaz USA Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from PCT/US2011/001305 external-priority patent/WO2012011965A2/fr
Application filed by Excalibur Almaz USA Inc filed Critical Excalibur Almaz USA Inc
Priority to US14/234,402 priority Critical patent/US20140151509A1/en
Publication of WO2013015840A1 publication Critical patent/WO2013015840A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/14—Space shuttles
    • 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
    • B64G1/60—Crew or passenger accommodations
    • 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
    • B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
    • 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
    • B64G1/646—Docking or rendezvous systems

Definitions

  • the invention relates generally to spacecraft and more particularly to reusable modular vehicles capable of orbital boost, reentry, docking, and carrying payloads or passengers.
  • Capsules such as the Almaz capsule are known in the art.
  • Service modules such as those from the Apollo program are known in the art.
  • Space stations such as the International Space Station are known in the art.
  • This invention pertains to the structure and function of spacecraft. Specifically, this invention is in the field of spacecraft having a modular design.
  • a spacecraft in accordance with certain embodiments of the present invention provides capability for orbital boost to a higher altitude, rendezvous, docking and return of a capsule and a reusable payload module for use with a commercial space station facility.
  • embodiments of the spacecraft architecture can comprise independent modules each comprising a common bulkhead.. These modules can be combined together in different combinations in order to give the spacecraft the hardware necessary to achieve different functional roles presented by the mission at hand.
  • F1G. 1 shows a spacecraft in accordance with an embodiment of the present invention comprising a nosecone 10, a capsule module 1 , a service module 2, and a fairing 60,
  • FIG, 2 shows a sendee module 2 comprising a pressurized, tunnel 70 and unpressurized support structure 50 in accordance with an embodiment of the present invention.
  • FIG. 3 shows a service module 2 comprising a pressurized tunnel 70 and unpressurized support structure 50 in accordance with an embodiment of the present invention.
  • FIG. 4 shows a service module 2 and a habitable module 3 in accordance with an embodiment of the present invention.
  • FIG. 5 shows a service module , and a habitable module 3 in accordance with an embodiment of the present invention.
  • FIG. 6 shows a payload return capsule reentry diagram
  • FIG 7 shows a human space vehicle in accordance with, the present invention comprising a nosecone 10.
  • a capsule module 1 comprising a capsule 20, and an escape tower 90.
  • FIG. 8 Shown in FIG. 8 is a spacecraft in accordance with an embodiment of the present invention comprising a service module 2 and a D-shaped pressurized cargo module 110.
  • FIG. 9 Shown in FIG. 9 is a spacecraft in accordance with an embodiment of the present invention comprising a service module 2 and a D-shaped pressurized cargo module 100.
  • FIG. 10 Shown in FIG. 10 is a spacecraft in accordance with an embodiment of the present invention comprising a service module 2 and a habitable module 3.
  • FIG. 11 Shown in FIG. 11 is a spacecraft in a long range tourist configuration in accordance with an embodiment of the present in vention comprising a nosecone 10, a capsule module 1 , a service module 2, and a habitable module 3.
  • FIG. 12 Shown in FIG. 12 is a spacecraft in a pressurized cargo transport configuration in accordance with an embodiment of the present invention comprising a nosecone 10, a capsule module I, a service module 2, and a D-shaped pressurized cargo module 1 10.
  • FIG. 13 Shown in FIG. 13 is a spacecraft in an unpressurized cargo transport configuration in accordance with an embodiment of the present invention comprising a nosecone 10, a capsule module 1. a service module 2, and an unpressurized cargo module 170.
  • the modular aspect of spacecraft architecture in accordance with an embodiment of the present invention is based on a common bulkhead.
  • This common bulkhead is a circular sheet of rigid material that is preferably the same interior diameter of the cargo modules.
  • the common bulkhead can itself serve multiple purposes by having a hatch, a window, a cupola, or some other feature, usually at the center of the common bulkhead.
  • the common bulkhead could also be solid rigid material with no penetrations.
  • the majority of modules that can affix to the the spacecraft architecture do so through either being affixed to another module being separated by the common bulkhead or attaching to a hatch located in the center of the common bulkhead.
  • FIG. 1 Shown in FIG. 1 is a spacecraft in accordance with an embodiment of the present invention comprising a capsule module 1 , a service module 2.
  • a capsule module according to an embodiment of the present invention could comprise a capsule 20 and a common bulkhead, A fairing 60 may be positioned around, the circumference of the service module 2 in this configuration.
  • the combination provides unique capabilities for transport of crew and payloads to an orbiting commercial space station.
  • a spacecraft in accordance with an embodiment of the present invention can provide for: orbital boost to a higher altitude of a ground launched capsule 1 ; fine positioning, rendezvous and docking with a space station; and separation, de-orbit and reentry of a reusable capsule 1 .
  • a service module 2 in accordance with an embodiment of the present invention can provide structure 50, tankage 30, plumbing, avionics, additional power, motors 40 for coarse and fine alignment and de-orbit, and a tunnel 70 for pressurized exchange of crew and payloads between modules, such as the payload docking module 3 and the capsule 1 as shown in FIG. 1.
  • the payload docking module 3 is reusable and provides all the elements needed for docking; the pressurized environment for payload storage and crew direction of proximity operations, rendezvous and docking system control.
  • a payload docking module 3 can be derived from the basic capsule 1 modified to include the docking system and a modified parachute landing system.
  • the service module 2 provides the maneuverability for the capsule module 1 and payload and docking module 3 to raise the combined vehicle altitude and allow for rendezvous and docking with a commercial space station.
  • the payload and docking module 3 provides the docking system and payload capacity to support space station logistics.
  • the combination of the crew capsule 1, sendee module 2 and. payload and docking module 3, as shown in FIG. 11, provides the integrated system for transport of crew and payloads to and from an orbiting space station.
  • the payload dockmg module 3 could comprise a reentry capsule, such as a Soyuz or Almaz capsule.
  • the combination of elements proposed can provide a very cost effective approach for routine travel to and from any compatible space station.
  • An embodiment wherein service module 2 is stacked at the bottom of the vehicle can perform a space tug function. Configuring an embodiment with the service module 2 on bottom allows for reuse of service module 2.
  • the service module 2 would, function in the same basic manner as other embodiments.
  • the payload docking module 3 could comprise a Soyuz OM or other capsule rather than an Almaz capsule .
  • An embodiment comprising an Almaz capsule has the capability for return of payloads in the Almaz capsule 20 reentry vehicle .
  • Figures 4 and 5 show an embodiment comprising a payload docking module 3 and a service module 2 with air resupply and propellant tanks 30, fine attitude thrusters 40 for rendezvous and docking and course thrusiers 40 for major delta velocity addition.
  • embodiments of the present invention could comprise a sendee module 2 having payload return capability.
  • a payload return vehicle is shown in Figure 6.
  • Certain embodiments could comprise one or more payload return vehicles. Payload return vehicles could be based on an existing Russian design,
  • FIG 6 shows a payload return capsule reentry diagram.
  • step A After ejection from the space craft (step A) it spins up (step B) by a small solid rocket motor. Then the main retro rocket fires (step C) and after burnout another small solid rocket fires (step D) to de-spin the capsule.
  • the rocket motor pack is jettisoned, (step E) before reentry.
  • step G Before landing, a drogue chute pulls (step G) the capsule out of the heat shield.
  • An airbag is inflated (step H) to cushion the landing (step I).
  • FIG 7 shows a human space vehicle in accordance with the present invention comprising an escape tower 90, a nosecone 10, and a capsule module 1 comprising a capsule 20 and a common bulkhead.
  • FIG. 8 Shown in FIG. 8 is a spacecraft in accordance with an embodiment of the present invention comprising a service module 2 and a D-shaped pressurized cargo module 110, said modules comprising common bulkheads 160.
  • FIG. 9 Shown in FIG. 9 is a spacecraft in accordance with an embodiment of the present invention comprising a service module 2 and a D-shaped pressurized cargo module 100, said modules comprising common bulkheads 160.
  • FIG. 10 Shown in FIG. 10 is a spacecraft in accordance with an embodiment of the present invention comprising a service module 2 and a habitable module 3, said modules comprising common bulkheads.
  • FIG. 11 Shown in FIG. 11 is a spacecraft in a long range tourist configuration in accordance with an embodiment of the present invention comprising a nosecone 10, a capsule module 1. a service module 2, and a habitable module 3.
  • FIG. 12 Shown in FIG. 12 is a spacecraft in a pressurized cargo transport configuration in accordance with an embodiment of the present invention comprising a nosecone 10, a capsule module 1, a sendee module 2, and a D-shaped pressurized cargo module 1 10.
  • FIG. 13 Shown in FIG. 13 is a spacecraft in an unpressurized. cargo transport configuration in accordance with an embodiment of the present invention comprising a nosecone 10, a capsule module 1, a sendee module 2, and. an unpressurized cargo module 170.
  • An embodiment of the present invention could comprise a modular spacecraft comprising one or more modules using a common bulkhead.
  • the modular spacecraft architecture preferably allows for compatibility with a plurality of existing launch vehicles so as to allow for maximum compatibility with minimal cost.
  • the spacecraft architecture can be equipped with different combinations of varying modules in order to best be adapted for the requirements presented by differing mission scenarios.
  • This embodiment of the present invention comprises a capsule module 1 that provides the crew of the mission with a pressurized living space from which ail of the spacecraft's systems are controllable, an escape tower 90 that allows for emergency separation of the manned capsule from the rest of the spacecraft in the event of an emergency, and an intermediate propulsion stage 2 that allows for maneuvering the spacecraft while it is under the effects of microgravity.
  • This embodiment of the present invention comprises a capsule module 1 that provides the crew of the mission with a pressurized living space from which ail of the spacecraft's systems are controllable, an escape tower module 90 that allow r s for emergency separation of the manned capsule from the rest of the spacecraft in the event of an emergency, an intermediate propulsion stage 2 that allows for
  • This embodiment of the present invention comprises: a capsule module 1 that provides the crew with a pressurized living space from which all of the spacecraft's systems are controllable, an escape tower module 90 that allows for emergency separation of the manned capsule from the rest of the spacecraft in the event of an emergency, an intermediate propulsion stage that allows for the maneuvering of the spacecraft while it is under the effects of microgravity, and a D- shaped pressurized cargo module 100 with either a copula or window set in the terminal common bulkhead, and another copula or window set in the flat portion of the D-shaped module, as shown in Figure 9, thus allowing the crew and tourist an extra pressurized living compartment that also allows a view outside of the spacecraft.
  • This embodiment of the present invention comprises: a capsule module 1 that provides the crew of the mission with a pressurized living space from which all of the spacecraft's systems are controllable, an intermediate propulsion stage 2 that allows for maneuvering the spacecraft while it is under the effects of microgravity, and a D-shaped pressurized cargo module 110 with a passive common berthing mechanism outfitted on the flat side of the D-shaped pressurized cargo module 1 10 so that the module can dock with the 1SS or a similar vessel and easily transfer cargo between the spacecraft and the IS8 or a similar vessel.
  • This embodiment of the present invention comprises; a capsule module 1 that provides the crew of the mission with a pressurized living space from which all of the spacecraft's systems are controllable, an intermediate propulsion stage 2 that allows for maneuvering the spacecraft while it is under the effects of microgravity, a D-shaped pressurized cargo module 110 with a passive common berthing mechanism , and a pressurized cargo module 3 that allows for increased pressurized, volume for the pressurized transport of materials.
  • This embodiment of the present invention comprises; a capsule module 1 that pro vides the crew of the mission with a pressurized living space from which all of the spacecraft's systems are controllable, an intermediate propulsion stage that allows for maneuvering the spacecraft while it is under the effects of micrograviiy, a D- shaped pressurized cargo module 1 10 with a passive common berthing mechanism outfitted on the flat side of the D-shaped pressurized cargo module 1 10 so that the module can dock with a spacecraft such as the TSS and easily transfer cargo between the two spacecraft, and an unpressurized cargo module 170 that allows for increased unpressurized volume for the unpressurized transport of materials.
  • This embodiment of the present invention comprises; an escape tower module that allows for emergency separation of the manned, capsule from the rest of the spacecraft in the event of an emergency, a nosecone 10, a capsule module 1 that provides the crew of the mission with a pressurized living space from which all of the spacecraft's systems are controllable, an intermediate propulsion stage 2 that allows for maneuvering the spacecraft while it is under the effects of micrograviiy, a pressurized cargo module 3 that provides extra pressurized volume for habitation by the crew and tourists, and a long range propulsion module (not shown) that would provide more delta v such that the spacecraft may perform maneuvers at a longer range than would be possible with just the intermediate propulsion stage.
  • a capsule module 1 can comprise an Almaz, Orion, or any other manned or unmanned,, pressurized or unpressurized capsule. If the capsule module is manned, then the capsule module will preferably be fixedly connected to the escape tower module 90 so that the escape tower module 90 can pull the manned, capsule module 1 away from the rest of the spacecraft in case of life threatening emergency.
  • the capsule module 1 comprises a common bulkhead and may also have a hatch that connects to the common bulkhead on the capsule's underside that allows the transfer of personnel or cargo to or from the capsule to any one of a plurality of other modules.
  • An escape tower module 90 contains one or more rocket motors.
  • the escape tower module is attached to the capsule module 1 so that in case of an emergency, the capsule module 1 can be separated from the rest of the spacecraft and pulled away from the rest of the spacecraft by firing the escape tower module's rocket motors.
  • the escape tower module In order to be able to perform this crucial separation and escape process at any time throughout the launch, deployment, and re-entry of the spacecraft, the escape tower module cannot be confined within the fairing at the time of the spacecraft's launch.
  • the intermediate propulsion module comprises fuel storage tanks, and one or more rocket motors in fluid communication via piping to fuel storage tanks.
  • the module further comprises a common bulkhead such that the intermediate propulsion module may be attached to another module on one or both sides.
  • Long range propulsion module could comprise a long range rocket propulsion module from the Orion spacecraft system. Said long range propulsion module should be mounted to the bottommost common bulkhead interface on the modular spacecraft embodiment.
  • a pressurized cargo module 3 according to the present invention comprises an airtight cylindrical shell, said cylindrical shell being capped at either end by a common bulkhead.
  • the common bulkheads at either end of the cylindrical shell can be equipped with any possible combination of common bulkhead additions.
  • this pressurized cargo module 3 can be used either as a cargo compartment or as a living compartment connected to the capsule module 1 via a hatch in one of the common bulkheads of the pressurized cargo module 3.
  • An unpressurized cargo module 170 comprises a frame of rigid material that is not air tight.
  • the module has a rigid cylindrical frame capped on both sides by common bulkheads so that the module has an interior volume.
  • the unpressurized cargo module 170 may be outfitted, with a hatch disposed in part of the cylindrical frame, so as to allow the ingress and egress of cargo without going through a hatch in one of the capping common bulkheads.
  • a D-shaped Pressurized Cargo Compartment module 100, 1 10 has a D-shaped cross-section instead of the cylindrical cross- section of the standard pressurized cargo compartment.
  • the D-shaped pressurized cargo compartment is capped at its ends by common bulkheads.
  • the flat portion of the D-shaped pressurized cargo compartment can be modularly fitted with a cupola, a hatch, or an extendable docking mechanism.
  • a fairing 60 can be placed on top of/around the spacecraft modules for improved aerodynamics.
  • a notable exception to the coverage of the fairing is when manned flights call for using an escape tower. If the spacecraft is configured for maxmed space missions the fairing would remain around the majority of the modules, however, the escape tower would protrude from the top of the fairing so that if necessary the rocket motors in the tower can fire and pull away the manned, capsule module 1 from the rest of the spacecraft without being encumbered or obstructed by the fairing.
  • the common bulkhead 160 comprises a rigid structure in the shape of a circle which prevents the flow of air. Common bulkheads can be attached to one another and when each common bulkhead has a hatch, transfer through the bulkheads is possible.
  • the common bulkhead 160 may further comprise a window, cupola, docking adapter, or pressurized tunnel 70 set usually in the middle of a rigid circular structure.
  • this module the perimeter of an end-cap comprising a common bulkhead 160 is affixed to one of the ends of D-shaped tube.
  • the other end of the D-shaped tube is similarly affixed to the perimeter of an end-cap comprising a common bulkheadl60.
  • a docking device, extendible docking device, window, or cupola may ⁇ be attached to flat surface of the D-shaped tube. Otherwise, the flat surface of D- shaped tube will be solid.
  • the parts of this module are rigidly or movably affixed to one another in such a manner as to have the interior volume of the module hermetically sealed from the exterior volume of the module.
  • this module the circumference of a wall comprising a common bulked 160 is affixed to one of the open ends of cylindrical wall.
  • the other open end of cylindrical wall is similarly affixed to the circumference of common bulkhead 160.
  • a window docking adapter, extendable docking adapter, or cupola can be set into the surface of the cylindrical wail.
  • the parts of this module are rigidly or movably affixed to one another in such a manner as to have the interior volume of the module hermetically sealed from the exterior v olume of the module.
  • this module the circumference of an end-cap comprising a common bulkhead 160 is affixed to one of the open ends of cylindrical cage.
  • the other open end of the cylindrical cage is similarly affixed to the perimeter of an end-cap comprising a common bulkhead 160.
  • a docking adapter or extendable docking adapter may be set into the wall of cylindrical cage. The parts of this module need not be affixed to one another so as to form a hermetic seal.
  • this module could comprise the propulsion system from an Orion Multi-Purpose Crew Vehicle service module attached to a common bulkhead 160.
  • This module comprises one or more rocket motors 40, one or more fuel tanks 30, piping, one or more parachutes, and an external fairing.
  • fuel tanks 30, and parachutes are retained within the interior volume of external fairing.
  • Rocket motors 40 are connected to fuel tanks 30 by piping. The nozzle ends of said rockets 40 are in fluid communication with the external fairing's exterior volume.
  • escape tower module 90 is fixedly attached to the nosecone 10 of the capsule module 1.
  • the bottom end of capsule module 1 is removably attached to the common bulkhead 160 of the intermediate propulsion module 2.
  • a fairing60 may be positioned around the circumference of intermediate propulsion module 2 for improved aerodynamics during launch.
  • an escape tower module 90 is fixedly attached to the nosecone 10 of capsule module 1.
  • the bottom end 20 of the capsule module 1 is removably attached to the common bulkhead 160 portion of intermediate propulsion module 2.
  • Habitable module 3, pressurized cargo module 1 10, or D-shaped pressurized cargo module 100 is fixedly attached to the aft end of intermediate propulsion module 2.
  • the interior volume of a habitable module 3, a pressurized cargo module 1 10 or a D-shaped pressurized cargo module 100 may be in fluid communication with the interior volume of a capsule module 1 through a pressurized tunnel 70 that nms through common bulkheads 160.
  • a fairing 60 may be positioned around the circumference of all modules in this configuration with the exception of the escape tower module 90 and capsule module 1.
  • a capsule module 1 is fixedly attached to the common bulkhead 160 portion of intermediate propulsion module 2.
  • Either a pressurized cargo module 1 10 or a D-shaped pressurized cargo module 100 is fixedly attached by one of its common bulkheads 160 to the other side of the intermediate propulsion module 2.
  • Grapple fixtures 170 may or may not be attached to the intermediate propulsion module 2, where the grapple fixtures 170 may be passive or have power and data capacities.
  • More habitable modules 3 Pressurized cargo modules 1 10 or D-shaped pressurized cargo modules 100 may optionally be connected (common bulkhead 160 to common bulkhead 160) to the first pressurized cargo module 1 10.
  • a fairing may be positioned around the circumference of all modules in this configuration so as to improve the aerodynamic properties of the system.
  • the pressurized cargo modules 1 10 or D-shaped pressurized cargo modules 100 can optionally include modular attachments such as a NASA Docking System (NDS) 130, an Androgynous
  • APAS Peripheral Attach System
  • PCBM Passive Common Berthing Mechanism
  • a capsule module 1 is fixedly attached to the common bulkhead 160 portion of intermediate propulsion module 2.
  • Either a pressurized cargo module 110 or a D-shaped pressurized cargo module 100 is fixedly attached by one of its common bulkheads 160 to the other side of of the intermediate propulsion module 2.
  • Grapple fixtures 170 may or may not be attached to the intermediate propulsion module 2, where the grapple fixtures 170 may be passive or have power and data capacities.
  • One or more unpressurized. cargo modules 220 may optionally be connected (common bulkhead 160 to common bulkhead 160) to the first pressurized cargo module 1 10.
  • a fairing may be positioned around the circumference of all modules in this configuration so as to improve the aerodynamic properties of the system.
  • the pressurized cargo modules 110 or D-shaped pressurized, cargo modules 100 can optionally include modular attachments such as a NASA Docking System (NDS) 130, an Androgynous Peripheral Attach System (APAS) 120, or a Passive Common Berthing Mechanism (PCBM) 140.
  • NDS NASA Docking System
  • APAS Androgynous Peripheral Attach System
  • PCBM Passive Common Berthing Mechanism
  • escape tower module 90 is fixedly attached to nosecone 10 of a capsule module 1.
  • the bottom end of the capsule module 20 is removably attached to the common bulkhead 160 of intermediate propulsion module 2.
  • Pressurized cargo module 110, or D-shaped pressurized cargo module 100 is fixedly attached to the aft end of the intermediate propulsion module 2.
  • the common bulkhead 160 of long range propulsion module 2 is fixedly attached to the remaining common bulkhead 160 of the pressurized cargo module 1 10.
  • the interior volume of pressurized cargo module 1 10 or D-shaped pressurized cargo module 100 may be in fluid communication with the interior volume of Capsule Module 1 through the use of a pressurized tunnel 70 that runs through common bulkheads 160.
  • a fairing may be positioned around the circumference of all modules in this configuration with the exception of the escape tower module 90 and capsule module 20.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automatic Assembly (AREA)

Abstract

La présente invention concerne un véhicule spatial modulaire comportant: un module de capsule comprenant une cloison commune, et un module de véhicule spatial additionnel comportant une cloison commune, ladite cloison commune du module de capsule étant attachée à ladite cloison commune du module de véhicule spatial additionnel.
PCT/US2012/022799 2010-07-22 2012-01-26 Système de capsule, module de service, charge utile réutilisable pour la rentrée dans l'atmosphère et module d'amarrage Ceased WO2013015840A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US14/234,402 US20140151509A1 (en) 2010-07-22 2012-01-26 Capsule system, service module, and reuseable reentry payload and docking module

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
USPCT/US11/001305 2011-07-23
PCT/US2011/001305 WO2012011965A2 (fr) 2010-07-22 2011-07-23 Système de capsule, module de service et charge utile réutilisable pour la rentrée en atmosphère et module d'amarrage

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WO2013015840A1 true WO2013015840A1 (fr) 2013-01-31

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104340379A (zh) * 2013-07-31 2015-02-11 宋新民 航天飞船全程逃逸塔和整流罩再利用装置组合
CN107380483A (zh) * 2017-07-05 2017-11-24 上海宇航系统工程研究所 一种航天器构型

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Publication number Priority date Publication date Assignee Title
US6293500B1 (en) * 2000-04-14 2001-09-25 Bigelow Development Aerospace Division, Limited Liability Company Integrated translation tube assembly for a space module
US7219859B2 (en) * 2005-04-01 2007-05-22 Spacehab, Incorporated Multipurpose modular spacecraft
US20090127398A1 (en) * 2006-12-11 2009-05-21 Michael David Johnson Modular spacecraft
US20100051751A1 (en) * 2005-06-29 2010-03-04 Mueller George E Reusable orbital vehicle with interchangeable modules

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6293500B1 (en) * 2000-04-14 2001-09-25 Bigelow Development Aerospace Division, Limited Liability Company Integrated translation tube assembly for a space module
US7219859B2 (en) * 2005-04-01 2007-05-22 Spacehab, Incorporated Multipurpose modular spacecraft
US20100051751A1 (en) * 2005-06-29 2010-03-04 Mueller George E Reusable orbital vehicle with interchangeable modules
US20090127398A1 (en) * 2006-12-11 2009-05-21 Michael David Johnson Modular spacecraft

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104340379A (zh) * 2013-07-31 2015-02-11 宋新民 航天飞船全程逃逸塔和整流罩再利用装置组合
CN107380483A (zh) * 2017-07-05 2017-11-24 上海宇航系统工程研究所 一种航天器构型
CN107380483B (zh) * 2017-07-05 2023-09-01 上海宇航系统工程研究所 一种航天器构型

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