WO2017134689A2 - Bus de satellite adaptable - Google Patents

Bus de satellite adaptable Download PDF

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Publication number
WO2017134689A2
WO2017134689A2 PCT/IN2017/050053 IN2017050053W WO2017134689A2 WO 2017134689 A2 WO2017134689 A2 WO 2017134689A2 IN 2017050053 W IN2017050053 W IN 2017050053W WO 2017134689 A2 WO2017134689 A2 WO 2017134689A2
Authority
WO
WIPO (PCT)
Prior art keywords
adaptable
satellite bus
supporting
sub
mounting provisions
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/IN2017/050053
Other languages
English (en)
Other versions
WO2017134689A3 (fr
Inventor
Priyank PUNTAMBEKAR
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.)
Axiom Research Labs Private Ltd
Original Assignee
Axiom Research Labs Private Ltd
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
Application filed by Axiom Research Labs Private Ltd filed Critical Axiom Research Labs Private Ltd
Publication of WO2017134689A2 publication Critical patent/WO2017134689A2/fr
Anticipated expiration legal-status Critical
Publication of WO2017134689A3 publication Critical patent/WO2017134689A3/fr
Ceased legal-status Critical Current

Links

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
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • 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
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/428—Power distribution and management
    • 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
    • B64G1/1021—Earth observation satellites

Definitions

  • Embodiments of the present invention relate to a spacecraft, and more particularly, to a satellite bus.
  • satellite bus which is used for applications such as imaging, telecommunication, and sensing.
  • the satellite buses include one or more payloads, which are used to perform the imaging, telecommunication, and the sensing.
  • a star sensor with gyros and actuators may be used for precision pointing capabilities and a high data rate transmitter such as an X-band transmitter for transmitting high data rate payload data.
  • the satellite manufacturers design one satellite bus including different types of payloads and based on customer's requirement, the satellite manufacturer configures one or more payloads in the satellite bus to serve the applications requested by the client.
  • the satellite manufacturer leads to higher costs of manufacturing and launch as the satellite bus becomes costlier and heavier to launch.
  • there is a need for an improved satellite bus which can address the aforementioned issues.
  • an adaptable satellite bus includes a plurality of coupling brackets.
  • the adaptable satellite bus further includes a plurality of structural panels configured to be coupled to each other via the plurality of coupling brackets, wherein at least one structural panel of the plurality of structural panels includes mounting provisions for supporting one or more different types of payloads, and one or more structural panels include mounting provisions for one or more supporting sub-systems, and wherein configuration of the mounting provisions for supporting one or more different types of payloads and configuration of the mounting provisions for one or more supporting subsystems are independent of an intended use of the adaptable satellite bus.
  • a method for making an adaptable satellite bus includes providing a plurality of coupling brackets.
  • the method further includes coupling a plurality of structural panels to each other via the plurality of coupling brackets, wherein at least one structural panel of the plurality of structural panels includes mounting provisions for supporting one or more different types of payloads, and one or more structural panels include mounting provisions for one or more supporting sub-systems, and wherein configuration of the mounting provisions for supporting one or more different types of payloads and configuration of the mounting provisions for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus.
  • FIG. 1 is a diagrammatical representation showing an expanded view of an adaptable satellite bus, in accordance with one embodiment of the present specification
  • FIG. 2 is a diagrammatical representation showing a perspective view of the adaptable satellite bus of FIG. 1, in accordance with one embodiment of the present specification
  • FIG. 3 is a diagrammatical representation showing perspective view of another adaptable satellite bus, in accordance with one embodiment of the present specification.
  • FIG. 4 is a flow-diagram showing a method for making an adaptable satellite, in accordance with one embodiment of the present specification.
  • references to "one embodiment”, “an embodiment”, “at least one embodiment”, “one example”, “an example”, “for example” and so on, indicate that the embodiment(s) or example(s) so described may include a particular feature, structure, characteristic, property, element, or limitation, but that not every embodiment or example necessarily includes that particular feature, structure, characteristic, property, element or limitation. Furthermore, repeated use of the phrase “in one embodiment” does not necessarily refer to the same embodiment, though it may.
  • an adaptable satellite bus includes a plurality of coupling brackets.
  • the adaptable satellite bus further includes a plurality of structural panels configured to be coupled to each other via the plurality of coupling brackets, wherein at least one structural panel of the plurality of structural panels includes mounting provisions for supporting one or more different types of payloads, and one or more structural panels include mounting provisions for one or more supporting sub-systems, and wherein configuration of the mounting provisions for supporting one or more different types of payloads and configuration of the mounting provisions for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus.
  • the adaptable satellite bus in accordance with some embodiments, has a universal design which can be used to couple different payloads in the satellite bus without changing the bus structure and design.
  • the proposed satellite bus configuration enhances the level of adaptability of the bus to the mission requirements such that all the required features and only the required features are a part of the flight configuration leading to a solution which is cost optimal and quickly deliverable.
  • FIG. 1 is a diagrammatical representation showing an expanded view of an adaptable satellite bus (100), in accordance with one embodiment of the present specification.
  • the adaptable satellite bus (100) may include a plurality of coupling brackets such as the coupling brackets (104) and a plurality of structural panels such as the structural panels (106, 108, 110, 112, 114, and 116) (hereinafter collectively referred to as structural panels (106-116)).
  • the plurality of coupling brackets 104 is L-shaped.
  • the structural panels (106-116) are configured to be coupled to each other via the plurality of coupling brackets (104).
  • the plurality of structural panels (106-116) may be coupled to the coupling brackets (104) via one or more fasteners, adhesives, or a combination thereof.
  • the structural panels (106- 116) may be coupled to the coupling brackets (104) such that a resultant satellite bus body having a cubical shape is formed (see FIGs. 2 and 3).
  • the structural panels (106-112) are disposed on sides of the cubical shape and also referred to as side structural panels (106-112).
  • the structural panel 114 is disposed on bottom side of the cubical shape and also referred to as a bottom structural panel 114.
  • the structural panel 116 is disposed on a top side of the cubical shape and also referred to as a top structural panel 116.
  • FIG. 1 sixteen (16) coupling brackets (104) and six (6) structural panels (106-116) are shown. Greater or fewer number of the coupling brackets and the structural panels may be employed without limiting the scope of the present specification. Moreover, although in the embodiment of FIG. 1, one or more the structural panels (106-116) having rectangular shapes are used, a satellite bus configuration with structural panels of different shapes is also envisioned.
  • At least one structural panel such as the top structural panel (116) of the plurality of structural panels (106-116) includes mounting provisions (118) for supporting one or more different types of payloads.
  • the structural panel (116) that includes the mounting provisions (118) for supporting payloads may also be referred to as a payload deck.
  • the mounting provisions (118) for supporting one or more different types of payloads may include but are not limited to one or more of holes, clamps, fastening means, or combinations thereof.
  • Non-limiting examples of the different types of payloads include an imaging payload (120), a global positioning system (GPS) antenna (122), a star sensor (124), or combinations thereof.
  • GPS global positioning system
  • the mounting provisions (118) may be designed such that any type of payloads can be mounted on the structural panel (116). More particularly, a configuration of the mounting provisions (118) for supporting the different types of payloads is independent of an intended use of the adaptable satellite bus (100).
  • one or more structural panels (106-116) may include mounting provisions (126) for one or more supporting sub- systems.
  • the mounting provisions (126) for supporting sub-systems may include but are not limited to one or more of holes, clamps, fastening means, or combinations thereof.
  • Non-limiting examples of the supporting sub-systems include a thermal control sub-system (TCS), an electrical power sub-system (EPS), an altitude and orbit determination and control subsystem (AOCS), a communication sub-system, a command and data handling sub-system (C&DH) disposed in an avionics box (127), flight software (FS), a propulsion sub-system, and an integrated tank assembly, or combinations thereof.
  • EPS may include power generation apparatus such as solar panels (128), an energy storage device such as a battery (130), and a power conditioning and distribution unit (PCDU) (132).
  • the solar panels (128) may be body mounted, deployed in-orbit without sun-tracking or deployed in-orbit with sun-tracking.
  • An actual size and configuration of the solar panels (128) may be a function of a mission power requirements and orbit geometry.
  • the battery ( 130) is configured to store the power and supply the power to the supporting sub-systems and/or the payloads when the solar power is not sufficient to meet their power requirements.
  • the battery (130) may have a baseline configuration irrespective of the configuration of the other systems such as the supporting sub-systems and the payloads.
  • the PCDU (132) may be configured to distribute power among the supporting sub-systems and/or the payloads.
  • the PCDU (132) may be a modular unit designed such that it would have interface cards with each sub-system baseline design and a provision to add cards for the add-on packages of each system.
  • components of the EPS may be located on a single structural panel. In some embodiments, the components of the EPS may be distributed over one or more of the plurality of structural panels (106-116).
  • the communication sub-system may be configured to provide a communication link between the satellite bus (100) and the ground station (not shown) for downlink of telemetry and housekeeping data along uplink of tele -commands and to facilitate the downlink of payload data.
  • the communication system may include a low data rate transceiver (or S-band transceiver) (134) for facilitating a low data rate communication link with the ground station via an S-band monopole (136).
  • low data rate transceiver (134) may be configured to facilitate a single communication link with the ground station which would be used for tele-command uplink, housekeeping and payload data.
  • the communication system may include a high data rate transmitter (or X-band transmitter) (138) for facilitating an independent transmit link via an X-band antenna (140).
  • the X-band transmitter (138) may be utilized dedicatedly for payload data downlink in addition to the communication link facilitated by the S-band transceiver (134).
  • components of the communication sub-system may be located on a single structural panel. In some embodiments, the components of the communication sub-system may be distributed over one or more of the plurality of structural panels (106-116).
  • the C&DH sub-system (not shown) may be disposed in the avionics box (127) may include an on-board computer.
  • the C&DH sub-system interfaces with all the payloads and/or supporting sub-systems of the satellite bus (100) and configured to run AOCS algorithms and manages the payload data storage, command and telemetry and basic fault detection isolation and recovery.
  • Various configurations in C&DH are defined based on the data interface, processing, storage and mission life time requirements.
  • the basic configuration of the C&DH sub-system meets the requirements of the low data rate payload operating for short mission life.
  • the intermediate configuration of the C&DH sub-system is capable of supporting higher data rate payloads and longer mission life.
  • the data storage is an order of magnitude higher than the basic configuration.
  • the highest configuration of the C&DH sub-system is capable of supporting very high data rate payloads and storing data an order of magnitude higher than the intermediate level. All the configurations are capable of meeting the interface and processing requirements of all other supporting subsystems.
  • the AOCS sub-system is configured to manage the altitude and orbit of the satellite bus (100) to ensure that the satellite bus (100) is pointing in the desired direction such that either the payload is pointing at the object of interest, or the communication antenna are pointing towards the ground station or the solar panels are generating power or any other operational pointing requirement. Orbit control may be desirable at lower operating altitude to compensate for the decay in the orbit due to atmospheric drag.
  • the AOCS sub-system has two configurations based on the pointing accuracy of the system, a coarse altitude pointing (CAP) and a precision altitude pointing (PAP).
  • the CAP is based on the most basic set of hardware such as magnetometers (142), GPS (not shown), sun sensors (not shown) and magnetorquers (144). These sensors may provide a coarse attitude knowledge and the actuators combine to give full 3-axis pointing capability.
  • the PAP may include precision attitude determination sensors like a star sensor (124) and gyros (not shown) and actuators like the reaction wheels (146) which augment the performance of the hardware in CAP to provide 3-axis precision pointing capability.
  • the altitude pointing modes are configurable through flight software implementation as per the specific mission requirement.
  • components of the AOCS sub-system may be located on a single structural panel. In some embodiments, the components of the AOCS subsystem may be distributed over one or more of the plurality of structural panels (106-116).
  • the satellite bus (100) may optionally include the propulsion sub-system (not shown).
  • the propulsion sub-system is designed to provide orbit maintenance capability at very low orbit altitude and de-orbit capability at high operating orbit altitudes.
  • the integrated tank assembly (148) may include one or more of a propellant tank (150), reaction wheels (146), a thruster (not shown), and an integrated mount (152) for the propellant tank (150), the reaction wheels (146), the thruster.
  • the integrated tank assembly (148) may be mounted to the bottom deck (for example, the bottom structural panel (114)), which also acts as the interface with a launch vehicle (not shown). Components of the integrated tank assembly (148) may be optional.
  • the reaction wheels (146) are only used if there is a need for precision pointing (see FIG. 2).
  • the propellant tank (150) and the thruster are mounted only if there is a need for the propulsion sub-system.
  • the integrated mount (152) may be used even if the is a need for only one of the two systems.
  • FIG. 2 is a diagrammatical representation showing a perspective view (200) of the adaptable satellite bus (100) of FIG. 1, in accordance with one embodiment of the present specification. More particularly, the perspective view (200) of FIG. 2 includes all elements of FIG. 1 except the front structural panel (108) for facilitating enhanced view of internal components.
  • FIG. 3 is a diagrammatical representation showing a perspective view 300 of another adaptable satellite bus (302), in accordance with one embodiment of the present specification. More particularly, the perspective view (300) of FIG. 3 shows another satellite bus (302) which does not include a payload such as a star sensor, and a reaction wheel as the star sensor is not required. In fact, FIGs.
  • FIG. 4 is a flow-diagram (400) showing a method for making an adaptable satellite, in accordance with one embodiment of the present specification.
  • FIG. 4 is described in conjunction with the adaptable satellite (100) of FIG. 1.
  • the method of making the adaptable satellite (100) includes steps (402) and (404).
  • a plurality of coupling brackets (104) are provided.
  • the plurality of coupling brackets (104) of L- shape are provided.
  • a plurality of structural panels such as the structural panels (106-116) may be coupled to each other via the plurality of coupling brackets. More particularly, at least one structural panel (e.g., the structural panel (116) of the plurality of structural panels (106-116) includes mounting provisions (118) for supporting one or more different types of payloads, and one or more structural panels (e.g., the structural panels (106-114)) may include mounting provisions (126) for one or more supporting subsystems, and wherein configuration of the mounting provisions (118) for supporting one or more different types of payloads and configuration of the mounting provisions (126) for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus (100).
  • the adaptable satellite bus has a universal design which can be used to couple different payloads in the satellite bus without changing structure and design and design of the satellite bus.
  • the top structural panel (116) may be used primarily as the payload deck and the mounting provisions are provided such that any type of payloads can be mounted on the payload deck.
  • the proposed satellite bus configuration enhances the level of adaptability of the bus to the mission requirements such that all the required features and only the required features are a part of the flight configuration leading to a solution which is cost optimal and quickly deliverable.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Power Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Patch Boards (AREA)
  • Navigation (AREA)

Abstract

L'invention concerne un bus de satellite adaptable (100, 300). Le bus de satellite adaptable (100, 300) comprend une pluralité de supports d'accouplement. Le bus de satellite adaptable (100, 300) comprend en outre une pluralité de panneaux structuraux (106-116) conçus pour être accouplés les uns aux autres par l'intermédiaire de la pluralité de supports d'accouplement (104), au moins un panneau structural de la pluralité de panneaux structuraux (106-116) comprenant des dispositions de montage (118) pour supporter un ou plusieurs types différents de charges utiles, et un ou plusieurs panneaux structuraux comprenant des dispositions de montage pour un ou plusieurs sous-systèmes de support, et la configuration des dispositions de montage (118) pour supporter un ou plusieurs types différents de charges utiles et la configuration des dispositions de montage (126) pour un ou plusieurs sous-systèmes de support étant indépendantes d'une utilisation prévue du bus de satellite adaptable (100). L'invention concerne également un procédé (400) pour fabriquer le bus de satellite adaptable (100).
PCT/IN2017/050053 2016-02-06 2017-02-06 Bus de satellite adaptable Ceased WO2017134689A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IN201641004296 2016-02-06
IN201641004296 2016-02-06

Publications (2)

Publication Number Publication Date
WO2017134689A2 true WO2017134689A2 (fr) 2017-08-10
WO2017134689A3 WO2017134689A3 (fr) 2019-04-25

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PCT/IN2017/050053 Ceased WO2017134689A2 (fr) 2016-02-06 2017-02-06 Bus de satellite adaptable

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019243500A1 (fr) * 2018-06-21 2019-12-26 Airbus Oneweb Satellites Sas Procédés et appareils de commande de satellite
CN119683011A (zh) * 2024-11-29 2025-03-25 上海卫星工程研究所 适用于多类载荷的通用化卫星构型

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5755406A (en) * 1995-12-22 1998-05-26 Hughes Electronics Modular, independent subsystem design satellite bus and variable communication payload configurations and missions
US6206237B1 (en) * 1999-03-08 2001-03-27 Pepsico, Inc. Bottle dispenser
US20110296675A1 (en) * 2009-08-26 2011-12-08 Roopnarine Means for rapidly assembling a spacecraft

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019243500A1 (fr) * 2018-06-21 2019-12-26 Airbus Oneweb Satellites Sas Procédés et appareils de commande de satellite
EP3587282A1 (fr) * 2018-06-21 2020-01-01 Airbus Oneweb Satellites SAS Appareils et procédés de commande de satellite
US11912439B2 (en) 2018-06-21 2024-02-27 Airbus Oneweb Satellites Sas Satellite control apparatuses and methods
CN119683011A (zh) * 2024-11-29 2025-03-25 上海卫星工程研究所 适用于多类载荷的通用化卫星构型

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Publication number Publication date
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