WO2004012995A1 - A secondary payload satellite - Google Patents

A secondary payload satellite Download PDF

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Publication number
WO2004012995A1
WO2004012995A1 PCT/GB2003/003152 GB0303152W WO2004012995A1 WO 2004012995 A1 WO2004012995 A1 WO 2004012995A1 GB 0303152 W GB0303152 W GB 0303152W WO 2004012995 A1 WO2004012995 A1 WO 2004012995A1
Authority
WO
WIPO (PCT)
Prior art keywords
satellite
locations
compartment
attachment points
structural
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/GB2003/003152
Other languages
French (fr)
Inventor
Robert Charles Parkinson
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.)
Airbus Defence and Space Ltd
Original Assignee
Astrium 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 Astrium Ltd filed Critical Astrium Ltd
Priority to AU2003260685A priority Critical patent/AU2003260685A1/en
Publication of WO2004012995A1 publication Critical patent/WO2004012995A1/en
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
    • B64G1/10—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
    • B64G1/223—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 invention relates to a secondary payload satellite design.
  • a well-known example of a type of launch vehicle secondary payload carrier is shown in Figure 1.
  • the so-called "ASAP-5" installation structure 30 available for satellites on Ariane 5 (“ASAP” denotes Ariane structure for Auxiliary Payloads) comprises a number of microsatellites, each of up to 100 kg mass, which are in turn mounted on an annular platform beneath the main (primary) payload 35.
  • ASAP denotes Ariane structure for Auxiliary Payloads
  • the space available 36 for the secondary satellite(s) is limited by the need to install it beneath the main payload 35 around the central payload adapter 37.
  • the mass available is limited by the load carrying capacity of the structure 38 beneath the attachment/release units 39, so that while in the shown example of ASAP-5 the complete structure can typically carry up to 800 kg mass of satellite(s) load, the individual attachment points can only typically carry less than 100 kg mass of satellite(s) load.
  • the present invention aims to overcome or at least substantially reduce some of the above-mentioned drawbacks.
  • the present invention resides in the concept of providing an improved satellite design, carrying onboard propulsion, with bridging means which cleverly bridges two of more of the launch vehicle attachment points/locations such as to permit the available mass and volume for the spacecraft to be increased.
  • a satellite comprising: an onboard propulsion system; an inner structural member; a plurality of outer structural members; said inner and outer structural members being mechanically coupled together to provide a multi-compartment facility; and wherein each said outer member is coupled to a different attachment point/location of a launch vehicle associated therewith to permit the different attachment points/locations to be mechanically bridged.
  • a central inner structural member and opposing sides of said central member are each attached to an outer structural member.
  • attachment points/locations there may be two separate attachment points/locations for use in the invention. Additional attachment points/locations could be readily provided, if desired.
  • the inner structural member is arranged to provide a first structural compartment box and the outer structural members are arranged to provide a plurality of outer structural compartment boxes.
  • first structural compartment box could be configured to carry a thruster and that the outer structural compartment boxes could each be configured to carry part of the onboard propulsion system, a propellant tank for example.
  • the proposed secondary payload satellite design is advantageously compact and simplified and it can be implemented at reasonable cost.
  • Figure 1 is a schematic of the ASAP-5 structure which is an example of a known type of launch vehicle secondary payload carrier.
  • Figure 2 is a schematic plan view of a satellite embodying the present invention.
  • the satellite design 10 carrying an onboard propulsion system 6, has a radial axis of symmetry (generally indicated in broken line).
  • the satellite design 10 comprises three box structure compartments 1 , 2, 3 in the form of a central box structure compartment 1 and two outer box structure compartments 2, 3.
  • the two outer box structure compartments 2, 3 are preferably configured to contain main propellant tanks 6 of the propulsion system which are in turn located in the vicinity of/above the two launch vehicle attachment points/locations 4, 5 to which they are appropriately connected by a rigid structural interface member (not shown).
  • the particular positioning of the two propellant tanks 6 above the two launch vehicle attachment points/locations 4, 5 is such as to reduce/minimise the load paths for these heavy items. This consideration provides a definite advantage over known arrangements.
  • the three box structure compartments 1 , 2, 3 are so arranged to bridge mechanically the two separate attachment points/locations 4, 5, permitting the available mass and volume for the spacecraft to be effectively increased.
  • the central box structure compartment 1 is preferably configured to carry a central thruster 7 which is arranged to point outwards from the centre of the launch vehicle (not shown) for launch.
  • the onboard propulsion system 6 may be a liquid propulsion system.
  • the onboard propulsion system 6 could equally be in the form of a hybrid (liquid/solid) propulsion system.

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Radio Relay Systems (AREA)

Abstract

An improved satellite design (10), carrying an onboard propulsion system, has a central box structure compartment (1), and a plurality of outer box structure compartments (2, 3) containing propellant tanks of the propulsion system which are in turn positioned above a plurality of launch vehicle attachment points/locations (4, 5). Significantly, the proposed arrangement of the invention bridges mechanically the various separate attachment points/locations, permitting the available mass and volume for the spacecraft to be effectively increased.

Description

A SECONDARY PAYLOAD SATELLITE
Field of the Invention
This invention relates to a secondary payload satellite design.
Background of the Invention Small (micro) satellites have been known to be using the surplus payload capability of larger-sized launchers/launch vehicles in order to obtain cheap launches into space as secondary payloads.
A well-known example of a type of launch vehicle secondary payload carrier is shown in Figure 1. As shown in the Figure, the so-called "ASAP-5" installation structure 30 available for satellites on Ariane 5 ("ASAP" denotes Ariane structure for Auxiliary Payloads) comprises a number of microsatellites, each of up to 100 kg mass, which are in turn mounted on an annular platform beneath the main (primary) payload 35. It is to be noted that the space available 36 for the secondary satellite(s) is limited by the need to install it beneath the main payload 35 around the central payload adapter 37. Further, the mass available is limited by the load carrying capacity of the structure 38 beneath the attachment/release units 39, so that while in the shown example of ASAP-5 the complete structure can typically carry up to 800 kg mass of satellite(s) load, the individual attachment points can only typically carry less than 100 kg mass of satellite(s) load.
Objects and Summary of the Invention
The present invention aims to overcome or at least substantially reduce some of the above-mentioned drawbacks.
It is the principal object of the present invention to provide an improved secondary payload satellite design which provides an increase in the available mass and volume for the spacecraft.
In broad terms, the present invention resides in the concept of providing an improved satellite design, carrying onboard propulsion, with bridging means which cleverly bridges two of more of the launch vehicle attachment points/locations such as to permit the available mass and volume for the spacecraft to be increased.
According to the present invention there is provided a satellite comprising: an onboard propulsion system; an inner structural member; a plurality of outer structural members; said inner and outer structural members being mechanically coupled together to provide a multi-compartment facility; and wherein each said outer member is coupled to a different attachment point/location of a launch vehicle associated therewith to permit the different attachment points/locations to be mechanically bridged. In accordance with an exemplary embodiment of the invention which will be described hereafter in detail, there is provided a central inner structural member and opposing sides of said central member are each attached to an outer structural member.
Conveniently, there may be two separate attachment points/locations for use in the invention. Additional attachment points/locations could be readily provided, if desired.
Advantageously, the inner structural member is arranged to provide a first structural compartment box and the outer structural members are arranged to provide a plurality of outer structural compartment boxes. In this connection, it is to be appreciated that the first structural compartment box could be configured to carry a thruster and that the outer structural compartment boxes could each be configured to carry part of the onboard propulsion system, a propellant tank for example.
The proposed secondary payload satellite design is advantageously compact and simplified and it can be implemented at reasonable cost.
The above and further features of the present invention are set forth in the appended claims and, together with advantages thereof, will become more clear from consideration of the following detailed description of an exemplary embodiment of the invention given with reference to the accompanying drawings. Brief Description of the Drawings
Figure 1 is a schematic of the ASAP-5 structure which is an example of a known type of launch vehicle secondary payload carrier; and
Figure 2 is a schematic plan view of a satellite embodying the present invention.
Detailed Description of an Exemplary Embodiment of the Invention
Referring to Figure 2, there is shown therein a schematic plan view of a preferred satellite design 10 embodying the present invention. As shown in the Figure, the satellite design 10, carrying an onboard propulsion system 6, has a radial axis of symmetry (generally indicated in broken line). The satellite design 10, comprises three box structure compartments 1 , 2, 3 in the form of a central box structure compartment 1 and two outer box structure compartments 2, 3. As shown, the two outer box structure compartments 2, 3 are preferably configured to contain main propellant tanks 6 of the propulsion system which are in turn located in the vicinity of/above the two launch vehicle attachment points/locations 4, 5 to which they are appropriately connected by a rigid structural interface member (not shown). In this connection, it is to be also noted that the particular positioning of the two propellant tanks 6 above the two launch vehicle attachment points/locations 4, 5 is such as to reduce/minimise the load paths for these heavy items. This consideration provides a definite advantage over known arrangements.
Thus, in the described embodiment, the three box structure compartments 1 , 2, 3 are so arranged to bridge mechanically the two separate attachment points/locations 4, 5, permitting the available mass and volume for the spacecraft to be effectively increased.
As also shown in Figure 2, the central box structure compartment 1 is preferably configured to carry a central thruster 7 which is arranged to point outwards from the centre of the launch vehicle (not shown) for launch. It is to be appreciated that the onboard propulsion system 6 may be a liquid propulsion system. Alternatively, the onboard propulsion system 6 could equally be in the form of a hybrid (liquid/solid) propulsion system.
Having thus described the present invention by reference to a preferred embodiment, it is to be appreciated that the embodiment is in all respects exemplary and that modifications and variations are possible without departure from the spirit and scope of the invention. For example, whilst in the described embodiment there are provided three box structure compartments for mechanically bridging two separate launch vehicle attachment points/locations, the arrangement could be readily modified to provide a multi-box structure compartment facility having four, five or more box structure compartments for mechanically bridging three or more separate attachment points/locations. The above-discussed arrangement could also be appropriately modified to carry additional thrusters and/or additional propellant tanks, if desired.

Claims

Claims
1. A satellite comprising: an onboard propulsion system; an inner structural member; a plurality of outer structural members; said inner and outer structural members being mechanically coupled together to provide a multi-compartment facility; and wherein each said outer member is coupled to a different attachment point/location of a launch vehicle associated therewith to permit the different attachment points/locations to be mechanically bridged.
2. A satellite as claimed in Claim 1 wherein there is a central inner structural member and opposing sides of said central member are each attached to an outer structural member.
3. A satellite as claimed in Claim 1 or 2 wherein there are two separate attachment points/locations.
4. A satellite as claimed in any preceding claim wherein the inner structural member is arranged to provide a first structural compartment box and the outer structural members are arranged to provide a plurality of outer structural compartment boxes.
5. A satellite as claimed in Claim 4 wherein the first structural compartment box is configured to carry thruster means and the outer structural compartment boxes are each configured to carry a part of the onboard propulsion system, a propellant tank for example.
6. A satellite substantially as herein described with reference to Figure 2 of the accompanying drawings.
PCT/GB2003/003152 2002-08-01 2003-07-24 A secondary payload satellite Ceased WO2004012995A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2003260685A AU2003260685A1 (en) 2002-08-01 2003-07-24 A secondary payload satellite

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0217864.8 2002-08-01
GBGB0217864.8A GB0217864D0 (en) 2002-08-01 2002-08-01 A secondary payload satellite

Publications (1)

Publication Number Publication Date
WO2004012995A1 true WO2004012995A1 (en) 2004-02-12

Family

ID=9941545

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2003/003152 Ceased WO2004012995A1 (en) 2002-08-01 2003-07-24 A secondary payload satellite

Country Status (3)

Country Link
AU (1) AU2003260685A1 (en)
GB (1) GB0217864D0 (en)
WO (1) WO2004012995A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008079841A1 (en) * 2006-12-21 2008-07-03 Intelsat Piggyback satellite payload arrangement, a device for and method of attaching a piggyback satellite payload and adapter to be used for a piggyback satellite payload arrangement for launching the piggyback satellite
EP2407384A1 (en) * 2010-07-16 2012-01-18 The Boeing Company Dual evolved expendable launch vehicle (EELV) secondary payload adaptor (ESPA) port small satellite design

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5779195A (en) * 1996-05-03 1998-07-14 Motorola, Inc. Satellite assembly having modular common bus components
US6206327B1 (en) * 1999-03-31 2001-03-27 Lockheed Martin Corporation Modular spacecraft bus

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5779195A (en) * 1996-05-03 1998-07-14 Motorola, Inc. Satellite assembly having modular common bus components
US6206327B1 (en) * 1999-03-31 2001-03-27 Lockheed Martin Corporation Modular spacecraft bus

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
BLAMONT J: "Ariane Piggyback Launches", ACTA ASTRONAUTICA, vol. 45, no. 4-9, 1999, UK, pages 499 - 516, XP002257381 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008079841A1 (en) * 2006-12-21 2008-07-03 Intelsat Piggyback satellite payload arrangement, a device for and method of attaching a piggyback satellite payload and adapter to be used for a piggyback satellite payload arrangement for launching the piggyback satellite
US7866607B2 (en) 2006-12-21 2011-01-11 Intelsat Piggyback satellite payload arrangement, a device for and method of attaching a piggyback satellite payload and adapter to be used for a piggyback satellite payload arrangement for launching the piggyback satellite
EP2407384A1 (en) * 2010-07-16 2012-01-18 The Boeing Company Dual evolved expendable launch vehicle (EELV) secondary payload adaptor (ESPA) port small satellite design
US8550408B2 (en) 2010-07-16 2013-10-08 The Boeing Company Dual evolved expendable launch vehicle (EELV) secondary payload adaptor (ESPA) port small satellite design

Also Published As

Publication number Publication date
AU2003260685A1 (en) 2004-02-23
GB0217864D0 (en) 2002-09-11

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