GB2396595A - A secondary payload satellite - Google Patents
A secondary payload satellite Download PDFInfo
- Publication number
- GB2396595A GB2396595A GB0230044A GB0230044A GB2396595A GB 2396595 A GB2396595 A GB 2396595A GB 0230044 A GB0230044 A GB 0230044A GB 0230044 A GB0230044 A GB 0230044A GB 2396595 A GB2396595 A GB 2396595A
- Authority
- GB
- United Kingdom
- Prior art keywords
- satellite
- structural
- propulsion system
- launch vehicle
- locations
- 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.)
- Withdrawn
Links
- 239000003380 propellant Substances 0.000 claims abstract description 9
- 108091092878 Microsatellite Proteins 0.000 abstract description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000011068 loading method Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
-
- 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
- B64G1/002—Launch systems
-
- 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
- B64G1/1085—Swarms and constellations
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
A secondary payload satellite 10 for attachment to a launch vehicle, the satellite 10 carrying an onboard propulsion system comprising a thruster 7, has a central box structure compartment 1, and a plurality of outer box structure compartments 2, 3 containing propellant tanks 6 of the propulsion system which are in turn positioned above a plurality of launch vehicle attachment points/locations 4, 5. The proposed arrangement of the invention bridges mechanically, separate attachment points/locations of the launch vehicle, permitting the available mass and volume for the spacecraft 10 to be effectively increased relative to a microsatellite mounted on only one attachment point. Further, there may additionally be provided tie means to mechanically link the propulsion system to the structure enabling a structural load path to the satellite to be provided.
Description
IMPROVEMENTS RELATING TO A SECONDARY PAYLOAD SATELLITE
Field of the Invention
This invention relates to an improved secondary payload satellite design.
Background of the Invention
5 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" 0 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 attachmenVrelease 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 Atypically carry less go than 100 kg mass of satellite(s) load.
It is also noted that the standard attachment interface between a satellite and a launch vehicle normally consists of a defined mounting rig to which the satellite is firmly clamped by means of loading or clamping mechanisms (e.g. a clamp band) which can be released by pyrotechnic means when the launch z5 vehicle reaches orbit. The clamping mechanism typically loads the satellite interface ring sufficiently to ensure that no movement can take place during the high vibrational environment encountered during launch. However, a known problem with designing a satellite with two attachment points is that the two geometric interfaces are defined independently (within limits) and the process of 30 clamping the attachments to the launch vehicle, as well as subsequent
distortions of the launch vehicle structure during launch, cause geometric distortions which generate stresses within a rigid satellite structure.
Objects and Summary of the Invention
The present invention aims to overcome or at least substantially reduce 5 some of the above-mentioned drawbacks.
It is a 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.
It is another principal object of the present invention to provide an to improved compliant secondary payload satellite design which is compliant with the geometric movements induced by the attachment structure prior to/during launch, while at the same time meeting the critical minimum stiffness requirements of the launch vehicle specification.
It is another principal object of the present invention to provide an improved compliant secondary payload satellite design which is capable of being attached to the launch vehicle through a plurality of predefined geometric interfaces. In broad terms, the present invention resides in one of its aspects in the concept of providing an improved satellite design, carrying onboard propulsion, 20 with bridging means which cleverly bridges two or 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 one aspect of the present invention there is provided a satellite comprising: an onboard propulsion system; an inner structural member; z5 a plurality of outer structural members; said inner and outer structural members being mechanically coupled together to provide a multicompartment facility; and wherein each said outer member is coupled to a different attachment poinVlocation of a launch vehicle associated therewith to permit the different attachment points/locations to be mechanically bridged.
- 3 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.
5 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 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.
Furthermore, in broad terms, the present invention resides in another of its aspects in the concept of providing an improved compliant satellite design, carrying onboard propulsion, with tie means which cleverly links the propulsion so system to the satellite structure such as to provide an effective structural load path to the main satellite body.
Thus, according to another aspect of 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 as structural members being mechanically coupled together to provide a multi compartment facility; and wherein each said outer member is coupled to a different attachment poinVlocation of a launch vehicle associated therewith to permit the different attachment points/locations to be mechanically bridged; and wherein tie means is provided to mechanically link the propulsion system to the 30 satellite structure, enabling a structural load path to the satellite to be provided.
- 4 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 5 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; Figure 2 is a schematic plan view of a satellite embodying the present o invention; and Figure 3 is another schematic view of a satellite embodying the present invention. Detailed Description of Exemplary Embodiments of the Invention
Referring to Figure 2, there is shown therein a schematic plan view of a 15 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.
20 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 25 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 30 compartments 1, 2, 3 are so arranged to bridge mechanically the two separate
- 5 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 5 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.
Referring next to Figure 3, there is shown therein a schematic view of to another preferred satellite design 11' embodying the present invention. As shown in the Figure, the satellite 11' comprises two outer structural boxes 11 attached to a central structural box 12. As shown, the outer boxes 11 contain the main propellant tanks 13 which are located above the launch vehicle attachments points 14 to which they are directly connected by a (rigid) structural s member 15. As shown, the propellant tanks are also connected to the eight corners of the outer boxes by ties 16 and 17 to provide a structural load path to the main satellite body. In each box two of the ties 16 are non-elastic pinned links allowing the propellant tanks to move and rotate relative to the spacecraft body, while the remaining six ties 17 are elastic and pre-tensioned with so properties which allow for the geometric tolerances on location of the launch vehicle attachment points while providing the required overall spacecraft rigidity and retaining tension in the ties over the range of expected spacecraft loadings.
In this way, the following conditions: allowing for the range of geometric tolerances, maintaining overall spacecraft rigidity, maintaining tension in the ties can be practically achieved by control of the following independent variables: the range of elongation of the ties, the elasticity of the ties,
ad - 6 and the pretensioning load in the ties.
Having thus described the present invention by reference to two preferred embodiments, it is to be appreciated that the embodiments are in all respects exemplary and that modifications and variations are possible without 5 departure from the spirit and scope of the invention. For example, whilst in the described embodiments 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 to 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 (7)
1. A satellite comprising: an onboard propulsion system; an inner structural member; 5 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 poinVlocation of a launch vehicle associated therewith to permit the to 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.
20
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 comprising: :5 an onboard propulsion system; an inner structural member; a plurality of outer structural members;
- 8 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 poinVlocation of a launch vehicle associated therewith to permit the 5 different attachment points/locations to be mechanically bridged; and wherein tie means is provided to mechanically link the propulsion system to the satellite structure enabling a structural load path to the satellite to be provided.
7. A satellite substantially as herein described with reference to Figures 2 10 and 3 of the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0230044A GB2396595A (en) | 2002-12-23 | 2002-12-23 | A secondary payload satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0230044A GB2396595A (en) | 2002-12-23 | 2002-12-23 | A secondary payload satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB0230044D0 GB0230044D0 (en) | 2003-01-29 |
| GB2396595A true GB2396595A (en) | 2004-06-30 |
Family
ID=9950344
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0230044A Withdrawn GB2396595A (en) | 2002-12-23 | 2002-12-23 | A secondary payload satellite |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2396595A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008030175A1 (en) * | 2006-09-04 | 2008-03-13 | Nanospace Ab | Nozzle arrangement for use in a gas thruster, gas thruster, method for manufacturing a nozzle arrangement, method for in-situ repairing of a nozzle arrangement and a method for operating a gas thrusters |
| CN106560401A (en) * | 2015-10-02 | 2017-04-12 | 波音公司 | Dual Port Payload Attach Ring Compatible Satellite |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5271582A (en) * | 1990-06-29 | 1993-12-21 | Standard Space Platforms Corp. | Modular mother satellite bus for subsidiary payloads |
| DE4243562A1 (en) * | 1992-12-22 | 1994-06-23 | Erno Raumfahrttechnik Gmbh | Payload-extension system from spacecraft |
-
2002
- 2002-12-23 GB GB0230044A patent/GB2396595A/en not_active Withdrawn
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5271582A (en) * | 1990-06-29 | 1993-12-21 | Standard Space Platforms Corp. | Modular mother satellite bus for subsidiary payloads |
| DE4243562A1 (en) * | 1992-12-22 | 1994-06-23 | Erno Raumfahrttechnik Gmbh | Payload-extension system from spacecraft |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008030175A1 (en) * | 2006-09-04 | 2008-03-13 | Nanospace Ab | Nozzle arrangement for use in a gas thruster, gas thruster, method for manufacturing a nozzle arrangement, method for in-situ repairing of a nozzle arrangement and a method for operating a gas thrusters |
| US8336314B2 (en) | 2006-09-04 | 2012-12-25 | Nanospace Ab | Method of manufacturing a nozzle arrangement and method for in-situ repairing a nozzle arrangement |
| CN106560401A (en) * | 2015-10-02 | 2017-04-12 | 波音公司 | Dual Port Payload Attach Ring Compatible Satellite |
| EP3153412A1 (en) * | 2015-10-02 | 2017-04-12 | The Boeing Company | Dual port payload attach ring compatible satellite |
| US9796488B2 (en) | 2015-10-02 | 2017-10-24 | The Boeing Company | Dual port payload attach ring compatible satellite |
| CN106560401B (en) * | 2015-10-02 | 2021-08-06 | 波音公司 | Dual port payload attachment ring compatible satellite |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0230044D0 (en) | 2003-01-29 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |