The present invention relates, in general, to the technical sector of systems for deploying spacecraft's/satellites in orbit from launch vehicles and, more particularly, to an efficient satellite structure concept and its dedicated launcher interface, suitable for a single launch, or a stacking multiple launch, from a single launch vehicle.
As is known, launch vehicles (also simply known as launchers) are used to deploy spacecraft's/satellites in a predetermined orbit around the Earth. To this end, one or more systems for deploying one or more spacecraft and/or one or more satellites are typically used, each of which is generally configured to:
Some known solutions related to this sector are provided in U.S. Pat. No. 8,915,472 B2, U.S. Pat. No. 9,669,948 B2, US 2016/0318635 A1, U.S. Pat. No. 5,522,569 A, EP 1 008 516 A1, US 2013/0099059 A1 and US 2015/0151855 A1.
In particular, U.S. Pat. No. 8,915,472 B2 concerns a multiple space vehicle launch system and discloses a launch system composed of two satellites: a lower one and an upper one. The lower one is releasably attached to the upper stage of the launch vehicle by means of a standard ring interface and again releasably attached to the upper satellite by means of the same type of standard ring interface. The lower satellite bears the launch loads induced by the upper satellite, thereby eliminating the need for additional support structures (e.g., a dispenser). Both satellites include a central core structure bearing the main portion of the launch loads that is connected to the ring interfaces.
U.S. Pat. No. 9,669,948 B2 relates to a side-by-side dual-launch spacecraft arrangement and discloses a launch system composed of two satellites placed side-by-side on a dual-launch adaptor. Both satellites are releasably attached to the dual-launch adaptor by means of a standard ring interface. The dual-launch adaptor is mounted on the last stage of the launch vehicle by means of a standard ring interface. Both satellites include a central core structure bearing the main portion of the launch loads connected to the ring interface.
For a better understanding of the present invention, preferred embodiments, which are intended purely by way of non-limiting examples, will now be described with reference to the attached drawings (all not to scale), where:
The concept of the present invention is based on the following considerations. From a structural mechanics point of view, the spacecraft can be simplified as a cantilever beam subject to inertial loads induced by the launcher. It is evident that the external satellite structures are more effective for bearing the launch loads due to their higher area moment of inertia opposed to central core structures (with cross-section dimension lower than external satellite structures cross-section dimension). The area moment of inertia is a key factor in structural stiffness and strength.
The typical external surfaces of a satellite are plane, to provide the simplest and most efficient support for internal electronic units and external thermal radiators. This implies the need to introduce a dedicated launcher interface that can provide the load transition mean from the corners among the plane surfaces and the launch vehicle bolted interface.
In summary, the present invention allows a more complete exploitation of the mass capability of the launch vehicle in conjunction with a dedicated launcher interface that is relatively light and compact and remains connected to the launch vehicle after satellite separation with Earth re-entry or graveyard disposal of itself.
The satellite structural concept according to the present invention comprises an external load-bearing structure 9, typically with square or rectangular base (but also other shapes may be conveniently used).
With reference to
The vertical panels 1 are connected by means of four (or even more) corner beams 2. The corner beams 2 may have any cross-section (typically, square, rectangular or circular) and can be realized in any material typically used for satellite manufacturing. The corner beams 2 have releasable interfaces at their bottom and upper edges 8. Internal vertical shear panels 3 and horizontal platform panels 4 may also be used for structural or equipment accommodation convenience.
Always with reference to
With reference to
With reference to
The stacking of the satellites can be realized as a single tower as shown in
The releasable interfaces between stacked satellites and between the lower satellite(s) and the PAF are identical. These interfaces conveniently include:
Again with reference to
With reference to
The external planar panels 1 may incorporate the corner beams 2; this is foreseeable if additive manufacturing technologies are used.
With reference to
Two preferred, non-limiting embodiments of the inventions are:
In conclusion, it is worth noting that the present invention, which relates to a satellite structural concept with a mainly external load-carrying structure and its dedicated launcher interface, allows an efficient exploitation of the launch vehicle mass capability and satellite internal volume. This concept according to the present invention can be advantageously used for any space mission/orbit/launcher if deemed convenient.
Number | Date | Country | Kind |
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18425039 | May 2018 | EP | regional |
Filing Document | Filing Date | Country | Kind |
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PCT/EP2019/061440 | 5/3/2019 | WO |
Publishing Document | Publishing Date | Country | Kind |
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WO2019/223984 | 11/28/2019 | WO | A |
Number | Name | Date | Kind |
---|---|---|---|
5344104 | Homer et al. | Sep 1994 | A |
5522569 | Steffy et al. | Jun 1996 | A |
5529264 | Bedegrew | Jun 1996 | A |
5803402 | Krumweide et al. | Sep 1998 | A |
6276639 | Hornung et al. | Aug 2001 | B1 |
8915472 | Aston et al. | Dec 2014 | B2 |
9669948 | Vichnin et al. | Jun 2017 | B2 |
9718566 | Field | Aug 2017 | B2 |
10017279 | Poncet | Jul 2018 | B2 |
10370124 | Dube | Aug 2019 | B2 |
10538348 | Riskas | Jan 2020 | B2 |
20110296675 | Roopnarine | Dec 2011 | A1 |
20130099059 | Cheynet De Beaupre | Apr 2013 | A1 |
20150151855 | Richards et al. | Jun 2015 | A1 |
20160311562 | Apland | Oct 2016 | A1 |
20160318635 | Field et al. | Nov 2016 | A1 |
20170096240 | Cook et al. | Apr 2017 | A1 |
20170327253 | Bogdanov | Nov 2017 | A1 |
20180111707 | Poncet et al. | Apr 2018 | A1 |
20180265227 | Cheynet De Beaupre | Sep 2018 | A1 |
Number | Date | Country |
---|---|---|
1008516 | Jun 2000 | EP |
2018-30556 | Mar 2018 | JP |
2 166 588 | May 2001 | RU |
29 126 | Apr 2003 | RU |
2 577 157 | Mar 2016 | RU |
Entry |
---|
International Search Report dated Jul. 18, 2019, issued in corresponding International Application No. PCT/EP2019/061440, filed May 3, 2019, 4 pages. |
Written Opinion of the International Searching Authority dated Jul. 18, 2019, issued in corresponding International Application No. PCT/EP2019/061440, filed May 3, 2019, 6 pages. |
Hatari90; “Space Google for the planet?”; located at https://habr.com/ru/users/hatari90/comments/page10/; found on the Internet Oct. 8, 2021; printed on Nov. 16, 2021; pp. 1-7. |
Search Report from the Patent Office of the Russian Federation dated Oct. 18, 2021, issued in corresponding Russian Application No. 2020136408, filed May 3, 2019, 2 pages. |
International Preliminary Report on Patentability completed Sep. 4, 2020, issued in corresponding International Application No. PCT/EP2019/061440, filed May 3, 2019, 12 pages. |
Japanese Office Action dated Apr. 19, 2022, issued in corresponding Japanese Patent Application No. 2020-562203, filed May 3, 2019, 9 pages. |
Brazilian Office Action dated Aug. 4, 2022, issued in corresponding Brazilian Application No. 112020022592-4, filed May 3, 2019, 7 pages. |
Canadian Examination Report dated Oct. 13, 2022, issued in corresponding Canadian Patent Application No. 3,099,349, filed May 3, 2019, 4 pages. |
Chinese Office Action dated Aug. 5, 2023, issued in corresponding Chinese Patent Application No. 201980030449.3, filed May 3, 2019, 12 pages. |
Number | Date | Country | |
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20210221540 A1 | Jul 2021 | US |