IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0306592
(2007-06-26)
|
등록번호 |
US-8136765
(2012-03-20)
|
우선권정보 |
FR-06 05794 (2006-06-27) |
국제출원번호 |
PCT/FR2007/051516
(2007-06-26)
|
§371/§102 date |
20081224
(20081224)
|
국제공개번호 |
WO2008/001002
(2008-01-03)
|
발명자
/ 주소 |
- Geneste, Jean-Francois
- Poussin, Jean-Francois
|
출원인 / 주소 |
|
대리인 / 주소 |
Miller, Matthias & Hull, LLP
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
11 |
초록
▼
A method is disclosed for placing a satellite in an operational orbit. The satellite is equipped with its own satellite propulsion system as well as a detachable separate propulsion device. The satellite and separate propulsion device are launched into a transfer orbit by means of a space launcher.
A method is disclosed for placing a satellite in an operational orbit. The satellite is equipped with its own satellite propulsion system as well as a detachable separate propulsion device. The satellite and separate propulsion device are launched into a transfer orbit by means of a space launcher. The separate propulsion device is controlled by a satellite. The satellite is transferred from the transfer orbit to an intermediate orbit by means of the separate propulsion device. The separate propulsion device is separated from the satellite in the intermediate orbit. The satellite then enters and operational orbit from the intermediate orbit by means of its own satellite propulsion system. The intermediate orbit is disposed between the transfer and operational orbits, and is in relatively close proximity to the operational orbit but is far enough away from the operational orbit to prevent possible interferences.
대표청구항
▼
1. A method of launching a satellite into an operational orbit from a transfer orbit obtained by means of a space launcher, the satellite comprising a satellite propulsion system, compatible with launchers available on market which are not capable of direct launching into operational orbit, the meth
1. A method of launching a satellite into an operational orbit from a transfer orbit obtained by means of a space launcher, the satellite comprising a satellite propulsion system, compatible with launchers available on market which are not capable of direct launching into operational orbit, the method comprising: a) connecting the satellite to a separate propulsion device being controlled by the satellite and mounting the satellite and the separate propulsion device onto the space launcher and launching the satellite, separate propulsion device and space launcher into the transfer orbit,b) conveying the satellite and separate propulsion device, by means of the propulsion device, from the transfer orbit into an intermediate orbit, the intermediate orbit being close to the operational orbit but sufficiently far away from the operational orbit to avoid any interference with the operational orbit,c) separating the satellite from the separate propulsion device, which remains in the intermediate orbit as a graveyard orbit for the propulsion device, andd) allowing the satellite to reach the operational orbit from the intermediate orbit by means of the satellite propulsion system. 2. A method according to claim 1, wherein the transition from the intermediate orbit to the operational orbit is made by means of at least one thrust, delivered by the satellite propulsion system. 3. A method according to claim 1, also comprising a stage of rendering the separate propulsion device passive in the intermediate orbit, before or after separation of the separate propulsion device from the satellite. 4. A method according to claim 1, wherein the operational orbit is a geostationary orbit, and the intermediate orbit is a so-called graveyard orbit, at an altitude several tens to several hundreds of kilometres away from the geostationary orbit. 5. A method according to claim 1, wherein the operational orbit is an orbit known as a MEO, at an altitude of around 20,000 km, and the intermediate orbit is a so-called graveyard orbit, at an altitude several tens to several hundreds of kilometres away from the MEO. 6. Propulsion device, for the implementation of a method of launching a satellite into operational orbit from a transfer orbit obtained by means of a space launcher, the satellite comprising a satellite propulsion system, the method being compatible with launchers available on market which are not capable of direct launching into operational orbit, the method comprising at least the following stages: a) attaching a separate propulsion device to the satellite and mounting the satellite and the separate propulsion device onto the space launcher before injection of the satellite, separate propulsion devices and space launcher into the transfer orbit by the means of the space launcher and separating the space launcher from the satellite and separate propulsion device,b) conveying the satellite and separate propulsion device, by means of the separate propulsion device, from the transfer orbit into an intermediate orbit, the intermediate orbit being close to the operational orbit but sufficiently far away from the operational orbit to avoid any interference with the operational orbit,c) separating the satellite from the separate propulsion device, which remains in the intermediate orbit as a graveyard orbit for the propulsion device, andd) allowing the satellite to reaches the operational orbit from the intermediate orbit by means of the satellite propulsion system,the separate propulsion device being controlled by the satellite and the separate propulsion device comprising a launcher satellite interface adapter,at least two tanks at least one of which contains a fuel propellant and at least one other of which contains an oxidizer propellant,at least one pressurisation tank for at least one propellant,at least one apogee thruster,manifolds to supply the apogee thruster with propellants from the tanks,wherein at least two of the tanks of propellant are toroidal tanks, at least one of which is inside and at least one other of which is outside the adapter. 7. Device according to claim 6, wherein the toroidal tanks are slanted relative to each other and relative to a plane perpendicular to an axis of the adapter. 8. Device according to claim 7, wherein the two toroidal tanks are slanted relative to each other in opposite phase. 9. Device according to claim 6, wherein the at least one toroidal tank inside the adapter is intended to contain whichever of the fuel and oxidizer propellants has the highest melting point. 10. Device according to claim 6, wherein the interface adapter is of a standard conical shape, having a large and a small bases which are intended to be separably attached to the launcher and the satellite respectively.
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