• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a satellite propulsion system comprising: - at least one reservoir comprising a propulsion reagent, and - at least one reservoir (6) comprising a propellant gas pressurizing the propulsion reagent - at least one transport means (8 ) propellant gas from the propulsion gas tank to the propulsion reagent tank, the conveying means (8) comprising at least one opening (13) for continuous leakage of the propellant gas (7), and - at least a device (12) for isolating, after the operational orbiting of the satellite, an area (14) comprising the opening (13) of the rest of the propulsion system (1).
    公开号:FR3023829A1
    申请号:FR1401586
    申请日:2014-07-16
    公开日:2016-01-22
    发明作者:Laurent Fontaine
    申请人:Thales SA；
    IPC主号:
    专利说明:

    [0001] The invention is in the field of satellites and more particularly relates to a propulsion device for satellite. The invention finds particular application in the field of geostationary satellites. In order to send a satellite on its operational orbit and then to keep it stationary for the duration of the satellite's operation, propulsion means must be provided. As a rule, a device comprising at least one reservoir comprising propellant is used which is pressurized. The term "ergol" means a substance used alone or in combination with other substances and intended to provide energy. There are several types of propellant propulsion device: A bi-propellant device comprising two tanks comprising the propellants. It further comprises a propellant tank comprising, for example, helium at high pressure, the propellant gas for pressurizing the propellants. A mono-propellant device comprising a reservoir divided into two compartments by a membrane: a compartment comprising propellant, usually hydrazine, and a compartment comprising a gas which presses on the membrane so as to pressurize the propellant. There are also mono-propellant devices without membrane whose structure is similar to that of bi-propellant devices.
    [0002] Figure 1 shows a block diagram of a propelling device biergol, according to the prior art. The bi-propellant propulsion device 1 comprises a first portion 2 at low pressure and a second portion 3 at high pressure.
    [0003] The first part 2 low pressure includes two tanks 4 propellant. In this case, the propellants used include MMH acronym for monomethylhydrazine and MON, acronym for Mixed Oxides Nitrogen. The second high pressure part 3 comprises at least one tank, in this case it comprises two tanks 6 containing a propellant gas 7, in this case helium, the propellant gas 7 being at high pressure, 300 bar approximately, before the satellite is put into orbit. The helium 7 under pressure is injected via conduits 8 and a pressure regulator 9 into the propellant tanks 4 so as to pressurize the propellants 5, the pressure regulated in the ducts 8 downstream of the pressure regulator 9 being of the order of 20 bars. In other words, all the ducts 8 situated in the second part 3 upstream of the pressure regulator 9 comprise propellant gas 7 at high pressure and the ducts 8 situated in a part 2 downstream of the pressure regulator 9 comprise Propulsion gas 7 at low pressure.
    [0004] In the second part 3, the pressure before launching the satellite is between 200 and 300 bar. After putting on its operational orbit, the pressure in the second part 3 is between 30 and 50 bar. Downstream of the pressure regulator 9, the pressure is about 20 bar. A PV1-NC valve 10 of the "closed" type in nominal mode is disposed between the propulsion gas tanks 6 and the pressure regulator 9. This valve PV1-NC 10 allows the supply of the propellant gas 7 at the regulator pressure 9 during the operation of the nozzles 11a, 11b in particular at the time of putting into orbit and holding the satellite station.
    [0005] The operating principle of the device according to the prior art is summarized as follows. During the filling of the propulsion reagent tanks 4 and the propulsion gas tanks 6, the PV1-NC valve 10 is in the "closed" position. When launching the satellite, the PV1-NC valve 10 is open, the propellant gas 7 is introduced under a pressure of about 20 bars inside the propellant tanks 4. The pressurized propellants 5 are then injected into the nozzles 11a, 11b. The amount of propellant gas 7 and propulsion reagents 5 must be sufficient to launch the satellite into its operational orbit, maintain the satellite in its operational orbit and position the satellite in its final orbit when the satellite it is at the end of service. Today, the end-of-service satellites include residual energy sources, such as propellant gases or propellants. In accordance with a new LOS Acronym for "Low Orbital Spatial" in English, which comes into force in 2020, all energy sources within a satellite must be eliminated when it is at the end of the year. service. A first solution envisaged to comply with the LOS regulation is to isolate the second part 3, in particular, using at least one PV7-NO 12 valve of the "open" type in nominal mode arranged in such a way as to isolate the first part 2 of Part 2 3 when the satellite is in its operational orbit, and to add a controllable "closed" type pyrotechnic valve disposed at the second part 3. When it is decided to terminate operation of the satellite, the "closed" type pyrotechnic valve disposed at the second part 3 is actuated so as to evacuate all the remaining propellant gases, the residual propellants 5 being able to be discharged via the nozzles 11a; 11b.
    [0006] However, this solution has certain drawbacks, in particular: the addition of additional mass of approximately 300 g corresponding in particular to the pyrotechnic valve and its supports. However, any excess mass aboard a satellite represents a significant additional cost. - the need for testing to ensure the proper functioning of the pyrotechnic valve requiring additional labor time. The present invention consists in proposing an alternating propulsion system enabling in particular the elimination of the propulsion gases from the propulsion system passively. The invention is particularly applicable to a propellant device of bi-ergol or mono-propellant type without membrane. According to one aspect of the invention, there is provided a satellite propulsion system comprising: at least one reservoir comprising a propulsion reagent, and at least one reservoir comprising a propellant gas pressurizing the propulsion reagent; means for transporting the propellant gas from the propulsion gas tank to the propellant reagent tank, the conveying means comprising at least one opening for continuous leakage of the propellant gas, and - at least one device for isolating after the satellite is put into operational orbit, an area comprising the opening of the remainder of the propulsion system. The invention notably allows the evacuation of the propulsion gases in a passive manner without the intervention of an operator.
    [0007] In one embodiment the means for transporting the propellant gas further comprises a pressure regulator, the opening being located downstream of the pressure regulator. Alternatively, the opening is located upstream of the pressure regulator.
    [0008] Advantageously, the diameter of the opening is between 1 and 20 microns and preferably equal to 11 microns. This order of magnitude of the diameter of the opening allows a slow and continuous elimination of the propellant during the operational lifetime of the satellite, and possibly for a few years after the scrapping of the satellite without interfering with the launch, the posting , maintaining on its operational orbit and putting it into position on its final orbital or satellite graveyard at the end of its life. In one embodiment, the opening is connected to the outside of the propulsion system.
    [0009] In another embodiment, the opening is connected with the propulsion reagent reservoirs. The invention will be better understood on reading the description given by way of examples. The description refers to the drawings which accompany it in which: FIG. 1, already described, schematically represents a bi-propellant propulsion device, according to the known art, FIG. embodiment of the bi-propellant type propulsion system, according to one aspect of the invention, and Figure 3 represents revolution of the helium pressure in a duct located upstream of the pressure regulator, according to one aspect of the invention.
    [0010] FIG. 2 represents an embodiment of a propulsion system according to the invention. The propulsion system comprises: - two propulsion gas tanks 6, a pressure regulator 9, and a valve PV1-NC 10 disposed between the pressure regulator 9 and the propulsion gas tanks 6, - two tanks 4 of propellants and nozzles 11a, 11b, propulsion gas transport means such as ducts 8, the ducts having at least one opening 13 for continuous gas leakage, and - a device 12 for isolating an area 14 comprising the opening 13, the device can be at least one PV7-NO 12 valve. In this case, the zone 14 comprises in particular the gas reservoirs 6, the pressure regulators 9. In practice, the opening 13 according to FIG. the invention may take the form of a T-shaped bypass of one of the ducts 8 in which the propellant gas 7 circulates, one of the mouths of the bypass being surmounted by a plug having a calibrated opening 13 of to allow a slow and continuous leak e propellant gas. In summary, the invention consists in producing an opening 13 so as to evacuate the propellant gas 7 throughout the duration of operation of the satellite so that the residual pressure P-Res of propellant gas at the end of use of the satellite is less than a threshold value Ps compliant with the LOS regulation without hindering or preventing the launch and maintenance of the satellite in its orbit, the threshold value Ps being of the order of 2 bars, 25 and preferably of 0.20 bar. In another embodiment, the zone 14 comprises only the opening 13, the opening 13 being connected with the outside of the propulsion system 1.
    [0011] In another embodiment, the zone 14 further comprises the tanks 4 propellant and the opening 13 is connected to the tanks 4 for pressurizing the propellant 5 and maintain the performance of the nozzles 11a; 11b. The zone 14 comprising the opening 13 and the tanks 4 propellant is well isolated from the rest of the propulsion system 1 The opening 13 is located upstream of the pressure regulator 9 or downstream of the pressure regulator 9. When the opening 13 is located upstream of the pressure regulator, the opening 13 must be sufficiently strong to prevent tearing of the walls of the opening under the effect of the pressure of about 200 to 300 bar and in particular during the start of satellite commissioning. By cons, when the opening 13 is downstream of the pressure regulator 9, the pressure exerted on the walls of the opening 13 is less important, it is limited to about 20 bar. The opening 13 has any section. Advantageously, the section of the opening 13 is circular. When the opening 13 is located downstream of the pressure regulator 9, the diameter of the opening 13 is between 1 and 20 microns, and preferably 11 microns. The value of the diameter of the opening 13 results from a compromise between the leakage velocity of the propellant gas 7 so that the residual pressure PR of the propulsion gas is lower than the threshold value Ps at the end of the operation of the satellite. and the need to maintain a minimum pressure within the second zone 2 so as to allow the propulsion device 1 to play its role in maintaining the position of the satellite until it is discarded. In other words, the propulsion gas leak 7 must be large enough for the amount of residual gas at the end of the satellite's service to comply with the LOS regulation. However, the leak must not be too important so as not to hinder the sending of the satellite in its operational orbit and to allow the satellite station to be maintained, that is to say to allow the operation of the nozzles 11a, 11b throughout the operational operation of the satellite.
    [0012] When the opening 13 is disposed downstream of the pressure regulator 9, a circular opening 13 having a diameter of 11 microns causes a decrease in the estimated pressure to about 5 to 30 bar in the tanks 6 of propellant gas during the first fifteen days corresponding to the launch into orbit. This loss of pressure is considered as an acceptable decrease in terms of impact with respect to the sending and the positioning of the satellite. At the end of the service of the satellite, that is to say, about 15 years after it is put into orbit, the estimated residual pressure of the propellant gas 7 is less than 0.2 bar. The operating principle of the propulsion system according to the invention described above can be summarized as follows. Before the launch of the satellite, the propulsion gas tanks 6 are filled with propellant gas, the pressure of the propellant gas 7 is about 300 bar. The PV1-NC valve 10 is in the closed position, the gas 7 is not injected into the tanks 4 of propulsion reagents. When launching the satellite, the PV1-NC valve 10 is open, the gas is injected into the propellant tank 4. After switching on the satellite, the pressure inside the propulsion gas tanks 6 is between 30 and 50 bars. The PV7-NO 12 valve is closed to isolate the zone 14 comprising the opening 13. The PV1-NC valve 10 remained in the open position allows the propellant gas 7 to escape via the opening 13. embodiment of the invention, the propellant gas 7 can be discharged to the outside of the propulsion system 1, or re-injected to the tanks 4 propellant so as to pressurize the propellant 5 for use of the nozzles 11a , 11 b later. In another mode of operation, the opening 13 may be composed of two or even a plurality of openings 13 arranged in opposition in order to avoid creating upsets disturbing the trajectories of the satellite.
    [0013] FIG. 3 shows an evolution of the pressure inside a pipe upstream of the pressure regulator during the operational service of the propulsion device according to the invention. In this case, the opening 13 is disposed downstream of the pressure regulator 9. A first period P1 corresponds to the filling period of the propellant tank 4, the PV1-NC valve 10 being in the "closed" position. During this period, the pressure increases rapidly to a pressure of about 300 bar.
    [0014] A second period P2 corresponds to a period of latency between the end of the filling of the propellant tank 4 and the beginning of putting on its operational orbit of the satellite. The PV1-NC valve 10 still being in the "closed" position, no decrease in pressure is observed. A third period P3 of about 15 days corresponds to the setting of the satellite. During this step, the valve PV1-NC 10 is activated in the "open" position and the valve PV7-NO 12 is inactive in the "open" position. This orbiting step requires a large amount of pressurized propellant, requiring a large amount of helium. The helium pressure in the high pressure zone 13 decreases sharply to a value of between 30 and 50 bar. During this third period, the propulsion gas leak 7 via the opening 13 is effective. However, the decrease in helium pressure related to the setting post is such that the decrease in helium pressure via the opening 13 appears to be negligible.
    [0015] A fourth period P4 corresponds to the operational operating time of the satellite, this period generally lasting between 15 and 20 years. During this fourth period P4, the pressure of the propulsion gas 7 decreases with a slope lower than the decrease observed at the time of setting to a minimum value, the decrease corresponding to the propellant gas leakage 7 according to the invention. The fifth period P5 corresponds to the end of the service of the satellite, part of the minimum pressure serving in particular for putting the final orbit of the satellite, the residual pressure after the final orbiting of the satellite at the end of service is less than a threshold pressure Ps defined by the LOS regulation. The remaining propellant gas continues to escape slowly and continuously via the opening 13.10
    权利要求:
    Claims (7)
    [0001]
    REVENDICATIONS1. A satellite propulsion system comprising: - at least one reservoir (4) comprising a propulsion reagent, and - at least one reservoir (6) comprising a propellant gas (7) pressurizing the propulsion reagent (5), - at least one means (8) for conveying the propellant gas from the propulsion gas reservoir to the propulsion reagent reservoir (4), the conveying means (8) comprising at least one opening (13) for continuous leakage of propellant gas (7), and - at least one device (12) for isolating, after the operational orbiting of the satellite, an area (14) comprising the opening (13) of the rest of the propulsion system (1).
    [0002]
    2. System according to claim 1, wherein the transport means (8) of the propellant gas further comprises a pressure regulator (9), the opening (13) being located downstream of the pressure regulator (9).
    [0003]
    3. System according to claim 1 wherein the transport means (8) of the propellant gas further comprises a pressure regulator (9), the opening (13) being located upstream of the pressure regulator (9). 20
    [0004]
    4. System according to one of the preceding claims wherein the diameter of the opening (13) is between 1 and 20 microns.
    [0005]
    5. System according to claim 4 wherein the diameter of the opening (13) is equal to 11 microns.
    [0006]
    6. System according to one of the preceding claims wherein the aperture (13) is connected with the outside of the propulsion system.
    [0007]
    7. System according to one of the preceding claims wherein the opening (13) is connected with the reservoir (4) of propellant reagent.
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    同族专利:
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    US20160016677A1|2016-01-21|
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3732693A|1970-11-27|1973-05-15|Chin Chu Ju|Controllable solid propulsion system|
    US5158362A|1991-02-08|1992-10-27|General Electric Company|Method for measuring the mass of liquid in a storage tank|
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    CN110104225A|2019-04-25|2019-08-09|北京控制工程研究所|A kind of in-orbit loading system of voltage-multiplying type satellite based on board-like surface tension propellant tank|
    CN110566369A|2019-08-27|2019-12-13|上海空间推进研究所|Pressure supplementing type space propulsion system suitable for high-capacity surface tension storage tank|
    法律状态:
    2015-06-29| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-22| PLSC| Search report ready|Effective date: 20160122 |
    2016-06-28| PLFP| Fee payment|Year of fee payment: 3 |
    2017-06-28| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-28| PLFP| Fee payment|Year of fee payment: 5 |
    2020-06-25| PLFP| Fee payment|Year of fee payment: 7 |
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    FR1401586A|FR3023829B1|2014-07-16|2014-07-16|PROPULSION DEVICE FOR SATELLITE FOR PASSIVE ELIMINATION OF PROPELLER GAS|FR1401586A| FR3023829B1|2014-07-16|2014-07-16|PROPULSION DEVICE FOR SATELLITE FOR PASSIVE ELIMINATION OF PROPELLER GAS|
    EP15174130.3A| EP2974966B1|2014-07-16|2015-06-26|Propulsion device for satellite allowing the passive removal of propellant gas|
    US14/796,969| US9908641B2|2014-07-16|2015-07-10|Satellite propulsion device allowing passive elimination of pressurizing gas|
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