CN115503984B - A satellite platform compatible with ion and Hall electric propulsion configurations - Google Patents
A satellite platform compatible with ion and Hall electric propulsion configurations Download PDFInfo
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- CN115503984B CN115503984B CN202211207103.6A CN202211207103A CN115503984B CN 115503984 B CN115503984 B CN 115503984B CN 202211207103 A CN202211207103 A CN 202211207103A CN 115503984 B CN115503984 B CN 115503984B
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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
- B64G1/40—Arrangements or adaptations of propulsion systems
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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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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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
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Abstract
The invention discloses a satellite platform compatible with ion and Hall electric propulsion configuration, wherein an electric propulsion subsystem mainly comprises two thruster modules, a storage tank supply module and a power supply module. The electric propulsion system can complete the tasks of orbital transfer of the satellite and north-south position maintenance, east-west position maintenance and angular momentum unloading of the satellite during the orbital transfer by using the full configuration of the ions and the Hall, can also complete the tasks by independently using the ions or the Hall, can directly remove the unconfigured functional modules when the ions or the Hall are independently configured for electric propulsion, has no need of adjusting the layout of other instruments and equipment of the platform, has the maximum envelope compatible with 4200C fairings, has the maximum envelope compatible with the 4200C fairings, has the advantages that equipment sensitive to electric propulsion plumes (such as optical sensors, solar wings and the like) are positioned outside the plumes, has higher ion electric propulsion ratio than the impulse, has less working medium consumption, has large Hall electric propulsion thrust and short orbital transfer time, has flexible platform configuration based on the layout scheme, has strong task adaptability and simplifies the technical state control of the platform.
Description
Technical Field
The invention relates to a satellite platform compatible with ion and Hall electric propulsion configuration, and belongs to the technical field of spacecraft design.
Background
Electric propulsion is a propulsion technique that uses electrical energy to convert it into kinetic energy of a spacecraft. Compared with the chemical propulsion technology, the specific impulse of the electric propulsion system is obviously improved, the propellant usage amount of the spacecraft can be greatly reduced, and the benefits of various aspects including reducing the launching weight of the spacecraft, improving the loading capacity of the spacecraft, prolonging the working life of the spacecraft, increasing the flight distance of the spacecraft and the like are brought, so that the full-direction capacity of the spacecraft is obviously improved.
Taking 2000kg of satellite life initial quality as an example, the propellant consumption during 15 years of life after electric propulsion can be saved by 190 kg-340 kg, and when 4000kg of satellite life initial quality is adopted, the propellant consumption during 15 years of life after electric propulsion can be saved by 500 kg-770 kg. The weight saved by the satellite can carry more load, so that the economic benefit of the satellite is improved, or the satellite with low weight can save more transmitting cost and reduce the transmitting cost of the satellite.
Currently, electric propulsion systems have been used for the mainstream geosynchronous orbit public satellite platforms in active use abroad, such as BSS-702 platform from boeing, LS-1300 platform from mike, LM2100 platform from rochal martin, ce, spaceBus Neo platform from TAS, eurostar Neo platform from air defense and aerospace, etc.
The most widely used currently on-track are ion electric propulsion systems and hall electric propulsion systems. The Hall thruster has the advantages of relatively simple structure, smaller volume, lower specific impulse than the ion thruster, larger required propellant filling quantity, larger thrust and short track changing time, relatively complex ion structure, larger volume, smaller required propellant filling quantity than the Hall thruster, smaller thrust and long track changing time.
The interface between the electric propulsion system and the spacecraft is complex, and the foreign satellite platforms are designed aiming at specific types of electric propulsion systems at present, so that compatibility design can be carried out for improving the market competitiveness of the satellite platforms, the platforms can be compatible with ions and Hall electric propulsion full configuration or selection configuration, and the configuration condition is determined according to project requirements, so that the flexibility of the application of the platforms can be greatly improved, the optimal configuration of different tasks is realized, and the comprehensive competitiveness of the satellite platforms is greatly improved.
Disclosure of Invention
The invention solves the technical problems of overcoming the defect of the adaptive capacity of the electric propulsion task of the existing platform, providing a satellite platform compatible with ion and Hall electric propulsion configuration, under any configuration condition, the satellite can complete the tasks of orbit changing, north-south position maintenance, east-west position maintenance and angular momentum unloading during the orbit of the satellite, and when the ion or Hall electric propulsion is independently configured, the unconfigured functional modules are directly removed, the layout of other instruments and equipment of the platform is not required to be adjusted, the adaptive capacity of the task of the platform is greatly improved, and the technical state control of the platform is simplified.
The technical scheme of the invention is that the satellite platform structure compatible with ion and Hall electric propulsion configuration is characterized in that an electric propulsion system is arranged on a satellite main body, the satellite main body mainly comprises a thruster module, a storage tank supply module and a power module, and the satellite main body comprises a back floor, a carrying docking frame, a satellite cabin and a satellite partition board, and the satellite platform structure is characterized in that:
Each thruster module comprises a deployable thrust vector adjusting mechanism, an ion thruster and/or a Hall thruster, wherein the ion thruster and/or the Hall thruster are/is arranged on the outer surface of the back floor through the deployable thrust vector adjusting mechanism;
the storage tank supply module comprises a gas cylinder, a pressure regulating module and a flow control module, and is used for providing propellant for the thruster module and controlling the flow of the thruster;
The power module is used for supplying power to the thruster module.
Further, the expandable thrust vector adjusting mechanism provides two side-by-side installation positions for the thrusters, the inner installation position is used for installing the ion thrusters with larger volumes, the outer installation position is used for installing the Hall thrusters with smaller volumes, the outer installation structure is of a detachable design, the outer installation structure is detached when only the ion thrusters are configured, and the Hall thrusters are connected with the inner installation structure by using the Hall switching support when only the Hall thrusters are configured, and meanwhile the outer installation structure is detached.
Further, in the storage tank supply module, the gas cylinders are one or two pairs, the gas cylinders are identical, each pair of gas cylinders is arranged on the inner surface of the back floor, and the gas cylinders are right above the carrying butt joint frame and are symmetrical about the center of the axis of the carrying butt joint frame.
Further, the bottom of the gas cylinder is arranged right above the carrying butt joint frame, and the mounting screw is directly connected with the carrying butt joint frame through the back floor.
Further, in the tank supply module, the pressure regulating module is one and is installed on the satellite partition board.
Further, in the storage tank supply module, the flow control module comprises two groups of ion flow control modules and/or two groups of hall flow control modules, wherein each two groups of ion flow control modules or each two groups of hall flow control modules are symmetrically arranged on two sides of the back floor, and each group of ion flow control modules or hall flow control modules are used for controlling the flow of the ion thrusters or hall thrusters on the same side.
Further, the power supply module comprises two ion power supply modules and/or two Hall power supply modules, and the power supply modules are intensively installed in the satellite cabin and supply power for the ion thruster and/or the Hall thruster.
Further, the gas cylinder is a xenon gas cylinder.
The electric propulsion system can complete the tasks of orbital transfer of the satellite and north-south position maintenance, east-west position maintenance and angular momentum unloading of the satellite during the orbital transfer by using the full configuration of the ions and the Hall, can also complete the tasks by independently using the ions or the Hall, can directly remove the unconfigured functional modules when the ions or the Hall are independently configured for electric propulsion, has no need of adjusting the layout of other instruments and equipment of the platform, has the maximum envelope compatible with 4200C fairings, has the maximum envelope compatible with the 4200C fairings, has the equipment sensitive to electric propulsion plumes (such as optical sensors, solar wings and the like) outside the plumes, has higher ion electric propulsion ratio and small Hall electric propulsion volume, has flexible platform configuration based on the layout scheme, has strong task adaptability and simplifies the technical state control of the platform.
Drawings
FIG. 1 is a schematic diagram of a thruster module layout (fully deployed);
FIG. 2 is a schematic diagram of a thruster module layout (single ion);
FIG. 3 is a schematic diagram of a thruster module layout (single Hall);
FIG. 4 is a schematic diagram of a xenon bottle layout;
FIG. 5 is a schematic diagram of a xenon bottle and flow control sub-module layout (fully configured);
FIG. 6 is a schematic diagram of a xenon bottle and flow control sub-module layout (single ion);
FIG. 7 is a schematic diagram of a xenon bottle and flow control sub-module layout (single Hall);
FIG. 8 is a schematic diagram of a power module and pressure regulation module layout (fully configured);
Detailed Description
The invention is described in further detail below with reference to the attached drawings and specific examples:
the instrument and equipment of the electric propulsion system can be divided into 3 functional modules according to the functions realized by the instrument and equipment, namely a thruster module, a storage tank supply module and a power supply module, wherein the thruster module consists of 1 expandable thrust vector adjusting mechanism 1, 1 ion thruster 2 and/or 1 Hall thruster 3, wherein the expandable thrust vector adjusting mechanism 1 is used for realizing the functions of installation and fixation of the thruster, thrust direction adjustment and the like, the storage tank supply module is used for realizing the functions of storage, pressure adjustment and flow control of electric propulsion working media, and the power supply module is used for converting input electric energy into various voltages and currents required by the operation of the thruster.
The following aspects are comprehensively considered when the layout of each functional module of the electric propulsion system is carried out:
the comprehensive efficiency of the electric thruster during operation is as high as possible, so that the working medium demand during on-orbit is reduced, and the volume and the weight of the storage and supply module are reduced;
The interference force and the interference moment of the electric thruster during working are as small as possible, so as to ensure that the attitude control precision of the satellite during the electric propulsion working meets the index requirement;
The adverse effect of the plume of the electric thruster on optical sensitive equipment, solar wings and other extra-satellite equipment is avoided, or the influence is reduced to be within an acceptable range during the service life of the satellite;
The adverse effect of heat flow on surrounding components during the operation of the electric thruster is avoided or the effect is reduced to be within an acceptable range;
When the storage and supply module layout is carried out, the mass center variation of the satellite caused by the consumption of the electric propulsion working medium during the orbit of the satellite is as small as possible so as to avoid the difficulty of attitude control of the satellite and increase the consumption of additional working medium;
the weight of the working medium container in a full state reaches tens to hundreds of kilograms, and the installation position must have better strength and rigidity;
Ensuring that the layout of the electric propulsion system is compatible with the available envelope of the carrying fairing;
As the variable configuration of the platform, the layout of each module of the electric propulsion system must be comprehensively considered, so that when the configuration is changed, the layout of other instruments and equipment of the platform can be kept unchanged, the centroid position of the platform is stable, and the centroid position is not deflected in a large range due to the configuration change.
Among the above 3 functional modules, the most significant effect of the thruster module on the platform layout is mainly due to the fact that the layout of the thruster module determines the on-orbit application strategy of the electric propulsion system, and thus the selection of solar wings (related to power requirements), the configuration of control subsystems (related to application strategy) and the arrangement of sensors (avoiding thruster plumes), the layout of the thruster module determines the working efficiency of the electric propulsion system, and thus the working medium consumption during service life and the size of the working medium storage container (gas cylinder or tank), the layout of the thruster module determines the structural design and material selection of relevant parts (related to the rigidity and strength of the platform structure), and the layout of the thruster module relates to the compatibility with the carrying envelope (related to the available space of the fairing).
In view of the above, when designing the layout of the electric propulsion system, the layout of the thruster module should be determined first, and then the layout work of the remaining three functional modules of the electric propulsion system should be performed.
(1) Layout of thruster modules
Each thruster module comprises 1 deployable thrust vector adjustment mechanism 1,1 ion thruster 2 and/or 1 Hall thruster 3, wherein the ion thruster 2 and/or the Hall thruster 3 are/is arranged on the outer surface of the satellite back floor 10 through the deployable thrust vector adjustment mechanism 1, and the installation positions of the two thruster modules are centrally symmetrical with respect to the Z axis of the satellite mechanical coordinate system;
The expandable vector adjustment mechanism is used for adjusting the thrust direction of the electric thruster, and expanding after entering orbit, and in the orbit changing process, the thrust vector is always directed to the satellite-Z direction so as to ensure that the angular efficiency of the thrust vector is not lost, and in the position protection process, the thrust vector always passes through the mass center of the satellite, thereby reducing the interference force and the interference moment during the electric propulsion work.
The deployable thrust vector adjusting mechanism 1 provides two side-by-side mounting positions for the electric thruster, the inner side mounting position is used for mounting the ion thruster 2 with larger volume, the outer side mounting position is used for mounting the Hall thruster 3 with smaller volume, the outer side mounting structure is of a detachable design, the outer side mounting structure is detached when only the ion thruster 2 is configured, and the Hall thruster 3 is connected with the inner side mounting structure by using the Hall switching support 5 when only the Hall thruster 3 is configured, and meanwhile the outer side mounting structure is detached.
The layout mode makes the installation, adjustment and test of the thruster module very convenient, and the platform outer envelope is compatible with the 4200C fairing carried, and when the thruster is unfolded, all the optical sensitive devices, solar wings and the like are positioned outside the plume main beam of the thruster.
In the fully configured state, the layout of the thruster module is shown in fig. 1;
when ion electric propulsion is independently configured, the layout of the thruster module is shown in fig. 2;
when the Hall electric propulsion is independently configured, the layout of the thruster module is shown in fig. 3;
(2) Layout of tank supply module
In the invention, the tank supply module consists of a gas cylinder (working medium container), a pressure regulating module 16, a flow control module, related pipelines and cables, and in the embodiment, the gas cylinder is a xenon gas cylinder.
In order to improve the structural strength and rigidity of the installation position of the electric thruster module, ensure that the change amount of the mass center of the satellite caused by the consumption of electric propulsion working medium during the orbit of the satellite is as small as possible, and provide enough space for the installation of instruments and equipment of the south plate 7 and the north plate 8 of the satellite, 4 xenon cylinders 13 are symmetrically installed at four corners of the back floor 10 and right above the carrying docking frame 4 and are positioned at a distance of 8300mm from the south plate 7 and the north plate 8, the symmetrical arrangement of the 4 xenon cylinders 13 ensures that the consumption of the electric propulsion working medium does not cause the change of the transverse mass center of the satellite, and meanwhile, the space of 300mm can cover the height of the equipment and provide enough operation space, so that the assembly operation of the instruments and the south plate 7 and the north plate 8 after the installation of the xenon cylinders 13 is convenient.
The bottom of the xenon bottle 13 is arranged right above the carrying docking frame 4, and the mounting screw is directly connected with the carrying docking frame 4 through the back floor 10, so that the mass center of a satellite is reduced, the force transmission path of the xenon bottle 13 is shortened, the structural design is lighter, and the top of the xenon bottle 13 is connected with the south plate 7, the north plate 8, the north-south partition plate 9 and the east-west plate 6 through the bottle support 17. The layout position of the xenon bottle 13 on the back floor 10 is shown in fig. 4.
When the ion electric propulsion is independently configured, the requirement can be met only by two xenon cylinders 13 because the filling amount of the working medium is less than that of the ion electric propulsion, at the moment, the two xenon cylinders 13 on the diagonal are not configured, and the configuration change of the xenon cylinders 13 can not cause the change of the transverse mass center of the satellite.
The flow control submodule has the function of providing working medium with required flow for various working modes of the electric thruster. In the invention, 2 groups of ion flow control modules 11 and 2 groups of Hall flow control modules 12 are symmetrically arranged on the two sides of the satellite back floor 10. The flow control submodule is completely symmetrical at the layout position of the platform, so that the transverse centroid of the whole star is basically unchanged in a single ion or single Hall state.
In the fully configured state, the layout of the xenon bottle 13 and the flow control sub-module back floor 10 is shown in fig. 5.
When the ion electric propulsion is independently configured, the layout of the xenon bottle 13 and the flow control sub-module back floor 10 is shown in fig. 6.
When the Hall electric propulsion is independently configured, the layout of the xenon bottle 13 and the flow control sub-module back floor 10 is shown in fig. 7.
The pressure regulating module 16 is mainly composed of a pressure reducing gas cylinder, a regulating valve and related pipelines (such as an electric propulsion pipeline 18), and has the function of regulating the high-pressure working medium in the gas cylinder to the pressure required by the normal operation of the flow control submodule. The pressure regulating sub-module has large volume, and is arranged on a satellite north-south partition board 9 in the invention, and the specific layout is shown in fig. 8.
(3) Layout of power supply module
In the invention, the power supply module comprises 2 ion power supply modules 14 and (or) 2 Hall power supply modules 15,4 power supply modules are intensively installed in the satellite cabin, each power supply module supplies power to the ion thruster 2 and (or) the Hall thruster 3 on the same side, the specific installation position of the single power supply unit depends on the heat consumption and the required heat dissipation area of the single power supply unit when the electric propulsion system works, and the single electric propulsion power supply unit is installed on the south plate 7 as shown in fig. 8. When ion or hall electric propulsion is configured separately, the power supply is configured accordingly.
Taking a medium capacity geosynchronous orbit satellite platform which is researched in China as an example, the implementation mode and implementation effect of the invention are described:
the platform may employ an ion electric propulsion system based on an ion thruster of about 30cm in diameter, a thrust of 160mN, a specific impulse of 3500, or a hall electric propulsion system based on a hall thruster of about 15cm in diameter, a thrust of 265mN, a specific impulse of 1650.
Assuming that the satellite emission mass m based on the platform is 2100kg, the average value of the Z-direction barycenter height in the middle of life is about 1300mm, the transverse (X, Y-direction) barycenter coordinates are assumed to be 0mm for simplicity, the orbit transfer efficiency of the Hall thruster and the ion thruster is 0.99, the thrust vector of the Hall thruster and the ion thruster (in the YOZ plane of the satellite and through the barycenter) and the Y-axis have included angles of 50 degrees and 45 degrees respectively, and the working efficiency eta of the satellite in the north-south position is about 0.65 and about 0.70 respectively.
The track-change speed increment is 2600m/s.
The satellite position remains at 770m/s for a 15 year lifetime with a total velocity increase.
When using ion electric propulsion:
total propellant consumption and rail change time during rail change are:
mp＝m·(1-e-Δv/Igη)=2100×(1-exp(-2600/3500/9.8/0.99))≈155kg。
Δt=Δm/(F p/I/g) =155/(0.16×2/3500/9.8) =192 days
The total propellant consumption during the 15 year life of the site is:
mp＝m·(1-e-Δv/Igη)=(2100-155)×(1-exp(-770/3500/9.8/0.70))≈61kg。
when using hall electric propulsion:
total propellant consumption and rail change time during rail change are:
mp＝m·(1-e-Δv/Igη)=2100×(1-exp(-2600/1650/9.8/0.99))≈314kg。
Δt=Δm/(F p/I/g) =314/(0.265×2/1650/9.8) =110 days
The total propellant consumption during the 15 year life of the site is:
mp＝m·(1-e-Δv/Igη)=(2100-314)×(1-exp(-770/1650/9.8/0.65))≈126kg。
In order to meet the use requirement of 15 years of north-south position maintenance, the total carrying capacity of the propellant is 155 kg+61kg=216 kg when using ion electric propulsion, namely, 2 xenon cylinders with the same size are arranged, each cylinder has 120kg capacity, the track changing time is 192 days, and the total carrying capacity of the propellant is 314 kg+126kg=440 kg when using Hall electric propulsion, namely, 4 xenon cylinders with the same size are arranged, and each cylinder has 120kg capacity. The track change time is 110 days;
Under the conditions of the same take-off weight, service life and load power, when the electric propulsion of the ion is configured, the payload carrying weight of the medium capacity geosynchronous orbit satellite platform is 224kg higher than that of the electric propulsion of the Hall satellite, but the orbit time is 82 days more, the platform can flexibly select the electric propulsion configuration according to the load weight and the orbit time, and the configuration layout design does not need to be adjusted, so that the electric propulsion platform has very strong task adaptability.
The present invention is not described in detail as being well known to those skilled in the art.
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| CN118549138B (en) * | 2024-07-02 | 2025-02-25 | 北京东方计量测试研究所 | Hall thruster oscillation photoelectric joint monitoring device and method |
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| CN105883008A (en) * | 2014-12-15 | 2016-08-24 | 中国空间技术研究院 | Satellite thruster layout method |
| CN111891404A (en) * | 2020-07-31 | 2020-11-06 | 上海卫星工程研究所 | Layout method and system for electrified dual-mode thruster of high-orbit maneuvering satellite platform |
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| CA2831309C (en) * | 2012-12-04 | 2017-05-30 | The Boeing Company | Methods and apparatus for performing propulsion operations using electric propulsion systems |
| FR3010053B1 (en) * | 2013-08-30 | 2016-10-21 | Thales Sa | METHOD AND DEVICE FOR ELECTRICAL PROPULSION OF SATELLITE |
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| CN111891404A (en) * | 2020-07-31 | 2020-11-06 | 上海卫星工程研究所 | Layout method and system for electrified dual-mode thruster of high-orbit maneuvering satellite platform |
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