Regional collaborative two-phase hybrid space propulsion system and propulsion method

Abstract

The present invention discloses a regional cooperative two-phase hybrid space propulsion system and propulsion method, including a propellant supply system and a chemical-electric composite thruster; the propellant in the propellant supply system can be used as an electric working medium; the chemical-electric composite thruster includes an electric thruster and a chemical thruster coaxially arranged from the inside to the outside or from the outside to the inside; 4m chemical thruster sub-areas are evenly arranged in the throat and expansion nozzle of the chemical thruster along the circumferential direction; 2m baffles that can rotate are arranged at the front end of the throat; the electric thruster can be divided into zones or not according to needs; when divided into zones, 4n grid insulation partitions are added to the grid, so that the grid is evenly divided into 4n grid sub-areas along the circumferential direction, and each grid sub-area can be individually energized and controlled. The present invention can realize the alternating operation of chemical and electric propulsion modes under the premise of sharing a set of propellant supply systems; it can also realize regional control of thrust, so as to meet the needs of different space propulsion tasks.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft space propulsion technology, and in particular to a regional cooperative two-phase hybrid space propulsion system and a propulsion method. Background Art

[0002] With the continuous expansion of space mission scenarios, in order to meet the growing demand for efficient use of space missions, future spacecraft propulsion systems need to have high specific impulse, wide range of adjustable thrust, green and non-toxic capabilities. At present, most spacecraft use traditional chemical propulsion, which has highly toxic propellants and low specific impulse, resulting in a large amount of propellant required, reducing the payload ratio, and making it difficult to achieve precise control of thruster performance. In comparison, most electric propulsion has greater advantages in specific impulse and thrust control, but because its thrust is relatively small compared to chemical propulsion, it is difficult to support rapid maneuvers and other attitude and orbit control tasks. The two propulsion methods have different characteristics and scope of application. There are certain limitations when performing tasks alone, and they cannot meet the established requirements of complex space missions. Carrying multiple different types of thrusters at the same time will complicate the system structure. Therefore, spacecraft urgently need a propulsion system that can realize the integration of chemical and electric propulsion.

[0003] In addition, when performing high-precision attitude control on a spacecraft, it is often necessary to set an additional direction or angle change mechanism for the thruster, which to a certain extent causes the weight of the spacecraft and the redundancy of various components. The present invention proposes a type of regional cooperative thrust system, which can achieve high-precision attitude adjustment of the spacecraft on the basis of simplifying the entire thrust system. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a regional collaborative two-phase hybrid space propulsion system and a propulsion method in view of the deficiencies of the above-mentioned prior art. The regional collaborative two-phase hybrid space propulsion system and the propulsion method can realize the alternating operation of chemical and electric propulsion modes under the premise of sharing a set of propellant supply system; and can also realize regional control of thrust, thereby meeting the needs of different space propulsion missions.

[0005] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0006] A regional cooperative two-phase hybrid space propulsion system comprises a propellant supply system and a chemical-electric composite thruster.

[0007] Chemical-electric composite thrusters include external chemical-internal electric composite thrusters and external electric-internal chemical-combined thrusters.

[0008] The externalized internal electric composite thruster includes an electric thruster and a chemical thruster coaxially sleeved on the outer periphery of the electric thruster.

[0009] The external-electric-internal-chemical composite thruster includes an electric thruster and a chemical thruster coaxially inserted in the center of the electric thruster.

[0010] The propellant supply system comprises a propellant supply branch 1, a propellant supply branch 2 and an electrical fluid supply branch.

[0011] The propellant 1 supply branch and the propellant 2 supply branch supply propellant 1 and propellant 2 to the chemical thruster respectively; one of the propellant 1 and the propellant 2 is a fuel, the other is an oxidant, and the propellant 2 can be used as an electrical medium.

[0012] The electric working fluid supply branch is connected to the second propellant supply branch and is used to supply the electric working fluid to the electric thruster.

[0013] The electric thruster includes a cylindrical tube and a grid, and the chemical thruster includes a combustion chamber, a throat and a diffuser arranged in sequence along the direction of the airflow.

[0014] A. When the chemical-electric thruster is an external chemical-internal electric thruster, the specific setting method of the electric thruster and the chemical thruster is:

[0015] The electric thruster is a non-partitioned electric heating type or resistance type thruster.

[0016] The cavity between the electric thruster and the chemical thruster is formed as a chemical thrust cavity.

[0017] For the chemical thruster: 4m partition plates are evenly arranged along the circumferential direction in the chemical thrust cavity corresponding to the throat and the expansion nozzle, thereby dividing the chemical thrust cavity into 4m chemical thrust sub-zones; 2m baffle plates are arranged in the chemical thrust cavity at the front end of the throat, each baffle plate can rotate along the circumferential direction and block the corresponding chemical thrust sub-zone; where m is a natural number,

[0018] B. When the chemical-electric thruster is an external-electric and internal-chemical thruster, the specific setting method of the electric thruster and the chemical thruster is:

[0019] For chemical thrusters: a central axis is set at the center of the throat and the expander, and 4m partition plates are evenly arranged along the circumference of the central axis, so as to divide the inner cavity of the throat and the inner cavity of the expander into 4m chemical thrust sub-zones; 2m baffles are arranged on the outer periphery of the central axis at the front end of the throat, each baffle can rotate along the circumference and seal the corresponding chemical thrust sub-zone.

[0020] For electric thrusters: the grid is arranged in a cylindrical tube on the outer periphery of the tail end of the expansion nozzle, and the grid partition form is set according to the selected electric thruster type, specifically:

[0021] a. When the electric thruster is a Hall thruster, the gate is not divided into zones.

[0022] b. When the electric thruster is a non-Hall thruster, 4n gate insulating partitions are added to the gate, so that the gate is evenly divided into 4n gate sub-areas along the circumferential direction, and each gate sub-area can be individually powered; wherein n is a natural number.

[0023] The electric heating or resistance type thrusters are arc thrusters or resistance heating thrusters.

[0024] Non-Hall thrusters are ion thrusters or electron cyclotron resonance ion thrusters.

[0025] When the chemical-electric composite thruster is an external-electric and internal-chemical composite thruster, the outer wall of the chemical thruster is coated with high-temperature resistant ceramic material to isolate the electric thruster.

[0026] When the chemical-electric hybrid thruster is an external-electric and internal-chemical hybrid thruster, the tail end face of the expansion nozzle protrudes from the outer end face of the grid.

[0027] Propellant 1 is oxygen or kerosene; propellant 2 is hydrogen, hydrogen peroxide or methane.

[0028] The propellant supply system also includes a high-pressure gas supply bottle, which is used to provide high-pressure inert gas to the propellant supply branch 1 and the propellant supply branch 2, so as to facilitate the propulsion supply of propellant 1 and propellant 2.

[0029] A regional collaborative two-phase hybrid space propulsion method comprises the following steps.

[0030] Step 1. Selection of chemical-electric composite thruster type: Select the chemical-electric composite thruster type according to the type of mission the spacecraft needs to perform; when the spacecraft needs to perform a long-term and long-distance mission, an external chemical-electric and internal electric composite thruster is used; when the spacecraft needs to perform a space orbit maintenance mission, an external electric-internal chemical-electric composite thruster is used.

[0031] Step 2, propellant supply: propellant 1 is supplied to the chemical thruster through propellant supply branch 1; propellant 2 is supplied to the chemical thruster and the electrical fluid supply branch through propellant 2 supply branch; the electrical fluid supply branch supplies electrical fluid to the electric thruster.

[0032] Step 3: Compound propulsion, including flight mission compound propulsion and orbit-maintaining compound propulsion.

[0033] The flight mission complex propulsion includes the following steps.

[0034] Step 3-A1, Flight Propulsion: The electric thrusters located in the center work to provide the thrust required for the spacecraft to perform long-term and long-distance flight missions.

[0035] Step 3-A2, rapid maneuver adjustment: When encountering an emergency during a long-term and long-distance flight mission, the chemical thrusters located outside the electric thrusters are turned on to perform zone-based rapid maneuver adjustments; rapid maneuver adjustments include rapid forward movement, vector rotation and attitude adjustment.

[0036] When moving forward quickly, the chemical thrust sub-areas in the chemical thruster are opened symmetrically to form axial thrust.

[0037] When it is a vector rotation or attitude adjustment, the corresponding chemical thruster area is opened asymmetrically according to the direction of the rotation or attitude adjustment, thereby forming torques in different directions, so that the spacecraft can realize its own attitude adjustment or rotation.

[0038] The orbit-maintaining compound propulsion comprises the following steps.

[0039] Step 3-B1, attitude adjustment: The electric thrusters located on the outside form multi-vector thrust by combining and partitioning different grid sub-areas, thereby achieving the attitude adjustment required for the spacecraft's space orbit maintenance mission.

[0040] Step 3-B2, orbit transfer: When a spacecraft in a space orbit maintenance mission needs to perform orbit transfer, the chemical thrusters located in the center are started, and the corresponding rapid maneuvering adjustments are completed with reference to step 3-A2.

[0041] In step 3-A2, each chemical thrust sub-zone is opened or closed by rotating the baffle disposed at the front end of the nozzle; in step 3-B1, each grid sub-zone is opened or closed by controlling the power on and off of the grid sub-zone.

[0042] In step 3-B1, when the electric thrusters work in combination and partition, the resolution of the multi-vector thrust required for attitude adjustment can reach 12μ and above.

[0043] The present invention has the following beneficial effects:

[0044] ① The present invention makes full use of the structural characteristics of various types of thrusters and designs a regional collaborative two-phase hybrid propulsion system with a highly reused propellant supply system and thruster structure. Two-phase refers to chemical and electric propulsion modes. The propulsion system can work in different regions in chemical and electric propulsion modes, combining the advantages of high thrust of chemical thrusters and high specific impulse and adjustable thrust of electric thrusters to a large extent, so that its comprehensive performance is improved and the mission types are covered more widely.

[0045] ② The present invention cleverly carries out a partitioned design for the thruster head. While realizing the reuse of the working fluid and subsystems of chemical and electric two-phase propulsion, it also greatly reduces the redundancy caused by the overall propulsion system to achieve different vector direction adjustments, realizes the simplification of the spacecraft attitude and orbit control system, and reduces the research and development cost: attitude and orbit control can be achieved through a single thruster.

[0046] ③ In the present invention, the chemical-electric combination mode under each partition is clarified, and according to the structural characteristics and the influence of temperature on the thruster grid and magnet, a more matched combination mode between chemistry and various types of electric thrusters is given to avoid mutual influence.

[0047] ④ The present invention proposes a zoning method for the throat of a chemical thruster, and achieves accelerated ejection of the combustion gas at a fixed point and in a fixed area by covering different positions of the throat with a baffle.

[0048] ⑤ The present invention realizes the zoned ejection of chemical high-temperature combustion gas by utilizing the baffle design of the chemical thruster throat without affecting the working performance of the thruster itself; it cleverly integrates the chemical thruster with the structural characteristics of the annular head of the Hall thruster; and it realizes the zoned extraction of electric thruster plasma by utilizing the insulation division of the electrostatic thruster grid.

[0049] ⑥ The present invention proposes a specific implementation method for the coordinated work of the chemical propulsion unit and the electric propulsion unit in a partitioned chemical-electric combined thruster. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 A structural schematic diagram of a regional cooperative two-phase hybrid space propulsion system of the present invention is shown.

[0051] Figure 2 A three-dimensional schematic diagram of the externalized internal electric composite thruster of the present invention is shown.

[0052] Figure 3 A side view of an externalized internal electric composite thruster according to the present invention is shown.

[0053] Figure 4 A schematic diagram showing the layout of partition partitions in the externalized internal electric composite thruster of the present invention is shown.

[0054] Figure 5 A schematic diagram showing the layout of partition plates and baffles in the externalized internal electric composite thruster of the present invention is shown.

[0055] Figure 6 A three-dimensional schematic diagram of the external-electric internalized composite thruster of the present invention is shown.

[0056] Figure 7 A schematic diagram showing the layout of partition partitions in the external-electric internalized composite thruster of the present invention is shown.

[0057] Figure 8 A schematic diagram showing the layout of partition plates and baffles in the external-electric internalized composite thruster of the present invention is shown.

[0058] Fig. 9 A schematic diagram showing the symmetrical opening of the chemical thruster region in the chemical thruster of the present invention is shown; wherein (a) is an external-electric and internal-electric composite thruster; and (b) is an external-electric and internal-electric composite thruster.

[0059] Fig.10 A schematic diagram showing the asymmetric opening of the chemical thruster region in the chemical thruster of the present invention; wherein (a) is an external-electrical-internal-chemical composite thruster; and (b) is an external-chemical-internal-electric composite thruster.

[0060] Among them are:

[0061] 10. Propellant supply system;

[0062] 11. High-pressure gas cylinder; 112. High-pressure gas main control valve; 113. Pressure reducing valve; 114. Total pressure sensor;

[0063] 12. Propellant supply branch; 121. Branch air supply control valve; 122. Propellant tank; 123. Flow solenoid valve; 124. Propellant control valve; 125. Branch pressure sensor;

[0064] 13. Propellant supply branch 2;

[0065] 14. Electrical fluid supply branch; 141. Electrical fluid control valve;

[0066] 20. Electric thruster; 21. Cylindrical barrel; 22. Grid; 23. Grid insulation partition;

[0067] 30. Chemical thruster; 31. Combustion chamber; 32. Throat; 321. Partition baffle; 322. Baffle; 33. Nozzle expansion pipe;

[0068] 40.Chemical-electric composite thruster. DETAILED DESCRIPTION

[0069] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific preferred embodiments.

[0070] In the description of the present invention, it should be understood that the terms "left side", "right side", "upper part", "lower part" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. "First", "second" and the like do not indicate the importance of the components, and therefore cannot be understood as limiting the present invention. The specific dimensions used in this embodiment are only for illustrating the technical solution, and do not limit the scope of protection of the present invention.

[0071] like Figure 1 As shown, a regional cooperative two-phase hybrid space propulsion system includes a propellant supply system 10 and a chemical-electric composite thruster 40.

[0072] The propellant supply system 10 includes a high-pressure gas cylinder 11 , a propellant supply branch 12 , a propellant supply branch 2 13 and an electrical fluid supply branch 14 .

[0073] The high-pressure gas cylinder 11 is connected to the propellant supply branch 12 and the propellant supply branch 13 through the high-pressure gas delivery pipeline. The high-pressure gas delivery pipeline is preferentially provided with a filling and discharging valve 111, a high-pressure gas main control valve 112, a pressure reducing valve 113 and a total pressure sensor 114 in sequence along the airflow direction.

[0074] The above-mentioned pressure relief valve is used for depressurizing the high-pressure gas transmission pipeline to prevent pressure overload.

[0075] The high-pressure gas main control valve 112 is used to control the opening and closing of the high-pressure gas transmission pipeline.

[0076] The above-mentioned pressure reducing valve is used for pressure control of high-pressure gas transmission pipeline.

[0077] The above-mentioned total pressure sensor is used to monitor the pressure of the high-pressure gas transmission pipeline.

[0078] The above-mentioned propellant one supply branch supplies propellant one to the chemical thruster, and the propellant two supply branch supplies propellant two to the chemical thruster; the propellant one supply branch 12 and the propellant two supply branch 13 are sequentially provided with a branch air supply control valve 121, a propellant tank 123, a flow solenoid valve 123, a propellant control valve 124 and a branch pressure sensor 125 along the propellant flow direction.

[0079] The branch air supply control valve is used for the opening and closing control of the propellant receiving in the propellant supply branch 1 or the propellant supply branch 2.

[0080] The propellant tank is used to store propellant 1 or propellant 2. One of propellant 1 and propellant 2 is a fuel, the other is an oxidant, and propellant 2 can be used as an electric medium. In this embodiment, propellant 1 is preferably oxygen or kerosene, etc.; propellant 2 is preferably hydrogen, hydrogen peroxide or methane, etc.

[0081] While realizing the combination of chemical and electric two-phase propulsion, the present invention also realizes the reuse of working fluids and subsystems, greatly reducing the redundancy caused to the entire propulsion system for realizing different vector direction adjustments.

[0082] The flow solenoid valve 123 is used to control the flow of the propellant; the propellant control valve 124 is used to control the on-off control of the propellant supply branch.

[0083] The branch pressure sensor is used to monitor the pressure of the propellant supply branch one or the propellant supply branch two.

[0084] The electric working fluid supply branch is connected to the second propellant supply branch and is used to supply the electric working fluid to the electric thruster.

[0085] The inlet end of the electric fluid supply branch is preferably connected between the flow solenoid valve and the branch pressure sensor, and an electric fluid control valve 141 is provided in the electric fluid supply branch for controlling the opening and closing of the electric fluid supply branch.

[0086] Chemical-electric composite thrusters include external chemical-internal electric composite thrusters and external electric-internal chemical-combined thrusters.

[0087] 1. Externalized internal electric composite thruster

[0088] like Figures 2 to 5 As shown, the externalized internal electric composite thruster includes an electric thruster 20 and a chemical thruster 30 coaxially sleeved on the outer periphery of the electric thruster.

[0089] The electric thruster comprises a cylindrical barrel 21 .

[0090] The chemical thruster includes a combustion chamber 31, a throat 32 and a nozzle expansion pipe 33 which are arranged in sequence along the airflow direction.

[0091] The cavity between the electric thruster and the chemical thruster is formed as a chemical thrust cavity.

[0092] 4m partition plates 321 are evenly arranged along the circumferential direction in the chemical thrust cavity corresponding to the throat and the expansion nozzle, so as to divide the chemical thrust cavity into 4m chemical thrust sub-zones; 2m baffle plates 322 are arranged in the chemical thrust cavity at the front end of the throat, each baffle plate can rotate along the circumferential direction and block the corresponding chemical thrust sub-zone; wherein m is a natural number,

[0093] The more partitions there are, the more precise the control of the spacecraft will be, but at the same time, the processing will be more complicated and the stability and reliability of the work will decrease. Therefore, when choosing the value of m or n below, the requirements of the spacecraft mission for the above two should be taken into account.

[0094] During operation, a large amount of high-temperature combustion gas is first generated by the reaction in the combustion chamber. The high-temperature combustion gas will only pass through the chemical thrust sub-area that is not covered by the baffle, and convert the thermal energy into kinetic energy in the throat and accelerate the ejection, corresponding to the different ejection areas at the end of the nozzle, to achieve propulsion of different vectors.

[0095] Since the electric thruster is located inside the ring, the high temperature generated by the chemical nozzle will have a great impact on its performance: the grid assembly will deform at high temperatures, and the magnet performance will also drop significantly at high temperatures. Therefore, in this configuration, the electric thruster is more suitable for electric heating, resistance type and other electric thrusters with higher reliability. More preferably, it is an arc thruster or a resistance heating thruster.

[0096] 2. External-electric internalized composite thruster

[0097] like Figures 6 to 8 As shown, the external-electric internal-chemical composite thruster includes an electric thruster 20 and a chemical thruster 30 coaxially inserted in the center of the electric thruster.

[0098] For chemical thrusters: a central axis is set at the center of the throat and the expander, and 4m partition plates are evenly arranged along the circumference of the central axis, so as to divide the inner cavity of the throat and the inner cavity of the expander into 4m chemical thrust sub-zones; 2m baffles are arranged on the outer periphery of the central axis at the front end of the throat, each baffle can rotate along the circumference and seal the corresponding chemical thrust sub-zone.

[0099] For electric thrusters: the grid is arranged in a cylindrical tube on the outer periphery of the tail end of the expansion nozzle, and the grid partition form is set according to the selected electric thruster type, specifically:

[0100] a. When the electric thruster is a Hall thruster, the gate is not divided into zones.

[0101] b. When the electric thruster is a non-Hall thruster, the type of electric thruster used at this time is mainly an electrostatic electric thruster. By adding 4n gate insulating partitions in the gate, the gate is evenly divided into 4n gate sub-areas along the circumferential direction, and each gate sub-area can be individually powered on and controlled; wherein n is a natural number.

[0102] The electrostatic electric thruster is preferably an ion thruster (radio frequency ion thruster) or an electron cyclotron resonance ion thruster or the like.

[0103] Each gate sub-region is preferably a sector-shaped gate, that is, formed by splicing 4n sector-shaped gates, and a gate insulating partition is arranged at the splicing position, and is preferably a ceramic insulating plate.

[0104] The chemical-electric hybrid thruster of the present invention is in a tabular form and is classified and summarized as shown in the following Table 1.

[0105] Table 1

[0106]

[0107] Since the electrostatic thruster has high requirements for the working state, its various working parts are also relatively sensitive. In order to further prevent the high temperature heat of the inner ring from affecting the outer ring, the present invention proposes that the outer wall of the chemical thruster is preferably coated with a high temperature resistant ceramic material to isolate the electric thruster. At the same time, the length of the central chemical propulsion nozzle is increased, that is, the tail end face of the expanded nozzle protrudes from the outer end face of the grid to reduce the impact of its ejected products on the grid, thereby meeting the stable operation of the electrostatic electric thruster.

[0108] A regional collaborative two-phase hybrid space propulsion method comprises the following steps.

[0109] Step 1. Selection of chemical-electric composite thruster type: Select the chemical-electric composite thruster type according to the type of mission the spacecraft needs to perform; when the spacecraft needs to perform a long-term and long-distance mission, an external chemical-electric and internal electric composite thruster is used; when the spacecraft needs to perform a space orbit maintenance mission, an external electric-internal chemical-electric composite thruster is used.

[0110] Step 2, propellant supply: propellant 1 is supplied to the chemical thruster through propellant supply branch 1; propellant 2 is supplied to the chemical thruster and the electrical fluid supply branch through propellant 2 supply branch; the electrical fluid supply branch supplies electrical fluid to the electric thruster.

[0111] Step 3: Compound propulsion, including compound propulsion for flight mission and compound propulsion for orbit maintenance;

[0112] The flight mission compound propulsion includes the following steps:

[0113] Step 3-A1, flight propulsion: The electric thruster located in the center works to provide the thrust required for the spacecraft to perform long-term and long-distance flight missions. At this time, the electric propulsion mode is very efficient, up to 60-80%, with extremely high specific impulse, and can continue to propel for several weeks or even years. The accumulation can allow the spacecraft to reach extremely high speeds, allowing the spacecraft to perform longer-distance space flight missions under the same load limit.

[0114] Step 3-A2, rapid maneuvering adjustment: When the spacecraft is performing a long-term and long-distance flight mission (such as hundreds of millions of kilometers), when encountering emergencies such as emergency obstacle avoidance, the chemical thrusters located outside the electric thrusters are turned on to perform zone-based rapid maneuvering adjustments; rapid maneuvering adjustments include rapid forward movement, vector rotation and attitude adjustment.

[0115] In this embodiment, it is preferred that each chemical thrust sub-zone is opened or closed by rotating a baffle disposed at the front end of the nozzle.

[0116] When moving forward quickly, the chemical thruster sub-areas in the chemical thruster are opened symmetrically, such as Fig. 9 As shown, axial thrust is generated.

[0117] At this time, the electric thruster and chemical thruster can work simultaneously to achieve the mission objectives with greater thrust. At this time, the fuel and oxidizer are respectively delivered to the chemical and electric propulsion nozzles through the extrusion supply system. A part of them reacts in the combustion chamber to generate high-temperature combustion gas, which is accelerated and ejected through the throat, and a part of them forms plasma in the thrust chamber and is drawn out.

[0118] When it is a vector rotation or attitude adjustment, according to the direction of rotation or attitude adjustment, such as Fig.10 As shown, the corresponding chemical thruster area is opened asymmetrically, thus forming torques in different directions. Make spaceflight The device can flexibly adjust its own posture and load orientation.

[0119] The baffle of the chemical throat opens at the required partition, and a large amount of high-temperature gas produced by the reaction in the combustion chamber is ejected from the corresponding throat; the electric thruster energizes the required fan-shaped grid plate, and the plasma formed in the thrust chamber will be accelerated and drawn out through the fan-shaped grid.

[0120] The orbit-maintaining compound propulsion includes the following steps:

[0121] Step 3-B1, attitude adjustment: The electric thrusters located on the outside form multi-vector thrust by combining and partitioning different grid sub-areas, thereby achieving the attitude adjustment required for the spacecraft's space orbit maintenance mission.

[0122] At this point, the working principles of the electric thrusters and chemical thrusters refer to the attitude adjustment in step 3-A2.

[0123] In this embodiment, it is preferred to control the on / off power of the gate sub-regions to thereby realize the opening or closing of each gate sub-region.

[0124] Furthermore, when the electric thrusters work in combination and in sections, the spacecraft attitude can be adjusted very finely, and the resolution of the multi-vector thrust required for attitude adjustment can reach 12μ or above. High-precision attitude control is especially important for spacecraft such as reconnaissance satellites that have high requirements for payload working stability.

[0125] Step 3-B2, orbit transfer: When a spacecraft in a space orbit maintenance mission needs to perform orbit transfer, the chemical thrusters located in the center are started, and the corresponding rapid maneuvering adjustments are completed with reference to step 3-A2.

[0126] The present invention ingeniously realizes the integration of the chemical thruster head and the electric thruster head structure, taking into account the advantages of large thrust and high specific impulse of the two propulsion modes, and meeting the established needs of complex aerospace missions; the first type of partitioning method in the present invention has a clear structure, is easy to implement, and has mature processing technology; the present invention makes full use of the structural characteristics of Hall thrusters and electrostatic thrusters, and realizes the partitioning of chemical-electric hybrid thrusters by redesigning the grid assembly and the nozzle throat; chemical and electric propulsion can share propellants such as methane, hydrogen, hydrogen peroxide, etc., saving space for propellant tanks and pipelines, and facilitating the optimization of thruster quality and structure.

[0127] The present invention is based on the mixing of chemical and electric phases, and according to the characteristics of different thruster types, the thruster is divided into multiple partitions by redesigning the grid and the throat, and the chemical and electric thruster partitions work in coordination.

[0128] The preferred embodiments of the present invention are described in detail above; however, the present invention is not limited to the specific details in the above embodiments. Within the technical concept of the present invention, various equivalent transformations can be made to the technical solutions of the present invention, and these equivalent transformations all belong to the protection scope of the present invention.

Claims

1. A regional cooperative two-phase hybrid space propulsion system, characterized by: It includes a propellant supply system and a chemical-electric composite thruster; The chemical-electric composite thruster includes an external chemical-internal electric composite thruster and an external electric-internal chemical-combined thruster; The externalized internal electric composite thruster includes an electric thruster and a chemical thruster coaxially sleeved on the outer periphery of the electric thruster; The external-electric internal-chemical composite thruster includes an electric thruster and a chemical thruster coaxially inserted in the center of the electric thruster; The propellant supply system includes a propellant supply branch 1, a propellant supply branch 2 and an electrical fluid supply branch; The propellant 1 supply branch and the propellant 2 supply branch supply propellant 1 and propellant 2 to the chemical thruster respectively; one of the propellant 1 and the propellant 2 is a fuel, the other is an oxidant, and the propellant 2 can be used as an electric medium; The electric working fluid supply branch is connected to the second propellant supply branch and is used to supply the electric working fluid to the electric thruster; The electric thruster includes a cylindrical barrel and a grid, and the chemical thruster includes a combustion chamber, a throat and a diffuser arranged in sequence along the airflow direction; A. When the chemical-electric hybrid thruster is an external chemical-internal electric hybrid thruster, the specific setting method of the electric thruster and the chemical thruster is as follows: the electric thruster is an unpartitioned electric heating type or resistance type thruster; The cavity between the electric thruster and the chemical thruster is formed as a chemical thrust cavity; For the chemical thruster: 4m partition plates are evenly arranged along the circumferential direction in the chemical thrust cavity corresponding to the throat and the expansion nozzle, thereby dividing the chemical thrust cavity into 4m chemical thrust sub-zones; 2m baffle plates are arranged in the chemical thrust cavity at the front end of the throat, each baffle plate can rotate along the circumferential direction and block the corresponding chemical thrust sub-zone; where m is a natural number, B. When the chemical-electric hybrid thruster is an external-electric and internal-chemical hybrid thruster, the specific setting method of the electric thruster and the chemical thruster is as follows: For the chemical thruster: a central axis is set at the center of the throat and the expansion nozzle, and 4m partition plates are evenly arranged along the circumference of the central axis, so that the inner cavity of the throat and the inner cavity of the expansion nozzle are divided into 4m chemical thrust sub-areas; 2m baffles are arranged on the outer circumference of the central axis at the front end of the throat, and each baffle can rotate along the circumference and block the corresponding chemical thrust sub-area; For electric thrusters: the grid is arranged in a cylindrical tube on the outer periphery of the tail end of the expansion nozzle, and the grid partition form is set according to the selected electric thruster type, specifically: a. When the electric thruster is a Hall thruster, the gate is not divided; b. When the electric thruster is a non-Hall thruster, 4n gate insulating partitions are added to the gate, so that the gate is evenly divided into 4n gate sub-areas along the circumferential direction, and each gate sub-area can be individually powered; wherein n is a natural number.

2. The regional cooperative two-phase hybrid space propulsion system according to claim 1 is characterized in that: The electric heating or resistance type thrusters are arc thrusters or resistance heating thrusters.

3. The regional cooperative two-phase hybrid space propulsion system according to claim 1 is characterized in that: Non-Hall thrusters are ion thrusters or electron cyclotron resonance ion thrusters.

4. The regional cooperative two-phase hybrid space propulsion system according to claim 1 is characterized in that: When the chemical-electric composite thruster is an external-electric and internal-chemical composite thruster, the outer wall of the chemical thruster is coated with high-temperature resistant ceramic material to isolate the electric thruster.

5. The regional cooperative two-phase hybrid space propulsion system according to claim 4 is characterized in that: When the chemical-electric hybrid thruster is an external-electric and internal-chemical hybrid thruster, the tail end face of the expansion nozzle protrudes from the outer end face of the grid.

6. The regional cooperative two-phase hybrid space propulsion system according to claim 1 is characterized in that: Propellant 1 is oxygen or kerosene; propellant 2 is hydrogen, hydrogen peroxide or methane.

7. The regional cooperative two-phase hybrid space propulsion system according to claim 1 is characterized in that: The propellant supply system also includes a high-pressure gas supply bottle, which is used to provide high-pressure inert gas to the propellant supply branch 1 and the propellant supply branch 2, so as to facilitate the propulsion supply of propellant 1 and propellant 2.

8. A regional collaborative two-phase hybrid space propulsion method, characterized by: The steps include: Step 1, chemical-electric composite thruster type selection: according to the type of mission that the spacecraft needs to perform, the type of chemical-electric composite thruster is selected; when the mission type that the spacecraft needs to perform is a long-term and long-distance flight mission, an external chemical-electric internal electrical composite thruster is used; when the mission type that the spacecraft needs to perform is a space orbit maintenance mission, an external electrical internal chemical-electric composite thruster is used; Step 2, propellant supply: propellant 1 is supplied to the chemical thruster through propellant supply branch 1; propellant 2 is supplied to the chemical thruster and the electrical fluid supply branch through propellant 2 supply branch; the electrical fluid supply branch supplies electrical fluid to the electrical thruster; Step 3: Compound propulsion, including compound propulsion for flight mission and compound propulsion for orbit maintenance; The flight mission compound propulsion includes the following steps: Step 3-A1, flight propulsion: The electric thrusters located in the center work to provide the thrust required for the spacecraft to perform long-term and long-distance flight missions; Step 3-A2, rapid maneuvering adjustment: When the spacecraft encounters an emergency during a long-distance flight mission, the chemical thrusters located outside the electric thrusters are turned on to perform zone-based rapid maneuvering adjustments; rapid maneuvering adjustments include rapid forward movement, vector rotation, and attitude adjustment; When moving forward quickly, the chemical thrust sub-areas in the chemical thruster are opened symmetrically to form axial thrust; When it is vector rotation or attitude adjustment, the corresponding chemical thruster area is opened asymmetrically according to the direction of rotation or attitude adjustment, thereby forming torques in different directions, so that the spacecraft can achieve its own attitude adjustment or rotation; The orbit-maintaining compound propulsion includes the following steps: Step 3-B1, attitude adjustment: The electric thrusters located on the outside form multi-vector thrust by combining and partitioning different grid sub-areas, thereby achieving the attitude adjustment required for the spacecraft's space orbit maintenance mission; Step 3-B2, orbit transfer: When a spacecraft in a space orbit maintenance mission needs to perform orbit transfer, the chemical thrusters located in the center are started, and the corresponding rapid maneuvering adjustments are completed with reference to step 3-A2.

9. The regional cooperative two-phase hybrid space propulsion method according to claim 8 is characterized in that: In step 3-A2, each chemical thrust sub-zone is opened or closed by rotating the baffle disposed at the front end of the nozzle; in step 3-B1, each grid sub-zone is opened or closed by controlling the power on and off of the grid sub-zone.

10. The regional cooperative two-phase hybrid space propulsion method according to claim 8, characterized in that: In step 3-B1, when the electric thrusters work in combination and partition, the resolution of the multi-vector thrust required for attitude adjustment can reach 12μ and above.

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