Propellant tank for variable specific impulse magnetoplasmadynamic rocket

Abstract

The application discloses a propellant tank for a variable specific impulse magnetoplasmadynamic rocket, comprising a tank body and a guide, the tank body has a containing cavity containing propellant, and the tank body has an outlet communicating with the containing cavity and an external pipeline at one end in the height direction of the tank body; the guide comprises a guide part extending from one end to the other end of the tank body in the height direction of the tank body, a guide channel is formed between the inner circumferential wall surface of the tank body and the guide part, and one end of the guide channel communicates with the outlet; even in a deep space microgravity environment, inertia force generated by speed change and direction change of a spacecraft can cause migration and disturbance of liquid-phase propellant in the tank, the guide part of the guide is used for guiding the propellant in the guide channel to move towards the outlet, and the propellant at the far end is guided to the outlet along the height direction of the tank body, so that it is helpful to inhibit invasion of gas-phase medium into the outlet and the external pipeline, and it is helpful to adapt to stable liquid supply requirements of the variable specific impulse magnetoplasmadynamic rocket under a dynamic working condition.

Description

Technical Field

[0001] This invention relates to the field of propulsion technology, and in particular to a propellant tank for a variable specific impulse magneto-plasma rocket. Background Technology

[0002] Variable Specific Impulse Magnetoplasma Rockets (VASIMRs), as high-power, high-specific-impulse electric propulsion devices adapted for deep space exploration missions, are widely used in various deep space aerospace missions such as interplanetary cruise and asteroid exploration due to their excellent propulsion performance. Spacecraft equipped with VASIMRs operate in orbit for extended periods in a microgravity environment, and during orbital maneuvers and attitude control operations, they need to frequently perform speed changes and reversals. The overall operating conditions are highly dynamic and volatile, placing extremely high demands on the stability of propellant supply, fluid controllability, and propellant utilization rate.

[0003] Currently, the propellant storage tank structure of variable specific impulse magneto-plasma rockets is relatively simple. The tank is equipped with only a basic capillary guide structure. The entire tank relies on a single liquid outlet at the bottom in conjunction with the built-in basic capillary guide structure to complete the collection and export of propellant inside the tank, thereby meeting the propellant supply requirements under normal steady-state conditions.

[0004] However, while the tank with capillary flow structure is simple in form and suitable for static and stable working conditions, it exposes many unavoidable technical defects under the dynamic working conditions of frequent speed changes and reversals of spacecraft in the microgravity environment of deep space, and cannot meet the working requirements of long-term deep space exploration by variable specific impulse magneto-plasma rockets.

[0005] Specifically, existing tank structures are unable to handle the fluid disturbances during microgravity acceleration and reversal operations, easily leading to gas blockage and flow interruption problems, causing rocket thrust pulsation or even operational failure. In the microgravity environment of deep space, the gas and liquid two-phase media inside the tank lack natural gravity stratification. The inertial force generated by the spacecraft's acceleration and maneuvering will push the liquid propellant inside the tank to the far end, causing the liquid outlet at the bottom of the tank to be directly exposed to the gas phase environment. Furthermore, the fluid disturbances generated by the spacecraft's reversal operations will further tear apart the stable gas cushion structure inside the tank, resulting in a mixed and disordered distribution of gas and liquid phases throughout the tank. Traditional tanks are prone to allowing mixed air bubbles to intrude into the liquid supply pipeline, causing intermittent propellant flow interruption failures. When the gas and liquid two-phase media enter the radio frequency ionization cavity of a variable specific impulse magneto-plasma rocket together, it will directly disrupt the stability of plasma ionization, reduce the power coupling efficiency of the device, and thus cause problems such as thrust pulsation and plasma plume deviation. In severe cases, it can even cause plasma flameout, ultimately leading to a decrease in the accuracy of spacecraft orbital maneuver control and even the safety risk of maneuver failure. Summary of the Invention

[0006] The purpose of this invention is to solve the technical problem that the existing variable specific impulse magneto-plasma rockets, which are equipped with only basic capillary guide structures inside their storage tanks, cannot stably supply propellant under the dynamic operating conditions of frequent speed changes and reversals of spacecraft in the microgravity environment of deep space, and are therefore difficult to adapt to the working requirements of variable specific impulse magneto-plasma rockets for long-term deep space exploration.

[0007] To solve the above-mentioned technical problems, the present invention discloses a propellant storage tank for a variable specific impulse magnetic plasma rocket, including a tank body and a guide member. The tank body has a receiving cavity for containing propellant, and one end of the tank body along its height direction has an outlet that connects the receiving cavity and an external pipeline.

[0008] The guide is located inside the receiving cavity. The guide includes a guide portion that extends from one end of the tank body to the other end in the height direction of the tank body. A guide channel is formed between the inner peripheral wall of the tank body and the guide portion. One end of the guide channel is connected to the outlet. The guide portion of the guide is used to guide the propellant in the guide channel to move toward the outlet.

[0009] By employing the above technical solution, in the microgravity environment of deep space, the inertial forces generated by the spacecraft's speed changes and reversals will cause the liquid propellant inside the tank to migrate and be disturbed. The guiding channel can provide a directional flow path for the propellant to penetrate the containment cavity in the height direction. Even if the liquid propellant is pushed to an area far from the outlet by the inertial force, the guiding channel can still guide the propellant at the far end to the outlet along the height direction of the tank body, thereby helping to suppress the intrusion of gaseous media into the outlet and external pipelines, and reducing the risk of gas blockage and flow interruption. At the same time, the guiding part extends from one end of the tank body to the other, so that the coverage of the guiding channel penetrates the entire containment cavity in the height direction, which helps to improve the working fluid utilization rate of the propellant, so that the propellant in each area of ​​the containment cavity can be collected and discharged, avoiding the problem of local propellant stagnation and supply failure. In addition, the setting of the guiding channel constrains the flow of propellant, which helps to maintain the continuous supply of liquid media in the case of gas-liquid two-phase mixing, thereby helping to adapt to the stable liquid supply requirements of variable specific impulse magneto-plasma rockets under dynamic conditions.

[0010] The present invention also discloses a propellant tank for a variable specific impulse magneto-plasma rocket, wherein the guide includes a guide shaft that extends from one end of the tank body to the other end in the height direction of the tank body, and the guide shaft is disposed in the middle of the receiving cavity on a plane perpendicular to the height direction of the tank body.

[0011] The guide section consists of guide blades that extend spirally from one end of the guide shaft to the other end on the side wall of the guide shaft. The outer edge of the guide blades is attached to the inner wall of the can body, so that a spiral guide channel is formed between the guide blades and the inner circumferential wall of the can body.

[0012] Furthermore, the guide shaft can rotate about an axis extending in the height direction of the tank body, and the guide vanes are used to guide the propellant in the guide channel toward the outlet.

[0013] By employing the above technical solution, the spiral guide channel can smoothly and stably guide the movement of propellant, helping to further suppress the intrusion of gaseous media. Furthermore, the guide shaft is positioned in the center of the receiving cavity, allowing the spiral guide blades to radiate outwards from the guide shaft, facilitating the collection of propellant from all radial directions within the receiving cavity and increasing the collection coverage. Moreover, the guide shaft can rotate around an axis extending along the height of the tank body. When the guide shaft rotates, the spiral guide blades generate a conveying force that propels the propellant within the guide channel in a spiral direction, driving the propellant towards the outlet. This helps maintain the directional and stable delivery of propellant under microgravity dynamic conditions, overcoming the problem of propellant reverse migration caused by inertial forces. In addition, the outer edge of the guide blades adheres to the inner wall surface of the tank body, forming a closed spiral flow channel, which helps prevent propellant from bypassing and leaking through the gap between the guide blades and the inner wall surface during delivery, improving the guiding efficiency.

[0014] The present invention also discloses a propellant storage tank for a variable specific impulse magnetic plasma rocket, wherein a first magnetic part is provided at one end of a guide shaft and a second magnetic part is provided at the other end; a first support member is provided on the outer side of one end of the tank body, and the first support member is provided with a first magnetic generating part corresponding to the first magnetic part; a second support member is provided on the outer side of the other end of the tank body, and the second support member is provided with a second magnetic generating part corresponding to the second magnetic part.

[0015] The magnetic poles on the relatively close sides of the first magnetic part and the first magnetic generating part have the same polarity, and the magnetic poles on the relatively close sides of the second magnetic part and the second magnetic generating part have the same polarity, so that there is a repulsive force between the first magnetic part and the first magnetic generating part and between the second magnetic part and the second magnetic generating part in the height direction of the can body, so as to suspend and support the guide shaft located between the first magnetic part and the second magnetic part through the corresponding wall surface of the can body.

[0016] Using the above technical solution, the magnetic poles of the first magnetic part and the first magnetic generating part, and the magnetic parts of the second magnetic part and the second magnetic generating part, are of the same polarity on their relatively close sides. Utilizing the principle of magnetic repulsion between like poles, a repulsive force is generated in the height direction of the tank body, causing the guide shaft to be suspended and supported within the receiving cavity through the tank body wall. This magnetic levitation support method eliminates the need for mechanical shafts or bearings passing through the tank wall between the guide shaft and the tank body, helping to maintain the sealing integrity of the tank body's receiving cavity and preventing propellant leakage along the gap between the shaft and the tank wall.

[0017] Furthermore, the magnetic levitation support prevents the guide shaft from mechanically contacting the tank body during rotation, reducing rotational resistance and allowing the guide shaft to respond more flexibly to external drives. It also reduces propellant contamination caused by friction-generated particles. In addition, the magnetic repulsion support has axial self-adjusting properties. When the guide shaft undergoes axial displacement under dynamic conditions, the magnetic repulsion provides a restoring force, helping to maintain the guide shaft's centered position within the housing cavity and ensuring proper contact between the guide vanes and the inner wall surface.

[0018] The present invention also discloses a propellant storage tank for a variable specific impulse magnetic plasma rocket. The first magnetic part is a first magnetic cone extending from one end face of the guide shaft away from the other end and with a gradually decreasing cross-section. The first magnetic generating part is a first concave magnetic generating part adapted to the first magnetic cone. At one end of the tank body corresponding to the guide shaft, there is a first convex structure adapted to the first magnetic cone and the first concave magnetic generating part. The outlet is disposed in the first convex structure, and an external pipeline passes through the first support component and communicates with the outlet.

[0019] The second magnetic part is a second magnetic cone that extends from the other end face of the guide shaft in a direction away from one end and whose cross-section gradually decreases. The second magnetic generating part is a second concave magnetic generating part that is adapted to the second magnetic cone. At the other end of the can body, corresponding to the position of the guide shaft, is a second convex structure that is adapted to the second magnetic part and the second concave magnetic generating part.

[0020] Using the above technical solution, the first and second magnetic parts each adopt a magnetic cone structure with a gradually decreasing cross-section, while the corresponding magnetic generating part adopts a concave structure, and the corresponding positions at both ends of the tank body adopt an outward convex structure. A conical and concave surface fits together between the magnetic cone and the concave magnetic generating part. The magnetic flux density is more concentrated in the tip region of the magnetic cone, which helps to generate a stronger magnetic repulsion force in the axial direction, improving the load-bearing capacity of the suspension support. Furthermore, the fit between the cone and the concave surface has a self-centering characteristic. When the guide shaft experiences radial displacement under dynamic operating conditions, the change in magnetic force distribution between the cone and the concave surface can generate a radial restoring force, helping the guide shaft to automatically return to the center position and improving the radial stability of the magnetic levitation support.

[0021] The present invention also discloses a propellant storage tank for a variable specific impulse magnetic plasma rocket. The other end of the tank body is provided with a guide drive, and the output end of the guide drive is connected to a second support component for transmission, and drives the second support component to rotate around an axis extending in the height direction of the tank body. The second support component rotates synchronously with the corresponding second magnetic part and the guide shaft through the second magnetic generator.

[0022] Using the above technical solution, a guide drive component is installed on the outer side of one end of the tank body. The output end of the guide drive component is connected to the second support component for transmission, driving the second support component to rotate around an axis extending in the height direction of the tank body. The second support component is linked to the guide shaft for synchronous rotation through the magnetic coupling between the magnetic generator and the second magnetic part. This structure allows the rotational driving force of the guide shaft to originate from outside the tank body, eliminating the need for connection holes on the tank wall and helping to maintain the sealing performance of the tank body.

[0023] Furthermore, the guide drive is located outside the tank body, which facilitates maintenance and repair, while preventing the heat generated by the drive from being directly transferred to the propellant inside the tank.

[0024] The present invention also discloses a propellant storage tank for a variable specific impulse magnetic plasma rocket. A first support frame is provided on the outer side of one end of the tank body. The first support frame includes a pair of first legs disposed opposite to each other on both sides of the tank body and a first mounting frame connected to the pair of first legs and located on the outer side of one end of the tank body in the height direction. A first support bearing assembly is provided on the first mounting frame, and the first support bearing assembly supports a first support component.

[0025] A second support frame is provided at the other end of the tank body. The second support frame includes a pair of second legs disposed opposite to each other on both sides of the tank body and a second mounting frame connected to the pair of second legs and located on the outer side of the other end of the tank body in the height direction. A second support bearing assembly is provided on the second mounting frame, and the second support bearing assembly supports the second support component.

[0026] Using the above technical solution, a first support frame and a second support frame are respectively installed at both ends of the tank body. Each support frame includes a pair of legs and a mounting bracket. A support bearing assembly is installed on the mounting bracket to support the corresponding support component. The support frame can stably fix the corresponding support component, while the support bearing assembly can reduce the frictional resistance when the support component rotates, allowing the driving force of the guide drive component to be efficiently transmitted to the second support component and linked to the rotation of the guide shaft. Furthermore, the installation of the support bearing assembly makes the rotational movement of the support component smoother, helping to reduce vibration during rotation.

[0027] The present invention also discloses a propellant storage tank for a variable specific impulse magnetic plasma rocket, wherein a transmission part is provided on the side of the tank body away from the tank body in the height direction of the second support member; and a guide drive member is also mounted on the second mounting bracket next to the second support member, and a transmission gear set is provided between the output end of the guide drive member and the transmission part.

[0028] And / or, the can body is made of silicon carbide.

[0029] Using the above technical solution, a transmission unit is provided on the second support component, and a guide drive component is mounted on the second mounting bracket. A transmission gear set is provided between the output end of the guide drive component and the transmission unit. The transmission gear set can provide stable power transmission, and the rotational speed can be adjusted by selecting the gear ratio, so that the rotational speed of the guide shaft can be adapted to different propellant delivery requirements.

[0030] When the tank body is made of silicon carbide, the material's high thermal conductivity and chemical stability help maintain uniform temperature inside the tank under cryogenic propellant storage conditions, while also resisting chemical corrosion from the propellant and extending the tank's service life. Furthermore, silicon carbide's high structural strength and hardness enhance the tank body's impact resistance. In addition, silicon carbide's insulating properties ensure that the magnetic field between the magnetizer and its corresponding magnetic components remains unaffected, achieving stable levitation support for the guide shaft and efficient power transmission.

[0031] The embodiments of the present invention also disclose a propellant storage tank for a variable specific impulse magnetic plasma rocket. The tank body has a spiral cooling channel extending in a spiral shape along the height direction of the tank body inside the side wall. A coolant inlet is formed on the outer wall surface of one end of the tank body, which connects to one end of the cooling channel, and a coolant outlet is formed on the outer wall surface of the other end, which connects to the other end of the cooling channel.

[0032] By employing the above technical solution, the cooling channel can be circulated with a cooling medium to control the temperature of the propellant within the tank body and the containment cavity. This helps maintain the propellant within a suitable liquid phase temperature range, preventing abnormal pressure increases or gas-liquid phase imbalances caused by propellant vaporization due to heat. Furthermore, the spirally extending cooling channel increases the contact area between the cooling medium and the tank wall, improving heat exchange efficiency.

[0033] The present invention also discloses a propellant storage tank for a variable specific impulse magnetic plasma rocket, wherein the tank body is disposed inside a Dewar, a vacuum chamber is formed between the Dewar and the tank body, and the propellant storage tank further includes an outer peripheral buffer assembly located on the outer periphery of the tank body and connected to the inner wall surface of the Dewar.

[0034] Using the above technical solution, the canister body is housed within the Dewar flask, forming a vacuum chamber between the Dewar flask and the canister body. This vacuum chamber provides highly efficient thermal insulation, significantly reducing heat exchange between the external environment and the canister body, which helps maintain cryogenic storage conditions for propellants during deep space exploration missions. Furthermore, the outer peripheral buffer assembly connects the inner wall of the Dewar flask to the outer periphery of the canister body, absorbing vibration and shock energy during spacecraft launch or orbital maneuvers, thus helping to protect the canister body and internal guiding components from severe impacts.

[0035] An embodiment of the present invention also discloses a propellant storage tank for a variable specific impulse magneto-plasma rocket, wherein the peripheral buffer assembly includes: a first buffer spring extending along the height direction on the outer side wall at both ends of the tank body in the height direction.

[0036] And / or, a plurality of second buffer springs are provided at intervals on the outer side wall of the tank body parallel to the height direction, each second buffer spring extending in a direction perpendicular to the height direction of the tank body.

[0037] With the above technical solution, the first buffer spring extends along the height direction of the tank body and is disposed on the outer side wall at both ends of the tank body in the height direction. It can absorb the axial impact energy transmitted along the height direction and help prevent the tank body from undergoing excessive displacement or deformation under axial impact.

[0038] In addition, multiple second buffer springs are spaced apart along the outer periphery of the tank body and extend in a direction perpendicular to the height of the tank body. They can absorb lateral impact energy transmitted radially and help limit the vibration and displacement of the tank body in the radial direction.

[0039] The beneficial effects of this invention are as follows:

[0040] This invention discloses a propellant storage tank for a variable specific impulse magneto-plasma rocket, comprising a tank body and a guide member. The tank body has a receiving cavity for containing propellant, and one end of the tank body along its height direction has an outlet connecting the receiving cavity and an external pipeline. The guide member is located within the receiving cavity and includes a guide portion extending from one end of the tank body to the other along its height direction. A guide channel is formed between the inner peripheral wall of the tank body and the guide portion, and one end of the guide channel is connected to the outlet. The guide portion of the guide member guides the propellant within the guide channel toward the outlet. Even in the microgravity environment of deep space, the inertial forces generated by spacecraft speed changes and reversals can cause migration and disturbance of the liquid propellant within the tank. The guide channel can also provide a directional flow path for the propellant through the receiving cavity along its height direction, guiding the propellant at the far end along the height direction of the tank body to the outlet. This helps to suppress the intrusion of gaseous media into the outlet and external pipeline, reducing the risk of gas blockage and flow interruption, thus helping to meet the stable liquid supply requirements of the variable specific impulse magneto-plasma rocket under dynamic operating conditions. Attached Figure Description

[0041] Figure 1 A schematic diagram of the tank body and guide of the propellant storage tank for a variable specific impulse magnetic plasma rocket provided in an embodiment of the present invention;

[0042] Figure 2 A schematic diagram of the structure of a guide for a propellant storage tank in a variable specific impulse magnetic plasma rocket, provided in an embodiment of the present invention;

[0043] Figure 3 A three-dimensional structural schematic diagram of a propellant storage tank for a variable specific impulse magnetic plasma rocket provided in an embodiment of the present invention;

[0044] Figure 4 This is a partially enlarged schematic diagram of one end of the tank body and the first support component of the propellant storage tank for a variable specific impulse magnetic plasma rocket provided in an embodiment of the present invention.

[0045] Figure 5 A partially enlarged schematic diagram of the first support component and the first magnetic part of the propellant tank for a variable specific impulse magnetic plasma rocket provided in an embodiment of the present invention;

[0046] Figure 6 A partially enlarged schematic diagram of the other end of the propellant tank body of a variable specific impulse magnetic plasma rocket, the second support component, and the guide drive component, provided for an embodiment of the present invention.

[0047] Figure 7 This is a partially enlarged schematic diagram of the second support component, the second magnetic part, and the guiding drive component for the propellant tank of a variable specific impulse magnetic plasma rocket, provided in an embodiment of the present invention.

[0048] Figure 8 A schematic diagram of the cooling channel inside the propellant storage tank of a variable specific impulse magnetic plasma rocket provided in an embodiment of the present invention;

[0049] Figure 9 This is a schematic diagram of the propellant storage tank and Dewar for a variable specific impulse magnetic plasma rocket, provided as an embodiment of the present invention.

[0050] Explanation of reference numerals in the attached figures:

[0051] 10. Propellant storage tanks;

[0052] 100. Tank body; 101. Outlet; 102. Guide channel; 103. First convex structure; 104. Second convex structure; 105. Cooling channel; 106. Coolant inlet; 107. Coolant outlet;

[0053] 200. Guide component; 201. Guide section; 210. Guide shaft; 211. Guide blade; 212. First magnetic section; 213. Second magnetic section; 214. First magnetic cone; 215. Second magnetic cone;

[0054] 300. First support component; 310. First magnet generator; 311. First concave magnet generator;

[0055] 400. Second support component; 410. Second magnetic generator; 411. Second concave magnetic generator; 412. Transmission unit;

[0056] 500. Guide drive component; 510. Transmission gear set;

[0057] 600. First support frame; 610. First support leg; 620. First mounting frame; 630. First support bearing assembly;

[0058] 700. Second support frame; 710. Second support leg; 720. Second mounting bracket; 730. Second support bearing assembly;

[0059] 800. Outer peripheral buffer assembly; 810. First buffer spring; 820. Second buffer spring;

[0060] 20. Dewar;

[0061] Z, altitude direction. Detailed Implementation

[0062] As mentioned in the background section, the tanks of variable specific impulse magneto-plasma rockets only have basic capillary guide structures inside. Under the dynamic conditions of frequent speed changes and reversals of spacecraft in the microgravity environment of deep space, they cannot stably supply propellant and are difficult to adapt to the working requirements of variable specific impulse magneto-plasma rockets for long-term deep space exploration.

[0063] Therefore, the present invention provides a propellant storage tank for a variable specific impulse magnetic plasma rocket. A guide is provided in the receiving cavity of the tank body. The guide has a guide portion that surrounds the inner peripheral wall of the tank body to form a guide channel. One end of the guide channel is connected to the outlet, and the guide portion can guide the propellant in the guide channel to move towards the outlet, which is adapted to the stable liquid supply requirements of the variable specific impulse magnetic plasma rocket under dynamic operating conditions.

[0064] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0065] This embodiment discloses a propellant storage tank 10 for a variable specific impulse magnetic plasma rocket. It should be noted that the propellant can be liquid helium, liquid hydrogen, or liquid argon, etc.

[0066] like Figure 1 and Figure 2 As shown, this propellant storage tank 10 includes a tank body 100 and a guide 200. The tank body 100 has a receiving cavity for containing propellant, and one end of the tank body 100 along its height direction Z has an outlet 101 that connects the receiving cavity and an external pipeline.

[0067] Specifically, the tank body 100 is used to contain and store propellant. Its shape can be cylindrical, ellipsoidal, or other suitable shapes, and its material can be stainless steel, aluminum alloy, titanium alloy, or silicon carbide, materials suitable for propellant storage. Taking silicon carbide as an example, silicon carbide has high thermal conductivity and chemical stability, which helps maintain uniform temperature inside the tank under cryogenic propellant storage conditions, while also being resistant to chemical corrosion from the propellant, extending the tank's service life. Furthermore, silicon carbide has high structural strength and hardness, which helps improve the impact resistance of the tank body 100.

[0068] And, as Figure 1 and Figure 2 As shown, the guide 200 is located within the receiving cavity. The guide 200 includes a guide portion 201, which extends from one end of the tank body 100 to the other end in the height direction Z. A guide channel 102 is formed between the inner peripheral wall of the tank body 100 and the guide portion 201, and one end of the guide channel 102 communicates with the outlet 101. The guide portion 201 of the guide 200 is used to guide the propellant within the guide channel 102 toward the outlet 101, i.e., the propellant can move along... Figure 1 The dashed line in the middle moves toward exit 101.

[0069] In the microgravity environment of deep space, the inertial forces generated by the spacecraft's acceleration and reversal will cause migration and disturbance of the liquid propellant inside the tank. Specifically, in the near-zero gravity environment formed during the spacecraft's on-orbit cruise and orbital maneuvering, gravity settling is ineffective, and fluid surface tension and inertial forces dominate. The propellant inside the tank does not exhibit natural gas-liquid stratification, and is prone to liquid film floating, fluid dispersion, and disordered sloshing, which are completely different from the fluid characteristics of the Earth's gravity environment. Furthermore, when the spacecraft performs deep space exploration missions in orbit, the dynamic maneuvers involving acceleration, reversal, and attitude deflection to adapt to orbit switching, attitude calibration, and positioning will cause instantaneous inertial disturbances to the fluid inside the tank.

[0070] The propellant storage tank 10 provided in this embodiment has a guiding channel 102 that provides a directional flow path for the propellant in the height direction Z through the containment cavity. Even if the liquid propellant is pushed to a region of the tank far from the outlet 101 under the action of inertial force, the guiding channel 102 can still guide the propellant at the far end to the outlet 101 along the height direction Z of the tank body 100. This helps to suppress the intrusion of gaseous medium into the outlet 101 and external pipelines, reducing the risk of gas blockage and flow interruption. At the same time, the guiding part 201 extends from one end of the tank body 100 to the other end, so that the coverage of the guiding channel 102 penetrates the entire containment cavity in the height direction Z. This helps to improve the utilization rate of the propellant working fluid, so that the propellant in each region of the containment cavity can be collected and discharged, avoiding the problem of local propellant stagnation and supply failure. In addition, the setting of the guiding channel 102 restricts the flow of propellant, which helps to maintain the continuous supply of liquid medium in the case of gas-liquid two-phase mixing, thereby helping to adapt to the stable liquid supply requirements of variable specific impulse magneto-plasma rockets under dynamic conditions.

[0071] Of course, this type of propellant storage tank 10 can also be used for other similar rockets in regular cruise, ground simulation tests or different gravity orbit conditions, and this embodiment does not limit it to this only.

[0072] Specifically, such as Figure 1 and Figure 2 As shown, the guide 200 includes a guide shaft 210, which extends from one end of the can body 100 to the other end in the height direction Z of the can body 100. The guide shaft 210 is disposed in the middle of the receiving cavity in a plane perpendicular to the height direction Z of the can body 100.

[0073] The guide section 201 is a guide blade 211 that extends spirally from one end of the guide shaft 210 along its length direction to the other end on the side wall of the guide shaft 210. The outer edge of the guide blade 211 is attached to the inner wall of the can body 100, so that a spiral guide channel 102 is formed between the guide blade 211 and the inner peripheral wall of the can body 100.

[0074] Furthermore, the guide shaft 210 can rotate about an axis extending in the height direction Z of the tank body 100, and the guide vanes 211 are used to guide the propellant in the guide channel 102 toward the outlet 101.

[0075] In this embodiment, as Figure 1As shown, the spiral guide channel 102 can smoothly and stably guide the movement of propellant, helping to further suppress the intrusion of gaseous media. Furthermore, the guide shaft 210 is located in the center of the receiving cavity, causing the spiral guide blades 211 to radiate outwards from the guide shaft 210, facilitating the collection of propellant from all radial directions within the receiving cavity and increasing the collection coverage. Moreover, the guide shaft 210 can rotate about an axis extending Z in the height direction of the tank body 100. When the guide shaft 210 rotates, the spiral guide blades 211 generate a conveying force that propels the propellant within the guide channel 102 in a spiral direction, driving the propellant towards the outlet 101. This helps maintain the directional and stable delivery of the propellant under microgravity dynamic conditions, overcoming the problem of propellant reverse migration caused by inertial forces. In addition, the outer edge of the guide blades 211 adheres to the inner wall surface of the tank body 100, forming a closed spiral flow channel in the guide channel 102. This helps prevent propellant from bypassing and leaking through the gap between the guide blades 211 and the inner wall surface during delivery, improving the flow guiding efficiency.

[0076] It should be noted that the guide vane 211 can be a variable pitch helical vane, meaning the pitch of the helical vane gradually changes along the length of the guide shaft 210, with a smaller pitch near the outlet 101 and a larger pitch further away from the outlet 101. This variable pitch design allows the propellant to receive a stronger pushing force near the outlet 101, helping to increase the liquid supply pressure at the outlet 101. Simultaneously, the larger pitch region further away from the outlet 101 helps to improve the initial propellant collection efficiency.

[0077] Furthermore, the guide section 201 can also be a corrugated rib structure extending Z along the height direction of the tank body 100, forming a corrugated guide channel 102 between the corrugated rib and the inner peripheral wall of the tank body 100. The corrugated channel can increase the contact area between the propellant and the channel wall, enhancing capillary flow. At the same time, the tortuous structure of the corrugated channel helps to slow down the intrusion speed of bubbles along the channel, further improving the gas-liquid separation and guiding effect. The guide section 201 can also be multiple longitudinal guide plates distributed at intervals along the circumference of the tank body 100, each guide plate extending from one end of the tank body 100 to the other end, with multiple guide channels 102 formed between adjacent guide plates and between the guide plates and the inner peripheral wall. The multi-channel structure helps to collect and export propellant from different circumferential directions within the tank body 100 simultaneously, improving collection efficiency.

[0078] Furthermore, such as Figure 2 and Figure 4 As shown, a first magnetic part 212 is provided at one end of the guide shaft 210, and a second magnetic part 213 is provided at the other end; a first support member 300 is provided on the outer side of one end of the can body 100, and the first support member 300 is provided with a first magnetic generating part 310 corresponding to the first magnetic part 212, as shown. Figure 2 and Figure 6 As shown, a second support member 400 is provided on the outer side of the other end of the can body 100, and the second support member 400 is provided with a second magnetic generating part 410 corresponding to the second magnetic part 213.

[0079] The magnetic poles of the first magnetic part 212 and the first magnetic generating part 310 that are relatively close to each other have the same polarity, and the magnetic poles of the second magnetic part 213 and the second magnetic generating part 410 that are relatively close to each other have the same polarity. This results in a repulsive force in the height direction Z of the can body 100 between the first magnetic part 212 and the first magnetic generating part 310, and between the second magnetic part 213 and the second magnetic generating part 410. This allows the guide shaft 210 located between the first magnetic part 212 and the second magnetic part 213 to be suspended and supported across the corresponding wall surface of the can body 100.

[0080] In this embodiment, the magnetic poles of the first magnetic part 212 and the first magnetic generating part 310, and the magnetic part 213 and the second magnetic generating part 410, are of the same polarity on their relatively close sides. Utilizing the principle of magnetic repulsion between like poles, a repulsive force is generated in the height direction Z of the tank body 100, causing the guide shaft 210 to be suspended and supported within the receiving cavity through the wall of the tank body 100. This magnetic levitation support method eliminates the need for a mechanical shaft or bearing passing through the tank wall between the guide shaft 210 and the tank body 100, helping to maintain the sealing integrity of the receiving cavity of the tank body 100 and preventing propellant leakage along the gap between the shaft and the tank wall.

[0081] Furthermore, the magnetic levitation support prevents the guide shaft 210 from generating mechanical contact friction with the tank body 100 during rotation, helping to reduce rotational resistance and allowing the guide shaft 210 to rotate more flexibly in response to external drives. It also reduces propellant contamination caused by friction-generated particulate matter. In addition, the magnetic repulsion support has self-adjusting characteristics in the axial direction. When the guide shaft 210 undergoes axial displacement under dynamic operating conditions, the magnetic repulsion provides a restoring force, helping to maintain the guide shaft 210 in a centered position within the receiving cavity and ensuring the fit between the guide vane 211 and the inner wall surface.

[0082] It should be noted that the first magnetic part 212 and the second magnetic part 213 are respectively disposed at both ends of the guide shaft 210, and are magnetic components that provide magnetic repulsion. They can be made of permanent magnet materials, such as neodymium iron boron permanent magnets or samarium cobalt permanent magnets. The first support component 300 and the second support component 400 are respectively disposed on the outer sides of both ends of the tank body 100, and are the load-bearing structures for mounting the magnetic generating parts. They can be configured as magnetic cylinder structures. The first magnetic generating part 310 and the second magnetic generating part 410 are components that generate magnetic fields. They can be electromagnetic coils or permanent magnet arrays, and are respectively disposed corresponding to the first magnetic part 212 and the second magnetic part 213 on the tank wall.

[0083] This embodiment does not limit the specific structure and arrangement of the first magnetic part 212, the second magnetic part 213 and the corresponding magnetic generating part. For example, the first magnetic part 212 and the second magnetic part 213 can be cylindrical permanent magnets, and the corresponding magnetic generating part can be a ring electromagnetic coil. The end face of the cylindrical permanent magnet is arranged opposite to the end face of the ring electromagnetic coil. The electromagnetic coil is energized to generate a magnetic field with the same polarity as the end face of the permanent magnet, forming an axial magnetic repulsion force.

[0084] The first magnetic part 212 and the second magnetic part 213 can also be disk-shaped permanent magnets, and the corresponding magnetic generating part adopts a disk-shaped permanent magnet array. The magnetic poles on opposite sides of the disk-shaped permanent magnets and the disk-shaped permanent magnet array have the same polarity. Axial levitation force is formed by the repulsion between the like poles of the permanent magnets. This scheme can maintain levitation without power supply, which helps to reduce system power consumption.

[0085] The first magnetic section 212 and the second magnetic section 213 can also adopt permanent magnet components with a Halbach array structure. The Halbach array arranges magnets with different magnetization directions, so that the magnetic field lines are concentrated on one side and weakened on the other side, thereby forming a unidirectional magnetic field. The Halbach array can enhance the magnetic field on one side and weaken the magnetic field on the other side, which helps to generate a stronger magnetic repulsion on the interaction side between the magnetic section and the magnetic generation section, while reducing magnetic field leakage on the opposite side and improving magnetic energy utilization.

[0086] Furthermore, such as Figure 4 and Figure 5 As shown, in this embodiment, the first magnetic part 212 is a first magnetic cone 214 that extends from one end face of the guide shaft 210 toward the opposite end and whose cross-section gradually decreases. The first magnetic generating part 310 is a first concave magnetic generating part 311 that is adapted to the first magnetic cone 214. At one end of the can body 100, corresponding to the position of the guide shaft 210, there is a first convex structure 103 that is adapted to the first magnetic cone 214 and the first concave magnetic generating part 311. The outlet 101 is provided on the first convex structure 103, and the external pipeline passes through the first support member 300 and communicates with the outlet 101.

[0087] like Figure 6 and Figure 7 As shown, the second magnetic part 213 is a second magnetic cone 215 that extends from the other end face of the guide shaft 210 in a direction away from one end and whose cross-section gradually decreases. The second magnetic generating part 410 is configured as a second concave magnetic generating part 411 that is adapted to the second magnetic cone 215. At the other end of the can body 100, corresponding to the position of the guide shaft 210, there is a second convex structure 104 that is adapted to the second magnetic part 213 and the second concave magnetic generating part 411.

[0088] It should be noted that the cone angle of the magnetic cone can be relatively small (e.g., 30°), making the cone more pointed and the magnetic flux density at the tip highly concentrated. This helps to generate a larger magnetic repulsion force in the axial direction, making it suitable for applications where the guide shaft 210 is relatively heavy. Of course, the cone angle of the magnetic cone can also be relatively large (e.g., 65°), making the cone more flat and increasing the contact area between the cone surface and the concave surface. This helps to improve the radial self-centering ability and levitation stability, making it suitable for applications with strong radial disturbances.

[0089] In this embodiment, the first magnetic part 212 and the second magnetic part 213 each adopt a magnetic cone structure with a gradually decreasing cross-section, and the corresponding magnetic generating part adopts a concave structure. The corresponding positions at both ends of the tank body 100 adopt an outward convex structure. A conical and concave surface fits together between the magnetic cone and the concave magnetic generating part. The magnetic flux density is more concentrated in the tip region of the magnetic cone, which helps to generate a stronger magnetic repulsion force in the axial direction and improve the load-bearing capacity of the suspension support. Furthermore, the fit between the cone and the concave surface has a self-centering characteristic. When the guide shaft 210 is radially offset under dynamic working conditions, the change in the magnetic force distribution between the cone and the concave surface can generate a radial recovery component force, which helps the guide shaft 210 to automatically return to the center position and improves the radial stability of the magnetic levitation support.

[0090] Furthermore, in this embodiment, as Figure 3 As shown, a guide drive component 500 is provided at the other end of the tank body 100. The guide drive component 500 can be a drive motor or a drive cylinder, etc., and the output end of the guide drive component 500 is connected to the second support component 400 for transmission, driving the second support component 400 to rotate around an axis extending Z in the height direction of the tank body 100. The second support component 400 rotates synchronously with the corresponding second magnetic part 213 and the guide shaft 210 through the second magnetic generator 410. The second support component 400 also rotates synchronously with the guide shaft 210 through the magnetic coupling between the magnetic generator and the second magnetic part 213. This structure allows the rotational driving force of the guide shaft 210 to come from outside the tank body 100, eliminating the need for connection holes on the tank wall and helping to maintain the sealing performance of the tank body 100.

[0091] Furthermore, the guide drive 500 is located outside the tank body 100, which facilitates maintenance and repair, while preventing the heat generated by the drive from being directly transferred to the propellant inside the tank.

[0092] Specifically, such as Figure 3As shown, a first support frame 600 is provided on the outer side of one end of the tank body 100. The first support frame 600 includes a pair of first legs 610 disposed opposite to the two sides of the tank body 100 and a first mounting frame 620 connected to the pair of first legs 610 and located on the outer side of the tank body 100 at one end in the height direction Z. A first support bearing assembly 630 is provided on the first mounting frame 620. The first support bearing assembly 630 supports the first support component 300. The first support bearing assembly 630 includes a pair of first support bearings spaced apart along the height direction Z.

[0093] A second support frame 700 is provided at the other end of the tank body 100. The second support frame 700 includes a pair of second legs 710 disposed opposite to both sides of the tank body 100 and a second mounting frame 720 connected to the pair of second legs 710 and located on the outer side of the other end of the tank body 100 in the height direction Z. A second support bearing assembly 730 is provided on the second mounting frame 720. The second support bearing assembly 730 supports the second support component 400. The second support bearing assembly 730 includes a pair of second support bearings spaced apart along the height direction Z.

[0094] In this embodiment, a first support frame 600 and a second support frame 700 are respectively provided at both ends of the tank body 100. Each support frame includes a pair of legs and a mounting bracket. A support bearing assembly is provided on the mounting bracket to support the corresponding support component. The support frame can stably fix the corresponding support component, while the support bearing assembly can reduce the frictional resistance when the support component rotates, so that the driving force of the guide drive 500 can be efficiently transmitted to the second support component 400 and drive the guide shaft 210 to rotate. Furthermore, the setting of the support bearing assembly makes the rotational movement of the support component smoother, which helps to reduce vibration during the rotation process.

[0095] It should be noted that the connection method between the first support frame 600 and the second support frame 700 and the tank body 100 is similar. Taking the first support frame 600 as an example, the tank body 100 has multiple pairs of columnar protrusions protruding outward in the circumferential direction on the side wall near one end in the height direction Z. For example, two pairs of columnar protrusions are provided on the side wall near one end in the height direction Z of the body. The two pairs of columnar protrusions are spaced apart in the height direction Z, and each pair of columnar protrusions is arranged opposite to each other on both sides of the tank body 100. Each first leg 610 is provided with a mounting hole corresponding to the columnar protrusion on the same side. The first support frame 600 includes a pair of single frames spliced ​​together. The two single frames are spliced ​​together and fixed by fasteners (such as bolts or screws), so that the mounting holes on the first leg 610 are nested on the outside of the corresponding columnar protrusion, thereby fixing the first support frame 600 to the tank body 100. The structure of the second support frame 700 is similar to that of the first support frame 600, and will not be described in detail here.

[0096] Furthermore, such as Figure 6As shown, in this embodiment, the second support member 400 is provided with a transmission part 412 on the side of the tank body 100 away from the tank body 100 in the height direction Z. The transmission part 412 can be a rod-shaped structure extending along the height direction Z of the tank body 100. Furthermore, a guide drive member 500 is also mounted on the second mounting bracket 720 next to the second support member 400. A transmission gear set 510 is provided between the output end of the guide drive member 500 and the transmission part 412. The transmission gear set 510 can provide stable power transmission and can adjust the rotation speed by selecting the gear ratio, so that the rotation speed of the guide shaft 210 can be adapted to different propellant delivery requirements.

[0097] Specifically, the guide drive 500 can be fixed to the drive bracket by fasteners, and the drive bracket is connected to the second mounting bracket 720 by fasteners. Alternatively, an assembly part for assembling the guide drive 500 can be directly provided on the second mounting bracket 720, and the guide drive 500 can be directly assembled on the second mounting bracket 720.

[0098] Of course, the guide drive 500 can also be connected to the transmission part 412 via a reducer or coupling, or via a transmission belt assembly. This embodiment does not limit this to a single method.

[0099] It should be noted that when the can body 100 is made of silicon carbide, the insulating properties of silicon carbide ensure that the magnetic field between the magnetic generating part and the corresponding magnetic part is not affected, thus achieving stable levitation support and power transmission for the guide shaft 210. Of course, the can body 100 can also be made of materials such as stainless steel, aluminum alloy, and titanium alloy.

[0100] In addition, such as Figure 8 As shown, in this embodiment, a spiral cooling channel 105 extending in a spiral shape along the height direction Z of the tank body 100 is also provided inside the side wall of the tank body 100. A coolant inlet 106 communicating with one end of the cooling channel 105 is formed on the outer wall surface of one end of the tank body 100 (see...). Figure 1 The outer wall surface at the other end has a coolant outlet 107 that connects to the other end of the cooling channel 105 (see...). Figure 1 ).

[0101] In this embodiment, the cooling channel 105 can be circulated with a cooling medium to control the temperature of the tank body 100 and the propellant in the containment cavity. This helps maintain the propellant within a suitable liquid phase temperature range and prevents abnormal pressure increases or gas-liquid phase imbalances caused by propellant vaporization due to heat. Furthermore, the spirally extending cooling channel 105 increases the contact area between the cooling medium and the tank wall, improving heat exchange efficiency.

[0102] It should be noted that, as Figure 9As shown, in this embodiment, the canister body 100 is disposed inside the Dewar 20, and a vacuum chamber is formed between the Dewar 20 and the canister body 100. The vacuum chamber can provide efficient thermal isolation, significantly reducing heat exchange between the external environment and the canister body 100, which helps to maintain the cryogenic storage conditions of propellant in deep space exploration missions.

[0103] Furthermore, the propellant storage tank 10 also includes an outer peripheral buffer assembly 800 located on the outer periphery of the tank body 100 and connected to the inner wall surface of the Dewar 20, which can absorb vibration and shock energy during spacecraft launch or orbital maneuvering, and help protect the tank body 100 and the internal guide 200 from severe impacts.

[0104] Specifically, such as Figure 9 As shown, the peripheral buffer assembly 800 includes: a first buffer spring 810 extending along the height direction Z on the outer side walls of both ends of the tank body 100 in the height direction Z, which can absorb the axial impact energy transmitted along the height direction Z and help prevent the tank body 100 from undergoing excessive displacement or deformation under axial impact. For example, one, two, three or other numbers of first buffer springs 810 are provided on the outer side walls of both ends of the tank body 100 in the height direction Z.

[0105] The peripheral buffer assembly 800 may also include a plurality of second buffer springs 820 spaced apart on the outer side wall of the tank body 100 parallel to the height direction Z. For example, two, four, six, eight or other numbers of second buffer springs 820 may be spaced apart on the outer side wall of the tank body 100 parallel to the height direction Z. The plurality of second buffer springs 820 are spaced apart circumferentially along the tank body 100, and each second buffer spring 820 extends in a direction perpendicular to the height direction Z of the tank body 100. It can absorb lateral impact energy transmitted radially, which helps to limit the vibration and displacement of the tank body 100 in the radial direction and adapt to the multi-directional vibration and impact environment under the complex dynamic working conditions of spacecraft.

[0106] Of course, the outer peripheral buffer assembly 800 may also include only a plurality of first buffer springs 810, adapted to operating conditions where axial vibration is the main disturbance direction, such as the axial inertial force generated when a spacecraft accelerates or decelerates along the flight direction. Alternatively, the outer peripheral buffer assembly 800 may include only a plurality of second buffer springs 820, adapted to operating conditions where lateral vibration is the main disturbance direction, such as the radial inertial force generated when a spacecraft performs lateral maneuvers or attitude adjustments. This embodiment is not limited to this only option.

[0107] In addition, the peripheral buffer assembly 800 can also use rubber damping pads, which have good damping characteristics and can effectively absorb high-frequency vibration energy.

[0108] It should be noted that, in addition to the specific embodiments described above, those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Although the description of the present invention is presented in conjunction with preferred embodiments, this does not mean that the features of the invention are limited to these embodiments. On the contrary, the purpose of describing the invention in conjunction with the embodiments is to cover other options or modifications that may be derived based on the claims of the present invention. To provide a deep understanding of the invention, many specific details are included in the above description, and the invention may also be implemented without using these details. Furthermore, to avoid confusion or obscuring the focus of the invention, some specific details will be omitted in the description. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of the present invention can be combined with each other.

[0109] It should be noted that in this specification, similar reference numerals and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0110] In the description of this embodiment, it should be noted that the terms "upper", "lower", "inner", "bottom", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship that the product of the invention is usually placed in during use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the present invention.

[0111] The terms “first”, “second”, etc., are used only to distinguish descriptions and should not be interpreted as indicating or implying relative importance.

[0112] In the description of this embodiment, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set up," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this embodiment based on the specific circumstances.

[0113] While the present invention has been illustrated and described with reference to certain preferred embodiments, those skilled in the art should understand that the above description is a further detailed explanation of the invention in conjunction with specific embodiments, and should not be construed as limiting the specific implementation of the invention to these descriptions. Various changes in form and detail can be made by those skilled in the art, including several simple deductions or substitutions, without departing from the spirit and scope of the invention.

Claims

1. A propellant storage tank for a variable specific impulse magnetic plasma rocket, characterized in that, include: The tank body has a cavity for containing propellant, and one end of the tank body along its height direction has an outlet connecting the cavity and an external pipeline; A guide member is located within the receiving cavity. The guide member includes a guide portion that extends from one end of the can body to the other end in the height direction of the can body. A guide channel is formed between the inner peripheral wall of the can body and the guide portion, and one end of the guide channel is connected to the outlet. The guide portion of the guide member is used to guide the propellant in the guide channel toward the outlet.

2. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in claim 1, characterized in that, The guide includes a guide shaft that extends from one end of the can body to the other end in the height direction of the can body, and the guide shaft is disposed in the middle of the receiving cavity in a plane perpendicular to the height direction of the can body. The guide portion comprises: a guide blade extending spirally from one end of the guide shaft along its length towards the other on the side wall surface of the guide shaft; the outer edge of the guide blade abuts against the inner wall surface of the can body, thereby forming a spiral guide channel between the guide blade and the inner peripheral wall surface of the can body; and... The guide shaft is rotatable about an axis extending in the height direction of the tank body, and the guide vanes are used to guide the propellant in the guide channel toward the outlet.

3. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in claim 2, characterized in that, One end of the guide shaft is provided with a first magnetic part, and the other end is provided with a second magnetic part; a first support member is provided on the outer side of one end of the can body, and the first support member is provided with a first magnetic generating part corresponding to the first magnetic part; a second support member is provided on the outer side of the other end of the can body, and the second support member is provided with a second magnetic generating part corresponding to the second magnetic part. The magnetic poles of the first magnetic part and the first magnetic generating part that are relatively close to each other have the same polarity, and the magnetic poles of the second magnetic part and the second magnetic generating part that are relatively close to each other have the same polarity, so that there is a repulsive force between the first magnetic part and the first magnetic generating part and between the second magnetic part and the second magnetic generating part in the height direction of the can body, so as to suspend and support the guide shaft located between the first magnetic part and the second magnetic part through the corresponding wall surface of the can body.

4. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in claim 3, characterized in that, The first magnetic part is a first magnetic cone extending from one end face of the guide shaft away from the other end and with a gradually decreasing cross-section. The first magnetic generating part is a first concave magnetic generating part adapted to the first magnetic cone. At one end of the can body corresponding to the guide shaft, there is a first convex structure adapted to the first magnetic cone and the first concave magnetic generating part. The outlet is disposed in the first convex structure. The external pipeline passes through the first support member and communicates with the outlet. The second magnetic part is a second magnetic cone that extends from the other end face of the guide shaft in a direction away from one end and whose cross-section gradually decreases. The second magnetic generating part is configured as a second concave magnetic generating part that is adapted to the second magnetic cone. At the other end of the can body, corresponding to the position of the guide shaft, is a second convex structure that is adapted to the second magnetic part and the second concave magnetic generating part.

5. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in claim 4, characterized in that, The other end of the can body is provided with a guide drive, and the output end of the guide drive is connected to the second support component in a transmission manner, and drives the second support component to rotate around the axis extending in the height direction of the can body. The second support component rotates synchronously with the corresponding second magnetic part and the guide shaft through the second magnetic generator.

6. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in claim 5, characterized in that, A first support frame is provided on the outer side of one end of the tank body. The first support frame includes a pair of first legs disposed opposite to the two sides of the tank body and a first mounting frame connected to the pair of first legs and located on the outer side of one end of the tank body in the height direction. A first support bearing assembly is provided on the first mounting frame, and the first support bearing assembly supports the first support component. A second support frame is provided at the other end of the tank body. The second support frame includes a pair of second legs disposed opposite to the two sides of the tank body and a second mounting frame connected to the pair of second legs and located on the outer side of the other end of the tank body in the height direction. A second support bearing assembly is provided on the second mounting frame, and the second support bearing assembly supports the second support component.

7. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in claim 6, characterized in that, The second support member has a transmission part provided on the side of the tank body away from the tank body in the height direction; and the guide drive is also mounted on the second mounting bracket next to the second support member, and a transmission gear set is provided between the output end of the guide drive and the transmission part. And / or, the can body is made of silicon carbide.

8. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in any one of claims 1 to 7, characterized in that, The tank body is also provided with a spiral cooling channel extending in a spiral shape along the height direction of the tank body. A coolant inlet is formed on the outer wall surface of one end of the tank body, which connects to one end of the cooling channel, and a coolant outlet is formed on the outer wall surface of the other end, which connects to the other end of the cooling channel.

9. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in any one of claims 1 to 7, characterized in that, The tank body is disposed inside the Dewar, and a vacuum chamber is formed between the Dewar and the tank body. The propellant storage tank also includes an outer peripheral buffer assembly located on the outer periphery of the tank body and connected to the inner wall surface of the Dewar.

10. The propellant storage tank for a variable specific impulse magneto-plasma rocket as described in claim 9, characterized in that, The peripheral buffer assembly includes: First buffer springs are disposed on the outer walls at both ends of the tank body, extending along the height direction; and / or, Multiple second buffer springs are provided at intervals on the outer side wall of the tank body parallel to the height direction, and each second buffer spring extends in a direction perpendicular to the height direction of the tank body.

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