A cubic satellite resistance propulsion device and method

Abstract

The present application discloses a resistance propulsion device and method for a cubic satellite. The propulsion device comprises a device base, a tank, a pressure sensor, a first solenoid valve mechanism, a second solenoid valve mechanism, a working fluid conduit, and a thruster mechanism; the thruster mechanism comprises a valve joint, a heating component, a working fluid guide component, a heat insulation component, a nozzle component, and a thrust direction adjustment component; in the propulsion method, the working fluid flows into the thruster mechanism through the first solenoid valve mechanism, the working fluid guide component, and the second solenoid valve mechanism in sequence; and enters the working fluid guide component through the valve joint, the heating component heats the working fluid, and the working fluid is ejected from the nozzle component after being heated and vaporized to generate thrust; the thrust direction adjustment component adjusts the direction of the ejected vaporized fluid to achieve precise thrust control; the present application achieves efficient and adjustable propulsion output by precisely controlling the flow, heating, guide and injection of the working fluid, and is suitable for orbit control and attitude adjustment of cubic satellites in complex tasks.

Description

Technical Field

[0001] The present application relates to the field of cubic satellite technology, and in particular to a cubic satellite resistance propulsion device and method. Background Art

[0002] CubeSat is a low-cost micro-nano satellite designed according to international standards. It uses "U" as its unit and is widely used in various space missions. Most of the current CubeSats use a fixed nozzle design, which cannot adjust the thrust direction, resulting in the CubeSat's lack of sufficient flexibility when performing complex tasks. This limitation of the fixed nozzle makes it difficult for CubeSats to adapt to high-demand tasks that require precise orbit control and attitude adjustment. Summary of the invention

[0003] In order to improve the defect that the fixed nozzle design of a cubic satellite cannot adjust the thrust direction, the present application provides a cubic satellite resistance propulsion device and method.

[0004] The present application provides a cubic satellite resistance propulsion device and method using the following technical solutions:

[0005] A cubic satellite resistance propulsion device, comprising a device base, a tank connected to the device base and used to store a working medium, a pressure sensor connected to the device base and in communication with the tank, a first solenoid valve mechanism connected to the device base and in communication with the tank, a second solenoid valve mechanism inserted in the middle of the tank and connected to the device base, a working medium conduit respectively in communication with the first solenoid valve mechanism and the second solenoid valve mechanism, and a thruster mechanism connected to the second solenoid valve mechanism;

[0006] The thruster mechanism includes a valve joint connected to the second solenoid valve mechanism, a heating assembly connected to the valve joint, a working fluid guide assembly connected to the valve joint and sleeved on the outside of the heating assembly, a heat insulation assembly sleeved on the outside of the working fluid guide assembly, a nozzle assembly connected to the outlet end of the working fluid guide assembly, and a thrust direction adjustment assembly connected to the nozzle assembly.

[0007] By adopting the above technical solution, the tank is used to store the working fluid, which flows out through the first solenoid valve mechanism and flows into the thruster mechanism through the working fluid conduit and the second solenoid valve mechanism; in the thruster mechanism, the working fluid enters the working fluid flow guide assembly through the valve joint, the heating assembly heats the working fluid in the working fluid flow guide assembly, and the working fluid is ejected from the nozzle assembly after being heated and vaporized to generate thrust; the thrust direction adjustment assembly adjusts the direction of the vaporized fluid ejected from the nozzle assembly to achieve precise thrust control and attitude adjustment; the present application achieves efficient and adjustable propulsion output by precisely controlling the flow, heating, diversion and injection of the working fluid, and is suitable for orbit control and attitude adjustment of cubic satellites in complex tasks.

[0008] Preferably, the thrust direction adjustment assembly includes a direction adjustment rotating disk rotatably connected to the nozzle assembly, a rotating guide component connected to the nozzle assembly and sleeved on the circumference of the direction adjustment rotating disk, a direction adjustment driving component connected to the nozzle assembly and used to drive the direction adjustment rotating disk to rotate, and a thrust guide component connected to the direction adjustment rotating disk; the direction adjustment rotating disk is provided with a guide spray hole corresponding to the outlet end of the nozzle assembly, and the thrust guide component is located on one side of the guide spray hole for guiding the ejection of the working fluid.

[0009] By adopting the above technical solution, the steering drive component is used to drive the steering rotating disk to rotate, and the steering rotating disk drives the guide nozzle and the thrust guide component to rotate. The working fluid is ejected from the nozzle assembly into the guide nozzle, and is guided in the injection direction by the thrust guide component, so that the working fluid can be accurately ejected in the set direction when ejected; the thrust guide component is located on one side of the guide nozzle, ensuring that the working fluid can be accurately guided when ejected, thereby achieving directional output of thrust; the present application uses precise rotation guidance and thrust guidance control to enable the injection of the working fluid to be flexibly adjusted in multiple directions, which not only enables the cubic satellite to adjust its attitude and orbit according to different mission requirements, but also improves its adaptability and survivability in complex space environments.

[0010] Preferably, the direction-adjusting rotating disk comprises a rotating disk body rotatably connected to the nozzle assembly, and an annular rack sleeved on the circumference of the rotating disk body;

[0011] The direction adjustment driving component includes a rotation driving part fixedly connected to the nozzle assembly, and a driving gear disposed at the output end of the rotation driving part and meshing with the annular rack.

[0012] By adopting the above technical solution, the rotary drive part is used to drive the driving gear, which meshes with the annular rack, thereby driving the adjustment rotating disk to rotate; the guide spray hole on the adjustment rotating disk is connected to the outlet end of the adjustment nozzle assembly, so that the spray of the working fluid can be adjusted in direction as needed, thereby realizing the adjustment and guidance of the thrust; the present application realizes the optimization of driving accuracy and torque transmission through gear meshing transmission, ensuring the efficient and smooth operation of the thrust adjustment assembly.

[0013] Preferably, the turntable body is provided with an annular guide groove which is sleeved on the circumference of the turntable body and located on one side of the annular rack; the rotating guide component includes an annular sleeve fixedly connected to the nozzle assembly, and an annular guide protrusion connected to the side edge of the annular sleeve and movably inserted in the annular guide groove.

[0014] By adopting the above technical solution, when the direction adjustment driving component drives the annular rack to rotate through the driving gear, the turntable body starts to rotate; the annular guide groove is coaxial with the turntable body and is located on one side of the annular rack; the annular guide convex edge is movably inserted in the annular guide groove to provide a guiding effect on the turntable body, ensuring the accurate rotation of the turntable body, thereby realizing the precise direction adjustment of the nozzle assembly; the present application effectively limits the degree of freedom of rotation through the cooperation between the annular guide groove and the annular guide convex edge, ensures the stability and accuracy of the thrust direction adjustment, avoids the nozzle deviation caused by irregular movement, and improves the direction adjustment accuracy.

[0015] Preferably, the guide spray holes include a first spray hole, a second spray hole, a third spray hole, a fourth spray hole, and a fifth spray hole arranged in an array along the circumference of the turntable body;

[0016] The thrust guide component includes a first guide portion connected to the turntable body and located on one side of the first spray hole, a second guide portion located on one side of the second spray hole, a third guide portion located on one side of the third spray hole, and a fourth guide portion located on one side of the fourth spray hole; an opening direction of the first guide portion is opposite to an opening direction of the second guide portion, an opening direction of the third guide portion is opposite to an opening direction of the fourth guide portion, and an opening direction of the first guide portion and an opening direction of the third guide portion are arranged at an angle.

[0017] By adopting the above technical solution, when the turntable body rotates, the first spray hole, the second spray hole, the third spray hole, the fourth spray hole and the fifth spray hole arranged on the turntable body are respectively aligned with the outlet end of the nozzle assembly as the outlet for the working fluid to be sprayed out; the thrust guide component is connected to the turntable body and is located on the side of the corresponding spray hole, which are the first guide part, the second guide part, the third guide part and the fourth guide part respectively; the opening directions of the first guide part and the second guide part are arranged oppositely, and the opening directions of the third guide part and the fourth guide part are also arranged oppositely, and the opening directions of the first guide part and the third guide part are arranged at an angle. As the turntable body rotates, the thrust guide component guides the working fluid to be accurately sprayed through different angles through different opening directions and arrangement angles, thereby adjusting the direction and distribution of the thrust, and the fifth spray hole is used for vertical injection; the present application uses multi-directional guide control to enable the nozzle assembly to be flexibly adjusted in multiple directions, thereby improving the directional accuracy and response speed of the thrust, and can meet the requirements of fine orbit control and attitude adjustment in complex tasks, improve the thrust adjustment accuracy, and improve the working fluid utilization efficiency and system stability.

[0018] Preferably, the first guide portion, the second guide portion, the third guide portion, and the fourth guide portion all include an arcuate guide side wall connected to the turntable body, and a guide side edge connected to the arcuate guide side wall; the arcuate guide side wall and the guide side edge are arranged to form an arcuate guide groove connected to the guide nozzle.

[0019] By adopting the above technical solution, the arc-shaped guide side wall and the guide side edge are surrounded to form an arc-shaped guide groove, ensuring that the working fluid can flow along the designed path and be accurately guided when entering from the guide nozzle; when the turntable body rotates, each guide part guides the flow of the working fluid through the arc-shaped guide groove, so that the working fluid is ejected along a predetermined path, and through the guiding effect in different directions, the nozzle assembly is pushed to accurately adjust the injection angle in multiple directions; since the design of each guide part accurately controls the injection direction, the working fluid can be injected efficiently and orderly, avoiding the irregularity of the injection direction, thereby improving the accuracy and stability of the thrust adjustment; the present application has a good fluid guiding effect, can optimize the thrust control, and improve the directional output of the thrust.

[0020] Preferably, the working medium flow guide assembly comprises a flow guide support seat connected to the valve joint, a flow guide inner shell connected to the flow guide support seat, a flow guide outer shell connected to the side edge of the flow guide support seat and sleeved on the outside of the flow guide inner shell, and a terminal connected to the end of the flow guide inner shell and the flow guide outer shell respectively; the flow guide support seat, the flow guide inner shell, the flow guide outer shell and the terminal are surrounded to form a working medium flow guide cavity;

[0021] The flow guide support seat is connected to the ends of the flow guide inner shell and the flow guide outer shell respectively, and the end head is connected to the other ends of the flow guide inner shell and the flow guide outer shell respectively.

[0022] By adopting the above technical solution, the working fluid enters through the guide support seat connected to the valve joint, and the guide support seat guides the working fluid into the working fluid guide cavity between the guide inner shell and the guide outer shell. The setting of the guide inner shell and the guide outer shell is used to protect and strengthen the guiding function of the working fluid; this application effectively reduces the flow resistance, optimizes the guiding path of the working fluid, improves the stability and guiding efficiency of the working fluid flow, and helps to ensure that the working fluid can be evenly distributed and flow to the nozzle assembly, thereby improving the thrust output efficiency, fluid guiding accuracy and working stability of the propulsion system.

[0023] Preferably, the nozzle assembly comprises a nozzle body connected to the guide outer shell, and a vibrating component sleeved on the periphery of the nozzle body; the nozzle body is provided with a working medium guide groove, a conical injection hole, and a working medium outlet hole provided between the working medium guide groove and the conical injection hole and used to connect the working medium guide groove and the conical injection hole;

[0024] The guide support seat is provided with a first guide hole for connecting the valve joint and the working medium guide cavity, and the end head is provided with a second guide hole for connecting the working medium guide cavity and the working medium guide groove; the opening end of the conical injection hole is used to align with the guide injection hole.

[0025] By adopting the above technical scheme, the working fluid enters the working fluid guide cavity through the first guide hole on the guide support seat, flows into the working fluid guide groove through the second guide hole on the end head, and then enters the conical injection hole from the working fluid outlet hole, and is ejected from the conical injection hole; the opening end of the conical injection hole is aligned with the guide injection hole to ensure that the working fluid is ejected along a predetermined direction; the vibration component sleeved on the periphery of the nozzle body may further adjust the working fluid flow and injection effect during the injection process through vibration; the present application effectively guides the working fluid flow through the precise layout of the first guide hole, the second guide hole, the working fluid guide groove and the conical injection hole, ensures the stable injection of the working fluid, and improves the directionality and efficiency of the thrust output through the design of the conical injection hole.

[0026] Preferably, the guide support seat is provided with a heating limit groove, the guide inner shell is provided with a heating cavity connected with the heating limit groove, and the heating component is inserted in the heating cavity;

[0027] The heating component includes a heating bracket with one end inserted in the heating limit groove and the other end connected to the end head, a heating wire guide pipe inserted in the guide support seat and the insulation component and used to connect the heating limit groove with the external space, and a heating wire component wound on the heating bracket and used to extend from the heating wire guide pipe to the external space.

[0028] By adopting the above technical scheme, one end of the heating bracket is inserted into the heating limit groove on the guide support seat, and the other end is connected to the end head, so that the heating bracket is fixed in the guide inner shell; through the connection between the heating limit groove and the heating cavity, the installation and positioning space of the heating component is provided; the heating wire guide pipe is inserted between the guide support seat and the insulation component, as a channel connecting the heating limit groove and the external space, guiding the heating wire component; the heating wire component is wound around the heating bracket and extends from the heating wire guide pipe to the external space; when the heating wire component is energized, it can generate heat, transfer the heat to the heating bracket through the heating cavity, and then transfer the heat to the guide support seat and the working fluid guide cavity through the heating bracket, so as to heat the working fluid flowing through, increase the temperature of the working fluid, and ensure the performance optimization of the working fluid during the advancement process; the present application not only improves the heating efficiency through precise heat conduction path design, but also avoids the influence of excessive heating on other components of the system, and ensures the stability of the heating process and uniform heating of the working fluid.

[0029] A cubic satellite resistance propulsion method, comprising the cubic satellite resistance propulsion device, further comprising the following steps:

[0030] S1: the first solenoid valve mechanism and the second solenoid valve mechanism are closed, the heating component is started and preheats the working fluid guiding component;

[0031] S2: the first solenoid valve mechanism and the second solenoid valve mechanism are opened, and the working medium flows out of the tank and passes through the first solenoid valve mechanism, the working medium conduit and the second solenoid valve mechanism in sequence;

[0032] S3: The working fluid flows from the second solenoid valve mechanism into the valve joint on the thruster mechanism, and then into the working fluid guide assembly;

[0033] S4: the heating component heats the working fluid in the working fluid guide component and vaporizes the working fluid, and the vaporized working fluid is ejected from the nozzle component and generates thrust;

[0034] S5: The thrust direction adjustment assembly rotates and adjusts the direction in which the vaporized medium on the nozzle assembly is ejected.

[0035] By adopting the above technical solution, when the first solenoid valve mechanism and the second solenoid valve mechanism are in a closed state, the heating component is started to preheat the working fluid flow guide component to ensure that the working fluid can flow smoothly in the subsequent stage and is ready for heating; when the first solenoid valve mechanism and the second solenoid valve mechanism are opened, the working fluid flows out of the tank, passes through the first solenoid valve mechanism, the working fluid conduit and the second solenoid valve mechanism, ensuring that the working fluid enters the subsequent propulsion system; the working fluid flows into the valve joint on the thruster mechanism through the second solenoid valve mechanism, and enters the working fluid flow guide component to prepare for the heating process; the heating component heats the working fluid in the working fluid flow guide component to promote the vaporization of the working fluid, and the vaporized working fluid flows out The nozzle assembly sprays out, generates thrust, and drives the cube satellite to move; the thrust direction adjustment assembly rotates, and by adjusting the direction of the nozzle assembly, the direction of the vaporized medium spraying is changed, and the direction of the thrust is further accurately adjusted; the present application ensures that the medium can efficiently flow, vaporize, and spray out through the nozzle assembly to achieve stable thrust output by accurately controlling the working process of the solenoid valve and the heating assembly; the precise adjustment of the thrust direction adjustment assembly ensures the flexibility and efficiency of the propulsion direction, and can meet the needs of the cube satellite in complex orbital control; it not only improves the propulsion efficiency, enhances the reliability and accuracy of the system, but also improves the flexibility of thrust control and the efficiency of thrust generation.

[0036] In summary, the present application includes at least one of the following beneficial technical effects:

[0037] 1. A cubic satellite resistance propulsion device, wherein a tank is used to store a working fluid, the working fluid flows out through a first solenoid valve mechanism, and flows into a thruster mechanism through a working fluid conduit and a second solenoid valve mechanism; in the thruster mechanism, the working fluid enters a working fluid flow guide assembly through a valve joint, a heating assembly heats the working fluid in the working fluid flow guide assembly, and the working fluid is sprayed out from a nozzle assembly after being heated and vaporized to generate thrust; a thrust direction adjustment assembly adjusts the direction of the vaporized fluid sprayed from the nozzle assembly to achieve precise thrust control and attitude adjustment; the present application achieves efficient and adjustable propulsion output by precisely controlling the flow, heating, diversion and injection of the working fluid, and is suitable for orbit control and attitude adjustment of cubic satellites in complex tasks;

[0038] 2. A cubic satellite resistance propulsion device, when the turntable body rotates, the first spray hole, the second spray hole, the third spray hole, the fourth spray hole and the fifth spray hole arranged on the turntable body are respectively aligned with the outlet end of the nozzle assembly as the outlet for the working fluid to be sprayed out; the thrust guide component is connected to the turntable body and is located on the side of the corresponding spray hole, which are the first guide part, the second guide part, the third guide part and the fourth guide part respectively; the opening directions of the first guide part and the second guide part are arranged oppositely, and the opening directions of the third guide part and the fourth guide part are also arranged oppositely, and the opening directions of the first guide part and the third guide part are arranged at an angle, as the turntable body rotates, the thrust guide component guides the working fluid to be accurately sprayed through different angles through different opening directions and arrangement angles, thereby adjusting the direction and distribution of the thrust, and the fifth spray hole is used for vertical spraying; the present application uses multi-directional guidance control to enable the nozzle assembly to be flexibly adjusted in multiple directions, thereby improving the directional accuracy and response speed of the thrust, and can meet the requirements of fine orbit control and attitude adjustment in complex tasks, improve the thrust adjustment accuracy, and improve the working fluid utilization efficiency and system stability;

[0039] 3. A cubic satellite resistance propulsion method, when the first solenoid valve mechanism and the second solenoid valve mechanism are in a closed state, the heating component is started to preheat the working fluid guide component to ensure that the working fluid can flow smoothly in the subsequent stage and is ready for heating; when the first solenoid valve mechanism and the second solenoid valve mechanism are opened, the working fluid flows out of the tank, passes through the first solenoid valve mechanism, the working fluid conduit and the second solenoid valve mechanism, ensuring that the working fluid enters the subsequent propulsion system; the working fluid flows into the valve joint on the thruster mechanism through the second solenoid valve mechanism, and enters the working fluid guide component to prepare for the heating process; the heating component heats the working fluid in the working fluid guide component to promote the vaporization of the working fluid, and the vaporized working fluid is The fluid is ejected from the nozzle assembly to generate thrust, which drives the cube satellite to move; the thrust direction adjustment assembly rotates, and by adjusting the direction of the nozzle assembly, the direction of the vaporized fluid ejection is changed, and the direction of the thrust is further accurately adjusted; the present application ensures that the fluid can efficiently flow, vaporize and be ejected through the nozzle assembly to achieve stable thrust output by accurately controlling the working process of the solenoid valve and the heating assembly; the precise adjustment of the thrust direction adjustment assembly ensures the flexibility and efficiency of the propulsion direction, and can meet the needs of the cube satellite in complex orbit control; it not only improves the propulsion efficiency, enhances the reliability and accuracy of the system, but also improves the flexibility of thrust control and the efficiency of thrust generation. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 This is a schematic cross-sectional view of an embodiment of a cubic satellite resistance propulsion device of the present application. Figure 1 .

[0041] Figure 2 This is a three-dimensional structural diagram of a thrust adjustment assembly of a cubic satellite resistance propulsion device embodiment of the present application. Figure 1 .

[0042] Figure 3 A schematic cross-sectional view of the thrust adjustment assembly of a cubic satellite resistance propulsion device embodiment of the present application.

[0043] Figure 4 This is a three-dimensional structural diagram of a thrust adjustment assembly of a cubic satellite resistance propulsion device embodiment of the present application. Figure 2 .

[0044] Figure 5 It is a schematic cross-sectional structural diagram of a thruster mechanism of an embodiment of a cubic satellite resistance propulsion device of the present application.

[0045] Figure 6 This is a schematic cross-sectional view of an embodiment of a cubic satellite resistance propulsion device of the present application. Figure 2 .

[0046] Figure 7 It is a schematic diagram of the steps of a cubic satellite resistance propulsion method embodiment of the present application.

[0047] Description of reference numerals:

[0048] 1. Device base; 2. Storage tank; 3. Pressure sensor; 4. First solenoid valve mechanism; 5. Second solenoid valve mechanism; 6. Working fluid conduit;

[0049] 7. thruster mechanism; 71. valve connector; 72. heating assembly; 73. fluid guide assembly; 74. heat insulation assembly; 75. nozzle assembly; 76. thrust adjustment assembly; 721. heating bracket; 722. heating wire guide pipe; 723. heating wire component; 731. guide support seat; 732. guide inner shell; 733. guide outer shell; 734. end; 735. fluid guide cavity; 741. heat dissipation guide shell; 742. Connecting support column; 743, heat dissipation support plate; 744, heat dissipation through hole; 745, heat insulation channel; 751, nozzle body; 752, vibration component; 753, working medium guide groove; 754, conical injection hole; 755, working medium outlet hole; 756, first guide hole; 757, second guide hole; 761, direction adjustment rotating disk; 762, rotation guide component; 763, direction adjustment driving component; 764, thrust guide component; 765, guide spray hole;

[0050] 7211, support body; 7212, first limiting convex edge; 7213, second limiting convex edge; 7214, spiral limiting groove; 7215, heating wire guide through hole; 7216, heating connecting hole; 7311, heating limiting groove; 7312, heating cavity; 7611, turntable body; 7612, annular rack; 7613, annular guide groove; 7621, annular sleeve; 7622, ​​annular guide convex edge; 763 1. Rotary drive unit; 7632. Drive gear; 7641. First guide unit; 7642. Second guide unit; 7643. Third guide unit; 7644. Fourth guide unit; 7645. Arc-shaped guide side wall; 7646. Guide side edge; 7647. Arc-shaped guide groove; 7651. First spray hole; 7652. Second spray hole; 7653. Third spray hole; 7654. Fourth spray hole; 7655. Fifth spray hole. DETAILED DESCRIPTION

[0051] The following is combined with Figures 1 to 7 This application is described in further detail.

[0052] The present application embodiment discloses a cubic satellite resistance propulsion device and method. Figure 1 A cubic satellite resistance propulsion device comprises a device base 1, a tank 2 connected to the device base 1 and used to store a working medium, a pressure sensor 3 connected to the device base 1 and communicated with the tank 2, a first solenoid valve mechanism 4 connected to the device base 1 and communicated with the tank 2, a second solenoid valve mechanism 5 inserted at a middle position of the tank 2 and connected to the device base 1, a working medium conduit 6 respectively communicated with the first solenoid valve mechanism 4 and the second solenoid valve mechanism 5, and a thruster mechanism 7 connected to the second solenoid valve mechanism 5;

[0053] The thruster mechanism 7 includes a valve connector 71 connected to the second solenoid valve mechanism 5, a heating assembly 72 connected to the valve connector 71, a working fluid guide assembly 73 connected to the valve connector 71 and sleeved on the outside of the heating assembly 72, a heat insulation assembly 74 sleeved on the outside of the working fluid guide assembly 73, a nozzle assembly 75 connected to the outlet end of the working fluid guide assembly 73, and a thrust adjustment assembly 76 connected to the nozzle assembly 75.

[0054] The tank 2 of the present application is used to store working fluid, which flows out through the first solenoid valve mechanism 4 and flows into the thruster mechanism 7 through the working fluid conduit 6 and the second solenoid valve mechanism 5; in the thruster mechanism 7, the working fluid enters the working fluid guide assembly 73 through the valve joint 71, and the heating assembly 72 heats the working fluid in the working fluid guide assembly 73, and the working fluid is sprayed out from the nozzle assembly 75 after being heated and vaporized to generate thrust; the thrust direction adjustment assembly 76 adjusts the direction of the vaporized fluid sprayed from the nozzle assembly 75 to achieve precise thrust control and attitude adjustment; the present application achieves efficient and adjustable propulsion output by precisely controlling the flow, heating, diversion and injection of the working fluid, and is suitable for orbit control and attitude adjustment of cubic satellites in complex tasks.

[0055] Furthermore, if Figure 2 As shown, the thrust direction adjustment assembly 76 includes a direction adjustment rotating disk 761 rotatably connected to the nozzle assembly 75, a rotating guide component 762 connected to the nozzle assembly 75 and sleeved on the circumference of the direction adjustment rotating disk 761, a direction adjustment driving component 763 connected to the nozzle assembly 75 and used to drive the direction adjustment rotating disk 761 to rotate, and a thrust guide component 764 connected to the direction adjustment rotating disk 761; the direction adjustment rotating disk 761 is provided with a guide spray hole 765 corresponding to the outlet end of the nozzle assembly 75, and the thrust guide component 764 is located on one side of the guide spray hole 765 for guiding the ejection of the working fluid.

[0056] The steering drive component 763 of the present application is used to drive the steering rotating disk 761 to rotate, and the steering rotating disk 761 drives the guide nozzle 765 and the thrust guide component 764 to rotate. The working fluid is ejected from the nozzle assembly 75 into the guide nozzle 765, and is guided in the ejection direction by the thrust guide component 764, so that the working fluid can be accurately ejected in the set direction when ejected; the thrust guide component 764 is located on one side of the guide nozzle 765 to ensure that the working fluid can be accurately guided when ejected, thereby achieving directional output of thrust; the present application uses precise rotation guidance and thrust guidance control to enable the ejection of the working fluid to be flexibly adjusted in multiple directions, which not only enables the cubic satellite to adjust its attitude and orbit according to different mission requirements, but also improves its adaptability and survivability in complex space environments.

[0057] Furthermore, if Figure 2 As shown, the direction-adjusting rotating disk 761 includes a rotating disk body 7611 rotatably connected to the nozzle assembly 75, and an annular rack 7612 sleeved on the circumference of the rotating disk body 7611;

[0058] The direction adjustment driving component 763 includes a rotation driving portion 7631 fixedly connected to the nozzle assembly 75 , and a driving gear 7632 provided at the output end of the rotation driving portion 7631 and meshing with the annular rack 7612 .

[0059] The rotary drive part 7631 of the present application is used to drive the driving gear 7632, and the driving gear 7632 is meshed with the annular rack 7612, thereby driving the direction-adjusting rotating disk 761 to rotate; the guide spray hole 765 on the direction-adjusting rotating disk 761 is correspondingly connected to the outlet end of the adjustment nozzle assembly 75, so that the spraying direction of the working medium can be adjusted as needed, thereby realizing the adjustment and guidance of the thrust; the present application realizes the optimization of driving accuracy and torque transmission through gear meshing transmission, ensuring the efficient and stable operation of the thrust direction-adjusting assembly;

[0060] The rotation driving unit 7631 is preferably a motor.

[0061] Specifically, Figure 3 As shown, the turntable body 7611 is provided with an annular guide groove 7613 which is sleeved on the circumference of the turntable body 7611 and located on one side of the annular rack 7612; the rotating guide component 762 includes an annular sleeve 7621 fixedly connected to the nozzle assembly 75, and an annular guide protrusion 7622 connected to the side edge of the annular sleeve 7621 and movably inserted into the annular guide groove 7613.

[0062] In the present application, when the adjustment driving component 763 drives the annular rack 7612 to rotate through the driving gear 7632, the turntable body 7611 starts to rotate; the annular guide groove 7613 is coaxial with the turntable body 7611 and is located on one side of the annular rack 7612; the annular guide protrusion 7622 is movably inserted in the annular guide groove 7613 to provide a guiding effect on the turntable body 7611, ensuring the accurate rotation of the turntable body 7611, thereby achieving precise adjustment of the nozzle assembly 75; the present application effectively limits the degree of freedom of rotation through the cooperation between the annular guide groove 7613 and the annular guide protrusion 7622, ​​ensures the stability and accuracy of the thrust adjustment, avoids the nozzle deviation caused by irregular movement, and improves the adjustment accuracy.

[0063] More specifically, if Figure 4 As shown, the guide spray holes 765 include a first spray hole 7651, a second spray hole 7652, a third spray hole 7653, a fourth spray hole 7654, and a fifth spray hole 7655 arranged in an array along the circumference of the turntable body 7611;

[0064] The thrust guide component 764 includes a first guide portion 7641 connected to the turntable body 7611 and located on the side of the first spray hole 7651, a second guide portion 7642 located on the side of the second spray hole 7652, a third guide portion 7643 located on the side of the third spray hole 7653, and a fourth guide portion 7644 located on the side of the fourth spray hole 7654; an opening direction of the first guide portion 7641 is opposite to an opening direction of the second guide portion 7642, an opening direction of the third guide portion 7643 is opposite to an opening direction of the fourth guide portion 7644, and an opening direction of the first guide portion 7641 and an opening direction of the third guide portion 7643 are arranged at an angle.

[0065] In the present application, when the turntable body 7611 rotates, the first spray hole 7651, the second spray hole 7652, the third spray hole 7653, the fourth spray hole 7654 and the fifth spray hole 7655 provided on the turntable body 7611 are respectively aligned with the outlet of the nozzle assembly 75 as the outlet for spraying the working medium; the thrust guide component 764 is connected to the turntable body 7611 and is located on the side of the corresponding spray hole, which are respectively the first guide part 7641, the second guide part 7642, the third guide part 7643 and the fourth guide part 7644; the first guide part 7641 and the second guide part 7642 are arranged in opposite directions to each other, and the third guide part 7643 and the fourth guide part 7644 are arranged in opposite directions to each other. The opening directions are also arranged opposite to each other, and the opening directions of the first guide portion 7641 and the third guide portion 7643 are arranged at an angle. As the turntable body 7611 rotates, the thrust guide component 764 guides the working fluid to be precisely sprayed through different angles through different opening directions and arrangement angles, thereby adjusting the direction and distribution of the thrust. The fifth nozzle 7655 is used for vertical injection. The present application uses multi-directional guiding control to enable the nozzle assembly 75 to be flexibly adjusted in multiple directions, thereby improving the directional accuracy and response speed of the thrust, being able to meet the requirements of fine orbit control and attitude adjustment in complex tasks, improving the thrust adjustment accuracy, and improving the working fluid utilization efficiency and system stability.

[0066] In addition, if Figure 3 As shown, the first guide portion 7641, the second guide portion 7642, the third guide portion 7643, and the fourth guide portion 7644 all include an arcuate guide side wall 7645 connected to the turntable body 7611, and a guide side edge 7646 connected to the arcuate guide side wall 7645; the arcuate guide side wall 7645 and the guide side edge 7646 are arranged to form an arcuate guide groove 7647 connected to the guide nozzle 765.

[0067] The arc-shaped guide side wall 7645 of the present application is connected to the guide side edge 7646, and the arc-shaped guide side wall 7645 and the guide side edge 7646 are surrounded to form an arc-shaped guide groove 7647, so as to ensure that the working fluid can flow along the designed path and be accurately guided when entering from the guide nozzle 765; when the turntable body 7611 rotates, each guide part guides the flow of the working fluid through the arc-shaped guide groove 7647, so that the working fluid is ejected along a predetermined path, and through the guiding effect in different directions, the nozzle assembly 75 is pushed to accurately adjust the injection angle in multiple directions; because the design of each guide part accurately controls the injection direction, the working fluid can be injected efficiently and orderly, avoiding the irregularity of the injection direction, thereby improving the accuracy and stability of the thrust adjustment; the present application has a good fluid guiding effect, can optimize the thrust control, and enhance the directional output of the thrust.

[0068] And, if Figure 5 As shown, the working medium flow guiding assembly 73 includes a flow guiding support seat 731 connected to the valve joint 71, a flow guiding inner shell 732 connected to the flow guiding support seat 731, a flow guiding outer shell 733 connected to the side edge of the flow guiding support seat 731 and sleeved on the outside of the flow guiding inner shell 732, and an end head 734 connected to the ends of the flow guiding inner shell 732 and the flow guiding outer shell 733 respectively; the flow guiding support seat 731, the flow guiding inner shell 732, the flow guiding outer shell 733 and the end head 734 are surrounded to form a working medium flow guiding cavity 735;

[0069] The flow guide support seat 731 is connected to the ends of the flow guide inner shell 732 and the flow guide outer shell 733 respectively, and the terminal 734 is connected to the other ends of the flow guide inner shell 732 and the flow guide outer shell 733 respectively.

[0070] The working fluid of the present application enters through the flow guide support seat 731 connected to the valve joint 71, and the flow guide support seat 731 guides the working fluid into the working fluid guide cavity 735 between the flow guide inner shell 732 and the flow guide outer shell 733. The setting of the flow guide inner shell 732 and the flow guide outer shell 733 is used to protect and strengthen the working fluid guiding function; the present application effectively reduces the flow resistance, optimizes the guiding path of the working fluid, improves the stability and guiding efficiency of the working fluid flow, and helps to ensure that the working fluid can be evenly distributed and flow to the nozzle assembly 75, thereby improving the thrust output efficiency, fluid guiding accuracy and working stability of the propulsion system.

[0071] Furthermore, if Figure 5As shown, the nozzle assembly 75 includes a nozzle body 751 connected to the guide outer shell 733, and a vibration component 752 sleeved on the periphery of the nozzle body 751; the nozzle body 751 is provided with a working medium guide groove 753, a conical injection hole 754, and a working medium outlet hole 755 provided between the working medium guide groove 753 and the conical injection hole 754 and used to connect the working medium guide groove 753 and the conical injection hole 754;

[0072] The guide support seat 731 is provided with a first guide hole 756 for connecting the valve joint 71 and the working medium guide cavity 735, and the end head 734 is provided with a second guide hole 757 for connecting the working medium guide cavity 735 and the working medium guide groove 753; the open end of the conical injection hole 754 is used to align with the guide injection hole 765.

[0073] The working fluid of the present application enters the working fluid guide cavity 735 through the first guide flow hole 756 on the guide support seat 731, and flows into the working fluid guide groove 753 through the second guide flow hole 757 on the end head 734, and then enters the conical injection hole 754 from the working fluid outlet hole 755, and is ejected from the conical injection hole 754; the open end of the conical injection hole 754 is aligned with the guide injection hole 765 to ensure that the working fluid is ejected along a predetermined direction; the vibration component 752 sleeved on the periphery of the nozzle body 751 may further adjust the working fluid flow and injection effect during the injection process through vibration; the present application effectively guides the working fluid flow through the precise layout of the first guide flow hole 756, the second guide flow hole 757, the working fluid guide groove 753 and the conical injection hole 754, ensures the stable injection of the working fluid, and improves the directionality and efficiency of the thrust output through the design of the conical injection hole 754;

[0074] The vibrating component 752 is preferably a vibrator.

[0075] Furthermore, if Figure 5 As shown, the guide support seat 731 is provided with a heating limit groove 7311, the guide inner shell 732 is provided with a heating cavity 7312 connected with the heating limit groove 7311, and the heating component 72 is inserted into the heating cavity 7312;

[0076] The heating component 72 includes a heating bracket 721 with one end inserted into the heating limit groove 7311 and the other end connected to the end 734, a heating wire guide pipe 722 inserted into the guide support seat 731 and the insulation component 74 and used to connect the heating limit groove 7311 with the external space, and a heating wire component 723 wound on the heating bracket 721 and used to extend from the heating wire guide pipe 722 to the external space.

[0077] One end of the heating bracket 721 of the present application is inserted into the heating limit groove 7311 on the guide support seat 731, and the other end is connected to the end 734, so that the heating bracket 721 is fixed in the guide inner shell 732; the connection between the heating limit groove 7311 and the heating cavity 7312 provides installation and positioning space for the heating component 72; the heating wire guide pipe 722 is inserted between the guide support seat 731 and the insulation component 74 as a channel connecting the heating limit groove 7311 and the external space to guide the heating wire component 723; the heating wire component 723 is wound around the heating bracket 721 The heating wire component 723 extends from the heating wire guide pipe 722 to the external space; when the heating wire component 723 is energized, it can generate heat, transfer the heat to the heating bracket 721 through the heating cavity 7312, and then transfer the heat to the guide support seat 731 and the working fluid guide cavity 735 through the heating bracket 721, thereby heating the working fluid flowing through, increasing the temperature of the working fluid, and ensuring the performance optimization of the working fluid during the propulsion process; the present application not only improves the heating efficiency through the precise design of the heat conduction path, but also avoids the influence of excessive heating on other components of the system, thereby ensuring the stability of the heating process and the uniform heating of the working fluid.

[0078] Specifically, Figure 5 As shown, the heating bracket 721 includes a bracket body 7211, a first limiting flange 7212 connected to one end of the bracket body 7211 and inserted into the heating limiting groove 7311, and a second limiting flange 7213 connected to the other end of the bracket body 7211 and inserted into the end 734;

[0079] The bracket body 7211 is provided with a spiral limiting groove 7214 which is sleeved on the outer wall of the bracket body 7211, a heating wire guide through hole 7215 which is arranged at the middle position of the bracket body 7211 and along the length direction of the bracket body 7211, and a heating connecting hole 7216 which is arranged at the lower end of the bracket body 7211 and is used to connect the spiral limiting groove 7214 and the heating wire guide through hole 7215; the upper port of the heating wire guide through hole 7215 is connected to the heating wire guide pipe 722.

[0080] The first limiting convex edge 7212 of the present application is inserted into the heating limiting groove 7311, and the second limiting convex edge 7213 is inserted into the end head 734 to ensure the fixation and stability of the heating bracket 721; a spiral limiting groove 7214 is provided on the outer wall of the bracket body 7211, and the spiral limiting groove 7214 cooperates with the heating wire guide through hole 7215 to limit the movement of the heating wire guide pipe 722 on the bracket body 7211; the heating wire guide through hole 7215 is located in the middle position of the bracket body 7211 and is arranged along the length direction of the bracket body 7211 to guide the installation of the heating wire component 723; a heating connecting hole 7216 is provided at the lower end of the bracket body 7211 to connect the spiral limiting groove 7214 and the heating wire guide through hole 72 15, ensure that the heating wire component 723 can pass smoothly through the heating wire guide through hole 7215, and is connected to the external space through the heating wire guide pipe 722; the upper port of the heating wire guide pipe 722 is connected to the heating wire guide through hole 7215, ensuring that the heating wire component 723 can effectively guide the path of the working medium and heat it evenly; the present application effectively stabilizes and controls the working position of the heating wire through precise limiting and guiding structures, avoids uneven heat and overheating, and improves the heating efficiency of the working medium; the overall structure optimizes the layout of the heating wire and the heat conduction path, ensures a stable heating process, improves the thermal control capability of the system, and has the beneficial effects of enhancing heating efficiency, ensuring thermal stability, and optimizing the heating effect of the working medium.

[0081] More specifically, if Figure 6 As shown, the heat insulation assembly 74 includes a heat dissipation guide shell 741 connected to the guide support seat 731 and sleeved on the outside of the guide shell 733, a connecting support column 742 connected to the device base 1, and a heat dissipation support plate 743 connected to the connecting support column 742 and sleeved on the outer wall of the heat dissipation guide shell 741, and the heat dissipation support plate 743 is provided with heat dissipation holes 744 arranged in an array; the guide shell 733 and the heat dissipation guide shell 741 are surrounded to form a heat insulation channel 745.

[0082] The heat insulation component 74 of the present application forms an effective thermal isolation and heat dissipation path through the cooperation of the heat dissipation guide shell 741, the connecting support column 742 and the heat dissipation support plate 743; the heat dissipation guide shell 741 is connected to the guide support seat 731 and is sleeved on the outside of the guide shell 733 to play a protective role and help guide heat to flow through the external heat dissipation channel; the connecting support column 742 connects the heat dissipation support plate 743 to the device base 1, the heat dissipation support plate 743 is sleeved on the outer side wall of the heat dissipation guide shell 741, and the heat dissipation support plate 743 is provided with heat dissipation through holes 744 arranged in an array, which can provide A channel for heat dissipation; the guide shell 733 and the heat dissipation guide shell 741 are arranged to form an insulating channel 745, which is used to block the heat transfer between the inside and the outside, ensure the stability of the internal temperature of the system and prevent overheating; the present application effectively guides the heat to the heat dissipation support plate 743 and accelerates the heat dissipation process through the heat dissipation holes 744, thereby avoiding the concentration of heat on key components; the present application improves the thermal isolation capability of the device, optimizes the heat dissipation, prevents the heating component 72 from overheating and ensures the stable heating of the working fluid, and has the beneficial effects of enhancing the heat dissipation capability, improving the thermal stability and protecting the system from overheating damage.

[0083] Furthermore, if Figure 7 As shown, a cubic satellite resistance propulsion method includes a cubic satellite resistance propulsion device, and further includes the following steps:

[0084] S1: the first solenoid valve mechanism 4 and the second solenoid valve mechanism 5 are closed, the heating component 72 is started and preheats the working medium guide component 73;

[0085] S2: the first solenoid valve mechanism 4 and the second solenoid valve mechanism 5 are opened, the working medium flows out of the tank 2 and passes through the first solenoid valve mechanism 4, the working medium conduit 6 and the second solenoid valve mechanism 5 in sequence;

[0086] S3: the working fluid flows from the second solenoid valve mechanism 5 into the valve connector 71 on the thruster mechanism 7 and into the working fluid guide assembly 73;

[0087] S4: The heating assembly 72 heats the working medium in the working medium guide assembly 73 and vaporizes the working medium, and the vaporized working medium is ejected from the nozzle assembly 75 and generates thrust;

[0088] S5: The thrust direction adjustment assembly 76 rotates and adjusts the direction in which the vaporized medium on the nozzle assembly 75 is ejected.

[0089] In the present application, when the first solenoid valve mechanism 4 and the second solenoid valve mechanism 5 are in the closed state, the heating component 72 is started to preheat the working fluid flow guide component 73 to ensure that the working fluid can flow smoothly in the subsequent stage and is ready for heating; when the first solenoid valve mechanism 4 and the second solenoid valve mechanism 5 are opened, the working fluid flows out of the tank 2, passes through the first solenoid valve mechanism 4, the working fluid conduit 6 and the second solenoid valve mechanism 5, ensuring that the working fluid enters the subsequent propulsion system; the working fluid flows into the valve joint 71 on the thruster mechanism 7 through the second solenoid valve mechanism 5, and enters the working fluid flow guide component 73 to prepare for the heating process; the heating component 72 heats the working fluid in the working fluid flow guide component 73 to promote the vaporization of the working fluid, and the vaporized working fluid The liquid is ejected from the nozzle assembly 75 to generate thrust, which drives the cube satellite to move; the thrust direction adjustment assembly 76 rotates, and by adjusting the direction of the nozzle assembly 75, the direction of the vaporized medium ejection is changed, and the direction of the thrust is further accurately adjusted; the present application ensures that the medium can efficiently flow, vaporize and be ejected through the nozzle assembly 75 to achieve stable thrust output by accurately controlling the working process of the solenoid valve and the heating assembly 72; the precise adjustment of the thrust direction adjustment assembly 76 ensures the flexibility and efficiency of the propulsion direction, and can meet the needs of the cube satellite in complex orbit control; it not only improves the propulsion efficiency, enhances the reliability and accuracy of the system, but also improves the flexibility of thrust control and the efficiency of thrust generation.

[0090] The implementation principle of a cubic satellite resistance propulsion device and method in the embodiment of the present application is:

[0091] A cubic satellite resistance propulsion device, wherein a tank 2 is used to store a working fluid, the working fluid flows out through a first solenoid valve mechanism 4, and flows into a thruster mechanism 7 through a working fluid conduit 6 and a second solenoid valve mechanism 5; in the thruster mechanism 7, the working fluid enters a working fluid guide assembly 73 through a valve joint 71, a heating assembly 72 heats the working fluid in the working fluid guide assembly 73, and the working fluid is vaporized after heating and ejected from a nozzle assembly 75 to generate thrust; a thrust direction adjustment assembly 76 adjusts the direction of the vaporized fluid ejected from the nozzle assembly 75 to achieve precise thrust control and attitude adjustment; the present application achieves efficient and adjustable propulsion output by precisely controlling the flow, heating, diversion and injection of the working fluid, and is suitable for orbit control and attitude adjustment of cubic satellites in complex tasks.

[0092] When the turntable body 7611 rotates, the first spray hole 7651, the second spray hole 7652, the third spray hole 7653, the fourth spray hole 7654 and the fifth spray hole 7655 provided on the turntable body 7611 are respectively aligned with the outlet end of the nozzle assembly 75 as outlets for spraying the working medium; the thrust guide component 764 is connected to the turntable body 7611 and is located on the side of the corresponding spray hole, which are the first guide part 7641, the second guide part 7642, the third guide part 7643 and the fourth guide part 7644; the opening direction of the first guide part 7641 is opposite to that of the second guide part 7642, and the opening direction of the third guide part 7643 is opposite to that of the fourth guide part 7644. The opening directions of the first guide part 7641 and the third guide part 7643 are also arranged in opposite directions, and the opening directions of the first guide part 7641 and the third guide part 7643 are arranged at an angle. As the turntable body 7611 rotates, the thrust guide component 764 guides the working fluid to be accurately sprayed through different angles through different opening directions and arrangement angles, thereby adjusting the direction and distribution of the thrust. The fifth spray hole 7655 is used for vertical spraying. The present application uses multi-directional guidance control to enable the nozzle assembly 75 to be flexibly adjusted in multiple directions, thereby improving the directional accuracy and response speed of the thrust, and can meet the requirements of fine orbit control and attitude adjustment in complex tasks, improve the thrust adjustment accuracy, and improve the working fluid utilization efficiency and system stability.

[0093] A cubic satellite resistance propulsion method, when the first solenoid valve mechanism 4 and the second solenoid valve mechanism 5 are in a closed state, the heating component 72 is started to preheat the working fluid guide component 73 to ensure that the working fluid can flow smoothly in the subsequent stage and is ready for heating; when the first solenoid valve mechanism 4 and the second solenoid valve mechanism 5 are opened, the working fluid flows out of the tank 2, passes through the first solenoid valve mechanism 4, the working fluid conduit 6 and the second solenoid valve mechanism 5, and ensures that the working fluid enters the subsequent propulsion system; the working fluid flows into the valve joint 71 on the thruster mechanism 7 through the second solenoid valve mechanism 5, and enters the working fluid guide component 73 to prepare for the heating process; the heating component 72 heats the working fluid in the working fluid guide component 73 to promote the vaporization of the working fluid, and the vapor The vaporized working fluid is ejected from the nozzle assembly 75, generating thrust to drive the cube satellite to move; the thrust direction adjustment assembly 76 rotates, and by adjusting the direction of the nozzle assembly 75, the direction of the vaporized working fluid ejection is changed, and the direction of the thrust is further accurately adjusted; the present application ensures that the working fluid can efficiently flow, vaporize and be ejected through the nozzle assembly 75 to achieve stable thrust output by accurately controlling the working process of the solenoid valve and the heating assembly 72; the precise adjustment of the thrust direction adjustment assembly 76 ensures the flexibility and efficiency of the propulsion direction, and can meet the needs of the cube satellite in complex orbit control; it not only improves the propulsion efficiency, enhances the reliability and accuracy of the system, but also improves the flexibility of thrust control and the efficiency of thrust generation.

[0094] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A cubic satellite resistance propulsion device, characterized in that: The invention comprises a device base (1), a tank (2) connected to the device base (1) and used for storing a working medium, a pressure sensor (3) connected to the device base (1) and in communication with the tank (2), a first solenoid valve mechanism (4) connected to the device base (1) and in communication with the tank (2), a second solenoid valve mechanism (5) inserted in the middle of the tank (2) and connected to the device base (1), a working medium conduit (6) respectively in communication with the first solenoid valve mechanism (4) and the second solenoid valve mechanism (5), and a thruster mechanism (7) connected to the second solenoid valve mechanism (5); The thruster mechanism (7) comprises a valve joint (71) connected to the second solenoid valve mechanism (5), a heating component (72) connected to the valve joint (71), a working fluid guide component (73) connected to the valve joint (71) and sleeved on the outside of the heating component (72), a heat insulation component (74) sleeved on the outside of the working fluid guide component (73), a nozzle component (75) connected to the outlet end of the working fluid guide component (73), and a thrust direction adjustment component (76) connected to the nozzle component (75); The thrust direction adjustment component (76) comprises a direction adjustment rotating disk (761) rotatably connected to the nozzle component (75), a rotating guide component (762) connected to the nozzle component (75) and sleeved on the circumference of the direction adjustment rotating disk (761), a direction adjustment driving component (763) connected to the nozzle component (75) and used for driving the direction adjustment rotating disk (761) to rotate, and a thrust guide component (764) connected to the direction adjustment rotating disk (761); the direction adjustment rotating disk (761) is provided with a guide spray hole (765) corresponding to the outlet end of the nozzle component (75), and the thrust guide component (764) is located on one side of the guide spray hole (765) for guiding the ejection of the working fluid.

2. A cubic satellite resistance propulsion device according to claim 1, characterized in that: The direction-adjusting rotating disk (761) comprises a rotating disk body (7611) rotatably connected to the nozzle assembly (75), and an annular rack (7612) sleeved on the circumference of the rotating disk body (7611); The direction adjustment driving component (763) comprises a rotation driving portion (7631) fixedly connected to the nozzle assembly (75), and a driving gear (7632) provided at the output end of the rotation driving portion (7631) and meshingly matched with the annular rack (7612).

3. A cubic satellite resistance propulsion device according to claim 2, characterized in that: The turntable body (7611) is provided with an annular guide groove (7613) which is sleeved on the circumference of the turntable body (7611) and located on one side of the annular rack (7612); the rotating guide component (762) includes an annular sleeve (7621) fixedly connected to the nozzle assembly (75), and an annular guide protrusion (7622) connected to the side edge of the annular sleeve (7621) and movably inserted into the annular guide groove (7613).

4. The cubic satellite resistance propulsion device according to claim 2, characterized in that: The guide spray holes (765) include a first spray hole (7651), a second spray hole (7652), a third spray hole (7653), a fourth spray hole (7654), and a fifth spray hole (7655) arranged in an array along the circumference of the turntable body (7611); The thrust guide component (764) includes a first guide portion (7641) connected to the turntable body (7611) and located on the side of the first spray hole (7651), a second guide portion (7642) located on the side of the second spray hole (7652), a third guide portion (7643) located on the side of the third spray hole (7653), and a fourth guide portion (7644) located on the side of the fourth spray hole (7654); an opening direction of the first guide portion (7641) is opposite to an opening direction of the second guide portion (7642), an opening direction of the third guide portion (7643) is opposite to an opening direction of the fourth guide portion (7644), and an opening direction of the first guide portion (7641) is arranged at an angle to an opening direction of the third guide portion (7643).

5. The cubic satellite resistance propulsion device according to claim 4, characterized in that: The first guide portion (7641), the second guide portion (7642), the third guide portion (7643), and the fourth guide portion (7644) all include an arc-shaped guide side wall (7645) connected to the turntable body (7611), and a guide side edge (7646) connected to the arc-shaped guide side wall (7645); the arc-shaped guide side wall (7645) and the guide side edge (7646) are arranged to form an arc-shaped guide groove (7647) connected to the guide nozzle (765).

6. The cubic satellite resistance propulsion device according to claim 5, characterized in that: The working medium flow guiding assembly (73) comprises a flow guiding support seat (731) connected to the valve joint (71), a flow guiding inner shell (732) connected to the flow guiding support seat (731), a flow guiding outer shell (733) connected to the side edge of the flow guiding support seat (731) and sleeved on the outside of the flow guiding inner shell (732), and an end head (734) respectively connected to the end of the flow guiding inner shell (732) and the end of the flow guiding outer shell (733); the flow guiding support seat (731), the flow guiding inner shell (732), the flow guiding outer shell (733) and the end head (734) are arranged to form a working medium flow guiding cavity (735); The flow guide support seat (731) is respectively connected to the ends of the flow guide inner shell (732) and the flow guide outer shell (733), and the end head (734) is respectively connected to the other ends of the flow guide inner shell (732) and the flow guide outer shell (733).

7. The cubic satellite resistance propulsion device according to claim 6, characterized in that: The nozzle assembly (75) comprises a nozzle body (751) connected to the flow guide outer shell (733), and a vibrating component (752) sleeved on the circumference of the nozzle body (751); the nozzle body (751) is provided with a working medium flow guide groove (753), a conical injection hole (754), and a working medium outlet hole (755) provided between the working medium flow guide groove (753) and the conical injection hole (754) and used for connecting the working medium flow guide groove (753) and the conical injection hole (754); The flow guide support seat (731) is provided with a first flow guide hole (756) for connecting the valve joint (71) and the working medium flow guide chamber (735); the end head (734) is provided with a second flow guide hole (757) for connecting the working medium flow guide chamber (735) and the working medium flow guide groove (753); the opening end of the conical injection hole (754) is used to align with the guide injection hole (765).

8. The cubic satellite resistance propulsion device according to claim 6, characterized in that: The flow guide support seat (731) is provided with a heating limit groove (7311), the flow guide inner shell (732) is provided with a heating cavity (7312) connected to the heating limit groove (7311), and the heating component (72) is inserted into the heating cavity (7312); The heating component (72) includes a heating bracket (721) having one end inserted into the heating limit groove (7311) and the other end connected to the end head (734), a heating wire guide pipe (722) inserted into the flow guide support seat (731) and the heat insulation component (74) and used to connect the heating limit groove (7311) with the external space, and a heating wire component (723) wound on the heating bracket (721) and used to extend from the heating wire guide pipe (722) to the external space.

9. A cubic satellite resistance propulsion method, characterized in that: A cubic satellite resistance propulsion device comprising any one of claims 1 to 8, further comprising the following steps: S1: the first solenoid valve mechanism (4) and the second solenoid valve mechanism (5) are closed, the heating component (72) is started and preheats the working fluid guiding component (73); S2: the first solenoid valve mechanism (4) and the second solenoid valve mechanism (5) are opened, and the working medium flows out of the tank (2) and passes through the first solenoid valve mechanism (4), the working medium conduit (6) and the second solenoid valve mechanism (5) in sequence; S3: the working fluid flows from the second solenoid valve mechanism (5) into the valve joint (71) on the thruster mechanism (7), and then flows into the working fluid flow guide assembly (73); S4: the heating component (72) heats the working fluid in the working fluid guide component (73) and vaporizes the working fluid, and the vaporized working fluid is ejected from the nozzle component (75) and generates thrust; S5: The thrust direction adjustment assembly (76) rotates and adjusts the direction in which the vaporized medium on the nozzle assembly (75) is ejected.

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