Space propulsor, space vehicle

Abstract

The application relates to a space propeller, which comprises a load bin, a force bearing component connected with the load bin, a solar panel assembly connected with the force bearing component, an extension mechanism connected with the force bearing component, the extension mechanism being capable of extending and retracting relative to the force bearing component, a folding mechanism connected with the extension mechanism, the folding mechanism being capable of unfolding or folding along with the extension mechanism, an asymmetric capacitor arranged on the folding mechanism, a controller for controlling the extension mechanism to extend and retract relative to the force bearing component, and a power supply, wherein the solar panel assembly, the asymmetric capacitor and the controller are electrically connected with the power supply. The application also relates to a space vehicle. The application is characterized in that a structure corresponding to the Biefeld-Brown effect is arranged on the folding mechanism, the folding mechanism is unfolded or folded along with the extension mechanism, and thus the space propeller is capable of multi-form and multi-thrust adjustment, belonging to the field of Biefeld-Brown effect application equipment.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of Biefeld-Brown effect application device, in particular to a space thruster and a space vehicle. BACKGROUND

[0002] Biefeld-Brown effect refers to a phenomenon that when high voltage is applied to asymmetric electrode, a force is generated to move the device.

[0003] At present, most of the devices applying Biefeld-Brown effect are similar to "hovering machine", which mainly uses Biefeld-Brown effect to generate thrust to push the device by placing asymmetric capacitor structure up and down.

[0004] There are many factors affecting the size of the thrust generated by Biefeld-Brown effect, among which the voltage applied to the two ends of the asymmetric capacitor structure is the main factor. In addition to the voltage provided by the power supply, the interference of external electric field will change the voltage at the two ends of the asymmetric capacitor structure, thereby changing the size of the thrust. However, the existing Biefeld-Brown effect thruster cannot be disassembled after assembly, and the structure is fixed, so the structure cannot be adjusted to adjust the size of the thrust. SUMMARY

[0005] In view of the technical problems existing in the prior art, the purpose of the present application is to provide a space thruster, which solves the problem that the existing B-B effect thruster has a fixed structure and cannot adjust the structure to adjust the size of the thrust.

[0006] Another purpose of the present application is to provide a space vehicle which can adjust the overall structure to adjust the size of the thrust as needed.

[0007] In order to achieve the above purpose, the present application adopts the following technical scheme:

[0008] A space thruster comprises:

[0009] A load bin;

[0010] A load-bearing member connected with the load bin;

[0011] A solar panel assembly connected with the load-bearing member;

[0012] A telescopic mechanism connected with the load-bearing member, the telescopic mechanism being capable of telescoping relative to the load-bearing member;

[0013] A folding mechanism connected with the telescopic mechanism, the folding mechanism being capable of unfolding or folding action along with the telescoping action of the telescopic mechanism; and an asymmetric capacitor is arranged on the folding mechanism.

[0014] a controller, the controller being configured to control the telescopic mechanism to telescope relative to the load bearing member;

[0015] a power supply, the solar panel assembly, the asymmetric capacitor and the controller being electrically connected to the power supply.

[0016] As a preferred embodiment, the telescopic mechanism comprises a first driving component and a telescopic assembly, the telescopic assembly being connected to the load bearing member, the telescopic assembly being capable of telescoping relative to the load bearing member, the first driving component driving the telescopic assembly to telescope relative to the load bearing member, the first driving component being electrically connected to the power supply and the controller, the folding mechanism being connected to the telescopic assembly.

[0017] As a preferred embodiment, the telescopic assembly comprises a plurality of hollow rods with gradually decreasing cross-sectional areas, the plurality of hollow rods being sequentially connected in a sliding manner according to the cross-sectional areas from large to small; the hollow rod with the largest cross-sectional area is connected to the load bearing member; the output end of the first driving component is connected to a traction member, the outer end of the traction member being fixedly connected to the hollow rod with the smallest cross-sectional area, the first driving component winding or unwinding the traction member to control the telescopic assembly to telescope; a spring is arranged in each hollow rod, the spring being configured to push other hollow rods inserted into the corresponding hollow rod to extend outward; the folding mechanism is connected to any hollow rod capable of telescoping relative to the load bearing member.

[0018] As a preferred embodiment, the space propulsion device further comprises a swinging assembly, the swinging assembly being connected to the load bearing member, the telescopic mechanism being connected to the load bearing member through the swinging assembly, the swinging assembly being configured to drive the telescopic mechanism to swing relative to the load bearing member.

[0019] As a preferred embodiment, the swinging assembly comprises a swinging seat, a rotating shaft and a second driving component, the swinging seat being connected to the load bearing member, the rotating shaft being rotatably connected to the swinging seat, the second driving component driving the rotating shaft to rotate on the swinging seat, the telescopic mechanism being fixedly connected to the rotating shaft.

[0020] As a preferred embodiment, the folding mechanism comprises at least one folding plate assembly, two ends of the folding plate assembly being respectively connected to the movable end and the fixed end of the telescopic mechanism;

[0021] or the number of the telescopic mechanisms is two, the two telescopic mechanisms being connected to the load bearing member, the two telescopic mechanisms forming an included angle on the same plane, the two ends of the folding plate assembly being respectively connected to the movable ends of the two telescopic mechanisms;

[0022] The folding plate assembly is provided with the asymmetric capacitor.

[0023] As a kind of preferred, folding mechanism includes at least three folding plate assemblies, the number of telescopic mechanism is at least three, at least three telescopic mechanism is evenly distributed on load-bearing member, the two ends of each folding plate assembly are connected with the movable end of adjacent two telescopic mechanism respectively, and at least three folding plate assemblies form the thrust structure surrounding the outside of load-bearing member.

[0024] As a kind of preferred, the number of thrust structure is multiple, and multiple thrust structures are distributed outwardly with load-bearing member as center.

[0025] As a kind of preferred, solar panel assembly includes at least two groups of solar panel folding units, at least two groups of solar panel folding units are symmetrically distributed on load-bearing member, and at least two groups of solar panel folding units are electrically connected with power supply.

[0026] Space vehicle, including vehicle body and at least two space thrusters, at least two space thrusters are connected in series or connected in parallel, and vehicle body is connected with load compartment of at least two space thrusters.

[0027] Overall, the present application has the following advantages:

[0028] The space thruster of the present application can realize the adjustment of the overall volume of the space thruster by setting the asymmetric capacitor generating the Biefeld-Brown effect on the folding mechanism and connecting the folding mechanism with the telescopic mechanism, so that the unfolding or folding action can be carried out along with the telescopic action of the telescopic mechanism, so that the space thruster can be adjusted by adjusting the structure of the space thruster, i.e. adjusting the interference degree of electric field between folding mechanisms (folding plate assemblies) to adjust the thrust, realizing multi-form and multi-thrust adjustment of the space thruster. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 The perspective view of the space thruster when the telescopic mechanism and the folding mechanism form a regular hexagon, the telescopic mechanism is in the extended state, and the folding mechanism is in the unfolded state.

[0030] Figure 2 Another perspective view of the space thruster when the telescopic mechanism and the folding mechanism form a regular hexagon, the telescopic mechanism is in the extended state, and the folding mechanism is in the unfolded state.

[0031] Figure 3 The perspective view of the space thruster when the telescopic mechanism and the folding mechanism form a regular hexagon, the telescopic mechanism is in the half-extended state, and the folding mechanism is in the half-unfolded state.

[0032] Figure 4 The top view of the space thruster when the telescopic mechanism and the folding mechanism form a regular hexagon, the telescopic mechanism is in the half-extended state, and the folding mechanism is in the half-unfolded state.

[0033] Figure 5 A perspective view of the telescopic mechanism and the folding mechanism surrounding a regular hexagon.

[0034] Figure 6 A top view of the telescopic mechanism and the folding mechanism surrounding a regular hexagon.

[0035] Figure 7 A schematic view of the telescopic mechanism as a telescopic joint structure and the folding mechanism as a folding plate assembly formed by sequentially hinged multiple plate pieces, when the two ends of the folding plate assembly are fixedly connected with the movable end and the fixed end of the telescopic mechanism.

[0036] Figure 8 A perspective view of the space thruster when the telescopic mechanism and the folding mechanism surround a regular hexagon, the telescopic mechanism is in a contracted state, and the folding mechanism is in a folded state.

[0037] Figure 9 A perspective view of the folding plate assembly.

[0038] Figure 10 A perspective view of the load bin.

[0039] Figure 11 A perspective view of the force-bearing member connected with the solar panel assembly.

[0040] Figure 12 A perspective view of the space thruster when the telescopic mechanism is a telescopic joint structure and the folding mechanism is a folding plate assembly.

[0041] In the figure, 1 is the load bin, 2 is the force-bearing member, 3 is the solar panel assembly, 4 is the telescopic mechanism, 4-1 is a hollow rod piece with the largest cross-sectional area, 4-2 is a hollow rod piece with the second largest cross-sectional area, 4-3 is a hollow rod piece with the smallest cross-sectional area, 5 is the folding mechanism, 5-1 is a plate piece, 6 is a hinge, and 7 is a swing seat. DETAILED DESCRIPTION

[0042] The application will be further described in detail below with reference to the specific embodiments.

[0043] As shown in Figures 1-12 , the space thruster provided by the embodiment includes:

[0044] As shown in Figure 10As shown, the load compartment 1 is a rectangular structure with rounded corners, and the bottom of the rectangular structure is provided with a groove for realizing the assembly connection of the load compartment and the load-bearing member 2. The inside of the rectangular structure is hollowed out into a thin-walled structure to accommodate components required for deep space exploration missions, such as sensors, cameras, etc. for planetary exploration, and also houses an intelligent controller, which is a general controller responsible for overall spacecraft state management. In addition, the load compartment can also be a cylinder, a cube or other structures, as long as the bottom is provided with a groove matched with the load-bearing member 2 and the inside is hollow.

[0045] As shown in Figure 11 , the load-bearing member 2 is connected with the load compartment 1; the load-bearing member 2 is a hollow cylinder (which can also be a hollow structure of other structures, such as a hollow cube), used to bear the load applied by the solar panel assembly 3, the telescopic mechanism 4, the folding mechanism 5 and the load compartment 1, and is the main load-bearing structure of the space thruster. The load-bearing member 2 has a certain wall thickness to ensure its structural strength. The hollow part is used to place components necessary for the normal operation of the satellite, such as on-board computers, power supplies, inverters and motors. The upper half of the load-bearing member 2 is used to install the load compartment 1, the middle part is used to install the solar panel assembly 3, and the lower half is used for the telescopic mechanism 4.

[0046] As shown in Figures 11-12 , the solar panel assembly 3 is connected with the load-bearing member 2; the solar panel assembly 3 can be an existing solar folding panel, such as the sunpower100W solar folding panel of Shenzhen Diyin Energy Technology Co., Ltd. on the market, which will not be described in detail here.

[0047] As shown in Figures 1-8 , 12, the telescopic mechanism 4 is connected with the load-bearing member 2, and the telescopic mechanism 4 can be extended and retracted relative to the load-bearing member 2; the telescopic mechanism 4 can be an existing electric push rod, an electric telescopic rod, a telescopic joint structure, a scissors-type telescopic frame, etc. For example, an electric push rod is used, the fixed end of the electric push rod is connected with the load-bearing member 2, and the movable end of the electric push rod extends outward, and the telescopic mechanism 4 is perpendicular to the load-bearing member 2.

[0048] As shown in Figures 1-9, 12, folding mechanism 5, folding mechanism 5 is connected with telescopic mechanism 4, folding mechanism 5 can be unfolded or folded with the telescopic action of telescopic mechanism 4; Asymmetric capacitor is arranged on folding mechanism 5; Folding mechanism 5 can be a plurality of hinge structure plate 5-1 in series, or can be similar to existing multi-layer folding blackboard, folding display board, folding screen structure, electric folding door, electric folding window structure, etc., its main function is to unfold or fold with the telescopic action of telescopic mechanism 4 when telescopic mechanism 4 telescopes, can refer to the blinds curtain in life, which can be shrunk into a ball after being pulled, and can be unfolded after being pulled; Specific examples are as follows:

[0049] Example 1: telescopic mechanism 4 adopts electric push rod, folding mechanism 5 adopts multi-layer folding plate structure similar to multi-layer folding blackboard structure, its fixed end is fixedly connected with the fixed end of electric push rod, and its movable end is connected with the movable end of electric push rod, and in the telescopic process of electric push rod, the multi-layer folding plate unfolds or folds with the telescopic action.

[0050] As shown in Figure 12 Example 2: the number of electric push rods is two, the two electric push rods are distributed in a fan shape on the same plane, and folding mechanism 5 also adopts multi-layer folding plate structure similar to multi-layer folding blackboard structure, and the two ends thereof are connected with the movable ends of the two electric push rods, respectively, and with the telescopic action of the two electric push rods, the distance between the movable ends of the two electric push rods increases or decreases, so that the multi-layer folding plate structure connected with the movable ends of the two electric push rods unfolds or folds with the telescopic action of the electric push rods.

[0051] As shown in Figures 1-6 Example 3: the number of electric push rods is six, the six electric push rods are uniformly distributed along the circumferential direction of force bearing member 2, and folding mechanism 5 can be composed of six multi-layer folding plate structures, each multi-layer folding plate is connected with the movable ends of two adjacent electric push rods, respectively, and after being connected to the six electric push rods, the six multi-layer folding plates form a regular hexagon and surround the outer periphery of force bearing member 2, and the action of electric push rod and multi-layer folding plate is consistent with that of example 2, which will not be described here, and example 3 can provide full-directional thrust and single-directional thrust (provide different voltages to asymmetric capacitors at different positions, thereby generating different moments on force bearing member 2), and examples 1 and 2 can only provide single-directional thrust.

[0052] The asymmetric capacitor is provided on the folding mechanism 5, and the positive electrode and the negative electrode are respectively arranged at the top and the bottom of the folding mechanism 5. The positive electrode and the negative electrode are asymmetric capacitor structures, and the positive electrode and the negative electrode are asymmetrically arranged at the top and the bottom of the folding mechanism 5. The main function of the asymmetric capacitor is to generate thrust by using the Biefeld-Brown effect, so that the folding mechanism 5 generates thrust. The thrust generated by the folding mechanism 5 is transmitted to the telescopic mechanism 4, and the telescopic mechanism 4 transmits the thrust to the load bearing member 2, and the load bearing member 2 transmits the thrust to the load compartment 1.

[0053] The controller is used to control the telescopic mechanism 4 relative to the load bearing member 2 to telescope. Specifically, the controller controls the telescopic mechanism 4 to telescope by controlling the driving component of the telescopic mechanism 4.

[0054] The power supply, the solar panel assembly 3, the asymmetric capacitor and the controller are electrically connected. Specifically, the solar panel assembly 3 absorbs solar energy and converts it into electrical energy to be stored in the power supply. The power supply supplies power to the asymmetric capacitor and the controller, and the power supply also supplies power to the drive of the telescopic mechanism 4.

[0055] The space thruster of the embodiment utilizes the solar panel assembly 3 to absorb solar energy and convert it into electrical energy to be stored in the power supply. The power supply supplies power to the asymmetric capacitor to generate the Biefeld-Brown effect. The power supply supplies power to the controller to control the telescopic mechanism 4 to telescope. The power supply supplies power to the drive of the telescopic mechanism 4 to telescope according to the command of the controller. The controller controls the telescopic mechanism 4 to drive the folding mechanism 5 to fold or unfold, thereby changing the distance between the different layers of the folding mechanism, adjusting the interference degree of the electric field between the different layers of the folding mechanism (folding plate), adjusting the thrust by adjusting the structure of the space thruster, realizing multi-form and multi-thrust adjustment of the space thruster. At the same time, when the space thruster is not in use, the structure is adjusted to reduce the overall volume, making it easy to store, carry and transport.

[0056] In some embodiments, the telescopic mechanism 4 includes a first driving component and a telescopic assembly. The telescopic assembly is connected to the load bearing member 2 and can telescope relative to the load bearing member 2. The first driving component drives the telescopic assembly to telescope relative to the load bearing member 2. The first driving component is electrically connected to the power supply and the controller. The folding mechanism 5 is connected to the telescopic assembly. For example, the first driving component can be an existing rotary motor, and the telescopic assembly can be an existing telescopic joint structure, a parallelogram linkage mechanism, a gear and rack structure, etc. The following is a simple example of how to apply:

[0057] For example, as shown in FIG. 6, the telescopic mechanism 4 includes a first driving component 41 and a telescopic assembly 42. The telescopic assembly 42 is connected to the load bearing member 2 and can telescope relative to the load bearing member 2. The first driving component 41 drives the telescopic assembly 42 to telescope relative to the load bearing member 2. The first driving component 41 is electrically connected to the power supply and the controller. The folding mechanism 5 is connected to the telescopic assembly 42. Figure 7As shown, Example 1: when the rotating motor is combined with the telescopic joint structure, the outermost end of the telescopic joint can be pulled to achieve contraction by connecting the rotating motor to a traction rope or a traction line, and then a spring is set in the telescopic joint, so that when the rotating motor releases the traction rope, the contracted telescopic joint is ejected by the restoring force of the spring to achieve contraction and extension. One end of the folding mechanism 5 is connected to the fixed end of the telescopic joint, and the other end of the folding mechanism 5 is connected to the movable end of the telescopic joint, so that it can be expanded or folded as the telescopic joint is extended or contracted.

[0058] Example 2: When the rotating motor is combined with the gear rack structure, the output shaft of the rotating motor is connected to the gear, the gear is meshed with the rack, the rack is slidingly connected to the load-bearing component 2, and the rack slides outward and extends or contracts into the load-bearing component 2 as the gear rotates. Both ends of the folding mechanism 5 are connected to the rack, and the folding mechanism 5 unfolds or folds as the rack slides.

[0059] like Figure 2 As shown, Example 3: the number of telescopic joints is two, the number of rotating motors is two, and the connection method of the telescopic joints and the rotating motors is the same as that of Example 1, except that the two telescopic joints are distributed in a fan shape, and the two ends of the folding mechanism 5 are connected to the movable ends of the telescopic joints, so that when the telescopic joints contract, the distance between the movable ends of the telescopic joints increases or decreases, so that the folding mechanism 5 connected to the movable ends of the two telescopic joints expands or folds as the telescopic joints perform a telescopic action.

[0060] Example 4: The number of telescopic joints is six, the number of rotating motors is six, the connection method of the telescopic joints and the rotating motors is the same as that of Example 1, and the connection method of the folding mechanism 5 and the telescopic joints is the same as that of Example 3. Through the telescopic components and folding mechanisms arranged in this way, it is possible to provide omnidirectional thrust and unidirectional thrust (providing different voltages to asymmetric capacitors located at different positions, thereby generating different torques on the load-bearing component 2). Examples 1, 2 and 3 can only provide unidirectional thrust.

[0061] By configuring the telescopic mechanism 4 to be a structure consisting of a first driving component and a telescopic assembly, assembly is convenient, the telescopic effect is good, and the telescopic action is easy to control.

[0062] like Figure 7As shown, in some embodiments, the telescopic assembly includes a plurality of hollow rods with gradually decreasing cross-sectional areas, and the plurality of hollow rods are slidably connected in sequence from large to small in cross-sectional areas; the hollow rod 4-1 with the largest cross-sectional area is connected to the load-bearing member 2; the output end of the first driving component is connected to a traction member, and the outer end of the traction member is fixedly connected to the hollow rod 4-3 with the smallest cross-sectional area, and the first driving component reels in or unfolds the traction member to control the contraction of the telescopic assembly; a spring is provided in each hollow rod, and the spring is used to push the other hollow rods inserted in the corresponding hollow rod to extend outward; the folding mechanism 5 is connected to any hollow rod that can be telescoped relative to the load-bearing member 2.

[0063] like Figure 7 As shown, the telescopic assembly includes three hollow rods with gradually decreasing cross-sectional areas. Of course, the outermost hollow rod can also be a solid rod. The hollow rod 4-2 with the second largest cross-sectional area is inserted into the hollow rod 4-1 with the largest cross-sectional area. The hollow rod 4-2 with the second largest cross-sectional area is fixedly connected to the spring located within the hollow rod 4-1 with the largest cross-sectional area. The hollow rod 4-3 with the smallest cross-sectional area is inserted into the hollow rod 4-2 with the second largest cross-sectional area and fixedly connected to the spring located within the hollow rod 4-2 with the second largest cross-sectional area. The hollow rod 4-1 with the largest cross-sectional area is fixedly connected to the load-bearing member 2. The hollow rod 4-2 with the second largest cross-sectional area can slide within the hollow rod 4-1 with the largest cross-sectional area, and the hollow rod 4-3 with the smallest cross-sectional area can slide within the hollow rod 4-2 with the second largest cross-sectional area. The traction member can be a rope, and the first drive component can be a rotary motor.

[0064] Specific application examples:

[0065] like Figure 12 As shown, when the number of telescopic components is one, one end of the folding mechanism 5 is connected to the hollow rod 4-1 with the largest cross-sectional area, and the other end of the folding mechanism 5 is connected to the hollow rod 4-2 with the second largest cross-sectional area or the hollow rod 4-3 with the smallest cross-sectional area. When the rotating motor retracts the rope so that the hollow rod 4-2 with the second largest cross-sectional area and the hollow rod 4-3 with the smallest cross-sectional area are extended and retracted toward the load-bearing component 2, the other end of the folding mechanism 5 is folded or unfolded as the hollow rod 4-2 with the second largest cross-sectional area or the hollow rod 4-3 with the smallest cross-sectional area are extended and retracted.

[0066] like Figures 1-6As shown, when the number of telescopic assemblies is two, the two telescopic assemblies are distributed in a fan shape on the load-bearing member 2, and the two ends of the folding mechanism 5 are connected with the hollow rod member 4-2 with the second largest cross-sectional area or the hollow rod member 4-3 with the smallest cross-sectional area of the two telescopic assemblies, so as to be folded as the distance between the two telescopic assemblies decreases after contraction, and unfolded as the distance between the two telescopic assemblies increases after extension.

[0067] As shown in Figures 11-12 As shown, when the number of telescopic assemblies is two, the two telescopic assemblies are distributed in a fan shape on the load-bearing member 2, and the two ends of the folding mechanism 5 are connected with the hollow rod member 4-2 with the second largest cross-sectional area or the hollow rod member 4-3 with the smallest cross-sectional area of the two telescopic assemblies, so as to be folded as the distance between the two telescopic assemblies decreases after contraction, and unfolded as the distance between the two telescopic assemblies increases after extension.

[0068] By setting the telescopic assembly as described above, the telescopic assembly has a simple structure, is easy to assemble with the load-bearing member 2, is easy to assemble with the folding mechanism 5, has good telescopic effect, is easy to control the telescopic action, and is also convenient for setting multiple folding mechanisms 5 around the outer periphery of the load-bearing member.

[0069] As shown in Figure 11 As shown, in some embodiments, the spatial thruster further comprises a swinging assembly, the telescopic mechanism 4 is connected with the load-bearing member 2 through the swinging assembly, and the swinging assembly is used to drive the telescopic mechanism 4 to swing relative to the load-bearing member 2. For example, the swinging assembly can be a rotating motor directly driving the telescopic mechanism 4 to swing up and down relative to the load-bearing member 2; or a rotating motor driving a rotating shaft, the rotating shaft driving the telescopic mechanism 4 to swing up and down; or a lever structure is provided, and an electric push rod is used to push one end of the telescopic mechanism 4 to make the other end of the telescopic mechanism 4 swing.

[0070] By setting the swinging assembly, the telescopic mechanism 4 can not only telescope relative to the load-bearing member 2, but also swing relative to the load-bearing member 2, so as to realize more forms and more thrust adjustment of the spatial thruster.

[0071] As shown in Figure 9 As shown, in some embodiments, the swinging assembly comprises a swinging seat 7, a rotating shaft, and a second driving component, the swinging seat 7 is connected with the load-bearing member 2, the rotating shaft is rotationally connected with the swinging seat 7, the second driving component drives the rotating shaft to rotate on the swinging seat 7, and the telescopic mechanism 4 is fixedly connected with the rotating shaft. By setting the swinging assembly in the above structure, the assembly is convenient, the swinging of the telescopic mechanism 4 is easy to control, and the overall structure is simple and reliable.

[0072] In addition, on the basis of the telescopic mechanism, the swinging assembly is provided, so that the folding mechanism provided with the asymmetric capacitor can be adjusted in two directions relative to the load-bearing member, and the space utilization is further improved.

[0073] Specific application example: the swing seat 7 is arranged on the outer surface of the load bearing member 2, the structure of the swing seat 7 can refer to the support of the seesaw in life, two through holes are arranged, the two ends of the rotating shaft are rotatably connected with the through holes, the second driving component can be a rotating motor, the rotating motor drives the rotating shaft to rotate, the telescopic mechanism 4 is fixedly connected with the rotating shaft, by controlling the rotation of the output shaft of the rotating motor, the rotating shaft rotates with the output shaft of the rotating motor, and the telescopic mechanism 4 swings up and down relative to the load bearing member 2 with the rotation of the rotating shaft.

[0074] As shown in Figures 1-9 in some embodiments,

[0075] The folding mechanism 5 comprises at least one folding plate assembly, the two ends of the folding plate assembly are respectively connected with the movable end and the fixed end of the telescopic mechanism 4;

[0076] Or the number of telescopic mechanisms 4 is two, both of which are connected with the load bearing member, and both of which form an included angle (for example, 30-60 degrees) on the same plane (for example, a fan-shaped distribution), and the two ends of the folding plate assembly are respectively connected with the movable ends of the two telescopic mechanisms; the folding plate assembly is provided with an asymmetric capacitor. The folding plate assembly is a known structure, which will not be described here. The embodiment provides a scheme capable of adjusting the single-side thrust of the space thruster. Through the above arrangement, the telescopic mechanism 4 drives the folding plate assembly to unfold or fold, so that the size of the single-side thrust of the space thruster can be adjusted.

[0077] As shown in Figures 1-6 in some embodiments, the folding mechanism comprises at least three folding plate assemblies, the number of telescopic mechanisms 4 is at least three, and the at least three telescopic mechanisms 4 are uniformly distributed on the load bearing member, the two ends of each folding plate assembly are respectively connected with the movable ends of the adjacent two telescopic mechanisms 4, and the at least three folding plate assemblies form a thrust structure surrounding the outer side of the load bearing member 2. Specifically, when the telescopic mechanism is three, the three telescopic mechanisms 4 are uniformly distributed along the circumference of the load bearing member 2, and the thrust structure forms a triangle. By arranging the folding plate assembly into a triangular thrust structure, the space thruster can be provided with thrust in all directions.

[0078] As shown in Figures 1-6 when the number of telescopic mechanisms 4 is six, the number of folding plate assemblies is also six, the six telescopic mechanisms 4 are uniformly distributed on the load bearing mechanism, and the six folding plate assemblies form a regular hexagonal structure. By arranging the folding plate assemblies and telescopic mechanisms 4 in this way, a better adjustment effect can be achieved compared with the arrangement of three telescopic mechanisms 4, for example, the size of the thrust in a more subtle direction can be adjusted.

[0079] As shown in Figures 11-12, 12, in some embodiments, the number of thrust structures is multiple, and the multiple thrust structures are spaced outwardly around the load-bearing member. For example, the number of thrust structures is three, and the three thrust structures form three different sizes of triangles, quadrilaterals, pentagones or hexagones on the outside of the load-bearing member, and the three thrust structures are spaced outwardly around the load-bearing member. Through the folding mechanism 5 thus arranged, the space thruster can apply equal-sized thrusts to the load-bearing member 2 in all directions, and the moments in each direction are counteracted, so that the thrusts are concentrated.

[0080] Of course, the folding mechanism 5 thus arranged can also be adjusted unilaterally. For example, by providing different voltages to different folding plate assemblies, the thrusts applied to the load-bearing member 2 by the annular structure are not equal, so that the load-bearing member 2 generates different control moments, thereby achieving adjustment of different attitudes of the space thruster.

[0081] As shown in FIGS. 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11 and 12, in some embodiments, the number of thrust structures is multiple, and the multiple thrust structures are spaced outwardly around the load-bearing member. For example, the number of thrust structures is three, and the three thrust structures form three different sizes of triangles, quadrilaterals, pentagones or hexagones on the outside of the load-bearing member, and the three thrust structures are spaced outwardly around the load-bearing member. Through the folding mechanism 5 thus arranged, the space thruster can apply equal-sized thrusts to the load-bearing member 2 in all directions, and the moments in each direction are counteracted, so that the thrusts are concentrated. ​ As shown in FIGS. 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11 and 12, in some embodiments, the solar panel assembly 3 includes at least two groups of solar panel folding units, the at least two groups of solar panel folding units are symmetrically distributed on the load-bearing member, and the at least two groups of solar panel folding units are electrically connected to the power supply. The solar panel folding unit is an existing solar folding plate, which will not be described here. Through the energy storage of the solar panel, the space thruster can achieve complete energy self-sufficiency, and can also adjust the energy consumption autonomously by changing the structure, and has the advantages of long service life and long endurance in space. At the same time, since it does not rely on fuel to work, the structural mass is greatly reduced, and there is no problem of space pollution, tail gas flow disturbance, etc.

[0082] The embodiment provides a space vehicle, which includes a vehicle body and at least two space thrusters, the at least two space thrusters are connected in series or in parallel, and the vehicle body is connected to a load compartment of the at least two space thrusters. Specifically, the vehicle body is a structure connecting the load compartment of the plurality of space thrusters, the number of the telescopic mechanisms 4 of the space thrusters is preferably six, and the number of the folding mechanisms 5 is also six (or a multiple of six), and the six telescopic mechanisms 4 are respectively hinged to the six folding mechanisms 5 to form a regular hexagon (if the number of the folding mechanisms 5 is 12 or 18, the folding mechanisms 5 can be divided into six parts each time, and each six folding mechanisms 5 are connected to form a regular hexagon on the telescopic mechanism 4, of course, the size of the folding mechanism 5 needs to be adjusted accordingly, so that the folding mechanism 5 forms different sizes of regular hexagons on the telescopic mechanism 4 at equal intervals).

[0083] When the number of space thrusters is two or more, the series connection mode is that the load-bearing member 2 of a space thruster is connected with the load-bearing member 2 of an adjacent space thruster, for example, the load-bearing members 2 of two cylindrical structures are coaxially connected, and the telescopic mechanism and the folding mechanism of the two space thrusters are distributed in parallel; and the parallel connection mode is that the outermost end of the telescopic mechanism 4 of a space thruster is hingedly connected with the outermost end of the telescopic mechanism 4 of an adjacent space thruster. The series-parallel connection of the space thrusters embodies the modular design idea, and the space thrusters can be diversified combined as basic thrust units, the magnitude and direction of the combined thrust can be changed, and the space thrusters have high extensibility.

[0084] The space vehicle provided by the embodiment can use the folding mechanism 5 provided with the asymmetric capacitor to provide thrust for orbit transfer. First, the controller in the load cabin issues an orbit transfer instruction, the power supply receives the instruction, and checks whether the power supply reaches a predetermined working threshold. If the power is sufficient, the telescopic mechanism 4 and the folding mechanism 5 can be unfolded for propulsion preparation. If the power is insufficient, the solar panel assembly 3 needs to be unfolded and adjusted on the original orbit for charging. The propulsion preparation includes pulse point selection and vehicle attitude adjustment. After the preparation is completed, the telescopic mechanism 4 and the folding mechanism 5 can be completely unfolded for continuous propulsion. In this process, the solar panel assembly 3 also needs to be unfolded to maintain power supply until the space vehicle reaches the predetermined orbit for work. The space vehicle has the characteristics of multiple forms, high flexibility, all-weather work, etc. The space vehicle has a foldable function. The telescopic assembly is controlled by a rotating motor to realize radial telescoping. The telescopic mechanism 4 can also be driven by a rotating motor to swing the assembly to make the telescopic mechanism 4 swing up and down. The folding mechanism 5 is passively compressed and folded due to the length shortening of the telescopic mechanism 4. In this way, the volume is greatly reduced, which is helpful for some specific application scenarios.

[0085] In the above embodiment, the plate 5-1 constituting the folding mechanism 5 is a rectangular flat plate, the top of which is embedded with a copper wire (or a copper rod), and the bottom is welded with a thin-plate structure metal plate. The copper wire and the metal plate form an asymmetric capacitor. The adjacent plate 5-1 can be connected through a hinge 6 to realize the folding and unfolding between the plate 5-1. Meanwhile, the hinge 6 is made of metal and can be used as a power supply element connected with the asymmetric capacitor and the power supply.

[0086] In the above embodiment, the connection between the telescopic mechanism 4 and the folding mechanism 5 can be connected through a spherical hinge. The spherical hinge can be fixedly connected to the telescopic mechanism 4 in advance, for example, the outer surface of each section of the telescopic joint structure.

[0087] In the above embodiment, in order to make the folding mechanism 5 stable during the unfolding and folding actions, a telescopic joint structure can be additionally arranged on the original telescopic joint structure vertical plane, so as to be connected with the top and bottom of the folding mechanism 5, so that the stress of the folding mechanism 5 is stable, thereby making the folding mechanism 5 stable during the unfolding and folding actions.

[0088] The space thruster of the above embodiment realizes overall volume compression by arranging the telescopic mechanism 4 and the folding mechanism 5, so that the volume occupation can be reduced when not working, and the space thruster can be unfolded to the normal state when working.

[0089] The above embodiment is the preferred embodiment of the present application, but the embodiments of the present application are not limited to the above embodiment, and any changes, modifications, substitutions, combinations, simplifications made without departing from the spirit and principles of the present application shall be equivalent replacement methods, and all shall be included in the protection scope of the present application.

Claims

1. A space propulsion device, characterized in that: include: payload compartment; A load-bearing member connected to the load compartment; A solar panel assembly, wherein the solar panel assembly is connected to a load-bearing member; A telescopic mechanism, the telescopic mechanism is connected to the load-bearing member and can be telescoped relative to the load-bearing member; A folding mechanism is connected to the telescopic mechanism, and the folding mechanism can be unfolded or folded along with the telescopic movement of the telescopic mechanism; an asymmetric capacitor is provided on the folding mechanism; A controller, the controller is used to control the telescopic mechanism to extend and retract relative to the load-bearing member; The power supply, the solar panel assembly, the asymmetric capacitor and the controller are all electrically connected to the power supply; The folding mechanism includes at least one folding plate assembly, and there are two telescopic mechanisms. The two ends of each folding plate assembly are respectively connected to the movable end and fixed end of the corresponding telescopic mechanism; the two telescopic mechanisms are both connected to the load-bearing member, and the two telescopic mechanisms form an angle on the same plane. The two ends of the folding plate assembly are respectively connected to the movable ends of the two telescopic mechanisms; The folding plate assembly is provided with an asymmetric capacitor; or, The folding mechanism includes at least three folding plate assemblies, the number of telescopic mechanisms is at least three, and the at least three telescopic mechanisms are evenly distributed on the load-bearing member. The two ends of each folding plate assembly are respectively connected to the movable ends of two adjacent telescopic mechanisms. The at least three folding plate assemblies form a thrust structure surrounding the outside of the load-bearing member. There are multiple thrust structures, and the multiple thrust structures are distributed outwards with the load-bearing component as the center.

2. The space propulsion device according to claim 1, characterized in that: The telescopic mechanism includes a first driving component and a telescopic assembly. The telescopic assembly is connected to the load-bearing component. The telescopic assembly can be telescoped relative to the load-bearing component. The first driving component drives the telescopic assembly to telescope relative to the load-bearing component. The first driving component is electrically connected to the power supply, the first driving component is electrically connected to the controller, and the folding mechanism is connected to the telescopic assembly.

3. The space propulsion device according to claim 2, characterized in that: The telescopic assembly includes a plurality of hollow rods with gradually decreasing cross-sectional areas, wherein the plurality of hollow rods are slidingly connected in sequence from large to small cross-sectional areas; the hollow rod with the largest cross-sectional area is connected to the load-bearing member; The output end of the first driving component is connected to a traction member, the outer end of which is fixedly connected to the hollow rod with the smallest cross-sectional area. The first driving component reels or unfolds the traction member to control the contraction of the telescopic assembly. Each hollow rod is provided with a spring, which is used to push the other hollow rods inserted into the corresponding hollow rod to extend outwards; The folding mechanism is connected to any hollow rod that can be telescoped relative to the load-bearing component.

4. The space propulsion device according to claim 1, characterized in that: It also includes a swing component, which is connected to the load-bearing component. The telescopic mechanism is connected to the load-bearing component through the swing component. The swing component is used to drive the telescopic mechanism to swing relative to the load-bearing component.

5. The space propulsion device according to claim 4, characterized in that: The swing assembly includes a swing seat, a rotating shaft and a second driving component. The swing seat is connected to the load-bearing component, the rotating shaft is rotatably connected to the swing seat, the second driving component drives the rotating shaft to rotate on the swing seat, and the telescopic mechanism is fixedly connected to the rotating shaft.

6. The space propulsion device according to claim 1, characterized in that: The solar panel assembly includes at least two groups of solar panel folding units, which are symmetrically distributed on the load-bearing component and are both electrically connected to a power source.

7. A space vehicle, characterized in that: The invention comprises an aircraft body and at least two space thrusters according to any one of claims 1 to 6, wherein the at least two space thrusters are connected in series or in parallel, and the aircraft body is connected to the payload compartments of the at least two space thrusters.

Images