A regenerative powder-based space projectile propulsion device and method of use thereof

Abstract

This invention relates to the field of aerospace technology and discloses a space projectile propulsion device based on regenerated powder and its application method. The space projectile propulsion device includes a powder box, a projectile assembly, and a timing switch. The powder box has a powder outlet. The drive structure of the projectile assembly drives a cantilever to rotate. The first end of the powder delivery pipe inside the cantilever is located near the rotation center of the cantilever, and the second end of the powder delivery pipe is located at the end of the cantilever away from the rotation center. The timing switch is located at the powder outlet. In the open state, the timing switch opens the powder outlet, which is connected to the powder delivery pipe. In the closed state, the timing switch closes the powder outlet. This invention achieves precise powder delivery and centrifugal acceleration projectile propulsion at a fixed phase through phase coordination between the timing switch and the powder delivery pipe inside the rotating cantilever. This allows for stable control of the thrust direction and solves the problems of uncontrollable projectile direction and the inability of spacecraft to move stably along a predetermined orientation.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to a space projectile propulsion device based on regenerated powder and its application method. Background Technology

[0002] With the rapid development of missions such as long-term space stays, orbital maneuvers, and deep space exploration (e.g., lunar base construction and Mars sample return), the demand for propellants in spacecraft is growing rapidly. Traditional space engines rely on carrying propellants from Earth, leading to a surge in launch costs. Transporting propellants from the ground into GEO orbit is expensive and limited by launch capacity, making it difficult to support long-distance, long-duration missions.

[0003] In-situ resource utilization (ISRU) technology is considered a key breakthrough, as it extracts resources from target celestial bodies to synthesize propellants, significantly reducing the dependence of extraterrestrial missions on Earth resupply. This technology involves collecting and ejecting materials from the aerospace environment, controlling the recoil of the ejected material for flight. However, this technology suffers from the inability to stably control the thrust direction during material ejection, causing the spacecraft to malfunction and fail to maintain stable movement towards its intended location. Summary of the Invention

[0004] This invention provides a space projectile propulsion device based on regenerated powder and its application method to solve the problem of unstable thrust direction control, which causes the aircraft to be unable to move stably in a predetermined direction.

[0005] In a first aspect, the present invention provides a space projectile propulsion device based on recycled powder, comprising a powder box, a projectile assembly, and a timing switch; the powder box has a powder outlet and contains powder; the projectile assembly includes a cantilever and a drive structure, the drive structure drives the cantilever to rotate, a powder feeding pipe is disposed within the cantilever, a first end of the powder feeding pipe is located near the rotation center of the cantilever and is adapted to communicate with the powder outlet, and a second end of the powder feeding pipe is located at the end of the cantilever away from the rotation center and is adapted to communicate with the external environment; the timing switch is disposed at the powder outlet; the timing switch has an open state and a closed state, in which the timing switch opens the powder outlet and the powder outlet communicates with the powder feeding pipe; in the closed state, the timing switch closes the powder outlet.

[0006] Beneficial effects: By coordinating the phase between the fixed-cycle switch and the powder delivery pipe inside the rotating cantilever, the powder can be precisely delivered and centrifugally accelerated at a fixed phase, which can stably control the thrust direction and solve the problems of uncontrollable ejection direction and the inability of spacecraft to move stably along a predetermined orientation in related technologies; the powder particles are fine and uniformly dispersed, and the powder can form a uniform stream, which is directionally ejected according to a predetermined phase and angle, with strong directional consistency, less wear on the inner wall of the powder delivery pipe, and improved overall service life.

[0007] In one optional implementation, in the open state, the first end of the powder feeding pipe is rotated to the powder outlet, the time-lapse switch is turned on, and the powder outlet is connected to the powder feeding pipe; in the closed state, the first end of the powder feeding pipe is misaligned with the powder outlet, and the time-lapse switch is turned off.

[0008] Beneficial effects: By judging the positional relationship between the powder feeding pipe and the powder outlet, the state of the fixed-cycle switch is switched to achieve precise powder delivery, prevent powder waste, and prevent powder from falling outside the powder feeding pipe.

[0009] In one alternative embodiment, the space projectile propulsion device based on recycled powder further includes a control component electrically connected to the time-lapse switch and electrically connected to the drive structure.

[0010] Beneficial effects: The control components are electrically connected to the timing switch and drive structure to achieve automated and coordinated control of powder feeding phase, cantilever speed and ejection timing. The thrust magnitude and direction can be adjusted to ensure stable output and reliable operation of the propulsion system, meeting the needs of complex space orbital maneuvers and attitude adjustment.

[0011] In one optional embodiment, the powder box has a conveying unit adapted to transport the powder to the powder outlet, and the control component is electrically connected to the conveying unit and adapted to control the conveying speed of the conveying unit.

[0012] Beneficial effects: The control components can continuously and precisely adjust the conveying speed of the conveying unit, thereby accurately controlling the powder supply flow rate and realizing linear and fine control of the thrust. This can meet the needs of fine attitude adjustment with small thrust, and can also provide large thrust to complete tasks such as orbit transfer and trajectory avoidance, greatly improving the mission adaptability of the propulsion system.

[0013] In one optional embodiment, the speed at which the powder travels from the first end of the powder feeding pipe to the second end of the powder feeding pipe is: The radial velocity of the powder from the first end of the powder feeding pipe to the second end of the powder feeding pipe is: The tangential velocity of the powder from the first end of the powder feeding pipe to the second end of the powder feeding pipe is The time required for the powder to travel from the first end of the powder feeding pipe to the second end of the powder feeding pipe is t, and the angle through which the cantilever rotates when the powder travels from the first end of the powder feeding pipe to the second end of the powder feeding pipe is θ, satisfying the following expression: ; ; ; ; ; The coefficient of friction of the inner wall of the powder feeding pipe is μ. R1 is the distance between the first end of the powder feeding pipe and the rotation center of the cantilever, R2 is the distance between the second end of the powder feeding pipe and the rotation center of the cantilever, and ω is the rotational angular velocity of the cantilever.

[0014] Beneficial effects: By establishing quantitative expressions for powder radial velocity, motion time and cantilever rotation angle, theoretical calculation, parameter optimization and precise design of centrifugal projectile propulsion process can be realized. This provides a reliable basis for determining key parameters such as cantilever structure size, rotational angular velocity and powder feeding position, ensuring high stability of powder ejection velocity, thrust output and directional control, and improving the engineering feasibility of the system.

[0015] In one alternative embodiment, the coefficient of friction μ of the inner wall of the powder feeding pipe is ≤0.1.

[0016] Beneficial effects: Limiting the friction coefficient of the inner wall of the powder delivery pipe to μ≤0.1 significantly reduces the movement resistance and energy loss of powder in the flow channel, improves centrifugal acceleration efficiency and powder terminal ejection speed, ensures the energy utilization rate and thrust output efficiency of the propulsion system, and at the same time reduces pipe wall wear and extends the on-orbit service life of the device.

[0017] In one optional embodiment, multiple cantilever arms are provided, each of which is connected to the drive structure in a transmission manner, and the multiple cantilever arms are evenly spaced around the rotation center.

[0018] Beneficial effects: Multiple cantilever arms are evenly arranged around the rotation center, which can form a multi-channel synchronous powder feeding and multi-point synchronous projectile structure, improve the total thrust output and thrust continuity, make the device more balanced in force and less vibrate when rotating at high speed, and enhance the operational stability and structural safety, making it suitable for high-load and long-cycle space propulsion tasks.

[0019] In one optional embodiment, a plurality of cantilever arms form a cantilever group, and two cantilever groups are provided. The two cantilever groups are spaced apart and coaxially arranged. The two cantilever groups rotate in opposite directions and at the same speed. There are two powder outlets, and the two powder outlets are arranged in a one-to-one correspondence with the two cantilever groups.

[0020] Beneficial effects: By setting up two cantilever groups with opposite rotation directions and coaxiality, the additional torque generated when a single rotating arm group rotates at high speed is eliminated, thereby improving the rotational stability of the projectile assembly.

[0021] In one alternative embodiment, the powder outlet is adjustable on the powder box about the rotation center of the drive structure.

[0022] Beneficial effects: By adjusting the phase of the powder outlet and the rotation speed of the drive structure, the powder ejection speed and thrust can be adjusted.

[0023] Secondly, the present invention also provides an application method for a space projectile propulsion device, applied to the aforementioned space projectile propulsion device based on recycled powder, comprising the following steps: Step S1, conveying the powder in the powder box to the powder outlet; Step S2, the driving structure drives the cantilever to rotate, causing the first end of the powder delivery pipe to rotate to the powder outlet, the fixed-cycle switch is turned on, and the powder is conveyed from the powder box to the powder delivery pipe; Step S3, the driving structure continues to drive the cantilever to rotate, the first end of the powder delivery pipe is misaligned with the powder outlet, the fixed-cycle switch is turned off, and the powder moves from the first end to the second end along the powder delivery pipe under the action of centrifugal acceleration; Step S4, the powder moves to the second end of the powder delivery pipe and is ejected outward to generate propulsion power; Step S5, repeating the above steps to continuously provide thrust to the space projectile propulsion device.

[0024] Beneficial effects: This method enables the on-site utilization of space resources through a closed-loop process of fixed-beat powder delivery, centrifugal acceleration, and directional ejection. At the same time, it can stably control the magnitude and direction of thrust, making it suitable for various scenarios such as lunar base construction, Mars exploration, asteroid development, disposal of failed spacecraft, and long-term orbital stays. It significantly improves the autonomy, economy, and sustainability of deep space missions. Attached Figure Description

[0025] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the structure when the powder enters the powder feeding pipe and when the powder is blasted, according to an embodiment of the present invention. Figure 2 This is a schematic diagram of the structure when the first end of the powder feeding pipe is misaligned with the powder outlet in an embodiment of the present invention; Figure 3 This is a schematic diagram of the integrally formed cantilever and connector structure according to an embodiment of the present invention; Figure 4 This is a schematic diagram of the electrical connection control of the control component according to an embodiment of the present invention; Figure 5 This is a flowchart illustrating the application method steps of the space projectile propulsion device according to an embodiment of the present invention. Figure 6 This is a schematic diagram of the structure of two cantilever assemblies according to an embodiment of the present invention.

[0027] Explanation of reference numerals in the attached figures: 10. Powder box; 11. Conveying unit; 20. Projectile assembly; 21. Cantilever; 211. Powder delivery pipe; 212. First end; 213. Second end; 22. Drive structure; 221. Drive shaft; 23. Connector; 30. Timer switch; 40. Control assembly; 50. Powder. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0030] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0031] The following is combined with Figures 1 to 6 The following describes embodiments of the present invention.

[0032] According to an embodiment of the present invention, in a first aspect, a space projectile propulsion device based on recycled powder 50 is provided, comprising a powder box 10, a projectile assembly 20, and a timing switch 30; the powder box 10 has a powder outlet and contains powder 50; the projectile assembly 20 includes a cantilever 21 and a drive structure 22, the drive structure 22 drives the cantilever 21 to rotate, a powder feeding pipe 211 is provided inside the cantilever 21, a first end 212 of the powder feeding pipe 211 is located near the rotation center of the cantilever 21 and is adapted to communicate with the powder outlet, and a second end 213 of the powder feeding pipe 211 is located at the end of the cantilever 21 away from the rotation center and is adapted to communicate with the external environment; the timing switch 30 is located at the powder outlet; the timing switch 30 has an open state and a closed state, in the open state the timing switch 30 opens the powder outlet and the powder outlet communicates with the powder feeding pipe 211; in the closed state the timing switch 30 closes the powder outlet.

[0033] It should be noted that in related technologies, flight is achieved by collecting and ejecting materials from the aviation environment and controlling the recoil of the ejected materials. However, in these technologies, the thrust direction cannot be stably controlled during material ejection, causing the aircraft to be unable to move stably in the intended direction.

[0034] The space projectile propulsion device of this embodiment achieves precise delivery and centrifugal acceleration of powder 50 at a fixed phase by phase coordination between the fixed-cycle switch 30 and the powder delivery pipe 211 inside the rotating cantilever 21. This allows for stable control of the thrust direction, solving the problems of uncontrollable projectile direction and the inability of spacecraft to move stably along a predetermined orientation in related technologies. Furthermore, the powder 50 particles are fine and uniformly dispersed, forming a uniform stream that is directionally ejected at a predetermined phase and angle, resulting in strong directional consistency, minimal wear on the inner wall of the powder delivery pipe 211, and improved overall service life.

[0035] Specifically, in this embodiment, the powder 50 in the powder box 10 is made from the in-situ transformation of materials from failed spacecraft, lunar / Mars soil, rocks, asteroid rocks, etc., to serve as a propulsion medium.

[0036] In one embodiment, in the open state, the first end 212 of the powder feeding pipe 211 is rotated to the powder outlet, the timer switch 30 is turned on, and the powder outlet is connected to the powder feeding pipe 211; in the closed state, the first end 212 of the powder feeding pipe 211 is misaligned with the powder outlet, and the timer switch 30 is turned off.

[0037] It is worth noting that the state switching of the time-lapse switch 30 is achieved by judging the positional relationship between the powder feeding pipe 211 and the powder outlet, so as to realize the precise delivery of powder 50, prevent powder 50 from being wasted, and prevent powder 50 from falling outside the powder feeding pipe 211.

[0038] Specifically, in this embodiment, referring to Figure 1 As shown in the figure, the powder 50 on the left side of the figure has just entered the powder feeding pipe 211 from the powder outlet, and is driven to the second end 213 of the powder feeding pipe 211 by the centrifugal force of the rotating cantilever 21; the powder 50 in the lower right corner of the figure is ejected from the second end 213 of the powder feeding pipe 211. The powder 50 has a radial velocity (Vr) and a tangential velocity (Ve).

[0039] Specifically, in this embodiment, referring to Figure 2 As shown in the figure, the cantilever 21 is misaligned with the fixed-cycle switch 30 on the powder outlet, at which time the fixed-cycle switch 30 is closed.

[0040] It should be noted that in other alternative embodiments, since the rotation speed of the cantilever 21 is relatively fast, the fixed-cycle switch 30 can be kept in the normally open state, and the portion of powder 50 falling outside the powder delivery pipe 211 can be ignored.

[0041] In one embodiment, refer to Figure 4 As shown, the space projectile propulsion device based on recycled powder 50 also includes a control component 40, which is electrically connected to a timing switch 30 and a drive structure 22.

[0042] Specifically, the control component 40 is electrically connected to the drive structure 22, controls the rotation speed of the drive structure 22 through electrical signals, and obtains the phase information of the cantilever 21; through the phase information of the cantilever 21, it transmits electrical signals to the time-lapse switch 30 to control the opening and closing of the time-lapse switch 30.

[0043] It is worth noting that the control component 40 is electrically connected to the timing switch 30 and the drive structure 22 to realize the automated and coordinated control of the powder feeding phase, the rotation speed of the cantilever 21, and the ejection timing. It can adjust the magnitude and direction of the thrust, ensure the stable output and reliable operation of the propulsion system, and meet the needs of complex space orbital maneuvers and attitude adjustments.

[0044] In one embodiment, refer to Figure 4 As shown, the powder box 10 has a conveying unit 11, which is adapted to transport the powder 50 to the powder outlet.

[0045] Specifically, in this embodiment, the conveying unit 11 adopts a mechanical conveying method to achieve stable conveying of the powder 50 propulsion medium: the conveying unit 11 includes a powder feeding screw and a drive motor; the powder 50 falls into the cavity where the powder feeding screw is located, and the control component 40 drives the drive motor to rotate the powder feeding screw. The powder 50 moves forward along the conveying channel under the push of the screw thread to complete the conveying; the control component 40 adjusts the speed of the drive motor to change the rotation speed of the powder feeding screw, thereby adjusting the conveying speed and the conveying amount per unit time of the powder 50 to achieve precise flow control.

[0046] It is worth noting that the mechanical conveyor structure is reliable, has a large thrust, and is highly adaptable, and can convey powders with high density and moderate flowability.

[0047] It should be noted that in other alternative embodiments, the conveying unit 11 can also use other methods to transport the powder 50, such as electrostatic conveying: the powder 50 enters the electrostatic conveying channel; multiple sets of high-voltage electrostatic electrodes are arranged on the inner wall of the channel, and the electrodes generate an alternating electrostatic field under the action of the control component 40; the powder 50 particles are induced to be charged in the electrostatic field, and move directionally along the preset channel under the drive of the electric field force; the control component 40 precisely adjusts the moving speed of the powder 50 by adjusting the electrostatic field strength and alternating frequency, thereby controlling the flow rate of the powder 50 reaching the powder outlet per unit time.

[0048] In one embodiment, refer to Figure 4 As shown, the control component 40 is electrically connected to the conveying unit 11, and the control component 40 is adapted to control the conveying speed of the conveying unit 11.

[0049] Specifically, the control component 40 transmits control signals to the conveying unit 11 to control the conveying speed of the conveying unit 11. The conveying speed of the conveying unit 11 directly determines the mass flow rate of the powder 50 entering the projectile assembly 20 per unit time. The faster the conveying speed, the more powder 50 is fed in per unit time, the greater the mass flow rate, and the greater the thrust generated. The slower the conveying speed, the less powder 50 is fed in per unit time, the smaller the mass flow rate, and the smaller the thrust generated.

[0050] It is worth noting that the control component 40 can continuously and precisely adjust the conveying speed of the conveying unit 11, thereby accurately controlling the powder supply flow rate and realizing linear and fine control of the thrust. This can meet the needs of fine attitude adjustment with small thrust, and can also provide large thrust to complete tasks such as orbit transfer and trajectory avoidance, greatly improving the mission adaptability of the propulsion system.

[0051] In one embodiment, the velocity at which powder 50 travels from the first end 212 of powder feeding pipe 211 to the second end 213 of powder feeding pipe 211 is... The radial velocity of powder 50 from the first end 212 of powder feeding pipe 211 to the second end 213 of powder feeding pipe 211 is... The tangential velocity of powder 50 from the first end 212 of powder feeding pipe 211 to the second end 213 of powder feeding pipe 211 is... The time required for powder 50 to travel from the first end 212 to the second end 213 of powder feeding pipe 211 is t, and the angle through which the cantilever 21 rotates when powder 50 travels from the first end 212 to the second end 213 of powder feeding pipe 211 is θ, satisfying the following expression: ; ; ; ; ; The friction coefficient of the inner wall of the powder feeding pipe 211 is μ. , refer to Figure 3 As shown, R1 is the distance between the first end 212 of the powder feeding pipe 211 and the rotation center of the cantilever 21, R2 is the distance between the second end 213 of the powder feeding pipe 211 and the rotation center of the cantilever 21, and ω is the rotational angular velocity of the cantilever 21.

[0052] Specifically, in this embodiment, the radial ejection velocity of powder 50 from the first end 212 of powder feeding pipe 211 to the second end 213 of powder feeding pipe 211 is required to be at least 550 m / s, the time required for powder 50 to reach the second end 213 of powder feeding pipe 211 from the first end 212 of powder feeding pipe 211 is required to be no more than 0.02 s, and the angle through which the cantilever 21 rotates when powder 50 reaches the second end 213 of powder feeding pipe 211 from the first end 212 of powder feeding pipe 211 is required to be approximately 180°.

[0053] Specifically, in this embodiment, the friction coefficient μ of the inner wall of the powder feeding pipe 211 is ≤0.1.

[0054] It is worth noting that limiting the friction coefficient of the inner wall of the powder feeding pipe 211 to μ≤0.1 significantly reduces the motion resistance and energy loss of the powder 50 in the flow channel, improves the centrifugal acceleration efficiency and the terminal ejection speed of the powder 50, ensures the energy utilization rate and thrust output efficiency of the propulsion system, and at the same time reduces pipe wall wear and extends the on-orbit service life of the device.

[0055] Specifically, in this embodiment, the rotational angular velocity ω of the cantilever 21 is 1950 rad / s, the coefficient of friction of the inner wall of the powder feeding pipe 211 is μ=0.05, the distance R1 between the first end 212 of the powder feeding pipe 211 and the rotation center of the cantilever 21 is 0.06m, and the distance R2 between the second end 213 of the powder feeding pipe 211 and the rotation center of the cantilever 21 is 0.3m, that is, R2 R1, the radial velocity of powder 50 from the first end 212 of powder feeding pipe 211 to the second end 213 of powder feeding pipe 211. =556.48m / s, the time required for powder 50 to reach the second end 213 of powder feeding pipe 211 from the first end 212 is t=0.0172s, and the angle θ through which the cantilever 21 rotates when powder 50 reaches the second end 213 of powder feeding pipe 211 from the first end 212 is 180°.

[0056] It should be noted that when the powder 50 is at the first end 212 of the powder feeding pipe 211, it is considered to be at zero degree phase. After the powder 50 enters the powder feeding pipe 211 and rotates with the cantilever 21 for about 180°, the powder 50 is thrown to the second end 213 of the powder feeding pipe 211 by the centrifugal force of the rotation of the cantilever 21 and is ejected.

[0057] It should be noted that when R2 is much larger than R1 and μ≤0.1, μ² approaches 0 and can be approximately ignored in the expression. It will not have a significant impact on the calculation results of speed, time, and angle. Furthermore, μ≤0.1 means that the pipe wall is smooth and the friction loss is small. The motion state of powder 50 is close to ideal frictionless centrifugal acceleration, and the theoretical formula can accurately reflect the real motion law. When the powder inlet R1 is much smaller than the outlet radius R2, the effective acceleration stroke of powder 50 in the pipe accounts for a very high proportion. The calculation deviation caused by the initial position of the inlet is greatly diluted, and the impact on the total speed, total motion time, and total rotation angle is negligible. Therefore, the time required for powder 50 to move from the first end 212 to the second end 213 of the powder delivery pipe 211, the angle rotated by the cantilever 21, and the radial ejection speed of powder 50 are all extremely small. Therefore, it can be regarded that powder 50 is ejected in a directional manner.

[0058] It should be noted that the thrust can be adjusted by adjusting the angle through which the cantilever 21 rotates when the powder 50 reaches the second end 213 of the powder feeding pipe 211 from the first end 212 of the powder feeding pipe 211.

[0059] It is worth noting that by establishing quantitative expressions for the radial velocity of powder 50, motion time, and rotation angle of cantilever 21, theoretical calculations, parameter optimization, and precise design of the centrifugal projectile propulsion process are achieved. This provides a reliable basis for determining key parameters such as the structural dimensions, rotational angular velocity, and powder delivery position of cantilever 21, ensuring the stability of powder 50 ejection velocity, thrust output, and directional control, and improving the engineering feasibility of the system.

[0060] In one embodiment, refer to Figure 3 As shown, multiple cantilever arms 21 are provided, and all multiple cantilever arms 21 are connected to the drive structure 22 for transmission. The multiple cantilever arms 21 are evenly spaced around the rotation center.

[0061] Specifically, refer to Figure 3 As shown, in this embodiment, there are two cantilever arms 21, which are evenly spaced around the rotation center.

[0062] Specifically, when the first end 212 of the powder feeding pipe 211 of each cantilever 21 rotates past the powder outlet, the control component 40 controls the fixed-cycle switch 30 to open.

[0063] It should be noted that in other alternative implementations, the number of cantilever 21 can be adjusted and selected according to the actual situation when facing different thrust requirements, such as three or four.

[0064] It is worth noting that the multiple cantilever arms 21 are evenly arranged around the rotation center, which can form a multi-channel synchronous powder feeding and multi-point synchronous projectile structure, improve the total thrust output and thrust continuity, make the device more balanced in force and less vibrate when rotating at high speed, and enhance the operational stability and structural safety, making it suitable for high-load and long-cycle space propulsion tasks.

[0065] In one embodiment, refer to Figure 3 As shown, the projectile assembly 20 also includes a connector 23, and multiple cantilever 21s are connected to the connector 23. The connector 23 is connected to the drive structure 22.

[0066] Specifically, the connector 23 is integrally formed with multiple cantilever 21.

[0067] It should be noted that in other alternative embodiments, the connector 23 and the cantilever 21 can also be separately and detachably connected. Multiple connection nodes can be provided on the connector 23, and the cantilever 21 can be installed onto the connector 23 using fasteners. Of course, in the detachable connection scheme, the connection nodes need to be further reinforced for locking, for example, by adding anti-loosening washers.

[0068] It is worth noting that the connector 23 provides unified fixation and constraint for the multiple cantilever 21, improving the overall rigidity and structural strength of the cantilever 21 group, avoiding the risk of deformation, displacement or breakage of the cantilever 21 under high-speed rotation, improving the mechanical reliability of the device, and ensuring the accurate position and stable projection direction of the powder delivery pipe 211 during long-term on-orbit operation. The connector 23 and the cantilever 21 adopt an integral molding structure, reducing assembly gaps, welding defects and mechanical failure points, simplifying the processing and assembly process, improving the overall structural integrity and coaxiality, reducing the risk of stress concentration and fatigue damage under high-speed rotation, and further improving the stability and durability of the propulsion device.

[0069] In one embodiment, the powder outlet is adjustable on the powder box 10 about the rotation center of the drive structure 22.

[0070] Specifically, in this embodiment, an arc-shaped opening is provided on the powder box 10, with the center of the arc-shaped opening being the rotation center of the drive structure 22. A sliding plate is slidably disposed inside the powder box 10 corresponding to the arc-shaped opening. The sliding plate slides around the rotation center of the drive structure 22, and can partially cover the arc-shaped opening. The sliding plate has a notch, which forms the powder outlet. When it is necessary to adjust the position of the powder outlet, simply slide the sliding plate, and the position of the notch will change accordingly, thereby realizing the adjustment of the powder outlet position.

[0071] Specifically, in this embodiment, the powder 50 is projected horizontally to the right.

[0072] It should be noted that since the powder feeding pipe 211 inside the cantilever 21 is fixedly opened, if the phase of the powder outlet is not adjusted after the rotation speed of the drive structure 22 is adjusted, the powder 50 may be ejected from the powder feeding pipe 211 earlier or later, causing the ejection direction of the powder 50 to deviate from the predetermined direction.

[0073] It is worth noting that by adjusting the phase of the powder outlet and adjusting the rotation speed of the drive structure 22, the ejection speed of the powder 50 can be adjusted, thereby adjusting the thrust.

[0074] In one embodiment, refer to Figure 6 As shown, multiple cantilever arms 21 form a cantilever group. There are two cantilever groups, which are spaced apart and coaxially arranged. The two cantilever groups rotate in opposite directions and at the same speed. There are two powder outlets, which correspond one-to-one with the two cantilever groups.

[0075] Specifically, the drive structure 22 has two coaxial drive shafts 221 with opposite rotation directions and the same rotation speed, and two cantilever groups are set one-to-one with the two drive shafts 221.

[0076] It is worth noting that by setting up two cantilever groups with opposite rotation directions and coaxiality, the additional torque generated when a single rotating arm group rotates at high speed is eliminated, thereby improving the rotational stability of the projectile assembly 20.

[0077] According to an embodiment of the present invention, in a second aspect, a method for applying a space projectile propulsion device is also provided, applied to the aforementioned space projectile propulsion device based on regenerated powder 50, with reference to... Figure 5 As shown, the steps include: Step S1: Convey the powder 50 in the powder box 10 to the powder outlet; Step S2: Drive structure 22 drives cantilever 21 to rotate, so that the first end 212 of powder feeding pipe 211 rotates to the powder outlet. The fixed beat switch 30 is turned on, and powder 50 is transported from powder box 10 to powder feeding pipe 211. Step S3: The drive structure 22 continues to drive the cantilever 21 to rotate. The first end 212 of the powder feeding pipe 211 is misaligned with the powder outlet. The fixed-beat switch 30 is closed. The powder 50 moves from the first end 212 to the second end 213 along the powder feeding pipe 211 under the action of centrifugal acceleration. Step S4: Powder 50 moves to the second end 213 of the powder feeding pipe 211 and is ejected outward, generating propulsion power; Step S5: Repeat the above steps to ensure that the space launch propulsion device continuously receives thrust.

[0078] Specifically, in step S1, powder 50 falls into the cavity where the powder feeding screw is located. The control component 40 drives the motor to rotate the powder feeding screw. The powder 50 moves forward along the conveying channel under the push of the screw thread to complete the conveying. In step S2, the control component 40 sends an electrical signal to drive the cantilever 21 to rotate. When the first end 212 of the powder feeding pipe 211 rotates to the powder outlet, the control component 40 sends an electrical signal to open the timer switch 30. The powder 50 is then conveyed from the powder box 10 into the powder feeding pipe 211.

[0079] The application method of the space ejection propulsion device in this embodiment realizes the on-site utilization of space resources through a closed-loop process of fixed-beat powder delivery, centrifugal acceleration, and directional ejection. At the same time, it can stably control the magnitude and direction of thrust. It is applicable to various scenarios such as lunar base construction, Mars exploration, asteroid development, disposal of failed spacecraft, and long-term orbital stay, which greatly improves the autonomy, economy and sustainability of deep space missions.

[0080] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A space projectile propulsion device based on recycled powder, characterized in that, include: A powder box (10) is provided with a powder outlet and contains powder (50). The projectile assembly (20) includes a cantilever (21) and a drive structure (22). The drive structure (22) drives the cantilever (21) to rotate. A powder feeding pipe (211) is provided inside the cantilever (21). The first end (212) of the powder feeding pipe (211) is opened near the rotation center of the cantilever (21). The first end (212) of the powder feeding pipe (211) is adapted to communicate with the powder outlet. The second end (213) of the powder feeding pipe (211) is opened at the end of the cantilever (21) away from the rotation center. The second end (213) of the powder feeding pipe (211) is adapted to communicate with the external environment. A timer switch (30) is provided at the powder outlet. The fixed-beat switch (30) has an open state and a closed state. In the open state, the fixed-beat switch (30) opens the powder outlet, and the powder outlet is connected to the powder delivery pipe (211). In the closed state, the fixed-beat switch (30) closes the powder outlet.

2. The space projectile propulsion device based on recycled powder according to claim 1, characterized in that, In the open state, the first end (212) of the powder feeding pipe (211) is rotated to the powder outlet, the fixed-cycle switch (30) is turned on, and the powder outlet is connected to the powder feeding pipe (211); in the closed state, the first end (212) of the powder feeding pipe (211) is misaligned with the powder outlet, and the fixed-cycle switch (30) is turned off.

3. The space projectile propulsion device based on recycled powder according to claim 1, characterized in that, The space projectile propulsion device based on recycled powder (50) further includes a control component (40), which is electrically connected to the timing switch (30) and the drive structure (22).

4. The space projectile propulsion device based on recycled powder according to claim 3, characterized in that, The powder box (10) has a conveying unit (11) which is adapted to transport the powder (50) to the powder outlet. The control component (40) is electrically connected to the conveying unit (11) and is adapted to control the conveying speed of the conveying unit (11).

5. The space projectile propulsion device based on recycled powder according to any one of claims 1-4, characterized in that, The speed at which powder (50) travels from the first end (212) of the powder feeding pipe (211) to the second end (213) of the powder feeding pipe (211) is: The radial velocity of the powder (50) from the first end (212) of the powder feeding pipe (211) to the second end (213) of the powder feeding pipe (211) is: The tangential velocity of the powder (50) from the first end (212) of the powder feeding pipe (211) to the second end (213) of the powder feeding pipe (211) is: The time required for powder (50) to reach the second end (213) of the powder feeding pipe (211) from the first end (212) of the powder feeding pipe (211) is t, and the angle through which the cantilever (21) rotates when powder (50) reaches the second end (213) of the powder feeding pipe (211) from the first end (212) of the powder feeding pipe (211) is θ, satisfying the following expression: ； ； ； ； ； The friction coefficient of the inner wall of the powder feeding pipe (211) is μ. R1 is the distance between the first end (212) of the powder feeding pipe (211) and the rotation center of the cantilever (21), R2 is the distance between the second end (213) of the powder feeding pipe (211) and the rotation center of the cantilever (21), and ω is the rotational angular velocity of the cantilever (21).

6. The space projectile propulsion device based on recycled powder according to claim 5, characterized in that, The friction coefficient μ of the inner wall of the powder feeding pipe (211) is ≤0.

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7. The space projectile propulsion device based on recycled powder according to any one of claims 1-4, characterized in that, Multiple cantilever arms (21) are provided, and all multiple cantilever arms (21) are connected to the drive structure (22) for transmission. The multiple cantilever arms (21) are evenly spaced around the rotation center.

8. The space projectile propulsion device based on recycled powder according to claim 7, characterized in that, Multiple cantilever arms (21) form a cantilever group. There are two cantilever groups. The two cantilever groups are spaced apart and coaxially arranged. The two cantilever groups rotate in opposite directions and at the same speed. There are two powder outlets. The two powder outlets are arranged in a one-to-one correspondence with the two cantilever groups.

9. The space projectile propulsion device based on recycled powder according to any one of claims 1-4, characterized in that, The powder outlet is adjustable on the powder box (10) around the rotation center of the drive structure (22).

10. A method for applying a space projectile propulsion device, characterized in that, The application of the space projectile propulsion device based on recycled powder (50) according to any one of claims 1 to 9 includes the following steps: Step S1: The powder (50) in the powder box (10) is conveyed to the powder outlet; Step S2: The drive structure (22) drives the cantilever (21) to rotate, so that the first end (212) of the powder feeding pipe (211) rotates to the powder outlet, the fixed beat switch (30) is turned on, and the powder (50) is transported from the powder box (10) to the powder feeding pipe (211); Step S3: The driving structure (22) continues to drive the cantilever (21) to rotate, the first end (212) of the powder feeding pipe (211) is misaligned with the powder outlet, the fixed-beat switch (30) is closed, and the powder (50) moves from the first end (212) to the second end (213) along the powder feeding pipe (211) under the action of centrifugal acceleration; Step S4: The powder (50) moves to the second end (213) of the powder delivery pipe (211) and is ejected outward to generate propulsion power; Step S5: Repeat the above steps to ensure that the space launch propulsion device continuously receives thrust.

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