Space-borne rotating wheel type multi-separation device

Abstract

This invention provides a spaceborne rotary multiple separation device, comprising an ejection device (1), a drive locking mechanism (2), a wheel-type turntable (3), an impactor (4), and a satellite body (5). The ejection device (1) provides thrust for the separation of the impactor (4); the drive locking mechanism (2) performs rotational replacement and limit positioning of the impactor (4). When launching the impactor, the magnetic force of the ejection device (1) pushes the impactor away; when replacing the impactor, the drive motor (21) rotates the next impactor to the impact port, and the locking spring component (22) cooperates with the limit device on the support structure (31) to perform limit locking, completing the launch preparation for the second impactor. This invention meets the requirement of continuous launch of multiple impactors and realizes the separation and launch of multiple impactors in a short period of time. At the same time, this rotary separation device can be set as an independent module and mounted on different detectors, possessing a certain degree of versatility.

Description

Technical Field

[0001] This invention belongs to the field of deep space exploration, specifically relating to a spaceborne rotary multi-separation device. More specifically, it relates to a device capable of repeatedly separating and launching impactors in a short period of time, applicable to in-situ asteroid penetration detection and on-orbit asteroid defense activities. Background Technology

[0002] Near-Earth asteroids are asteroids in the solar system whose orbits are less than 0.3 times the Earth-Sun distance from Earth's orbit. Some asteroids even have orbits that intersect Earth's orbit, posing a potential future collision risk. Current research indicates that when an impactor is less than 25-50 meters in diameter, it will cause an airburst, resulting in a meteor shower; a diameter exceeding 140 meters will have a regional impact; a diameter exceeding 300 meters will have a continental impact; a diameter of 1000 meters or more could trigger a global catastrophe; and a diameter of 10,000 meters could lead to a mass extinction event. Currently, nearly 27,000 near-Earth asteroids have been discovered and tracked, of which at least 2,000 have orbits within 7.5 million kilometers of Earth's orbit and are larger than 140 meters, considered to pose a "potential threat."

[0003] For near-Earth asteroids that pose a "potential threat," proposed solutions include impact and laser ablation. Furthermore, soil exploration of extraterrestrial objects will provide crucial data support for planetary science and other fields. Under current technological conditions, in-situ penetration exploration via impact is a more economical and feasible method than sample return.

[0004] Compared with existing patents.

[0005] Patent document CN111547271A, with application number CN202010418782.6 and titled "Dual-purpose Space-based Laser System for Debris Removal and Asteroid Defense," mainly designs a space-based laser system comprising multiple space-based laser-driven platforms with identical parameters. When no asteroid impact threat is detected, each platform operates independently to remove space debris; when an impact threat is detected, they form a laser array for laser ablation. Compared to this invention, this patent document uses multiple satellite platforms and represents a different technical approach.

[0006] Patent document CN112319867A, with application number CN202011181754.3 and titled "An Integrated Ejection-Type Connection and Separation Device," mainly designs an integrated ejection separation device. This device primarily consists of a housing assembly, a pusher plate assembly, a telemetry device, and a connection and unlocking device. Compared to this invention, this device has a more complex mechanical structure, including mechanical components such as guide rails, making the separation motion accuracy more susceptible to interference. Furthermore, the ejection separation device is connected to the satellite via explosive bolts, resulting in a larger impact during unlocking.

[0007] Patent document CN111547269A, with application number CN202010318314.1 and titled "Asteroid Exploration Reconnaissance Projector Rotation and Release Device," mainly designs a release device for a reconnaissance projector used in asteroid exploration. It primarily includes a rotation mechanism, an electromagnetic release mechanism, a spring-force release mechanism, a reconnaissance projector fork, and a reconnaissance projector. During operation, a motor drives the cup-shaped body of the reconnaissance projector fork to rotate, which in turn drives the reconnaissance projector to rotate. An expansion joint is energized and breaks the weak point of the connecting shaft. Under the spring force, the reconnaissance projector fork moves upward a certain distance and is then stopped. The reconnaissance projector continues to move upward and disengages from the fork, thus releasing the projector. Compared to this invention, the axial release of this device requires breaking the connecting shaft, resulting in a larger instantaneous impact.

[0008] Patent document CN115009540A, with application number CN202210624545.4 and titled "A Wall-Mounted Pi-Satellite Ring Unlocking Device," mainly designs a ring-shaped pit-satellite unlocking device, comprising a base, a locking and releasing mechanism, a clamping ring, a thrust mechanism, and a docking ring. This design solves the problems of repetitive structure, heavy weight, and large unlocking impact in pit-satellite separation mechanisms. Compared to this invention, this device cannot achieve time-sharing ejection of multiple sub-modules.

[0009] Patent document CN110127087A, with application number CN201910410710.4 and titled "A Cubic Star Multi-Star Orbit Release Device," mainly designs a cubic star multi-star ejection mechanism. This mechanism primarily includes interconnected housing components, hatch components, hatch unlocking components, mounting bosses, limit unlocking components, main spring ejection components, and guide rails. This device can load and eject combinations of three 1U or two 1.5U cubic stars. Compared to this invention, this device has an excessively long axial length and relatively low space utilization.

[0010] Patent document CN109649696A, with application number CN201811642601.7 and titled "A Tray-Type Micro / Nano Satellite Separation Device with Roughly Controllable Rotational Angular Velocity," mainly designs a tray-type micro / nano satellite separation device with roughly controllable rotational angular velocity. The device mainly includes a mother satellite support, a sleeve, a spring, a torsion spring seat, a torsion spring, a ratchet seat, a ratchet, and a rotating tray. This device, through the combination of springs and torsion springs, provides axial force and rotational torque to the micro / nano satellite during separation, allowing the micro / nano satellite to spin and be ejected upon separation from the mother satellite. Compared to this invention, this device does not achieve reuse of the ejection mechanism, while micro / nano satellites are generally launched using a multi-satellite launch method.

[0011] Patent document CN107128511A, with application number CN201710242309.5 and titled "A Reusable Spaceborne Micro / Nano Satellite Ejection Device," mainly designs a novel reusable connection and separation device for micro / nano satellites. This device primarily includes a connection and separation mechanism and a launch orientation adjustment device. The satellite connection and separation mechanism consists of a four-bar linkage, a resettable latching mechanism, and an ejection device. After ejecting and releasing the previous micro / nano satellite, the satellite connection and separation device can reload a new satellite using a robotic arm or similar method for the next ejection. Compared to this invention, this patent document relies on a robotic arm for the preparation of multiple satellite ejections, resulting in a longer preparation time and a more complex preparation mechanism. Summary of the Invention

[0012] In view of the deficiencies in the prior art, the purpose of this invention is to provide a spaceborne rotary multi-separation device.

[0013] According to the present invention, a spaceborne rotary multi-separation device includes: an ejection device 1, a drive locking mechanism 2, a wheel-type turntable 3, a spacecraft body 5, and multiple impactors 4.

[0014] Multiple impactors 4 are installed at different positions on the wheel turntable 3;

[0015] The ejection device 1 is installed inside the star body 5;

[0016] The wheel-type turntable 3 is installed inside the star body 5 via the drive locking mechanism 2;

[0017] The drive locking mechanism 2 drives the wheel turntable 3 to rotate, so that the impactor 4 in one position enters the launch position, i.e. the separation position. The ejection device 1 ejects and separates the impactor 4 located in the launch device, so that the separated impactor 4 is ejected from the opening 500 of the star body 5.

[0018] Preferably, it is suitable for in-situ asteroid penetration detection and asteroid on-orbit defense activities, and multiple impactors 4 are ejected in a time-sharing manner; wherein, the multiple impactors 4 are pre-installed on the wheel turntable 3 before the probe is launched.

[0019] Preferably, after the impactor 4 at the current launch position is fired, the drive locking mechanism 2 drives the wheel turntable 3 to rotate, so that the impactor 4 at the next position enters the launch position.

[0020] Preferably, the ejection device 1 includes: a first magnet 11 and a support base 12;

[0021] The support base 12 is installed on the inner wall of the star body 5. The first magnet 11 and the second magnet 401 located at the bottom of the impactor 4 at the launch position have the same magnetic poles on their opposite surfaces. They repel each other to generate a thrust for ejection and separation against the impactor 4 at the launch position. Separation is not achieved by using explosive bolts or breaking the connecting shaft.

[0022] Preferably, the drive locking mechanism 2 includes: a drive motor 21 and a limiting component 23;

[0023] The drive shaft 211 of the drive motor 21 is connected to the wheel turntable 3 to drive the wheel turntable 3 to rotate. The limiting component 23 includes a plurality of spring balls located on the end face of the drive shaft 211, which are in a compressed state. When the wheel turntable 3 rotates to the corresponding position, the spring balls are compressed into the limiting hole on the end face of the drive shaft 211 of the wheel turntable 3, thereby playing a limiting role.

[0024] Preferably, the drive locking mechanism 2 further includes: a locking component 22;

[0025] The locking component 22 includes multiple explosive studs, which fix and support the wheel turntable 3 and the drive locking mechanism 2 when not in operation. When in operation, the explosive studs are cut to release the lock, and the wheel turntable 3 and the drive locking mechanism 2 can rotate relative to each other.

[0026] Preferably, the wheel turntable 3 includes: a support structure 31 and a separation bracket 32;

[0027] Each support structure 31 is provided with a limit hole 311 at a position close to the drive motor 21, which works in conjunction with the limit component 23 to limit movement.

[0028] Preferably, the wheel-type turntable 3 further includes: a separation bracket 32;

[0029] The separation bracket 32 ​​uses explosive bolts 321 to connect the impactor 4 to the support structure 31. Before launch, the explosive bolts 321 are ignited and disconnected, and the impactor 4 separates from the support structure 31.

[0030] Preferably, multiple impactors 4 share a single ejection device 1.

[0031] A detector according to the present invention includes the aforementioned spaceborne rotary multi-separation device.

[0032] Compared with the prior art, the present invention has the following beneficial effects:

[0033] 1. When launching the impactor 4, the explosive bolts on the separation bracket 32 ​​are unlocked, and the impactor 4 is pushed away by the magnetic force of the ejection device 1. When replacing the impactor 4, the next impactor 4 is rotated to the impact opening 500 by the drive motor 21, and is locked by the locking component 22 in conjunction with the limiting device on the support structure 31, thus completing the launch preparation for the second impactor 4. This can meet the need for continuous launch of multiple impactors 4 and realize the separation and launch of multiple impactors 4 in a short period of time.

[0034] 2. The wheel-type turntable 3 used in this invention can be set as an independent module and mounted on different detectors, thus possessing a certain degree of versatility.

[0035] 3. This invention provides technical support for a single detector carrying multiple impactors 4 to conduct in-situ asteroid penetration detection or asteroid disposal. Attached Figure Description

[0036] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0037] Figure 1 A three-dimensional diagram of the multiple separation device proposed in this invention is provided.

[0038] Figure 2 A three-dimensional diagram of the ejection device is provided for this invention.

[0039] Figure 3 A three-dimensional diagram of the driving locking mechanism is provided for this invention.

[0040] Figure 4 A three-dimensional view of the wheel-type turntable is provided for this invention.

[0041] Figure 5 This is a schematic diagram of the separation process proposed in this invention.

[0042] Figure 6 This is a schematic diagram illustrating the impactor replacement process proposed in this invention.

[0043] Figure 7 This invention provides a schematic diagram of the installation of the separation device module.

[0044] The diagram shows:

[0045] Detailed Implementation

[0046] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0047] Figure 1 The diagram shown is a three-dimensional representation of a multi-separation device. The spaceborne rotary multi-separation device includes an ejection device 1, a drive locking mechanism 2, a wheel-type turntable 3, an impactor 4, and a spacecraft body 5. The spacecraft body 5 has an opening 500, through which the impactor 4 can be launched after separation.

[0048] Figure 2 The diagram shows a three-dimensional view of the ejection device 1, which includes a first magnet 11 and a support base 12. The support base 12 is mounted on the star body 5. The first magnet 11 and the second magnet 401 at the bottom of the impactor 4 have the same magnetic poles on their opposite surfaces, and the two repel each other, thereby generating a thrust for the impactor 4.

[0049] Figure 3 The diagram shows a three-dimensional view of the drive locking mechanism 2, which includes a drive motor 21, a locking component 22, and a limiting component 23. The drive shaft 211 of the drive motor 21 is connected to the wheel turntable 3, enabling the wheel turntable 3 to rotate. The locking component 22 mainly consists of four explosion studs, which normally serve to fix and support the wheel turntable 3 and the drive locking mechanism 2. During operation, the explosion studs are cut to release the lock, allowing the wheel turntable 3 and the drive locking mechanism 2 to rotate relative to each other. The limiting component 23 mainly consists of four spring balls, which are under pressure. When the wheel turntable 3 rotates to the corresponding position, the spring balls are compressed into the limiting holes of the wheel turntable 3, thus limiting the movement.

[0050] Figure 4 The diagram shows a three-dimensional view of the wheel-type turntable 3, which includes a support structure 31 and a separation bracket 32. The support structure 31, located close to the drive motor 21, has four limiting holes 311 that cooperate with limiting components 23 for positioning. The separation bracket 32 ​​uses explosive bolts 321 to connect the impactor 4 to the support structure 31. Before launch, the explosive bolts 321 are ignited and detonated, separating the impactor 4 from the support structure 31.

[0051] Figure 5 The diagram shows the separation process. Before launch, the explosive bolts 321 on the separation support 32 detonate. The two separate, and the impactor 4 is propelled by the first magnet 11 on the ejection device 1, flying out from the opening 500 position of the star body 5.

[0052] Figure 6 The diagram illustrates the impactor rotation and replacement process. After the first impactor 41 is launched, the locking component 22 on the drive locking mechanism 2 unlocks, and the drive motor 21 drives the wheel turntable 3 to rotate 90 degrees clockwise. The spring ball on the limiting component 23 enters the limiting hole of the support structure 31, allowing the second impactor 42 to enter the launch position. The third impactor 43 and the fourth impactor 44 rotate accordingly.

[0053] Figure 7 The diagram shows the installation of the separation device module. The device can be installed by bolting it to the satellite body 5 through the threaded hole 121 on the support base 12, or the drive locking mechanism and ejection device can be directly installed on the satellite body panel to install the entire module.

[0054] In summary, the ejection device 1 of this invention employs a magnetically driven impactor separation design, which facilitates rapid and reliable impactor separation and launch. The drive locking mechanism 2, driven by a motor, moves the wheeled turntable 3 to the separation station, providing support for multiple consecutive separations within a short period. The locking component 22 in the drive locking mechanism 2 uses a spring ball bearing in conjunction with a spherical groove on the wheeled turntable 3 for limiting, ensuring reliable locking and guaranteeing that the next impactor accurately enters the predetermined position. Through the wheeled mechanism design, four impactors 4 share one ejection device 1, effectively reducing the weight of the ejection functional components. The number of impactor mounting stations on the wheeled turntable 3, which serves as the impact mounting turntable, can be designed and adjusted according to actual needs. The design concept of this invention is applicable to the design of separation devices with different numbers of impactors. This invention can be used as an independent module, mounted on different detectors, and possesses a certain degree of versatility.

[0055] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0056] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A space-borne rotating wheel multi-separation device, characterized by, The application relates to a star-shaped asteroid probe device. The multiple impactors (4) are respectively arranged at different positions of the wheel-shaped rotating disc (3). The ejection device (1) is arranged in the star-shaped body (5). The wheel-shaped rotating disc (3) is arranged in the star-shaped body (5) through the driving locking mechanism (2). The driving locking mechanism (2) drives the wheel-shaped rotating disc (3) to rotate, so that the impactor (4) at a position enters a launching position, i.e. a separation station, the ejection device (1) ejects and separates the impactor (4) at the launching position, and the separated impactor (4) is ejected from an opening (500) of the star-shaped body (5). The driving locking mechanism (2) comprises a driving motor (21) and a limiting component (23). The driving shaft (211) of the driving motor (21) is connected with the wheel-shaped rotating disc (3) to drive the wheel-shaped rotating disc (3) to rotate, the limiting component (23) comprises multiple spring balls arranged at the end surface of the driving shaft (211) and in a compressed state, when the wheel-shaped rotating disc (3) rotates to a corresponding point, the spring balls are compressed into the limiting holes in the end surface of the driving shaft (211) of the wheel-shaped rotating disc (3) to play a limiting role. The driving locking mechanism (2) further comprises a locking component (22). The locking component (22) comprises multiple explosive studs which support and fix the wheel-shaped rotating disc (3) and the driving locking mechanism (2) in a non-working state, and are cut off to release the locking in a working state, so that the wheel-shaped rotating disc (3) and the driving locking mechanism (2) can rotate relatively. The application is suitable for asteroid in-situ penetration detection and asteroid on-orbit defense activities, and multiple impactors (4) are ejected in time, wherein the multiple impactors (4) are pre-installed on the wheel-shaped rotating disc (3) before the probe is launched.

2. The space-borne rotating wheel multi-separation device of claim 1, wherein, After the impactor (4) at the current launching position is ejected, the driving locking mechanism (2) drives the wheel-shaped rotating disc (3) to rotate, so that the impactor (4) at the next position enters the launching position.

3. The space-borne rotating wheel multi-separation device of claim 1, wherein, The ejection device (1) comprises a first magnet (11) and a supporting base (12).

4. The space-borne rotating wheel multi-separation device of claim 1, wherein, The supporting base (12) is arranged on the inner wall of the star-shaped body (5), the first magnet (11) and the second magnet (41) at the bottom of the impactor (4) at the launching position have the same magnetic poles between the opposite surfaces, and the two repel each other to generate a thrust for ejecting and separating the impactor (4) at the launching position. The wheel-shaped rotating disc (3) comprises a supporting structure (31) and a separation support (32).

5. The space-borne rotating wheel multi-separation device of claim 1, wherein, Each supporting structure (31) is provided with a limiting hole (311) at a position close to the driving motor (21) to cooperate with the limiting component (23) to play a limiting role. The wheel-shaped rotating disc (3) further comprises a separation support (32).

6. The space-borne rotating wheel multi-separation device of claim 5, wherein, The separation support (32) connects the impactor (4) and the supporting structure (31) through explosive studs (321), the explosive studs (321) are ignited and disconnected before launching, and the impactor (4) is separated from the supporting structure (31). Multiple impactors (4) share one ejection device (1).

7. The space-borne rotating wheel multi-separation device of claim 1, wherein, ​ 8. A probe, characterized in that The space-borne rotating wheel multi-separation device according to any one of claims 1 to 7. The space-borne rotating wheel multi-separation device according to any one of claims 1 to 7.

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