Release mechanism and launch vehicle for stacked flat-panel satellites

Abstract

Provided are a release mechanism and a launch vehicle for stacked flat-panel satellites. The release structure includes: an extension portion having a relative head end and a terminal end, the extension portion having an axial channel inside; a cable passing through the channel, the cable having a relative head end and a terminal end, the cable terminal end being close to the extension portion terminal end; a claw exposed at the extension portion terminal end and connected to the cable terminal end, the claw being normally in an open state; a claw opening and closing assembly connected to the cable terminal end, used for pulling back and releasing the cable, so that the claw switches between a retracted state and an open state; and an extension portion recovery assembly connected to the extension portion terminal end, used for driving the extension portion to be recovered in the direction of the rocket body. The present application can increase the distance between the satellite and the rocket / satellite during release and reduce the risk of collision.

Description

Technical Field

[0001] The present application mainly relates to the field of aerospace technology, and in particular to a release mechanism and a launch vehicle for stacked flat-panel satellites. Background Art

[0002] The separation technology of stacked flat-panel satellites is the key technology for the successful launch of stacked flat-panel satellites into the predetermined orbit, among which the most critical is the near-field safety issue of stacked flat-panel satellites.

[0003] At present, the satellite-rocket and intersatellite separation systems usually use pyrotechnic separation devices. However, under the current aspect ratio of flat-panel satellites, this device cannot control the separation timing of stacked flat-panel satellites, which will cause the risk of collision between satellites and satellites and between satellites and rockets. In addition, the pyrotechnic separation device will produce a large impact during the release process, the unlocking impact response is highly discrete, and the pollution is serious. The safety of single machines such as on-board lasers that are sensitive to impact loads and excess materials is poor, and pyrotechnics are destructive separations, the experimental cost is high, and it is not easy to transport and store.

[0004] There are various types of known non-pyrotechnic separation devices, but they have disadvantages such as being expensive and being prone to jamming the satellite during separation. Summary of the invention

[0005] It would be advantageous to provide a mechanism that mitigates, alleviates or eliminates at least one of the problems discussed above.

[0006] One aspect of the present application provides a release mechanism for a stacked flat-panel satellite, comprising: an extension portion having a relative head end and a terminal end, the extension portion having an axial channel therein; a cable passing through the channel, the cable having a relative head end and a terminal end, the terminal end of the cable being close to the terminal end of the extension portion; a claw exposed at the terminal end of the extension portion and connected to the terminal end of the cable, the claw being normally in an open state; a claw opening and closing assembly connected to the cable head end, for pulling back and releasing the cable, so that the claw switches between a retracted state and an open state; and an extension portion recovery assembly connected to the extension portion head end, for driving the extension portion to be recovered in the direction of the rocket body.

[0007] Another aspect of the present application provides a launch vehicle for stacking flat-panel satellites, comprising: a rocket body for carrying a satellite stacking column, wherein the satellite stacking column comprises a plurality of flat-panel satellites; a release mechanism for separating the rocket and the satellite, comprising: an extension portion having a relative head end and a terminal end, wherein the extension portion has an axial channel inside, and the extension portion is suitable for being inserted into the satellite stacking column; a cable inserted into the channel, wherein the cable has a relative head end and a terminal end, and the terminal end of the cable is close to the terminal end of the extension portion; a claw exposed at the terminal end of the extension portion and connected to the terminal end of the cable, wherein the claw is normally in an open state to lock the satellite stacking column; a claw opening and closing assembly, disposed in the rocket body and connected to the cable head end, and used for pulling back and releasing the cable to switch the claw between a retracted state and an open state; and an extension recovery assembly, disposed in the rocket body and connected to the extension head end, and used for driving the extension portion to be recovered toward the rocket body.

[0008] It should be understood that the invention summary is not intended to identify the key or essential features of the embodiments of the present disclosure, nor is it intended to limit the scope of the present disclosure. Other features of the present disclosure will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] The accompanying drawings are included to provide a further understanding of the present application. They are included and constitute a part of the present application. The accompanying drawings illustrate embodiments of the present application and together with the present specification serve to explain the principles of the present application. In the accompanying drawings:

[0010] Figure 1 It is a schematic diagram of the side structure of a launch vehicle with a release mechanism according to an embodiment of the present application.

[0011] Figure 2 It is a schematic diagram of the three-dimensional structure of the rocket body of a launch vehicle according to an embodiment of the present application.

[0012] Figure 3 It is a schematic diagram of some components of a release structure of an embodiment of the present application.

[0013] Figure 4-6 This is a schematic diagram of various states of the clamping claws of an embodiment of the present application.

[0014] Figure 7-9 Schematic diagram of spring compression rate according to an embodiment of the present application.

[0015] Figure 10-12 It is a schematic diagram of the satellite release process according to an embodiment of the present application.

[0016] Fig.13 This is a satellite release flow chart of an embodiment of the present application.

[0017] Fig.14A more detailed process of satellite release according to an embodiment of the present application is illustrated. DETAILED DESCRIPTION

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for the description of the embodiments. Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. Unless it is obvious from the language environment or otherwise explained, the same reference numerals in the figures represent the same structure or operation.

[0019] As shown in this application, unless the context clearly indicates an exception, the words "a", "an", "a kind" and / or "the" do not refer to the singular, but also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0020] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the application. Meanwhile, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to actual proportional relationships. The technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0021] In the description of the present application, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction, and therefore cannot be understood as limiting the scope of protection of the present application; the directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0022] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0023] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0024] The embodiments of the present application provide a release mechanism and a launch vehicle for stacked flat-panel satellites, which can increase the distance between satellites and rockets / satellites during release and reduce the risk of collision.

[0025] Figure 1 It is a schematic diagram of the side structure of a launch vehicle with a release mechanism according to an embodiment of the present application. Figure 2 Schematic diagram of the three-dimensional structure of the launch vehicle body of an embodiment of the present application. Figure 1-2 As shown, the launch vehicle 100 of the present embodiment includes a rocket body 110 and a release mechanism 120 for separating the rocket and the satellite. The rocket body 110 is used to carry the satellite stacking column 200. The rocket body 110 can use any known structure, and the present application is not limited. For the sake of simplicity, only the local structure of the rocket body is shown in the figure. The satellite stacking column 200 includes a plurality of parallel flat-panel satellites 210. The edge of each flat-panel satellite 210 is supported by a support tube 220. A plurality of support tubes 220 can be arranged around each flat-panel satellite 210. The support tubes 220 at the same position of each layer of flat-panel satellites 210 are stacked together.

[0026] Figure 3 Schematic diagram of some components of the release structure of an embodiment of the present application. Figure 1 and Figure 3 As shown, the release mechanism 120 includes an extension 121, a cable 122, a claw 123, a claw opening and closing assembly 124, and an extension recovery assembly 125. The extension 121 has a head end (lower end in the figure) and a tail end (upper end in the figure) opposite to each other, and is suitable for being inserted into the satellite stacking column 200. Figure 1 In the example of FIG. 1 , the extension portion 121 is disposed in the support tube 220. However, it is understood that in other embodiments, the extension portion 121 may be disposed in other positions of the satellite stacking column 200. Figure 1 and Figure 3 In the example, the extension 121 is a flexible rope that can be wound. In other embodiments, the extension 121 is a rigid telescopic rod, and its length can increase or decrease with telescoping. The extension 121 has an axial channel 121a inside, and the cable 122 is inserted into the channel 121a. The cable 122 has a relative head end (the lower end in the figure) and an end (the upper end in the figure), and the end of the cable 122 is close to the end of the extension 121. The extension recovery assembly 125 includes a length measuring component to measure the length of the extension extended or retracted. In one embodiment, the length measuring component includes a guide wheel and an encoder, and the encoder can determine the length of the extension by measuring the number of rotations of the guide wheel.

[0027] As mentioned above, the claw 123 is exposed at the end of the extension portion 121 and connected to the end of the cable 122. The claw 123 is normally in an open state to lock the satellite stacking column 200. When the extension portion 121 is inserted into the support tube 220, the claw 123 locks the satellite stacking column 200 by locking the support tube 220. The claw opening and closing assembly 124 is disposed in the rocket body 110 and connected to the head end of the cable 122, and is used to pull back and release the cable 122, so that the claw 123 switches between the retracted and open states. In one embodiment, the claw opening and closing assembly 124 includes a motor 124a and a spring 124b, the spring 124b is connected to the head end of the cable 123a, and the motor 124a is used to control the compression and rebound of the spring 124b to pull back and release the cable 122, thereby changing the state of the claw 123. Reference Figure 4-6 , Figure 7-9 As shown, when the motor 124a is not powered and the spring 124b is completely uncompressed, the cable 122 does not move and the claw 123 is in an open state; when the motor 124a is powered and the spring 124b is partially compressed (for example, 50%), the cable is partially pulled back and the claw 123 is retracted to a certain extent; when the spring 124b is greatly compressed (for example, close to or reaching 100%, the cable is pulled back), the claw 123 is in a retracted state.

[0028] In some embodiments, the claw 123 is made of high-toughness metal material and has no rotation friction. In some embodiments, the flexible rope as an example of the extension 121 is a flexible hollow structure woven from metal wire, carbon fiber and / or Kevlar fiber.

[0029] The extension part recovery assembly 125 is arranged in the rocket body 110, more specifically below the installation surface of the satellite stacking column 200. The extension part recovery assembly 125 is connected to the head end of the extension part 121, and is used to drive the extension part 121 to be recovered in the direction of the rocket body 110. In the example where the extension part 121 is a flexible rope, the extension part recovery assembly 125 includes a motor 125a and a guide groove 125b. The motor 125a is located near the top of the rocket body 110, and the guide groove 125b is located at the opening at the top of the rocket body 110. The motor 125a is connected to the head end of the extension part 121, and is used to drive the extension part 121 to be recovered in the direction of the rocket body 110, and stored in the guide groove 125b. The guide groove 125b includes annular grooves concentrically arranged on the rocket body 110. These concentric multi-circle annular grooves can accommodate flexible ropes coiled into the same ring shape. Figure 2 In the example, the guide groove 125b is just located at the opening of the rocket body 110, but it can be understood that the guide groove 125b can be a predetermined distance from the opening of the rocket body 110. After the motor 125a is powered on, the gear rotates, driving the flexible rope to move along the guide groove 125b toward the rocket body 110, thereby realizing the recovery of the flexible rope. In the embodiment of the present application, the guide groove 12b is designed along the inner wall of the launch rocket body 110 or along the periphery of the satellite assembly and the carrier final stage installation surface, which can firstly reduce the weight and secondly maximize the use of the turning radius to reduce the friction between the peripheral structure of the flexible rope and the high-strength cable of the core body.

[0030] In one embodiment, further, a flexible bracket structure can be integrally designed on the outside of the extension portion 121 to serve as an anti-collision measure for the flexible rope during the active phase of the rocket and an anti-hooking structure for the flexible rope during the pulling back action.

[0031] In one embodiment, the release mechanism 110 further includes a stop structure 126 disposed in each flat panel satellite 210 in the satellite stacking column 200. Fig.10 As shown, a limiting structure 126 is respectively disposed in each support tube 221 of each flat-panel satellite 210. When the claw 123 is in an open state, it cooperates with the limiting structure 126 to lock the corresponding flat-panel satellite 210, and when the claw 123 is in a closed state, it leaves the limiting structure 126 to release the flat-panel satellite 210. In some embodiments, the limiting structure 126 is an inverted wedge-shaped structure.

[0032] Figure 10-12 It is a schematic diagram of the satellite release process according to an embodiment of the present application. Fig.13 This is a satellite release flow chart of an embodiment of the present application. Figure 1 , Figure 10-12 , Fig.13 As shown, the satellite release process according to an embodiment of the present application is as follows.

[0033] In step 301, in response to the launch vehicle's carrying attitude meeting the requirements, the claw opening and closing assembly is controlled to pull back the cable to retract the claw.

[0034] refer to Fig.10 When the cable is pulled back, the claw 123 retreats along the axis of the flexible rope (an example of the extension part 121) and is retracted under the restriction of the peripheral structure of the flexible rope. The outer envelope size of the retracted claw mechanism is smaller than the inner diameter of the inverted wedge structure inside the satellite stacking column 200.

[0035] In step 302, the extension part recovery assembly is controlled to recover the extension part of a preset length, so that the claws leave the limiting structure of the first flat-panel satellite in the satellite stacking column to release the first flat-panel satellite.

[0036] Specifically, the extension recovery assembly 125 drives the gear in the guide groove 125b to rotate, and pulls the flexible rope to recover. When the recovery length of the flexible rope reaches the set value, the recovery stops. At this time, the claw 123 is completely retracted under the compression and pullback of the spring 124b, and the flexible rope is pulled back to a position below the limit structure 126 in the stacking column. After completely separating from the first support tube 220a corresponding to the first flat-panel satellite 210a of the upper layer, the satellite constraint is released, and the first flat-panel satellite 210a and its first support tube 220a are thrown out of the rocket body 110 to achieve the separation of the upper satellite.

[0037] In step 303, the claw opening and closing assembly is controlled to release the cable, so that the claw is opened to cooperate with the limiting structure of the second flat-panel satellite in the satellite stacking column to lock the second flat-panel satellite.

[0038] Specifically, when the retracted length of the flexible rope reaches the set value in step 302, the motor of the claw opening and closing assembly 124 is not powered, the spring compression is released, the cable 122 is released, and the claw 123 at the top of the flexible rope is fully unfolded, cooperating with the limiting structure 126 in the second support tube 220b corresponding to the second flat satellite 210b of the next layer, thereby locking the second flat satellite 210b.

[0039] In step 304, in response to the inter-satellite separation signal meeting the requirement, the claw opening and closing assembly is controlled to pull back the cable to retract the claws.

[0040] Specifically, the satellite determines whether the separation signal of the intersatellite trip switch is satisfied. If the separation signal is satisfied, it continues to determine whether all stacked flat-panel satellites have been released. If the separation signal is not satisfied, the claw 123 starts to retract under the drive of the motor 124a.

[0041] In step 305, the extension part recovery assembly is controlled to recover the extension part of a preset length, so that the claws leave the limiting structure of the second flat-panel satellite to release the second flat-panel satellite.

[0042] Specifically, the flexible rope is pulled back under the drive of the extension recovery assembly 125 to release the second flat-panel satellite 210b, and so on, until all satellites (such as the third flat-panel satellite 210c and the fourth flat-panel satellite 210d) and their support tubes (such as the third support tube 220c and the third support tube 220d) are released.

[0043] Fig.14 A more detailed process of satellite release according to an embodiment of the present application is shown. Fig.14 As shown, in step 401, the operation data of the launch vehicle is collected, and in step 402, it is determined whether the launch attitude of the launch vehicle meets the requirements. If the requirements are not met, otherwise, return to step 401 to continue collecting data; if the requirements are met, enter step 403, control the claw opening and closing assembly to pull back the cable to close the claw. In step 404, control the extension recovery assembly to recover the extension, and in step 405, determine whether the recovery length release of the extension meets the requirements. If the requirements are not met, return to step 404; if the requirements are met, it indicates that the claw has left the limiting structure of the first flat-panel satellite in the satellite stacking column, and enter step 406. In step 406, control the claw opening and closing assembly to release the cable to open the claw. In step 407, it is determined whether the inter-satellite separation signal meets the requirements. If not, return to step 406; if satisfied, enter step 408. In step 408, determine whether all stacked flat-panel satellites have been released. If not, return to step 403 to release the next flat-panel satellite. If yes, end the process.

[0044] This embodiment can achieve the separation of satellites at different layers in a timed sequence by controlling the speed of claw recovery, reasonably increase the distance between the rocket and the satellite, and reduce the probability of collision. In one embodiment, the release structure 120 also includes a controller 127, which connects the claw opening and closing assembly 124 and the extension recovery assembly 125 to achieve the aforementioned functions. In one embodiment, the controller 127 may include a processor and a memory. The processor is used to execute a computer-readable program to implement the aforementioned steps 301-305, and the memory is used to store programs and / or data for execution by the processor.

[0045] The satellite-rocket and intersatellite release mechanism of the present application can achieve release by using structures such as extensions, cables and claws, and has a simple structure. The release mechanism of the present application can reduce the risks of collision and failure that may occur in the satellite-rocket and intersatellite process because it has little coupling with the mechanical and electrical interfaces on the carrier side, thereby consuming less system resources. In addition, the release mechanism of the present application can be used for the release of stacked flat-panel satellites and has a certain adaptability.

[0046] The basic concepts have been described above. Obviously, for those skilled in the art, the above application disclosure is only an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary embodiments of the present application.

[0047] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0048] Some aspects of the present application may be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software may be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor may be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. In addition, various aspects of the present application may be represented as computer products located in one or more computer-readable media, which include computer-readable program codes. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, tapes ...), optical disks (e.g., compact disks CDs, digital versatile disks DVDs ...), smart cards, and flash memory devices (e.g., cards, sticks, key drives ...).

[0049] A computer-readable medium may include a propagated data signal containing computer program code, such as in baseband or as part of a carrier wave. The propagated signal may have a variety of manifestations, including electromagnetic, optical, etc., or a suitable combination. A computer-readable medium may be any computer-readable medium other than a computer-readable storage medium, which may be connected to an instruction execution system, device or apparatus to communicate, propagate or transmit a program for use. The program code on the computer-readable medium may be propagated via any suitable medium, including radio, cable, fiber optic cable, radio frequency signal, or similar medium, or any combination of the above mediums.

[0050] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus help understand one or more embodiments, in the above description of the embodiments of this application, multiple features are sometimes combined into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than the features mentioned. In fact, the features of the embodiment are less than all the features of the single embodiment disclosed above.

[0051] In some embodiments, the numbers describing the number of components and attributes are used. It should be understood that such numbers used for the description of the embodiments are modified by the modifiers "about", "approximately" or "substantially" in some examples. Unless otherwise specified, "about", "approximately" or "substantially" indicate that the numbers allow a change of ±20%. Accordingly, in some embodiments, the numerical parameters used in this application are approximate values, which can be changed according to the required characteristics of individual embodiments. In some embodiments, the numerical parameters should consider the specified significant digits and adopt the method of general digit retention. Although the numerical domains and parameters used to confirm the breadth of the range in some embodiments of the present application are approximate values, in a specific embodiment, the setting of such numerical values ​​is as accurate as possible within the feasible range.

[0052] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions may be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the scope of the essential spirit of the present application, they will fall within the scope of the present application.

Claims

1. A release mechanism for a stacked flat-panel satellite, comprising: An extension portion having a head end and a tail end opposite to each other, wherein the extension portion has an axial passage therein; A cable, passing through the channel, the cable having a head end and a tail end opposite to each other, the tail end of the cable being close to the tail end of the extension portion; A claw, exposed at the end of the extension portion and connected to the end of the cable, the claw being normally in an open state; A claw opening and closing assembly connected to the head end of the cable and used for pulling back and releasing the cable to switch the claw between a closed state and an open state; and An extension part recovery assembly is connected to the head end of the extension part and is used to drive the extension part to be recovered in the direction of the rocket body.

2. The release mechanism for stacked flat-panel satellites according to claim 1, characterized in that: The claw opening and closing assembly includes a motor and a spring, wherein the spring is connected to the head end of the cable, and the motor is used to control the compression and rebound of the spring to pull back and release the cable.

3. The release mechanism for stacked flat-panel satellites according to claim 1, characterized in that: The extension part is a rope, and the extension part recovery component includes a motor and a guide groove. The motor is connected to the head end of the rope and is used to drive the rope to be recovered toward the arrow body and stored in the guide groove.

4. The release mechanism for stacked flat-panel satellites as claimed in claim 3, characterized in that: The guide groove comprises an annular groove concentrically arranged on the arrow body.

5. The release mechanism for stacked flat-panel satellites according to claim 1, characterized in that: The extension portion is a telescopic rod.

6. The release mechanism for stacked flat-panel satellites according to any one of claims 1 to 5, characterized in that: It also includes a limiting structure, which is suitable for being arranged in the flat-panel satellite in the satellite stacking column. When the clamping claw is in the open state, it cooperates with the limiting structure to lock the flat-panel satellite, and when the clamping claw is in the retracted state, it leaves the limiting structure to release the flat-panel satellite.

7. The release mechanism for stacked flat-panel satellites as claimed in claim 6, characterized in that: It also includes a controller, which is connected to the claw opening and closing assembly and the extension recovery assembly and is configured as follows: Control the claw opening and closing assembly to pull back the cable to retract the claw, and control the extension part recovery assembly to recover the extension part of a preset length to make the claw leave the limiting structure of the first flat-panel satellite in the satellite stacking column to release the first flat-panel satellite; Controlling the claw opening and closing assembly to release the cable, so that the claw opens and cooperates with the limiting structure of the second flat-panel satellite in the satellite stacking column to lock the second flat-panel satellite; as well as The claw opening and closing assembly is controlled to pull back the cable to retract the claw, and the extension part recovery assembly is controlled to recover the extension part of a preset length to make the claw leave the limiting structure of the second flat-panel satellite to release the second flat-panel satellite.

8. A launch vehicle for stacking flat-panel satellites, comprising: A rocket body, used to carry a satellite stack column, wherein the satellite stack column includes a plurality of flat-panel satellites; The release mechanism for the separation of rocket and satellite includes: An extension part, having a head end and a tail end opposite to each other, the extension part having an axial passage inside, and the extension part being suitable for being inserted into the satellite stacking column; A cable, passing through the channel, the cable having a head end and a tail end opposite to each other, the tail end of the cable being close to the tail end of the extension portion; A claw, exposed at the end of the extension portion and connected to the end of the cable, the claw being normally in an open state to lock the satellite stacking column; A claw opening and closing assembly is disposed in the arrow body and connected to the head end of the cable, and is used to pull back and release the cable to switch the claw between a retracted state and an open state; and The extension part recovery component is arranged in the arrow body and connected to the head end of the extension part, and is used for driving the extension part to be recovered in the direction of the arrow body.

9. The launch vehicle for stacked flat-panel satellites as claimed in claim 8, characterized in that: The claw opening and closing assembly includes a motor and a spring, wherein the spring is connected to the head end of the cable, and the motor is used to control the compression and rebound of the spring to pull back and release the cable.

10. The launch vehicle for stacked flat-panel satellites according to claim 8, characterized in that: The extension part is a rope, and the extension part recovery component includes a motor and a guide groove. The motor is connected to the head end of the extension part and is used to drive the extension part to be recovered in the direction of the arrow body and stored in the guide groove.

11. The launch vehicle for stacked flat-panel satellites according to claim 10, characterized in that: The guide groove comprises an annular groove concentrically arranged on the arrow body.

12. The launch vehicle for stacked flat-panel satellites according to claim 8, characterized in that: The extension portion is a telescopic rod.

13. The launch vehicle for stacked flat-panel satellites according to claim 8, characterized in that: The release mechanism also includes a limiting structure, which is arranged in each flat-panel satellite in the satellite stacking column. When the clamping claw is in the open state, it cooperates with the limiting structure to lock the flat-panel satellite, and when the clamping claw is in the retracted state, it leaves the limiting structure to release the flat-panel satellite.

14. A launch vehicle for stacked flat-panel satellites as claimed in any one of claims 8 to 12, characterized in that: It also includes a release mechanism controller, which is connected to the claw opening and closing assembly and the extension recovery assembly and is configured as follows: In response to the launch posture of the launch vehicle meeting the requirement, the claw opening and closing assembly is controlled to pull back the cable to retract the claw, and the extension part recovery assembly is controlled to recover the extension part of a preset length, so that the claw leaves the limiting structure of the first flat-panel satellite in the satellite stacking column to release the first flat-panel satellite; Controlling the claw opening and closing assembly to release the cable, so that the claw opens and cooperates with the limiting structure of the second flat-panel satellite in the satellite stacking column to lock the second flat-panel satellite; as well as In response to the intersatellite separation signal meeting the requirements, the claw opening and closing assembly is controlled to pull back the cable to retract the claw, and the extension part recovery assembly is controlled to recover the extension part of a preset length to make the claw leave the limiting structure of the second flat-panel satellite to release the second flat-panel satellite.

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