Separation and release mechanism of stacked flat-panel satellite and launch vehicle

Abstract

The present application provides a separation and release mechanism for stacked flat-panel satellites and a launch vehicle. The separation and release mechanism includes: a pressure rod bracket, suitable for switching between a pressed state and an unfolded state, in which the pressure rod bracket is suitable for pressing on the first flat-panel satellite on the top of the satellite stacking column, and in the unfolded state, the pressure rod bracket leaves the first flat-panel satellite; an extension portion, having a relative head end and a tail end, and the extension portion has an axial channel inside; a claw, exposed at the end of the extension portion and connected to the end of the extension portion, the claw has an open state and a retracted state, and the normal state is an open state; and an extension portion recovery assembly, connected to the head end of the extension portion, used to drive the extension portion to be recovered in the direction of the rocket body. The present application can control the satellite separation timing and reduce the risk of collision.

Description

Technical Field

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

[0002] At present, low-orbit giant satellite constellations are developing rapidly, with the number of satellites in the constellation ranging from a few hundred to tens of thousands. In order to meet the needs of rapid construction and development of giant constellations, satellites are often flattened and stacked on rockets, and launch costs are reduced by launching multiple satellites with one rocket.

[0003] 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. The most critical issue is the near-field safety of stacked flat-panel satellites. The existing satellite-rocket separation technology for stacked satellites often adopts a one-time unlocking and multi-satellite overall separation operation mode. This separation operation mode is likely to cause collisions between satellites, resulting in satellite damage. Summary of the invention

[0004] It would be advantageous to provide a mechanism that mitigates, alleviates or eliminates at least one of the problems discussed above.

[0005] One aspect of the present application provides a separation and release mechanism for stacked flat-panel satellites, including: a pressure rod bracket, suitable for switching between a pressed state and an unfolded state, in which the pressure rod bracket is suitable for pressing on a first flat-panel satellite on the uppermost layer of a satellite stacking column in the pressed state, and in the unfolded state, the pressure rod bracket leaves the first flat-panel satellite; an extension portion, having a head end and a tail end relative to each other, the extension portion having an axial channel inside; a claw, exposed at the tail end of the extension portion and connected to the tail end of the extension portion, the claw having an open state and a retracted state, and the normal state is the open state; and an extension portion recovery assembly, connected to the head end of the extension portion, for driving the extension portion to be recovered in the direction of the rocket body.

[0006] Another aspect of the present application provides a launch vehicle for stacking flat-panel satellites, comprising: a rocket body, used to carry a satellite stacking column, wherein the satellite stacking column comprises a plurality of flat-panel satellites; a separation and release mechanism for separating the rocket and the satellite, comprising: a pressure rod bracket, suitable for switching between a pressed state and an unfolded state, wherein in the pressed state, the pressure rod bracket is suitable for pressing on a first flat-panel satellite at the uppermost layer of the satellite stacking column, and in the unfolded state, the pressure rod bracket leaves the first flat-panel satellite; an extension portion, having a head end and a tail end opposite to each other, wherein the extension portion has an axial channel inside; a claw, exposed at the tail end of the extension portion and connected to the tail end of the extension portion, wherein the claw has an open state and a retracted state, and the normal state is the open state; and an extension portion recovery assembly, disposed in the rocket body and connected to the head end of the extension portion, and used for driving the extension portion to be recovered toward the rocket body.

[0007] 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

[0008] 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:

[0009] Figure 1 It is a schematic diagram of the side structure of a launch vehicle with a separation and release mechanism according to an embodiment of the present application.

[0010] Figure 2 , 3 It is a schematic top view of a launch vehicle according to an embodiment of the present application.

[0011] Figure 4 It is a schematic diagram of some components of a separation and release structure according to an embodiment of the present application.

[0012] Figure 5 It is a schematic diagram of the extension part structure of an embodiment of the present application.

[0013] Figure 6 It is a schematic diagram of the extension structure of another embodiment of the present application.

[0014] Figure 7 It is a longitudinal cross-sectional view of a support tube of a launch vehicle according to an embodiment of the present application.

[0015] Figure 8 It is a transverse cross-sectional view of a support tube according to an embodiment of the present application.

[0016] Figure 9-12 It is a schematic diagram of the satellite release process according to an embodiment of the present application.

[0017] Fig.13 This is a satellite separation and release flow chart of an embodiment of the present application. 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] In order to solve the technical problem that existing stacked satellites are prone to collision during separation, the present application provides a separation and release mechanism for stacked flat-panel satellites and a launch vehicle, which can control the satellite separation sequence and reduce the risk of collision.

[0025] Figure 1 It is a schematic diagram of the side structure of a launch vehicle with a separation and release mechanism according to an embodiment of the present application. Figure 2 , Figure 3 1 is a schematic top view of a launch vehicle according to an embodiment of the present application. Figure 1-3 As shown, the launch vehicle 100 of this embodiment includes a rocket body 110 and a separation and release mechanism 120 for separating the rocket and the satellite. The rocket body 110 is used to carry the satellite stack column 200. The rocket body 110 can use any known structure, and the present application is not limited. The satellite stack column 200 includes a plurality of parallel flat-panel satellites 210. Two flat-panel satellites 210 can be arranged on each layer of the satellite stack column 200, so the satellite stack column 200 is divided into two vertical columns. The edge of each flat-panel satellite 210 is supported by a support tube 220. Multiple support tubes 220 (3 in the example in the figure) 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 in series along the longitudinal axis of the rocket (Z direction in the figure). The separation and release mechanism 120 includes a pressure rod bracket 121, which is suitable for switching between a pressed state and an unfolded state. In Figure 2In the pressed state shown, the pressure rod bracket is suitable for pressing on the first flat-panel satellite 210a on the uppermost layer of the satellite stacking column 200, and by applying a pressing force to the first support tube 220a corresponding to the first flat-panel satellite 210a, the entire satellite stacking column 200 is pressed, so that the satellite is in a fixed state during the flight of the active phase of the rocket. In one embodiment, the pressure rod bracket 121 is correspondingly arranged around the support tube 220, and thus the number is the same as the support tube 220. Each column of flat-panel satellites 210 is restricted by three pressure rod brackets 121. The pressure rod bracket 121 can bounce upward a short distance and unfold in a direction away from the longitudinal axis of the rocket, thereby switching to the unfolded state. After the pressure rod bracket 121 is unfolded, it will be approximately parallel to the Y-axis of the rocket to avoid hindering the satellite separation movement. Figure 3 In the unfolded state shown, the strut support 121 is away from the first flat panel satellite 210a. In one embodiment, the strut support 121 is a door-type structure, and its top crossbeam 121a is only in contact with the first flat panel satellite 210a.

[0026] Figure 4 Schematic diagram of some components of the separation and release structure of an embodiment of the present application. Figure 1 and Figure 4 As shown, the separation release mechanism 120 also includes an extension 122, a claw 123 and an extension recovery assembly 124. The extension 122 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 122 is disposed in the support tube 220. However, it is understood that in other embodiments, the extension portion 122 may be disposed in other positions of the satellite stacking column 200. Figure 1 and Figure 4 In the example of the embodiment, the extension portion 122 is a rigid telescopic rod, and its length can increase or decrease with telescoping. In other embodiments, the extension portion 122 is a flexible rope that can be wound.

[0027] Figure 5 It is a schematic diagram of the extension part structure of an embodiment of the present application. Figure 6 Schematic diagram of the extension structure of another embodiment of the present application. Figure 5 and Figure 6 As shown, in some embodiments, the extension 122 includes a telescopic rod. The extension recovery assembly 124 is disposed in the rocket body 110, more specifically below the mounting surface of the satellite stacking column 200. The extension recovery assembly 124 is connected to the head end of the extension 122 and is used to drive the extension 122 to be recovered in the direction of the rocket body 110. Figure 5 In the embodiment of the invention, the extension recovery assembly 124 includes a motor 124a. In this embodiment, the telescopic rod is a threaded telescopic rod and is connected to the motor 124a. The motor 124a drives the thread on the telescopic rod to rotate to achieve telescopic movement. Figure 6 In the embodiment of the invention, the extension part recovery assembly 124 further comprises a rope 124c disposed inside the telescopic rod. The rope 124c is connected to the motor 124a. The motor 124a drives the rope 124c wound inside the telescopic rod to pull downward and retract.

[0028] As mentioned above, the claw 123 is exposed at the end of the extension 122 (e.g., a telescopic rod). The claw 123 has an open state and a retracted state, and the claw 123 is normally in the open state to lock the satellite stacking column 200. When the extension 122 is inserted into the support tube 220, the claw 123 in the open state locks the satellite stacking column 200 by locking the support tube 220. When the extension recovery component 124 recovers the extension 122 to a predetermined length, the claw 123 moves downward accordingly, is squeezed by the support tube 220 and becomes a retracted state, and leaves the support tube 220, thereby releasing the support tube 220 and its corresponding flat-panel satellite.

[0029] Figure 7 FIG. 1 is a longitudinal cross-sectional view of a support tube of a launch vehicle according to an embodiment of the present application. Figure 7 As shown, the upper opening 221 and the lower opening 222 of the support tube 220 are both downward conical openings, and the lower conical opening 222 of the upper support tube 220 (such as the first support tube 220a) can be embedded in the upper conical opening 222 of the lower support tube 220 (such as the second support tube 220b), and the lower conical opening of the lowest support tube 220d is directly embedded in the corresponding conical opening of the rocket 110 (not shown), thereby realizing the displacement constraint of the satellite in the XOY plane of the rocket, and the clamping effect of the combined pressure rod bracket 121 can prevent the satellite from moving laterally along the XOY plane during the active phase of the rocket flight.

[0030] refer to Figure 7 and Figure 8 As shown, in one embodiment, the release mechanism 110 further includes a limiting structure 125, which is disposed in each flat-panel satellite 210 in the satellite stacking column 200. A limiting structure 125 is disposed in each support tube 220 of each flat-panel satellite 210. Fig. 9 As shown, when the claw 123 is in the open state, it cooperates with the limiting structure 125 to lock the corresponding flat-panel satellite 210 (such as the second flat-panel satellite 210b). Fig.10As shown, when the extension part recovery assembly 124 recovers the extension part 122 of the first preset length, the claw 123 is squeezed by the limiting structure 125 and is in a retracted state, and leaves the limiting structure 125, thereby releasing the flat-panel satellite 210 (such as the second flat-panel satellite 210b). After the claw 123 leaves the limiting structure 125, it returns to an open state under the action of elastic force. In some embodiments, the limiting structure 125 is a cone bowl structure, which is arranged in the support tube near the lower opening. The upper opening diameter Du of the cone bowl structure is substantially consistent with the inner diameter of the support tube 220, and the lower opening diameter Dd is smaller, and a slope of a smaller distance is formed between the upper and lower openings. The claw 123 is a spring claw with an upward opening, and the spring claw has a plurality of claw petals. The claw petals have an expanded diameter greater than the lower opening diameter Dd of the cone bowl structure, and the minimum expanded diameter of the claw petals after being squeezed by the limiting structure 125 is designed to be smaller than the lower opening diameter Dd of the cone bowl structure. The spring claw in the freely deployed state contacts the inclined surface of the cone bowl structure, and the elastic force of the spring claw is designed to be large enough so that the friction force generated by the spring claw and the inclined surface of the cone bowl structure can provide the centripetal force for the flat-panel satellite 210 to move with the rocket 100 after the pressure rod bracket 121 is unlocked, and the force to overcome the lateral relative movement between the flat-panel satellites 210 in the XOY plane.

[0031] Figure 9-12 It is a schematic diagram of the satellite release process according to an embodiment of the present application. Fig.13 1 is a flow chart of satellite separation and release according to an embodiment of the present application. Figure 1 , Figure 9-12 , Fig.13 As shown, the satellite separation and release process according to an embodiment of the present application is as follows.

[0032] In step 301, in response to the launch vehicle's launch posture meeting the requirements, the control rod bracket 121 is switched from a pressed state to an unfolded state to release the first flat-panel satellite in the satellite stacking column.

[0033] Before the separation of the satellite and the rocket, the rocket 100 generates an angular velocity in a certain direction through jetting to drive all the satellites to rotate. When the predetermined separation posture is reached, the pressure rod bracket 121 is unlocked using a command.

[0034] Reference Figure 2-3 As shown, each pressure rod bracket 121 in the separation release mechanism 120 swings from the pressed state to the unfolded state. Figure 1 and Fig. 9 The first flat-panel satellite 210a on the uppermost layer is connected to its first support tube 220a and is released first because there is no restriction from the claw 123. The first flat-panel satellite 210a will generate centrifugal motion due to rotational inertia and be ejected relative to the rocket 100, realizing the separation of the satellite and the rocket and separating from other flat-panel satellites.

[0035] At this time, the claws 123 in the free-expanding state in the separation and release mechanism 120 are still in contact with the inclined surface of the limiting structure 125 in the second supporting tube 220b of the second flat-panel satellite 210b.

[0036] In step 302, in response to the inter-satellite separation signal meeting the requirements, the extension part recovery assembly is controlled to recover the extension part of the first preset length, so that the clamping claw is squeezed by the limiting structure of the second flat-panel satellite in the satellite stacking column to be in a retracted state and leaves the limiting structure of the second flat-panel satellite to release the second flat-panel satellite.

[0037] Specifically, if Figure 1 , Figure 10-11 As shown, the extension part recovery assembly 124 pulls the extension part 122 back to the first preset length to a position below the limiting structure 125 of the second support tube 220b. In this process, the claws of the claw 123 are squeezed by the limiting structure 125 and are in a retracted state, and are able to pass through the current limiting structure 125 and the second support tube 220b. After the claw 123 is completely separated from the second support tube 220b, the constraint of the second flat satellite 210b is released, and the second flat satellite 210b and the second support tube 220b are thrown out by the rocket body 110. After the claw 123 passes through the current limiting structure 125, its claws are restored to the open state under the action of elastic force.

[0038] In step 303, the extension part recovery assembly is controlled to recover the extension part of the second preset length, so that the claw in the open state cooperates with the limiting structure of the third flat-panel satellite in the satellite stacking column to lock the third flat-panel satellite.

[0039] like Figure 1 , Figure 11-12 As shown, the extension part recovery assembly 124 recovers the extension part 122 of the second preset length, so that the top end of the extension part 122 reaches the third support tube 220c corresponding to the third flat-panel satellite 210c. At this time, the claw 123 is in an open state, and cooperates with the limiting structure 125 in the third support tube 220c corresponding to the third flat-panel satellite 210c to achieve the locking of the third flat-panel satellite 210c.

[0040] After that, steps 302-303 are repeated until all satellites are released. In this process, the flat-panel satellites in the satellite stacking column 200 have different separation linear velocities at the separation time due to the different mass center positions when stacked on the rocket 100. Under this linear velocity difference, the flat-panel satellites will gradually separate, and finally all flat-panels will be separated and released on orbit.

[0041] In the above process, the time taken for the claw 123 to move downward from the limiting structure 125 in the second support cylinder 220b of the second flat-panel satellite 210b through the limiting structure 125 until it completely moves out of the second support cylinder 220b is the separation time interval between the second flat-panel satellite 210b and the first flat-panel satellite 210a; the time taken for the claw 124 to completely move out of the second support cylinder 220b and gradually descend in the third support cylinder 220c and completely move out of the third support cylinder 220c is the separation time interval between the third flat-panel satellite 210c and the second flat-panel satellite 210b, and the separation of other layers of satellites is similar. Therefore, in one embodiment, the separation time interval of the front and rear layers of satellites is controlled by controlling the speed of contraction of the extension part 122, thereby controlling the relative distance between the front and rear satellites when they are separated. When the separation time interval is long enough, the relative distance between the front and rear satellites will be large enough, and even if the satellites rotate in attitude during separation, the front and rear satellites will not collide, thereby achieving the purpose of safe collision avoidance.

[0042] This embodiment can realize the time-sequence separation of satellites in different layers by controlling the speed of claw recovery, reasonably increase the distance between satellites and rockets / satellites, and reduce the probability of collision.

[0043] In one embodiment, the release structure 120 further includes a controller 126, a compression rod support 121 and an extension recovery assembly 124, so as to achieve the aforementioned functions. In one embodiment, the controller 126 may include a processor and a memory. The processor is used to execute a computer-readable program to implement the aforementioned steps 301-303, and the memory is used to store programs and / or data to be executed by the processor. For example, in Figure 5 In the embodiment of the present invention, the motor 124a is electrically connected to the controller 126. The motor 124a rotates under the control of the telescopic controller 124b, driving the thread on the telescopic rod to rotate to achieve telescopic movement. Figure 6 In the embodiment of the present invention, the motor 124a is electrically connected to the telescopic controller 126. The motor 124a rotates under the control of the telescopic controller 124b, driving the rope 124c wound inside the telescopic rod to pull downward and retract. In the case of two flat-panel satellites in a tandem, although Figure 4 Two controllers 126 are shown, but it is understood that the controllers 126 of the extension recovery assembly 124 can be integrated into one. In the embodiment of the present application, the pressure rod bracket 121 and the extension recovery assembly 124 can have their own controllers (controllers 126) or use an integrated controller together.

[0044] The separation and release mechanism of the stacked flat-panel satellite of the present application can achieve release by using structures such as extension parts and claws, and has a simple structure. The separation and release mechanism of the present application can reduce the risks of collision and failure that may occur during the satellite-rocket and intersatellite process because of the small 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.

[0045] 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.

[0046] 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.

[0047] 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 ...).

[0048] 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.

[0049] 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.

[0050] 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.

[0051] 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 essential spirit of the present application, they will fall within the scope of the present application.

Claims

1. A separation and release mechanism for a stacked flat-panel satellite, comprising: A pressure rod bracket, adapted to switch between a pressed state and an unfolded state, wherein in the pressed state, the pressure rod bracket is adapted to be pressed on the first flat-panel satellite at the uppermost layer of the satellite stacking column, and in the unfolded state, the pressure rod bracket is away from above the first flat-panel satellite; 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 claw exposed at and connected to the end of the extension part, the claw having an open state and a retracted state, with the normal state being the open state; and an extension part recovery assembly connected to the head end of the extension part, for driving the extension part to be recovered toward the body of the rocket.

2. The separation and release mechanism of the stacked flat-panel satellite as claimed in claim 1, characterized in that: Each flat-panel satellite of the satellite stacking column includes at least one supporting tube, and the supporting tubes in the same orientation in each flat-panel satellite are stacked in the stacking direction of each flat-panel satellite. The extending portion passes through the stacked supporting tubes, and the claw is locked in the target supporting tube in the open state and leaves the target supporting tube in the retracted state.

3. The separation and release mechanism of the stacked flat-panel satellite according to claim 1, characterized in that: The extension portion is a telescopic rod.

4. The separation and release mechanism of the stacked flat-panel satellite as claimed in claim 2, characterized in that: It also includes a limiting structure, which is suitable for being arranged in the supporting tube of each flat-panel satellite. 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.

5. The separation and release mechanism of the stacked flat-panel satellite as claimed in claim 4, characterized in that: Also included is a controller, connected to the compression rod support and the extension recovery assembly, and configured as follows: Controlling the compression rod bracket to switch from the compression state to the expansion state to release the first flat-panel satellite in the satellite stacking column; Controlling the extension part recovery assembly to recover the extension part of the first preset length, so that the clamping claw is squeezed by the limiting structure of the second flat-panel satellite in the satellite stacking column to be in the retracted state and leaves the limiting structure of the second flat-panel satellite to release the second flat-panel satellite, wherein the clamping claw returns to the open state under the action of elastic force after leaving the limiting structure of the second flat-panel satellite; The extension part recovery assembly is controlled to recover the extension part of the second preset length, so that the claw in the open state cooperates with the limiting structure of the third flat-panel satellite in the satellite stacking column to lock the third flat-panel satellite.

6. 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 separation and release mechanism for the separation of the satellite and the rocket includes: A pressure rod bracket, adapted to switch between a pressed state and an unfolded state, wherein in the pressed state, the pressure rod bracket is adapted to be pressed on the first flat-panel satellite at the uppermost layer of the satellite stacking column, and in the unfolded state, the pressure rod bracket is away from above the first flat-panel satellite; 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 claw, exposed at the end of the extension part and connected to the end of the extension part, the claw has an open state and a retracted state, and is normally in the open state; as well as 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.

7. The launch vehicle for stacked flat-panel satellites as claimed in claim 6, characterized in that: Each flat-panel satellite of the satellite stacking column includes at least one supporting tube, and the supporting tubes in the same orientation in each flat-panel satellite are stacked in the stacking direction of each flat-panel satellite. The extending portion passes through the stacked supporting tubes, and the claw is locked in the target supporting tube in the open state and leaves the target supporting tube in the retracted state.

8. The launch vehicle for stacked flat-panel satellites as claimed in claim 6, characterized in that: The extension portion is a telescopic rod.

9. The launch vehicle for stacked flat-panel satellites according to claim 6, characterized in that: The separation and 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.

10. The launch vehicle for stacked flat-panel satellites according to claim 9, characterized in that: Also included is a controller, connected to the compression rod support and the extension recovery assembly, and configured as follows: In response to the launch attitude of the launch vehicle meeting the requirement, controlling the compression rod bracket to switch from the pressed state to the unfolded state to release the first flat-panel satellite in the satellite stacking column; In response to the inter-satellite separation signal meeting the requirement, the extension part recovery assembly is controlled to recover the extension part of the first preset length, so that the clamping claw is squeezed by the limiting structure of the second flat-panel satellite in the satellite stacking column to be in the retracted state and leaves the limiting structure of the second flat-panel satellite to release the second flat-panel satellite, wherein the clamping claw returns to the open state under the action of elastic force after leaving the limiting structure of the second flat-panel satellite; The extension part recovery assembly is controlled to recover the extension part of the second preset length, so that the claw in the open state cooperates with the limiting structure of the third flat-panel satellite in the satellite stacking column to lock the third flat-panel satellite.

11. The launch vehicle for stacked flat-panel satellites according to claim 10, characterized in that: The controller is further configured to control the time interval between the moment when the claw leaves the limiting structure of the second flat-panel satellite and the moment when the claw leaves the limiting structure of the third flat-panel satellite, thereby controlling the time interval between the second flat-panel satellite and the third flat-panel satellite.

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