Satellite-rocket layered release system and release method for stacked satellites

Abstract

The present disclosure relates to a satellite-rocket layered release system and release method for a stacked satellite, wherein the system comprises a carrier assembly and a plurality of satellites arranged in a stack, and further comprises a layered release device. The device comprises a guide portion, a pushing portion, a release device and a restraint portion: the guide portion is arranged on the upper layer satellite; the pushing portion cooperates with the guide portion and provides a separation thrust on the lower layer satellite through elastic device pre-pressing; the release device is installed on the upper layer satellite and fixed to the lower layer satellite at one end of the restraint portion and connected to the output end of the release device at the other end, and the release device releases the restraint portion after being energized. The layered release method realizes the separation of each layer of satellites in turn through multiple rounds of unlocking and release operations to ensure the safety of satellite-rocket separation.

Description

Technical Field

[0001] This disclosure relates to the field of spacecraft, specifically to a stacked satellite-launcher layered release system and release method. Background Technology

[0002] Satellite-launch separation is a crucial component of spacecraft. Existing satellite-launch separation technologies typically employ pyrotechnics such as explosive bolts and separation nuts, which suffer from drawbacks including undetectability, high separation impact, severe pollution, and poor safety. Furthermore, their separation effectiveness is directly related to the satellite's mounting method. Traditional satellites are often designed with predetermined shapes, such as circles, and are mounted in a matrix on spacecraft for release after launch. Current satellite-launch separation methods suffer from low utilization of launch space and capacity. Launch vehicle adapters need to be adapted to the satellite configuration, requiring pyrotechnics to be mounted from the side to secure the satellite, resulting in complex adapter structures that occupy significant space and are heavy. Flat-plate stacking launches can maximize the utilization of launch space and capacity, but existing disordered release methods cannot guarantee satellite separation safety, and the inherent complexity of traditional separation structures further exacerbates safety hazards. Summary of the Invention

[0003] To address the problems existing in the prior art, this disclosure provides a stacked satellite-launcher layered release system and release method.

[0004] According to a first aspect of this disclosure, a satellite-launch layered release system for stacked satellites is provided, characterized in that it includes a launch vehicle assembly and a plurality of satellites disposed on the launch vehicle assembly, the plurality of satellites being configured to be stacked sequentially; and further includes a layered release device, the layered release device comprising:

[0005] The guide section is configured to be mounted on the upper-level satellite;

[0006] A propulsion unit, configured to guide and cooperate with the guide unit, and configured to pre-compress the next layer of satellite via an elastic device;

[0007] A release device, configured to be connected to the upper-level satellite;

[0008] The restraint part has one end configured to be connected to the next layer satellite and the other end configured to be connected to the output end of the releaser;

[0009] The release device is configured to release the restraint portion after being energized, and the pusher is configured to move relative to the guide portion under the force of the elastic device to push the upper-layer satellite to separate from the lower-layer satellite.

[0010] In one embodiment of this disclosure, the satellite is provided with a first mounting portion and a second mounting portion; the guide portion is configured as a fixed sleeve fixed on the first mounting portion, and the push portion is configured to guide and cooperate with the inner cavity of the fixed sleeve; the elastic device is configured to be disposed between the push portion and the fixed sleeve; the free end of the push portion is configured to be pre-pressed onto the second mounting portion of the next layer satellite by the elastic device.

[0011] In one embodiment of this disclosure, a retractor is provided on the second mounting portion, and the releaser is configured to retract the restraint portion after the restraint portion is released.

[0012] In one embodiment of this disclosure, a pin is provided at one end of the restraint portion, and the output end of the releaser is configured to cooperate with the pin.

[0013] In one embodiment of this disclosure, the pin shaft is provided with a pin hole, the output end of the release device is configured to extend into the pin hole, and is configured such that after the release device is energized, the output end of the release device disengages from the pin hole.

[0014] In one embodiment of this disclosure, the pushing part is configured as a movable sleeve with an inner cavity, and the restraining part is configured to pass through the movable sleeve from the position of the next layer satellite and connect to the output end of the releaser.

[0015] In one embodiment of this disclosure, the release device is configured to be fixed to the first mounting portion by a mounting base; the restraining portion is configured to pass through the movable sleeve and the mounting base in sequence and then connect to the output end of the release device.

[0016] In one embodiment of this disclosure, the restraint is a tension rope.

[0017] In one embodiment of this disclosure, multiple layered release devices are provided, and the multiple layered release devices are distributed in the circumferential direction of the satellite.

[0018] In one embodiment of this disclosure, the plurality of satellites includes a bottom-layer satellite at the bottom, a top-layer satellite at the top, and an intermediate-layer satellite between the bottom-layer satellite and the top-layer satellite; the layered release device is configured to be disposed on the intermediate-layer satellite and the bottom-layer satellite; and the pusher on the bottom-layer satellite is configured to pre-compress the launch vehicle assembly by the elastic device.

[0019] In one embodiment of this disclosure, a top-level release device is provided on the top-level satellite. The top-level release device includes a guide fixed on the top-level satellite and a pusher that is pre-pressed onto the next-level satellite by an elastic member.

[0020] It also includes a rigid restraint rod located outside the satellite, one end of which is configured to be movably connected to the launch vehicle assembly, and the other end of which is configured to be locked to the top-level satellite; the restraint rod is configured to restrain multiple satellites to the launch vehicle assembly, and is configured such that after the satellites are unlocked, the pusher moves relative to the guide under the force of the elastic member to push the top-level satellite to separate from the next layer of satellites.

[0021] In one embodiment of this disclosure, the satellite is provided with a power supply and a trigger switch for controlling the power supply; the trigger switch on the satellite is configured to abut against the upper-layer satellite and be triggered after the upper-layer satellite separates; the satellite is configured to control the power supply to power on the satellite after the trigger switch is triggered.

[0022] In one embodiment of this disclosure, the plurality of satellites include a bottom-layer satellite at the bottom, a top-layer satellite at the top, and an intermediate-layer satellite between the bottom-layer satellite and the top-layer satellite; the trigger switch of the top-layer satellite is configured to abut against the next-layer satellite and to be triggered after the top-layer satellite is separated, and the top-layer satellite is configured to control a power supply to power on the top-layer satellite after the trigger switch is triggered.

[0023] According to a second aspect of this disclosure, a method for layered release of stacked satellites via launch vehicle is also provided, characterized by comprising the following steps:

[0024] S1: Control the launch vehicle assembly to spin to the first attitude, control the restraint rods to unlock, and the top satellite automatically separates under the action of the pusher;

[0025] S2: Adjust the spin of the launch vehicle assembly to the second attitude, control the release device to release the restraint part, and the next layer satellite will automatically separate under the action of the thruster;

[0026] S3: Repeat step S2 until all satellites are separated from the launch vehicle assembly.

[0027] In one embodiment of this disclosure, when the upper-layer satellite separates, the trigger switch of the lower-layer satellite is triggered to power on the corresponding satellite.

[0028] In one embodiment of this disclosure, each layer of satellites is configured to control the corresponding release device to operate after power-on or after a predetermined time following power-on.

[0029] One beneficial effect of this disclosure is that the layered release system can achieve the sequential and orderly separation of stacked satellites by means of the coordinated action of the guide unit, propulsion unit, release device, and restraint unit in the layered release device, under the control of the release device, releasing the restraints layer by layer and using the elastic device to provide separation thrust. This avoids the safety problems such as satellite collisions and trajectory intersections caused by simultaneous release of multiple satellites or improper separation methods in the prior art, and has the advantages of controllable separation process, high safety, and strong structural adaptability.

[0030] Other features and advantages of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0031] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments of the present disclosure and, together with their description, serve to explain the principles of the present disclosure.

[0032] Figure 1 This is a schematic diagram of the stacked satellite and launch vehicle assembly in this disclosure;

[0033] Figure 2 This is a cross-sectional view of the layered release device under the compressed state in this disclosure;

[0034] Figure 3 yes Figure 2 Enlarged view of point A in the middle;

[0035] Figure 4 yes Figure 2 Enlarged view at point B;

[0036] Figure 5 This is a partial cross-sectional view of the layered release device under the compressed state in this disclosure;

[0037] Figure 6 yes Figure 5 A magnified view at point C;

[0038] Figure 7 yes Figure 5 A magnified view at point D;

[0039] Figure 8 This is a schematic diagram showing the connection of some components of the layered release device in this disclosure;

[0040] Figure 9 This is a structural schematic diagram of the multi-layered stacked satellite, the layered release device, and the restraint rods disclosed herein;

[0041] Figure 10 This is a schematic diagram of the trigger switches of the top-level satellite, intermediate-level satellite, and bottom-level satellite under the compressed state in this disclosure;

[0042] Figure 11This is a schematic diagram of the trigger switch in the top-level satellite separation state in this disclosure.

[0043] Figures 1 to 11 The one-to-one correspondence between the component names and the reference numerals in the figures is as follows:

[0044] 1. Launch vehicle assembly; 2. Satellite; 201. Top-layer satellite; 202. Middle-layer satellite; 203. Bottom-layer satellite; 3. Layered release device; 21. First mounting section; 22. Second mounting section; 31. Guide section; 32. Pushing section; 33. Elastic device; 34. Release device; 35. Restraint section; 351. Pin shaft; 352. Pin hole; 36. Retractor; 37. Mounting base; 41. Guide component; 42. Elastic component; 43. Pushing component; 5. Restraint rod; 6. Trigger switch. Detailed Implementation

[0045] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the present disclosure.

[0046] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this disclosure or its application or use.

[0047] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0048] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0049] In this article, terms such as "up," "down," "front," "back," "left," and "right" are used only to indicate the relative positional relationship between related parts, rather than to define the absolute position of these related parts.

[0050] In this article, "first," "second," etc., are used only to distinguish one another, and not to indicate degree of importance, order, or prerequisite for each other.

[0051] In this document, terms such as “equal” and “same” are not strict mathematical and / or geometric limitations, but also include errors that are understandable to those skilled in the art and permissible in manufacturing or use.

[0052] This disclosure provides a satellite-launcher layered release system and method for stacked satellites, and more specifically, a satellite-launcher release system and method that achieves orderly layer-by-layer separation of stacked satellites through a layered release device. The purpose of this disclosure is to address the problem that existing multi-satellite stacking separation methods (such as launch vehicle spin separation, inter-satellite spring separation, etc.) cannot guarantee separation safety, and to solve the problem of potential collisions that may occur during the separation process of stacked satellites.

[0053] This system utilizes a layered release mechanism with a guide section providing precise guidance, a propulsion section providing separation thrust under the action of an elastic device, and a release mechanism controlling the unlocking timing of the restraint section. This allows for the sequential separation of satellites in a predetermined order, offering advantages such as orderly separation, high safety, and precise control. Through this system, a multi-round attitude adjustment and unlocking / release step-by-step operation method is employed to achieve the safe separation of stacked satellites from the launch vehicle assembly.

[0054] The specific embodiments of this disclosure are described below with reference to the accompanying drawings.

[0055] refer to Figures 1 to 8 This disclosure provides a stacked satellite launch system for layered release, including a launch vehicle assembly 1 and multiple satellites 2 mounted on the launch vehicle assembly 1, wherein the multiple satellites 2 are configured to be stacked sequentially. The launch vehicle assembly 1 carries the stacked satellites 2 into a predetermined orbit and adjusts its own spin attitude (e.g., adjusting the angles of the pitch axis Y-axis and / or yaw axis Z-axis) to provide an adaptive attitude for the separation of each layer of satellites 2, ensuring that the separation trajectories of the satellites 2 do not intersect.

[0056] In one embodiment of this disclosure, reference is made to Figure 1 Satellite 2 is constructed as a flat plate, which allows multiple satellites to be stacked together in the direction of their thickness. This not only increases the number of satellites that can be stacked, but also ensures the stability of the installation between multiple satellites.

[0057] The satellite-launch layered release system disclosed herein also includes a layered release device 3, which comprises a guide section 31, a propulsion section 32, a release device 34, and a restraint section 35. The guide section 31 is mounted on the upper-layer satellite, the propulsion section 32 is guided and coordinated with the guide section 31, and the propulsion section 32 pre-presses the lower-layer satellite via an elastic device 33.

[0058] Specifically, refer to Figure 1The satellite 2 disclosed herein includes a satellite body and a base connected to the satellite body. The base can be fixedly installed at a notch on the outside of the satellite 2, saving space, not affecting satellite separation, and not damaging the satellite structure. The base and the satellite body can be installed in a manner well known to those skilled in the art, which will not be described in detail here. The guide part 31, the push part 32, the release device 34, and the restraint part 35 are all located within the cavity of the base. The guide part 31 provides a guiding engagement position for the push part 32, allowing the push part 32 to move relative to the guide part 31 in a predetermined direction.

[0059] refer to Figure 2 and Figure 4 The guide section 31 is mounted on the upper-layer satellite, and the push section 32 can move relative to the guide section 31 towards the lower-layer satellite. When two adjacent satellites are stacked together, the push section 32 is pre-pressed onto the lower-layer satellite by the elastic device 33, which makes the push section 32 tend to move towards the lower-layer satellite under the action of the elastic device 33.

[0060] The propulsion unit 32 provides initial velocity for the separation of stacked satellites through the elastic device 33, ensuring a smooth separation process and controllable initial velocity, avoiding attitude deviation of satellite 2 due to unstable separation force, and ensuring that the separation direction is consistent with the preset trajectory.

[0061] Continue to refer to Figure 4 The satellite-launch layered release system disclosed herein also includes a releaser 34 and a restraint unit 35, wherein the releaser 34 is connected to the upper-layer satellite. One end of the restraint unit 35 is connected to the lower-layer satellite, and the other end is connected to the output end of the releaser 34.

[0062] Specifically, one end of the restraint part 35 is connected to the next layer satellite, and the other end is connected to the output of the release device 34 on the upper layer satellite. This allows two adjacent satellites to be restrained together. Before release, a pre-tension force maintains the stacking constraint between the upper and lower layers of satellites 2, ensuring a stable stacking state. The release device 34 of this disclosure releases the constraint on the restraint part 35 after being energized, causing the restraint part 35 to change from its initial taut state to a free state. At this point, the release of the restraint part 35 releases the stacking constraint between the two adjacent satellites. This disclosure provides a precise unlocking trigger mechanism for satellite 2 separation by releasing the constraint on the restraint part 35 through the release device 34, ensuring controllable timing of the separation operation.

[0063] In this disclosed satellite-rocket layered release system, the releaser 34 releases the restraint part 35 after being energized. The pushing part 32 moves relative to the guide part 31 under the force of the elastic device 33, thereby pushing the upper and lower layer satellites apart. One end of the restraint part 35 is connected to the output end of the releaser 34. When the releaser 34 is energized, its output end releases the restraint part 35, leaving the restraint part 35, which connects the upper and lower layers of satellites 2, in a free state, thus releasing the clamping force acting on the upper and lower layers of satellites 2. When the clamping force acting on the upper and lower layers of satellites 2 is lost, the elastic device 33 of the pushing part 32 rebounds. The rebound force causes the pushing part 32 to move relative to the guide part 31 under its own force, applying a reverse force to the guide part 31, thereby pushing the upper and lower layers of satellites 2 apart.

[0064] The satellite-rocket layered release system disclosed herein can realize the layered release of stacked satellites through the layered release device 3, and can provide a precise unlocking trigger mechanism for the layered separation of satellite 2 by controlling the power-on timing of the release device, ensuring that the timing of the separation operation is controllable and guaranteeing the safety of satellite-rocket separation.

[0065] The following section uses two satellites as examples to provide a detailed description of the proposed scheme, with reference to... Figure 2 , Figure 3 Two adjacent satellites are designated as Satellite 1 and Satellite 2. Satellite 1 and Satellite 2 are adjacent and stacked together. Satellite 1 is located on the side furthest from Launch Vehicle Assembly 1 relative to Satellite 2. (Refer to...) Figure 1 , Figure 2 In the view direction, the first satellite is the upper layer satellite of the second satellite, and correspondingly, the second satellite is the lower layer satellite of the first satellite. The first satellite is equipped with a first base, and the second satellite is equipped with a second base. When the first and second satellites are stacked together, the first and second bases are correspondingly positioned, and both bases are constructed to have hollow inner cavities. Layered release devices 3 are installed on the first and second bases.

[0066] like Figure 4 As shown, in order to realize the installation of the layered release device 3 on the first base and the second base, a first mounting part 21 and a second mounting part 22 are respectively provided in the inner cavity of the first base and the second base. The guide part 31 of this disclosure can be connected to the first mounting part 21, for example, by bolts, screws, welding or other methods known to those skilled in the art. In a specific embodiment of this disclosure, the guide part 31 is fixed to a fixing sleeve on the first mounting part 21, and the pushing part 32 is guided and engaged with the inner cavity of the fixing sleeve.

[0067] Specifically, such as Figure 2 and Figure 4As shown, the first mounting portion 21 and the second mounting portion 22 can be disposed on the inner wall of the first base and the second base, and are configured to extend radially inward from the inner wall to form a mounting platform for mounting other components. Within the first base or the second base, the first mounting portion 21 is located below the second mounting portion 22, allowing the first mounting portion 21 within the first base to cooperate with the second mounting portion 22. The first mounting portion 21 has a first mounting hole, and the second mounting portion 22 has a second mounting hole, with the axes of the two holes strictly coaxial, i.e., coinciding with a common straight line perpendicular to the cavity wall. Both the first mounting portion 21 and the second mounting portion 22 have upper and lower end faces. The guide portion 31 is a fixed sleeve with a through-cavity, one end of which is fixedly mounted to the lower end face of the first mounting portion 21 of the first base, and the fixed sleeve is coaxially mounted with the first mounting hole of the first mounting portion 21. The pushing part 32 can be built into the inner cavity of the fixed sleeve and penetrate the inner cavity of the fixed sleeve in its length direction, so that the pushing part 32 can be guided and engaged with the inner cavity of the fixed sleeve. The pushing part 32 can move relative to the fixed sleeve on its own axis, for example, by relative displacement toward or away from the second base.

[0068] An elastic device 33 is disposed between the pushing part 32 and the fixed sleeve. The free end of the pushing part 32 is pre-pressed onto the second mounting part 22 of the next-layer satellite by the elastic device 33. Specifically, when the first satellite, which is the upper-layer satellite, and the second satellite, which is the lower-layer satellite, are stacked and installed, the first mounting part 21 of the first base and the second mounting part 22 of the second base are aligned, which allows the pushing part 32 in the first base to abut against the second mounting part 22 of the second base. The elastic device 33 can be disposed between the pushing part 32 and the fixed sleeve. The elastic device 33 disclosed herein can be a spring or other component that can provide elastic force. One end of the elastic device 33 abuts against the fixed sleeve, and the other end abuts against the flange provided on the pushing part 32. Thus, under the action of the elastic device 33, the free end of the pushing part 32 is pre-pressed onto the upper surface of the second mounting part 22 of the second base. When the release device 34 releases the restraint part 35, the push part 32 extends towards the second mounting part 22 relative to the guide part 31 under the action of the elastic device 33. Since the free end of the push part 32 is already in contact with the second mounting part 22, the guide part 31 moves the first base away from the second mounting part 22 under the reaction force, and finally realizes the separation of the first satellite and the second satellite.

[0069] In one embodiment of this disclosure, such as Figure 4 , Figure 7As shown, a retractor 36 is provided on the second mounting part 22. After the releaser 34 releases the restraint part 35, the retractor 36 winds up the restraint part 35. Specifically, a retractor 36 is fixedly installed on the lower end face of the second mounting part 22 of the layered release device 3 for each layer of satellite 2, and the retractor 36 is connected to one end of the restraint part 35. When the releaser 34 is energized, its output end releases the restraint part 35, and the restraint part 35 used to connect the upper and lower layers of satellite 2 is in a free state. The retractor 36 connected to one end of it winds up the restraint part 35 to prevent the restraint part 35 from getting tangled with other parts in the free state, causing device malfunction and posing a collision hazard to the satellite 2 during separation.

[0070] In one embodiment of this disclosure, reference is made to Figure 4 One end of the restraint part 35 is provided with a pin 351, and the output end of the release device 34 cooperates with the pin 351. Specifically, in order to connect the restraint part 35 and the release device 34, a pin 351 is provided at the end of the restraint part 35 that connects to the release device 34, and the pin 351 is connected to the output end of the release device 34. Through the detachable cooperation between the pin 351 and the output end of the release device 34, the restraint part 35 can controllably restrain the upper and lower layer satellites 2—when the release device 34 is not powered on, the cooperation is tight to maintain stacking constraint; when powered on, the cooperation is released to release the restraint, ensuring the reliability of constraint and release.

[0071] In one embodiment of this disclosure, the restraint part 35 is a tension rope. Specifically, when the multi-layer satellite 2 is stacked in a compressed state, the tension rope assists in the compressed state of the multi-layer satellite 2, using its own tension force to tighten the upper and lower layers of satellite 2. Since the tension rope needs to pass through multiple sleeves, its surface needs to have low friction to reduce wear, while maintaining flexibility to allow the retractor 36 to wind it back. The restraint part 35 of this disclosure uses a flexible tension rope, which has good mechanical adaptability. With the base (stacked column) designed with an anti-shear cone, slight misalignment does not affect the function of the mechanism, resulting in good adaptability and high reliability.

[0072] In one embodiment of this disclosure, such as Figure 4 As shown, a pin hole 352 is provided on the pin shaft 351. The output end of the release device 34 extends into the pin hole 352, and after the release device 34 is energized, the output end of the release device 34 disengages from the pin hole 352. Specifically, a pin hole 352 is provided on the pin shaft 351 that connects the binding part 35 to the output end of the release device 34. The shape of the output end of the release device 34 is configured to extend into the pin hole 352 and match the size of the pin hole 352. The binding part 35 is connected to the output end of the release device 34 through the pin hole 352 on the pin shaft 351. When the release device 34 is energized, the output end of the release device 34 disengages from the pin hole 352 of the binding part 35, thereby releasing the binding part 35, which is then wound up by the retractor 36 connected to the other end of the binding part 35.

[0073] In one embodiment of this disclosure, the pushing part 32 is a movable sleeve with an inner cavity, and the restraining part 35 passes through the movable sleeve from the position of the next layer satellite and is connected to the output end of the release device 34. Specifically, as Figure 4 and Figure 7 As shown, the pushing part 32 is guided and engaged with the inner cavity of the fixed sleeve. The body of the pushing part 32 is a movable sleeve with an inner cavity. The movable sleeve can extend into the fixed sleeve and extend out from the first mounting hole of the first mounting part 37. One end of the binding part 35 is connected to the retractor 36 installed on the lower end face of the second mounting part 22 of the next layer satellite. Its other end first passes through the second mounting hole of the second mounting part 22, extends into the inner cavity of the movable sleeve and passes through the movable sleeve, and then connects to the output end of the releaser 34 of the layer release device 3 located on the upper layer satellite.

[0074] In one embodiment of this disclosure, such as Figure 4 and Figure 7 As shown, the release device 34 is fixed to the first mounting portion 21 via the mounting base 37; the restraining portion 35 passes through the movable sleeve and the mounting base 37 in sequence and connects to the output end of the release device 34. Specifically, the mounting base 37 has an inner cavity, and one end of it connected to the upper end face of the first mounting portion 21 has an opening. This opening matches the size of the first mounting hole of the first mounting portion 21, and the mounting base 37 is coaxially mounted with the first mounting hole and fixedly connected to the upper end face of the first mounting portion 21. The release device 34 is fixed to the first mounting portion 21 of the layered release device 3 of the upper satellite via the mounting base 37. The pushing portion 32, i.e., the movable sleeve, extends out from the first mounting hole of the first mounting portion 21 after passing through the inner cavity of the guide portion 31 and continues to extend into the inner cavity of the mounting base 37. That is, the inner cavity size of the mounting base 37 can match the movable sleeve, so that the movable sleeve can also guide and cooperate with the mounting base 37 and can generate frictionless displacement relative to the mounting base 37.

[0075] Continue to refer to Figure 4 and Figure 7 One end of the restraint part 35 is connected to the retractor 36 located on the lower end face of the second mounting part 22 of the next layer satellite, and the other end extends upward, passing through the second mounting hole, the movable sleeve, and the mounting base 37 in sequence, and then connecting to the output end of the release device 34 located on the mounting base 37. The restraint part 35 is connected at one end to the layer release device 3 of the next layer satellite and at the other end to the layer release device 3 of the previous layer satellite. It uses its own tension force to pull the layer release devices 3 of the two layers of satellites together, and then presses the two layers of satellites together. In the stacked state of the multi-layer satellites 2, the restraint part 35 of each layer of satellite 2 is in a pre-tightened state. The tension force of the tension rope and the pre-pressure of the elastic device 33 are balanced to maintain the stable stacking of the multi-layer satellites 2, ensuring that there is no relative displacement due to vibration, impact or other factors during the launch process.

[0076] In one embodiment of this disclosure, to achieve satellite stacking, multiple layer release devices 3 are provided, and the multiple layer release devices 3 are distributed in the circumferential direction of the satellite 2. Specifically, refer to... Figure 9 Each layer of satellites has multiple bases in the circumferential direction. When stacked, the bases of adjacent satellites are aligned. A layered release device 3 can be installed in each base, thereby providing a binding force in the circumferential direction of the satellites. When releasing satellites layer by layer, the release device 3 in the circumferential direction of the satellites simultaneously releases the binding part to push the corresponding satellites outward evenly, achieving safe separation of the satellites. In one embodiment of this disclosure, the elastic device 33 in each layered release device 3 is configured to provide different elastic forces according to the center of mass of the satellite. That is, the elastic forces provided by the different elastic devices 33 in the circumferential direction between two adjacent satellites are different, specifically related to the position of the center of mass of the satellite. By setting the elastic force differently according to the position of the center of mass of each layer of satellites, the influence of the center of mass offset of satellites on the separation attitude can be offset, ensuring that the force on satellites is balanced during separation, avoiding attitude deflection caused by unilateral force, and ensuring the accuracy of the separation trajectory.

[0077] In one specific embodiment of this disclosure, such as Figure 9 As shown, since the center of mass of each layer of satellites 2 may differ, three layer release devices 3 are installed in the circumferential direction of each layer of satellites 2. The three elastic devices 33 provide three different elastic forces depending on the position of the center of mass. This is because each layer of satellites 2 uses the reaction force generated by the rebound of the elastic devices 33 of the layer release devices 3 to detach from the next layer of satellites. If all three springs provide the same elastic force when the centers of mass of each layer of satellites 2 are different, the satellites 2 may easily deflect when separating from the launch vehicle assembly 1, potentially colliding with other satellites 2 during the separation process. Therefore, adjusting the elastic forces provided by the three elastic devices 33 according to the center of mass of each layer of satellites 2 can prevent the satellites 2 from rotating during separation, ensuring a smooth detachment. For example, when the center of mass of the satellite is close to one of the layer release devices 3, the elastic force provided by the elastic device 33 of that layer release device 3 should be greater than the elastic forces of the other elastic devices 33.

[0078] The satellite-launch layered release system disclosed herein can fix each layer of satellites through the aforementioned layered release device 3, and release them layer by layer from the first layer to the last layer during release.

[0079] In one embodiment of this disclosure, such as Figure 9As shown, the multiple satellites 2 include a bottom layer satellite 203 at the bottom, a top layer satellite 201 at the top, and an intermediate layer satellite 202 located between the bottom layer satellite 203 and the top layer satellite. From a spatial distribution perspective, the multi-layer satellites 2 can be distinguished according to their positional relationship as follows: the bottom layer satellite 203, which is connected to the launch vehicle assembly 1 and located at the bottom of all satellites 2; the top layer satellite 201, located at the top of the multi-layer satellites 2; and the remaining multi-layer satellites 2 are collectively referred to as the intermediate layer satellites 202.

[0080] The layered release device 3 is installed on the intermediate layer satellite 202 and the bottom layer satellite 203, and the pusher 32 on the bottom layer satellite 203 pre-presses the carrier assembly 1 through the elastic device 33. Specifically, after the multiple layers of satellites 2 are stacked, the top layer satellite 201 does not need to press against any other satellites 2 above it, so there is no need to install any other device on the top layer satellite 201 that is equivalent to or cooperates with the second mounting part 22. Therefore, the layered release device 3 is not installed on the top layer satellite 201. The intermediate layer satellite 202, located between the bottom layer satellite 203 and the top layer satellite 201, has multiple layers, and each layer of satellites 2 needs to be equipped with a layered release device 3 for mutual pressing and release. The bottom layer satellite 203, located at the bottom of all satellites 2, needs to be connected to the carrier assembly 1, so the pusher 32 in the layered release device 3 on the bottom layer satellite 203 needs to be pre-pressed onto the carrier assembly 1 through its elastic device 33. The launch vehicle assembly 1 has a plate-like structure at one end near the bottom satellite 203, and the layered release device 3 of the bottom satellite 203 abuts against the plate-like structure.

[0081] In one embodiment of this disclosure, a top-level release device is provided on the top-level satellite 201. The top-level release device includes a guide member 41 fixed to the top-level satellite 201 and a pusher member pre-pressed onto the next-layer satellite by an elastic member 42. Unlike the bottom-level satellite 203 and the intermediate-level satellite 202, the top-level satellite 201, based on its positional relationship and pressing method, is provided with a top-level release device different from the layered release device 3. For example... Figure 3 and Figure 6 As shown, the top-level release device includes a guide member 41 fixed to the first mounting part 21 of the top-level satellite 201, which is equivalent to the guide part 31 of the layered release device 3. A pusher member, which is pre-pressed onto the second mounting part 22 of the next-layer satellite by an elastic member 42, is equivalent to the pusher part 32 of the layered release device 3, wherein the elastic member 42 is equivalent to the elastic device 33.

[0082] Unlike the layered release device 3, the top-level release device lacks the restraint part 35, i.e., the tension rope that is tightened to the next layer satellite, and therefore lacks the retractor 36 connected to the restraint part 35. Compared to the layered release device 3, the top-level release device also does not include the device that functions as the releaser 34 and the mounting base 37. Furthermore, multiple top-level release devices should be provided, distributed along the circumferential direction of the top-level satellite 201, corresponding to the positions of the next layer satellites. The elastic element 42 in each top-level release device provides different elastic forces according to the center of mass of the top-level satellite 201, ensuring that the top-level satellite 201 does not rotate during separation and can detach smoothly.

[0083] In order to bind the top-level satellite 201 to the next-level satellite, continue to refer to Figure 9 The top-level release device also includes a rigid restraint rod 5 located on the outside of satellite 2. One end of the restraint rod 5 is movably connected to the launch assembly 1, and the other end is locked to the top-level satellite 201. Therefore, the top-level satellite 201 does not have a restraint part 35 because the top-level satellite 201 is pressed against the intermediate-layer satellite 202 and the bottom-level satellite by the restraint rod 5. Specifically, one end of the restraint rod 5 is hinged to the launch assembly 1, and the other end is locked to the outside of the top-level release device of the top-level satellite 201, providing a downward force to the top-level satellite 201, pressing the top-level satellite 201 against the next layer of satellites, thereby pressing all the stacked multi-layer satellites 2 against the launch assembly 1. It should be noted that the intermediate layer satellite 202 and the bottom layer satellite 203 are still stacked and secured together by the corresponding layer release device 3. One end of the restraint rod 5 is hinged to the launch assembly 1, and the other end cooperates with the top layer satellite 201 to provide downward clamping force for the top layer satellite 201. In addition to securing the top layer satellite 201 to the next layer of satellites, it also provides further restraint force to other satellites, ensuring the safety of satellite stacking.

[0084] The restraint rod 5 secures multiple satellites 2 to the launch assembly 1. After the satellites 2 are unlocked, the pusher moves relative to the guide 41 under the force of the elastic member 42, thereby pushing the top satellite 201 to separate from the next layer of satellites. Specifically, one end of the restraint rod 5 is locked to the top of the top release device of the top satellite 201. The restraint rod 5 can be unlocked from the top satellite 201 by pyrotechnics or an electronic control device, which will not be described in detail here. When the locked part is unlocked, the top satellite 201 loses the clamping force pressing against the next layer of satellites. At this time, the pusher of the top release device moves relative to the guide 41 under the force of the elastic member 42, providing a reverse thrust to the top satellite 201, thereby pushing the top satellite 201 to separate from the next layer of satellites. Therefore, the top satellite 201 separates immediately after the restraint rod 5 is unlocked.

[0085] refer to Figure 9Multiple restraint rods 5 can be provided, and these rods 5 can be installed on the bases of the multi-layer satellite 2. Specifically, at multiple notches along the circumferential direction of the satellite, a columnar body is fixed by multiple corresponding bases, which are interconnected. The restraint rods 5 press and fix these to the launch assembly 1 by the bases, thereby pressing the multi-layer satellite 2 onto the launch assembly 1. The locking points of the restraint rods 5 and the top satellite 201 are distributed on the circumferential edge of the top satellite 201, ensuring that the restraint force on the top satellite 201 is evenly applied to the entire satellite 2, preventing the top satellite 201 from tilting or shifting in the stacked state due to unilateral force. Each restraint rod 5 is connected to the base of the top satellite 201 through an independent locking structure, and the unlocking is synchronized, ensuring that the top satellite 201 is subjected to balanced force in the initial separation stage, providing a stable foundation for the smooth propulsion of the subsequent pusher, and further ensuring the accuracy of the separation trajectory of the top satellite 201.

[0086] The satellite-rocket separation system disclosed herein requires multiple restraint rods 5 to unlock all satellites before release. After unlocking, the top-level satellite, having lost its restraint, separates from the next-level satellite under the action of its elastic element 42 and pushing element. Following the separation of the top-level satellite, the release device 34 of the intermediate-level satellite 202 releases its restraint part 35 upon energization, causing the pushing element 32 to move under the force of its elastic device 33, thereby pushing the satellite of that layer to separate from the next-next-layer satellite. Satellite separation is achieved step-by-step in this manner.

[0087] In the above embodiment, the top-level satellite can automatically separate after the restraint rod 5 is unlocked. After the top-level satellite separates, the separation of its lower-level satellites requires the satellites to be powered on and separated by their own release mechanisms. Additionally, each layer of satellites has a power control trigger switch 6. To ensure safety, the power supply will not provide power to the components inside the satellite before it enters high altitude. After entering high altitude, the power-on and release timing of the satellites can be controlled. Based on this, in one embodiment of this disclosure, such as... Figure 10 As shown, satellite 2 is equipped with a power supply and a trigger switch 6 for controlling the power supply. The trigger switch 6 on satellite 2 is in contact with the upper-layer satellite and is triggered after the upper-layer satellite is separated. After the trigger switch 6 is triggered, the control power supply of satellite 2 powers on satellite 2.

[0088] Specifically, in the stacked state of multiple satellites 2, the trigger switch 6 of the multiple satellites 2 can be located on the upper surface of satellite 2. The trigger switch 6 is mechanically pressed by the upper satellite and is in a normally closed or locked state, ensuring that the power circuit is disconnected when satellite 2 is not separated. This prevents accidental power-on caused by vibration, impact or electromagnetic interference during the launch phase and ensures that satellite 2 is absolutely powered off during the non-separation phase.

[0089] After the upper-layer satellite separates, the trigger switch 6 loses pressure, and the mechanical reset closes the circuit, ensuring strict synchronization between the separation of the upper-layer satellite and the power-on process of the lower-layer satellite. Each layer of satellite 2 is equipped with an independent battery to avoid cascading failures caused by cross-layer circuits. After the multi-layer stacked satellites 2 arrive at the predetermined orbit aboard the launch vehicle assembly 1, the launch vehicle assembly 1 adjusts its attitude and spins. After the upper-layer satellite separates, the trigger switch 6 of the lower-layer satellite mechanically resets, controlling the power supply to power up satellite 2. The power-on time for each layer of satellite 2 is approximately 1 minute. After power-on, the layer release device 3 of that layer of satellite 2 can be unlocked immediately to achieve separation.

[0090] Specifically, after the trigger switch 6 is activated, the control power supply powers the release device 34 of satellite 2. When the release device 34 is powered on, its output end disengages from the pin hole 352 of the pin shaft 351, releasing the restraining part 35. As the retractor 36 winds up the restraining part 35, the elastic device 33 loses pressure and rebounds, thus separating from the lower-level satellites. By gradually releasing all satellites in this manner, the timing of release can be precisely controlled, achieving the purpose of layered release and layered control.

[0091] In one embodiment of this disclosure, such as Figure 10 and Figure 11 As shown, the multiple satellites 2 include a bottom-layer satellite 203 at the bottom, a top-layer satellite 201 at the top, and an intermediate-layer satellite 202 located between the bottom-layer satellite 203 and the top-layer satellite 201. The trigger switch 6 of the top-layer satellite 201 is engaged with the next-layer satellite and is triggered after the top-layer satellite 201 is separated. After the trigger switch 6 is triggered, the control power supply of the top-layer satellite 201 powers on the top-layer satellite 201.

[0092] Specifically, in the stacked state of multi-layer satellites 2, from the perspective of spatial distribution, the multi-layer satellites 2 can be distinguished according to their positional relationship as follows: the bottom layer satellite 203, which is connected to the launch vehicle assembly 1 and located at the bottom of all satellites 2; the top layer satellite 201, which is located at the top of the multi-layer satellites 2; and the remaining multi-layer satellites 2 are collectively referred to as the intermediate layer satellites 202.

[0093] In this system, the trigger switches 6 of the intermediate layer satellite 202 and the bottom layer satellite 203 are located on the upper surface of each layer satellite 2, and are mechanically pressed against by the satellite above. The top layer satellite 201, however, differs from the bottom layer satellite 203 and the intermediate layer satellite 202. Its trigger switch 6 is located on the lower surface of the top layer satellite 201, pressing against the satellite below it and remaining in a closed or locked state. When the restraining rod 5 of the top layer release device unlocks from the top layer satellite 201, the top layer satellite 201 loses its clamping force and automatically separates. Figure 11 As shown, when the top satellite 201 separates, the trigger switch 6 located on the lower end face of the top satellite 201 resets the closed circuit and controls the power supply of the top satellite 201 to power it on.

[0094] Simultaneously, the trigger switch 6 of the intermediate layer satellite 202 below the top-level satellite 201 is reset and powered on for approximately 1 minute. Immediately after power-on, the layer release device 3 is unlocked to achieve satellite separation. The launch vehicle assembly 1 continues to spin, and the multi-layered stacked satellites 2 repeat the above power-on, unlocking, and layer release steps until all satellites 2 are separated from the launch vehicle assembly 1.

[0095] In a second aspect of this disclosure, a method for layered release of stacked satellites using a launch vehicle is also provided, employing the aforementioned layered release system. This method includes the following steps:

[0096] S1: Control the launch vehicle assembly 1 to spin to the first attitude, control the restraint rod 5 to unlock, and the top satellite 201 will automatically separate under the action of the pusher;

[0097] S2: Adjust the spin of the launch vehicle assembly 1 to the second attitude, control the release device 34 to release the restraint part 35, and the next layer satellite will automatically separate under the action of the propulsion part 32;

[0098] S3: Repeat step S2 until all satellites 2 are separated from launch vehicle 1.

[0099] Specifically, in step S1, the first attitude is the optimal attitude for the separation of the top-level satellite 201. By adjusting the deflection angles of the launch vehicle assembly 1 around the Z-axis and Y-axis, it is ensured that the separation trajectory of the top-level satellite 201 does not intersect with the remaining satellites 2 and the launch vehicle assembly 1. After the restraint rod 5 is unlocked, the top-level satellite 201 loses its downward constraint. The pusher moves along the guide 41 under the pre-pressure of the elastic member 42, applying an upward thrust to the top-level satellite 201, causing it to separate smoothly in the preset direction.

[0100] In step S2, the second attitude is a specific attitude for the separation of the next layer of satellites. By readjusting the angle of the launch vehicle assembly 1 around the Z-axis or Y-axis, the separation trajectory of the satellite 2 in this layer is prevented from overlapping with the trajectory of the already separated top-level satellite 201 and the launch vehicle assembly 1. After the release device 34 is energized, its output end disengages from the restraint part 35. The pre-pressure drive of the elastic device 33 drives the push part 32 to move along the guide part 31, applying a separation thrust to the next layer of satellites, so that the satellite 2 in this layer smoothly separates along the preset trajectory.

[0101] In step S3, each time the launch vehicle assembly 1 repeats step S2, it adjusts to the corresponding attitude according to the position of the next layer satellite and the trajectory of the separated satellite 2. The release device 34 releases the restraint part 35 and the pusher 32 provides thrust in a coordinated manner, so that the satellites 2 of each layer separate in sequence, and finally ensures that all satellites 2 are safely separated from the launch vehicle assembly 1.

[0102] In one embodiment of this disclosure, after the upper-layer satellite separates, the trigger switch 6 of the lower-layer satellite is triggered to power on the corresponding satellite 2. In the above-described layer-by-layer release step, after the upper-layer satellite separates, the trigger switch 6 of the lower-layer satellite is reset due to the loss of pressure from the upper-layer satellite, the trigger power circuit is turned on, and power is supplied to the release device 34 and other components of the satellite 2 at that layer, providing power support for subsequent separation operations. Unlike the power-on timing of other satellites, the trigger switch 6 of the top-layer satellite 201 is also triggered after separation, thereby powering on the top-layer satellite 201.

[0103] In one embodiment of this disclosure, each layer of satellites 2 is configured to control the corresponding release device 34 to operate after power-on or after a predetermined time following power-on. Specifically, after each layer of satellites 2 has been powered on (approximately 1 minute), or after a delay time agreed upon with the launch vehicle has elapsed, the satellite 2 control system sends an electrical signal to the release device 34, controlling the output of the release device 34 to disengage from the restraint part 35. Subsequently, the separation of that layer of satellites 2 is achieved through the thrust of the pusher 32, ensuring precise synchronization between the separation timing and the launch vehicle attitude adjustment.

[0104] In one specific embodiment of this disclosure, taking an N-layer satellite stacked on a launch vehicle assembly 1 as an example, the working process of the satellite-rocket layered release system of this disclosure will be described in detail. The Nth layer of satellites is the aforementioned top-layer satellite 201, the first layer of satellites is the aforementioned bottom-layer satellite 203, and those in between are the aforementioned intermediate-layer satellites 202. The specific steps are as follows:

[0105] S100, the launch vehicle assembly 1, carrying N layers of stacked satellites, arrives at the predetermined orbit and adjusts the attitude of the launch vehicle assembly;

[0106] Specifically, for example, it can spin according to its pitch axis or yaw axis to control the launch vehicle assembly 1 to spin to a preset attitude. This attitude can be achieved through the attitude control system of the launch vehicle assembly 1 to ensure that the satellite and the launch vehicle assembly 1 have no spatial overlap.

[0107] S200, Nth layer satellite separation;

[0108] The rigid restraint rod 5 located outside satellite 2 receives the unlocking signal, unlocks the restraint rod 5 from the satellite, and flips outward around the hinge point, releasing the downward restraint force on all satellites, including the Nth layer satellites.

[0109] The Nth-layer satellite is equipped with a top-layer release device, whose guide member 41 and push member form a guiding engagement. After the multiple sets of restraint rods 5 are unlocked, the elastic member 42 between the push member and the guide member 41 releases its pre-pressure, causing the push member to tend to move downwards along the inner cavity of the guide member 41, as its lower end contacts the second mounting part 22 of the (N-1)th-layer satellite. Under the reaction force, the guide member 41 drives the Nth-layer satellite to separate from the (N-1)th-layer satellite at an initial velocity along a preset trajectory. The trigger switch 6 on the lower surface of the Nth-layer satellite, originally pressed by the (N-1)th-layer satellite, resets after separation, activating the built-in power supply of the Nth-layer satellite and powering on its onboard equipment.

[0110] S200, separation of satellites in layer N-1;

[0111] The trigger switch 6 of the N-1 layer satellite is pressed down by the N layer satellite in the stacked state. After the N layer satellite is separated, the trigger switch 6 of the N-1 layer satellite is triggered at the same time, turning on the power of the N-1 layer satellite and entering the power-on process, which lasts for about 1 minute.

[0112] After the Nth layer satellite separates, the launch vehicle assembly 1 continues to spin to adjust its own attitude. This attitude adjustment can avoid the orbit of the Nth layer satellite and reserve independent space for the separation of the N-1th layer satellite.

[0113] After the power supply of the N-1 layer satellite completes the power-on process, its layer release device 3 enters the standby state.

[0114] After the release device 34 is energized, its output end drives the locking pin to retract from the pin hole 352 of the pin shaft 351, releasing the tension rope. The retractor 36 quickly winds up the tension rope to prevent it from entangled in satellite 2 or launch vehicle assembly 1. The elastic device 33 releases the preload, pushing the movable sleeve downward along the inner cavity of the fixed sleeve. Its lower end face pushes the second mounting part 22 of the N-2 layer satellite, transmitting the reaction force to the N-1 layer satellite. Under the thrust, the N-1 layer satellite separates from the N-2 layer satellite at an initial velocity along a trajectory with a preset angle to the axis of the launch vehicle assembly 1.

[0115] S300, separation of satellites in layer N-2;

[0116] After the N-1 layer satellites separate, the launch vehicle assembly 1 continues to spin. The trigger switch 6 for the N-2 layer is activated, initiating the power-on of the N-2 layer satellites. Separation is performed in the same manner as in step S200, and so on, gradually releasing all satellites.

[0117] The satellite-launch layered release system and method disclosed herein rely on the coordinated action of the corresponding top-level release device or layered release device 3 for the separation of each satellite 2. The timing linkage between power-on and separation is achieved through the trigger switch 6, ultimately ensuring that the motion trajectories of all satellites 2 and the launch vehicle assembly 1 do not intersect, thus achieving safe separation.

[0118] The various embodiments of this disclosure have been described above. These descriptions are exemplary and not exhaustive, and are not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein. The scope of this disclosure is defined by the appended claims.

Claims

1. A stacked satellite launch system for layered satellite release, characterized in that, The system includes a launch vehicle assembly (1) and multiple satellites (2) mounted on the launch vehicle assembly (1), the multiple satellites (2) being configured to be stacked sequentially; it also includes a layered release device (3), the layered release device (3) comprising: The guide (31) is configured to be disposed on the upper-level satellite; The propulsion unit (32) is configured to guide and cooperate with the guide unit (31), and the propulsion unit (32) is configured to pre-compress the next layer of satellite by means of the elastic device (33); Release device (34), which is configured to be connected to the upper-level satellite; The restraint part (35) has one end configured to be connected to the next layer satellite and the other end configured to be connected to the output end of the releaser (34); The release device (34) is configured to release the restraint part (35) after being energized, and the pusher (32) is configured to move relative to the guide part (31) under the force of the elastic device (33) to push the upper layer satellite to separate from the lower layer satellite; The satellite (2) is provided with a first mounting part (21) and a second mounting part (22); the guide part (31) is configured as a fixed sleeve fixed on the first mounting part (21), and the push part (32) is configured to guide and cooperate with the inner cavity of the fixed sleeve; the elastic device (33) is configured to be disposed between the push part (32) and the fixed sleeve; the free end of the push part (32) is configured to be pre-pressed on the second mounting part (22) of the next layer satellite by the elastic device (33).

2. The star-rocket layered release system according to claim 1, characterized in that, A retractor (36) is provided on the second mounting portion (22), the retractor (36) being configured to roll up the restraint portion (35) after the restraint portion (35) is released.

3. The star-rocket layered release system according to claim 1, characterized in that, One end of the restraint part (35) is provided with a pin (351), and the output end of the releaser (34) is configured to cooperate with the pin (351).

4. The star-rocket layered release system according to claim 3, characterized in that, The pin (351) is provided with a pin hole (352), the output end of the release device (34) is configured to extend into the pin hole (352), and is configured to disengage from the pin hole (352) after the release device (34) is energized.

5. The star-rocket layered release system according to claim 1, characterized in that, The pusher (32) is configured as a movable sleeve with an inner cavity, and the restraint (35) is configured to pass through the movable sleeve from the position of the next layer satellite and connect to the output end of the releaser (34).

6. The star-rocket layered release system according to claim 5, characterized in that, The release device (34) is configured to be fixed to the first mounting part (21) by the mounting base (37); the restraint part (35) is configured to pass through the movable sleeve and the mounting base (37) in sequence and then be connected to the output end of the release device (34).

7. The star-rocket layered release system according to claim 1, characterized in that, The binding part (35) is a tension rope.

8. The star-rocket layered release system according to claim 1, characterized in that, Multiple layered release devices (3) are provided, and the multiple layered release devices (3) are distributed in the circumferential direction of the satellite (2).

9. The star-rocket layered release system according to claim 1, characterized in that, The plurality of satellites (2) include a bottom layer satellite (203) at the bottom, a top layer satellite (201) at the top, and an intermediate layer satellite (202) between the bottom layer satellite (203) and the top layer satellite (201); the layered release device (3) is configured to be disposed on the intermediate layer satellite (202) and the bottom layer satellite (203); and the pusher (32) on the bottom layer satellite (203) is configured to pre-compress the launch vehicle assembly (1) by means of the elastic device (33).

10. The star-rocket layered release system according to claim 9, characterized in that, A top-level release device is provided on the top-level satellite (201). The top-level release device includes a guide (41) fixed on the top-level satellite (201) and a pusher (43) pre-pressed on the next-level satellite by an elastic member (42). It also includes a rigid restraint rod (5) located outside the satellite (2), one end of which is configured to be movably connected to the carrier assembly (1), and the other end of which is configured to be locked to the top satellite (201); the restraint rod (5) is configured to restrain multiple satellites (2) to the carrier assembly (1), and is configured such that after the satellite (2) is unlocked, the pusher (43) moves relative to the guide (41) under the force of the elastic member (42) to push the top satellite (201) to separate from the next layer of satellites.

11. The star-rocket layered release system according to claim 1, characterized in that, The satellite (2) is equipped with a power supply and a trigger switch (6) for controlling the power supply; the trigger switch (6) on the satellite (2) is configured to be in contact with the upper-layer satellite and to be triggered after the upper-layer satellite is separated; the satellite (2) is configured to control the power supply to power on the satellite (2) after the trigger switch (6) is triggered.

12. The star-rocket layered release system according to claim 11, characterized in that, The multiple satellites (2) include a bottom layer satellite (203) at the bottom, a top layer satellite (201) at the top, and an intermediate layer satellite (202) between the bottom layer satellite (203) and the top layer satellite (201); the trigger switch (6) of the top layer satellite (201) is configured to abut against the next layer satellite and to be triggered after the top layer satellite (201) is separated, and the top layer satellite (201) is configured to control the power supply to power on the top layer satellite (201) after the trigger switch (6) is triggered.

13. A method for layered release of stacked satellites using a launch vehicle, employing the layered release system according to any one of claims 1 to 12, characterized in that, Includes the following steps: S1: Control the launch vehicle assembly (1) to spin to the first attitude, control the restraint rod (5) to unlock, and the top satellite (201) automatically separates under the action of the pusher (43); S2: Adjust the launch vehicle assembly (1) to spin to the second attitude, control the release device (34) to release the restraint part (35), and the next layer satellite will automatically separate under the action of the propulsion unit (32); S3: Repeat step S2 until all satellites (2) are separated from the launch vehicle assembly (1).

14. The star-rocket layered release method according to claim 13, characterized in that, When the upper-layer satellite separates, the trigger switch (6) of the lower-layer satellite is triggered to power on the corresponding satellite (2).

15. The star-rocket layered release method according to claim 14, characterized in that, Each satellite (2) is configured to control the corresponding release device (34) to operate after power-on or after a predetermined time after power-on.

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