A satellite separation system

Abstract

This disclosure relates to a satellite separation system, including a launch vehicle assembly, N layers of flat-panel satellites stacked sequentially on the launch vehicle assembly, a separation mechanism, and a layered release mechanism; the top flat-panel satellite is designated as the Nth layer flat-panel satellite, and the bottom flat-panel satellite as the 1st layer flat-panel satellite. One end of the separation mechanism is hinged to the launch vehicle assembly, and the other end is locked to the Nth layer flat-panel satellite; the separation mechanism can apply pressure towards the launch vehicle assembly to restrain all flat-panel satellites, and release the Nth layer flat-panel satellites upon unlocking. The layered release mechanism is located between adjacent flat-panel satellites in layers N-1 to 1, used to restrain the upper and lower layers of flat-panel satellites, and release the upper layer flat-panel satellites upon release. The satellite separation system of this disclosure enables the orderly separation of flat-panel satellites from the top to the bottom, avoiding the collision risk of simultaneous release of multiple layers of flat-panel satellites, and improving the safety and reliability of flat-panel satellite separation.

Description

Technical Field

[0001] This disclosure relates to the aerospace field, specifically to a satellite separation system. Background Technology

[0002] In the aerospace field, satellite separation is a critical step in spacecraft deployment, and existing technologies have many shortcomings. Traditional satellite-rocket separation methods often employ pyrotechnic techniques such as explosive bolts and separation nuts. These techniques are undetectable, subject to high impact loads during separation, easily damage sensitive satellite components, and may generate debris that pollutes the space environment.

[0003] For the separation of multi-layered stacked satellites, existing solutions lack efficient and stable restraint and release mechanisms: some solutions use flexible restraint components (such as ropes and straps), which are prone to loosening or deformation due to vibrations during launch, causing the satellite stack attitude to shift; some solutions do not achieve layered and orderly release, and multiple satellites may detach simultaneously, leading to overlapping separation trajectories and collision risks. Furthermore, uneven force transmission in traditional separation systems can easily cause satellite separation attitude to become uncontrollable, affecting the reliability of subsequent orbital deployment. With the increasing number of satellites launched in a single launch, the requirements for the orderliness, safety, and stability of the separation system have significantly increased, necessitating a satellite separation system capable of precisely restraining and releasing multi-layered stacked satellites layer by layer. Summary of the Invention

[0004] This disclosure provides a satellite separation system to address the problems existing in the prior art.

[0005] According to a first aspect of this disclosure, a satellite separation system is provided, comprising:

[0006] Carrier assembly;

[0007] A flat-panel satellite, wherein the flat-panel satellite has N layers, and the N layers of flat-panel satellites are constructed to be stacked sequentially on the launch vehicle assembly; the flat-panel satellite at the top layer is referred to as the Nth layer flat-panel satellite, and the flat-panel satellite at the bottom layer is referred to as the 1st layer flat-panel satellite;

[0008] A separation mechanism is configured to apply pressure to the Nth layer of flat-panel satellites in the direction of the launch vehicle assembly and to bind all the flat-panel satellites to the launch vehicle assembly; one end of the separation mechanism is configured to be hinged to the launch vehicle assembly, and the other end is configured to be locked with the Nth layer of flat-panel satellites; the Nth layer of flat-panel satellites are configured to be released after the separation mechanism is unlocked;

[0009] It also includes a layered release mechanism between the N-1 layer and the 1st layer of flat-panel satellites. Multiple layered release mechanisms are provided and are located between two adjacent layers of flat-panel satellites to bind the upper layer of flat-panel satellites to the lower layer of flat-panel satellites. After the layered release mechanism between two adjacent layers of flat-panel satellites in the N-1 layer and the 1st layer of flat-panel satellites is released, the upper layer of flat-panel satellites is released.

[0010] In one embodiment of this disclosure, the Nth layer flat-panel satellite is provided with a top-level release assembly, which is configured to pre-press onto the (N-1)th layer flat-panel satellite and provide separation thrust to separate the Nth layer flat-panel satellite after the separation mechanism unlocks from the Nth layer flat-panel satellite.

[0011] In one embodiment of this disclosure, multiple separation mechanisms are provided, and the multiple separation mechanisms are configured to be distributed in the circumferential direction outside all the flat-panel satellites; the multiple separation mechanisms are configured to unlock synchronously.

[0012] In one embodiment of this disclosure, the separation mechanism is configured as a rigid rod-shaped structure.

[0013] In one embodiment of this disclosure, the layered release mechanism includes:

[0014] The guide section is configured to be mounted on the upper-layer flat-panel satellite;

[0015] A propulsion unit, configured to guide and cooperate with the guide unit, and configured to pre-press the lower layer of flat satellite via an elastic device;

[0016] A release device, configured to be connected to the upper-layer flat-panel satellite;

[0017] The restraint part has one end configured to be connected to the next layer of flat-panel satellite, and the other end configured to be connected to the output end of the releaser;

[0018] The release device is configured such that, after releasing the restraint portion, the push portion is configured to move relative to the guide portion under the force of the elastic device to push the upper-layer flat-panel satellite to separate from the lower-layer flat-panel satellite.

[0019] In one embodiment of this disclosure, the propulsion unit on the first-layer flat-panel satellite is configured to be pre-pressed onto the launch vehicle assembly by the elastic device.

[0020] In one embodiment of this disclosure, the restraint is a tension rope.

[0021] In one embodiment of this disclosure, the top-level release assembly includes a guide fixed on the Nth layer flat-panel satellite and a pusher pre-pressed on the (N-1)th layer flat-panel satellite by an elastic element; the guide is configured to guide and cooperate with the pusher, and the elastic element is configured to release the pre-pressure after the separation mechanism is unlocked, driving the pusher to separate the Nth layer flat-panel satellite.

[0022] In one embodiment of this disclosure, the flat-panel satellite has a plurality of stacking pillars configured to be distributed along the circumferential direction of the flat-panel satellite; the layer release mechanism is disposed within the stacking pillars.

[0023] In one embodiment of this disclosure, each layer of the flat-panel satellite is provided with a first mounting portion and a second mounting portion; the guide portion is configured to be fixed on the first mounting portion, and the free end of the push portion is configured to be pre-pressed onto the second mounting portion of the next layer of satellite by an elastic device.

[0024] One beneficial effect of this disclosure is that, through the synergistic action of the separation mechanism and the layered release mechanism, the sequential and orderly release of N-layer flat-panel satellites from the top to the bottom is achieved. The separation mechanism provides stable initial tethering for all flat-panel satellites, preventing attitude deviation during launch, and can release the top-layer flat-panel satellite while simultaneously releasing it from tethering. The layered release mechanism ensures that lower-layer flat-panel satellites are only released from tethering after the upper-layer flat-panel satellites have separated, completely avoiding the collision risk of simultaneous release of multiple layers of flat-panel satellites, significantly improving the safety and reliability of the flat-panel satellite separation process, and adapting to the needs of multi-satellite stacked deployment.

[0025] 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

[0026] 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.

[0027] Figure 1 This is a simulation diagram of a launch vehicle assembly carrying N layers of flat-panel satellites, provided in this public disclosure;

[0028] Figure 2 This is a schematic diagram of the structure of the layered release mechanism provided in this disclosure;

[0029] Figure 3 This is a cross-sectional schematic diagram of the stacked pillars in an embodiment of this disclosure;

[0030] Figure 4 yes Figure 3 Enlarged view of point A in the middle;

[0031] Figure 5 yes Figure 3 Enlarged view of point B in the middle.

[0032] Figures 1 to 5 The one-to-one correspondence between the component names and the reference numerals in the figures is as follows:

[0033] 10. Launch vehicle assembly; 20. Flat panel satellite; 201. Nth layer flat panel satellite; 202. N-1th layer flat panel satellite; 203. 1st layer flat panel satellite; 30. Separation mechanism; 40. Layered release mechanism; 401. Guide section; 402. Propulsion section; 403. Release device; 404. Restraint section; 405. Elastic device; 406. Retractor; 50. Top layer release assembly; 501. Guide component; 502. Elastic component; 503. Propulsion component; 60. Stacking column. Detailed Implementation

[0034] 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.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] 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.

[0040] 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.

[0041] This disclosure provides a satellite separation system, including a launch vehicle assembly, N layers of flat-panel satellites stacked sequentially on the launch vehicle assembly, a separation mechanism, and a layered release mechanism; the top flat-panel satellite is designated as the Nth layer, and the bottom flat-panel satellite as the first layer. One end of the separation mechanism is hinged to the launch vehicle assembly, and the other end is locked to the Nth layer flat-panel satellite. The separation mechanism can apply pressure towards the launch vehicle assembly to all flat-panel satellites to restrain them, and release the Nth layer flat-panel satellite upon unlocking. The layered release mechanism is located between adjacent flat-panel satellites in layers N-1 to 1, used to restrain the upper and lower layers of flat-panel satellites, and release the upper layer flat-panel satellite upon release. This satellite separation system enables the orderly separation of flat-panel satellites from the top to the bottom, avoiding the collision risk of simultaneous release of multiple layers of flat-panel satellites, and improving the safety and reliability of flat-panel satellite separation.

[0042] The specific embodiments of this disclosure are described below with reference to the accompanying drawings.

[0043] refer to Figures 1 to 5 This disclosure provides a satellite separation system, including a launch vehicle assembly 10, flat-panel satellites 20, a separation mechanism 30, and a layered release device. The launch vehicle assembly 10 carries N stacked flat-panel satellites 20 into a predetermined orbit and adjusts its own spin attitude (e.g., adjusting the pitch axis Y-axis and / or yaw axis Z-axis angles) to provide a suitable attitude for the smooth and safe separation of each layer of flat-panel satellites 20, ensuring that the separation trajectories of all flat-panel satellites 20 do not intersect. The attitude adjustment strategy of the launch vehicle assembly 10 must be negotiated and confirmed with the launch vehicle to avoid collisions with previously launched satellites due to velocity differences. When adjusting the pitch axis Y-axis and / or yaw axis Z-axis angles, the launch vehicle assembly 10 needs to determine the adjustment range based on the total number of N stacked flat-panel satellites 20, the separation direction requirements of each layer, and the predetermined orbital parameters to avoid drastic attitude changes affecting its own stability.

[0044] like Figure 1 As shown, the flat-panel satellite 20 has N layers, which are stacked sequentially on the launch vehicle assembly 10. The top layer of flat-panel satellite 20 is designated as the Nth layer flat-panel satellite 201, and the bottom layer flat-panel satellite 20 is designated as the first layer flat-panel satellite 203. Specifically, the stacking axis of the N layers of flat-panel satellites coincides with the central axis of the launch vehicle assembly 10. They are stacked and aligned sequentially according to their thickness direction. This not only maximizes the utilization of the axial space of the launch vehicle assembly 10 and increases the number of satellites carried in a single launch, but also prevents relative swaying of the flat-panel satellites 20 during launch, ensuring the installation stability between the N layers of flat-panel satellites 20.

[0045] The Flat Panel Satellite 20 adopts a lightweight and modular design. The main structure is mostly rectangular or circular flat panels, with high integration and a regular shape, making it suitable for multi-layer stacking scenarios. The core payloads (such as communication modules and control systems) and independent power supplies are all built into the flat panel. Only the interface structure required for stacking and destabilization is reserved on the outside, without affecting the stacking compactness.

[0046] Continue to refer to Figure 1 The separation mechanism 30 applies pressure to the N-layer flat-panel satellites 20 in the direction of the launch vehicle assembly 10, and binds all the flat-panel satellites 20 to the launch vehicle assembly 10. One end of the separation mechanism 30 is hinged to the launch vehicle assembly 10, and the other end is locked to the N-layer flat-panel satellite 201; the N-layer flat-panel satellite 201 is released after the separation mechanism 30 is unlocked. Specifically, the lower end of the separation mechanism 30 can be movably connected to the docking part of the launch vehicle assembly 10 through a hinge with bearings, and the upper end can be provided with an electromagnetic locking component, which is adapted to the metal locking seat at the top of the N-layer flat-panel satellite 201. There are various ways in which the separation mechanism 30 is hinged and locked, and this disclosure does not make specific limitations, but only uses a hinge with bearings and an electromagnetic locking component as an example for explanation. In the stacked state, the separation mechanism 30 maintains its restrained posture through pre-tension, and the locking component is tightly locked to the locking seat. This applies a pressure along the axis of the separation mechanism 30 towards the launch assembly 10 to the Nth layer flat-panel satellite 201, and sequentially restrains the other satellites below the Nth layer flat-panel satellite 201 to the launch assembly 10. After unlocking, the separation mechanism 30 can only be rotated outwards, and the rotation angle can completely avoid the separation area of ​​the flat-panel satellite 20, preventing the rod from colliding with the satellites during the separation process. The electromagnetic locking component equipped at the upper end of the separation mechanism 30 uses an electromagnetic drive to achieve locking and unlocking. The load of the electromagnetic locking component must cover the total pre-pressure generated by the stacking of N layers of flat-panel satellites 20.

[0047] like Figure 2 As shown, it also includes a layered release mechanism 40 disposed between the N-1th layer and the 1st layer of flat-panel satellites 20. Multiple layered release mechanisms 40 are provided, each located between adjacent layers of flat-panel satellites 20, to secure the upper layer of flat-panel satellites 20 to the lower layer. Specifically, the number of layered release mechanisms 40 can be adapted according to the diameter or shape of different types of flat-panel satellites 20, and they are evenly distributed along the circumferential direction of the docking of adjacent layers of flat-panel satellites 20. A binding force is provided between adjacent layers of flat-panel satellites 20, ensuring that the binding force is evenly transmitted. The pre-pressure of the separation mechanism 30 is transmitted to all lower-layer flat-panel satellites 20 through the Nth layer flat-panel satellite 201, working in conjunction with the pre-pressure of the layered release mechanisms 40 of each layer of flat-panel satellites 20 to ensure that the entire stacked flat-panel satellite array and the docking platform of the launch vehicle assembly 10 are free from loosening or axial swaying, achieving stable binding of all flat-panel satellites 20.

[0048] In the N-1 layer to the 1st layer of flat-panel satellites 20, after the layer release mechanism 40 of adjacent layers of flat-panel satellites 20 is released, the upper layer of flat-panel satellite 20 is released. Originally, the upper layer of flat-panel satellite 20 was bound to the lower layer of flat-panel satellite 20 by the layer release mechanism 40. When the binding is released, the upper layer of flat-panel satellite 20, which is no longer bound, will be released. The layer release mechanism 40 releases pre-compression potential energy, pushing the upper layer of flat-panel satellite 20 to separate smoothly along the axial direction. During the separation process, the launch vehicle assembly 10 needs to be adjusted to the appropriate attitude simultaneously to ensure that the separation trajectory of the flat-panel satellite 20 does not intersect with the separated satellite and the launch vehicle assembly 10.

[0049] In one embodiment of this disclosure, such as Figure 3 and Figure 4 As shown, the Nth layer flat panel satellite 201 is provided with a top-level release component 50. The top-level release component 50 is pre-pressed onto the N-1th layer flat panel satellite 202, and provides separation thrust to separate the Nth layer flat panel satellite 201 after the separation mechanism 30 is unlocked from the Nth layer flat panel satellite 201.

[0050] Specifically, the top-level release components 50 are uniformly arranged circumferentially along the Nth-layer flat-panel satellite 201, with the number consistent with the lower-layer release mechanisms 40, ensuring symmetrical transmission of separation thrust. In the stacked state, the top-level release components 50 are kept in a compressed, energy-storing state due to the pre-pressure of the separation mechanism 30. The amount of stored energy needs to be precisely calculated based on the weight of the Nth-layer flat-panel satellite 201 and the required initial separation velocity to avoid insufficient thrust leading to separation lag or excessive thrust damaging the structure of the flat-panel satellite 20. After the separation mechanism 30 unlocks, the top-level release components 50 instantly release their stored energy, applying a uniform axial thrust to the Nth-layer flat-panel satellite 201, propelling the satellite to separate along a preset trajectory. Furthermore, the thrust direction of the release components is parallel to the axis of the launch vehicle assembly 10, with no radial component, preventing attitude deflection during satellite separation. Simultaneously, the action of the top-level release components 50 is strictly synchronized with the unlocking sequence of the separation mechanism 30, preventing the flat-panel satellite 20 from becoming stuck due to lack of thrust support after unlocking, ensuring separation efficiency and safety.

[0051] In one embodiment of this disclosure, such as Figure 3 and Figure 4As shown, the top-level release assembly 50 includes a guide member 501 fixed on the Nth layer flat-panel satellite 201, and a pusher member 503 pre-pressed onto the (N-1)th layer flat-panel satellite 202 by an elastic member 502. The guide member 501 and the pusher member 503 are guided and engaged. After the separation mechanism 30 is unlocked, the elastic member 502 releases the pre-pressure, driving the pusher member 503 to separate the Nth layer flat-panel satellite 201. The Nth layer flat-panel satellite 201 is configured to trigger its own power-on procedure after release. Specifically, the top-level release component 50 is a component that works with the separation mechanism 30 to achieve rapid and automatic separation of the Nth layer flat satellite 201. Since the separation mechanism 30 has rigidly constrained the Nth layer flat satellite 201 onto the (N-1)th layer flat satellite 202 and can directly unlock and release the constraint, the top-level release device does not need to be equipped with a restraint part 404 and a matching release device 403 like the layered release mechanism 40 of the lower layer flat satellite 20. Separation can be achieved simply by using the guide member 501, the elastic member 502 and the pusher member 503, ensuring that the Nth layer flat satellite 201 can immediately detach after the separation mechanism 30 is unlocked.

[0052] Continue to refer to Figure 4 The guide 501 is a guide sleeve fixed to the Nth layer flat satellite 201, and its inner cavity is precisely matched with the outer dimensions of the pusher 503; the pusher 503 can be a cylindrical push rod, with its lower end extending out of the guide sleeve to contact the N-1th layer flat satellite 202. The elastic element 502 can be a compression spring sleeved on the outside of the guide element 501. In the satellite stacking state, the separation mechanism 30 applies a pre-pressure to the Nth layer flat satellite 201 pointing towards the launch vehicle assembly 10. This pre-pressure is transmitted to the elastic element 502 through the Nth layer flat satellite 201, so that the elastic element 502 is in a compressed state and stores elastic potential energy. Since the Nth layer flat satellite 201 has no additional constraints from the upper layer satellite, its required initial separation thrust must be provided entirely by the elastic element 502. Therefore, the compression and energy storage of the elastic element 502 must be greater than the elastic device 405 in the layer release mechanism 40 of the lower layer flat satellite 20 to ensure that sufficient thrust can be generated during separation, and to avoid separation lag or attitude deviation of the Nth layer flat satellite 201 due to insufficient thrust.

[0053] After the separation mechanism 30 unlocks from the Nth layer flat satellite 201, the pusher 503 moves relative to the guide 501 under the force of the elastic member 502, thus separating the Nth layer flat satellite 201 from the (N-1)th layer flat satellite 202. The pre-pressure applied to the Nth layer flat satellite 201 by the separation mechanism 30 disappears instantly, and the elastic member 502 immediately releases its stored potential energy, generating an upward axial rebound force that pushes the push rod downwards along the inner cavity of the guide sleeve. Because the lower end of the push rod remains in contact with the (N-1)th layer flat satellite 202, the push rod applies downward pressure to the docking platform during the sliding process. According to the principle of action and reaction, the Nth layer flat satellite 201 experiences an upward reaction force, smoothly separating axially from the (N-1)th layer flat satellite 202.

[0054] Unlike the flat-panel satellites 20 from layer N-1 to layer 1, the Nth-layer flat-panel satellite 201 only triggers its own power-on procedure after release. This is because, as the top-level satellite, the Nth-layer flat-panel satellite 201 is not constrained by any upper-level satellites. For example, its mechanically reset limit switch (located on the lower end face of the Nth-layer flat-panel satellite 201, abutting against the N-1th-layer flat-panel satellite 202) can only be triggered by its separation from the N-1th-layer flat-panel satellite 202. In the stacked state, the limit switch is kept open by the N-1th-layer flat-panel satellite 202, preventing premature power-on due to vibration or electromagnetic interference during transport and reducing ineffective battery consumption. When the separation mechanism 30 unlocks and the top-level release component 50 pushes the Nth-layer flat-panel satellite 201 away, the limit switch loses its pressure and mechanically resets, allowing the power circuit to be closed and the power-on procedure to be initiated. This design ensures the power safety of the Nth-layer flat-panel satellite 201 during the stacking phase, and can immediately power the core equipment on board after separation, enabling it to quickly enter orbital operation. Simultaneously, through the strong linkage of "separation-power-on," it avoids the risk of the flat-panel satellite 201 becoming uncontrollable due to power failure after separation. In one embodiment of this disclosure, such as... Figure 1 As shown, there are multiple separation mechanisms 30, which are distributed in the circumferential direction on the outside of all flat-panel satellites 20; the multiple separation mechanisms 30 are unlocked simultaneously.

[0055] Specifically, the number of separation mechanisms 30 is adapted to the diameter or size of the flat-panel satellite 20, and is evenly distributed along the circumferential edge of the flat-panel satellite 20. The locking end of each separation mechanism 30 can correspond to the locking seat at the top of the Nth layer of flat-panel satellite 201. The spacing between the separation mechanisms 30 is also determined according to the external dimensions of the flat-panel satellite 20. For example, circular flat-panel satellites 20 are distributed at equal angles, while rectangular flat-panel satellites 20 are distributed at the four corners to ensure that the pressure of each separation mechanism 30 on the flat-panel satellite 20 is evenly transmitted, avoiding excessive pressure on one side that could cause the flat-panel satellites 20 to tilt when stacked.

[0056] Synchronous unlocking is achieved through the built-in control system of the launch vehicle assembly 10: the control system sends a unified unlocking command to all separation mechanisms 30 to avoid unilateral force on the Nth-layer flat-panel satellite 201 due to differences in unlocking timing, prevent separation attitude deviation, and ensure accurate trajectory in the initial stage of top-layer satellite separation. Furthermore, the flipping speed of the separation mechanism 30 after unlocking must be controlled within a reasonable range to avoid collisions with other flat-panel satellites 20 or the launch vehicle assembly 10 due to excessively rapid flipping. After flipping into position, the separation structure should be fixed with appropriate limiting structures to prevent rebound of the separation structure due to vibration during on-orbit operation, which could affect the separation of the flat-panel satellite 20.

[0057] In one embodiment of this disclosure, the separation mechanism 30 is a rigid rod-shaped structure. The core function of the separation mechanism 30 is to apply pre-pressure to all the stacked flat-panel satellites 20 pointing towards the launch vehicle assembly 10, while not interfering with the satellite separation trajectory after unlocking. It is a key component to ensure the stability of multi-layer satellite stacking and the safety of separation.

[0058] Specifically, the rod-shaped main body of the separation mechanism 30 can be made of lightweight, high-strength materials, preferably titanium alloys or carbon fiber composites. These materials can meet the strength requirements of the space environment while minimizing their own weight, thus avoiding increasing the burden on the launch vehicle assembly 10. The specific material of the separation mechanism 30 is not limited in this disclosure.

[0059] The length of the rod-shaped main body needs to be precisely designed according to the total height of the N-layer flat-panel satellites 20 after stacking, to ensure that its upper end can reliably dock with the locking structure of the top-layer flat-panel satellite 20, and its lower end can be stably connected with the hinge seat of the launch vehicle assembly 10. In the stacked state, it should maintain an attitude perpendicular to the docking platform of the launch vehicle assembly 10 to avoid uneven pre-pressure transmission due to length deviation.

[0060] Compared to traditional flexible restraints (such as restraint ropes and flexible straps), the rigid rod-like structure of the separation mechanism 30 has significant advantages: Firstly, the rigid structure can maintain the alignment of the stacking axes of each layer of flat satellites 20 through precise axial support, controlling attitude deviation within millimeters and preventing satellite stacking tilt due to loosening or deformation of flexible components. Secondly, after unlocking, the rod flips outward via hinges, potentially resting against the side wall of the launch vehicle assembly 10 or being fixed by a limiting structure, unlike flexible components that may entangle satellites or launch equipment due to irregular drifting after unlocking, thus completely eliminating the risk of entanglement. Simultaneously, the preload transmitted by the rigid rod-like structure is uniform and stable, working in synergy with the pre-tightening force of the layer release mechanism 40 of each layer of flat satellites 20 to ensure that the entire stacked array is tightly fitted to the docking platform of the launch vehicle assembly 10 during launch, without axial loosening or swaying, laying a stable foundation for subsequent layer separation. In the satellite separation system disclosed herein, when the separation mechanism 30 is released, the Nth layer flat panel satellite 201 is unbound and separates under the action of the top layer release component 50; the other satellites are released layer by layer under the action of the layer release mechanism 40.

[0061] Specifically, in one embodiment of this disclosure, such as Figure 2 and Figure 5 As shown, the layered release mechanism 40 includes a guide section 401, a push section 402, a release device 403, and a restraint section 404. These components work together to achieve stable restraint and orderly separation of adjacent two-layer flat-panel satellites 20. Specifically, the guide section 401 is mounted on the upper-layer flat-panel satellite 20; the push section 402 guides and cooperates with the guide section 401, and the push section 402 pre-presses the lower-layer flat-panel satellite 20 via an elastic device 405; the release device 403 is connected to the upper-layer flat-panel satellite 20; one end of the restraint section 404 is connected to the lower-layer flat-panel satellite 20, and the other end is connected to the output end of the release device 403, thereby achieving the restraint and fixation of the upper and lower layers of flat-panel satellites 20.

[0062] Specifically, refer to Figure 5 The guide part 401 is a fixed sleeve fixed on the upper-layer flat satellite 20. It can be precisely matched with the push part 402, restricting the radial offset of the push part 402, ensuring that the push part 402 moves only along the axial direction, and ensuring the accuracy of the separation direction.

[0063] The propulsion unit 402 is a hollow movable sleeve. Its outer diameter is in clearance fit with the inner cavity size of the fixed sleeve that serves as the guide unit 401, allowing it to slide flexibly along the inner cavity of the guide unit 401. The lower end of the propulsion unit 402 extends out of the guide unit 401 and directly contacts the next layer of flat-panel satellite 20, preparing for the subsequent transmission of separation thrust.

[0064] like Figure 2 and Figure 5As shown, the elastic device 405 can be a spring sleeved on the outside of the pushing part 402, with its two ends respectively abutting between the upper end of the guide part 401 and the lower end of the pushing part 402. In the satellite stacking state, the elastic device 405 is in a compressed state, storing sufficient separation elastic potential energy to provide stable thrust for the separation process. At the same time, the elastic device 405 needs to be differentiated according to the center of mass position of the corresponding layer flat satellite 20. If the satellite's center of mass is biased in a certain direction, the preload of the elastic device 405 of the layer release mechanism 40 in that direction needs to be appropriately increased to offset the influence of the center of mass offset on the separation attitude and ensure that the flat satellite 20 is subjected to balanced force during separation.

[0065] In addition, the release device 403 can be fixed to the top of the stacking column 60 of the upper-layer flat satellite 20 by means of a metal mounting base. The mounting base has a through channel inside, which is connected to the inner cavity of the pusher 402, and together they form the passage of the restraint part 404.

[0066] One end of the restraint part 404 is connected to the next layer flat satellite 20, and the other end passes through the push part 402 and the mounting base in sequence and is connected to the output end of the release device 403.

[0067] In the N-1 layer to the 1st layer of flat panel satellite 203, the flat panel satellite 20 is triggered to power on after the upper layer flat panel satellite 20 is separated; after power-on, the release device 403 releases the restraint part 404, and the push part 402 moves relative to the guide part 401 under the force of the elastic device 405, so as to push the upper layer flat panel satellite 20 to separate from the lower layer flat panel satellite 20.

[0068] Specifically, in the N-layer flat-panel satellite 20 stacked state, the release device 403 tightens the upper and lower layers of flat-panel satellite 20 through the output end constraint part 404, so that the elastic device 405 maintains compressed energy storage; when the release device 403 receives the power-on signal, the output end unlocks the constraint part 404; at the same time, the elastic device 405 rebounds and releases the stored elastic potential energy, pushing the movable sleeve to slide downward along the fixed sleeve, and the lower end of the movable sleeve pushes directly against the lower layer of flat-panel satellite 20; according to the principle of action and reaction force, the upper layer of flat-panel satellite 20 is subjected to an upward reaction force and smoothly separates from the lower layer of flat-panel satellite 20 along the axial direction. The entire separation process has no radial offset, ensuring that the satellite separation trajectory is accurate and safe.

[0069] In one embodiment of this disclosure, between the N-1th layer and the 1st layer of flat-panel satellites 20, each layer of flat-panel satellites 20 is configured to control the corresponding release device 403 to operate after power-on or after a predetermined time following power-on. Specifically, after each layer of flat-panel satellites 20 is powered on, its built-in control system first performs a status check on the release device 403. If it is confirmed to be normal and no delay is required, it directly controls the release device 403 to operate. If it is necessary to synchronize with the attitude adjustment of the launch vehicle assembly 10, the release device 403 can be activated after a predetermined time following the reception of the launch vehicle attitude confirmation signal, ensuring that the separation trajectory of each layer of flat-panel satellites 20 does not intersect with the separated flat-panel satellites 20 and the launch vehicle, thus avoiding collisions.

[0070] In one embodiment of this disclosure, the propulsion unit 402 on the first-layer flat-panel satellite 203 is pre-pressed onto the launch vehicle assembly 10 by an elastic device 405. Specifically, the first-layer flat-panel satellite 203, as the bottom-layer satellite, has its propulsion unit 402 of the layer release mechanism 40 directly abutting against the docking platform at the top of the launch vehicle assembly 10. When the elastic device 405 of the first-layer flat-panel satellite 203 is in a compressed state, the propulsion unit 402 applies pre-pressure to the launch vehicle assembly 10, which, in conjunction with the restraint unit 404 of the layer release mechanism 40, stably restrains the first-layer flat-panel satellite 203 onto the launch vehicle assembly 10, while providing a thrust basis for the subsequent separation of the first-layer satellite from the launch vehicle. It should be noted that the preload of the elastic device 405 of the first-layer flat satellite 203 needs to be designed in conjunction with the weight (including the load) of the first-layer satellite and the maximum acceleration during the launch process to ensure that the preload can offset the impact force generated by the vibration of other layers of flat satellites 20 during launch, and prevent the first-layer flat satellite 203 from separating from the launch vehicle assembly 10 under the impact force.

[0071] In one embodiment of this disclosure, the restraint portion 404 is a tension rope. Specifically, the restraint portion 404 may be a high-strength tension rope, the surface of which may be treated with a low-friction process to reduce motion wear. Simultaneously, the high-strength tension rope should possess the ability to withstand the extreme temperatures and high vacuum environment of space. Its length is precisely designed according to the stacking gap between two adjacent flat-panel satellites 20, ensuring that the tension rope is in a pre-tensioned state during stacking, balancing with the pre-pressure of the elastic device 405 to maintain the stability of the satellite stack.

[0072] In addition, such as Figure 2 and Figure 5 As shown, a retractor 406 can also be provided on the next layer of flat-panel satellite 20. The retractor 406 is connected to the binding part 404. When the releaser 403 releases the binding part 404, the retractor 406 can quickly roll up the binding part 404 to prevent the binding part 404 from getting tangled and causing equipment failure.

[0073] In one embodiment of this disclosure, the flat-panel satellite 20 has a plurality of stacking pillars 60 distributed along the circumferential direction of the flat-panel satellite 20; a layer release mechanism 40 is disposed within the stacking pillars 60.

[0074] Specifically, such as Figure 1 and Figure 3 As shown, the stacking pillars 60 are cylindrical hollow structures, which can be made of lightweight, high-strength materials commonly used in the aerospace field, such as titanium alloys and carbon fiber reinforced composite materials. These materials can meet the structural strength requirements during the launch phase while controlling their own weight, avoiding excessive occupation of launch vehicle resources, and conforming to the lightweight design principles of aerospace equipment. The stacking pillars 60 are evenly distributed circumferentially along the edge of the flat-panel satellite 20 (the number is consistent with the layered release mechanism 40). The core function of this layout is to construct a "multi-point rigid support system": on the one hand, during launch, the axial impact and lateral vibration generated by the launch vehicle will be evenly transmitted to all flat-panel satellites 20 through the stacking pillars 60, avoiding local stress concentration that could lead to structural cracking of the flat-panel satellite 20; on the other hand, during the on-orbit stacking phase, the stacking pillars 60 can offset the overturning moment generated by the displacement of the center of mass of each flat-panel satellite 20, ensuring that the stacking axis of the multi-layer flat-panel satellite 20 is coaxial with the central axis of the launch vehicle assembly 10, and maintaining a stable stacking attitude.

[0075] The inner diameter of each stacking column 60 is precisely matched to the outer dimensions of the layered release mechanism 40, fully accommodating components such as the guide section 401, push section 402, and elastic device 405 of the layered release mechanism 40, without occupying the internal payload space of the flat-panel satellite 20. Furthermore, the axis of the stacking column 60 is parallel to the central axis of the flat-panel satellite 20, ensuring that the separation thrust of the layered release mechanism 40 is transmitted axially, avoiding radial force-induced satellite attitude deviation. Through the distribution of multiple stacking columns 60, the binding force and separation thrust of the layered release mechanism 40 are evenly applied to each layer of the flat-panel satellite 20, preventing unilateral force-induced separation attitude deviation and ensuring accurate separation trajectory.

[0076] In one embodiment of this disclosure, each layer of flat satellite 20 is provided with a first mounting part and a second mounting part; the guide part 401 is fixed on the first mounting part, and the free end of the push part 402 is pre-pressed on the second mounting part of the next layer of satellite by the elastic device 405.

[0077] Specifically, the guide portion 401 of this disclosure can be connected to the first mounting portion, for example, by bolts, screws, welding, or other methods well known to those skilled in the art. In a specific embodiment of this disclosure, the guide portion 401 is a fixed sleeve fixed to the first mounting portion, and the pushing portion 402 guides and cooperates with the inner cavity of the fixed sleeve.

[0078] The first and second mounting parts can be disposed on the inner wall of the stacking column 60 of each layer of flat-panel satellite 20, and are configured as mounting platforms extending radially inward from the inner wall for mounting other components. Within each stacking column 60, the first mounting part is located below the second mounting part, which allows the first mounting part located on the upper layer of flat-panel satellite 20 to cooperate with the second mounting part located on the lower layer of flat-panel satellite 20.

[0079] The first mounting part may also be provided with a first mounting hole, and the second mounting part may be provided with a second mounting hole, and the axes of the two holes are strictly coaxial, that is, the axes coincide on a common straight line perpendicular to the cavity wall. Both the first mounting part and the second mounting part have upper and lower end faces. The guide part 401 is a fixed sleeve with a through cavity. One end of the fixed sleeve is fixedly installed on the lower end face of the first mounting part of the upper-layer flat satellite 20, and the fixed sleeve is coaxially installed with the first mounting hole of the first mounting part.

[0080] The pusher 402 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 pusher 402 can be guided and engaged with the inner cavity of the fixed sleeve. The pusher 402 can move relative to the fixed sleeve on its own axis, for example, by moving towards or away from the next layer flat satellite 20.

[0081] When the N-layer flat-panel satellites 20 are stacked, the first mounting portion of the upper layer flat-panel satellite 20 is aligned with the second mounting portion of the lower layer flat-panel satellite 20, allowing the pushing portion 402 within the upper layer flat-panel satellite 20 to abut against the second mounting portion of the lower layer flat-panel satellite 20. One end of the elastic device 405 abuts against the fixed sleeve, and the other end abuts against the flange provided on the pushing portion 402. Thus, under the action of the elastic device 405, the free end of the pushing portion 402 is pre-pressed onto the upper end surface of the second mounting portion of the lower layer flat-panel satellite 20. When the release device 403 releases the restraining portion 404, the pushing portion 402 extends towards the second mounting portion relative to the guide portion 401 under the action of the elastic device 405. Since the free end of the pushing portion 402 was originally abutting against the second mounting portion, the guide portion 401, under the reaction force, moves the upper layer flat-panel satellite 20 away from the second mounting portion, ultimately achieving the separation of the upper layer flat-panel satellite 20 from the lower layer flat-panel satellite 20.

[0082] 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 satellite separation system, characterized in that, include: Carrier assembly; A flat-panel satellite, wherein the flat-panel satellite has N layers, and the N layers of flat-panel satellites are constructed to be stacked sequentially on the launch vehicle assembly; The flat-panel satellite located at the top layer is designated as the Nth layer flat-panel satellite, and the flat-panel satellite located at the bottom layer is designated as the 1st layer flat-panel satellite. A separation mechanism is configured to apply pressure to the Nth layer of flat-panel satellites in the direction of the launch vehicle assembly and to bind all the flat-panel satellites to the launch vehicle assembly; one end of the separation mechanism is configured to be hinged to the launch vehicle assembly, and the other end is configured to be locked with the Nth layer of flat-panel satellites; the Nth layer of flat-panel satellites are configured to be released after the separation mechanism is unlocked; It also includes a layered release mechanism between the flat-panel satellites in the N-1 layer to the 1st layer. There are multiple layered release mechanisms, which are located between two adjacent layers of flat-panel satellites to bind the upper layer flat-panel satellite to the lower layer flat-panel satellite. After the layered release mechanism between two adjacent layers of flat-panel satellites in the N-1 layer to the 1st layer is released, the upper layer flat-panel satellite is released. The separation mechanism is constructed as a rigid structure and multiple such separation mechanisms are arranged in a circumferential direction distributed on the outside of all the flat-panel satellites. Multiple separation mechanisms are configured to unlock synchronously; The layered release mechanism includes: The guide section is configured to be mounted on the upper-layer flat-panel satellite; A propulsion unit, configured to guide and cooperate with the guide unit, and configured to pre-press the lower layer of flat satellite via an elastic device; A release device, configured to be connected to the upper-layer flat-panel satellite; The restraint part has one end configured to be connected to the next layer of flat-panel satellite, and the other end configured to be connected to the output end of the releaser; The release device is configured such that, after releasing the restraint portion, the push portion is configured to move relative to the guide portion under the force of the elastic device to push the upper-layer flat-panel satellite to separate from the lower-layer flat-panel satellite.

2. The satellite separation system according to claim 1, characterized in that, The Nth layer flat-panel satellite is equipped with a top-level release assembly, which is configured to pre-press onto the (N-1)th layer flat-panel satellite and provide separation thrust to separate the Nth layer flat-panel satellite after the separation mechanism unlocks from it.

3. The satellite separation system according to claim 1, characterized in that, The separation mechanism is constructed as a rigid rod-shaped structure.

4. The satellite separation system according to claim 1, characterized in that, The propulsion unit on the first-layer flat-panel satellite is configured to be pre-pressed onto the launch vehicle assembly via the elastic device.

5. The satellite separation system according to claim 1, characterized in that, The restraint part is a tension rope.

6. The satellite separation system according to claim 2, characterized in that, The top-level release assembly includes a guide fixed on the Nth layer flat-panel satellite and a pusher pre-pressed on the (N-1)th layer flat-panel satellite by an elastic element; the guide is configured to guide and cooperate with the pusher, and the elastic element is configured to release the pre-pressure after the separation mechanism is unlocked, driving the pusher to separate the Nth layer flat-panel satellite.

7. The satellite separation system according to claim 1, characterized in that, The flat-panel satellite has multiple stacked pillars, which are configured to be distributed along the circumferential direction of the flat-panel satellite; the layer release mechanism is disposed within the stacked pillars.

8. The satellite separation system according to claim 1, characterized in that, Each of the flat-panel satellites is provided with a first mounting part and a second mounting part; the guide part is configured to be fixed on the first mounting part, and the free end of the push part is configured to be pre-pressed onto the second mounting part of the next layer of satellite by an elastic device.

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