Stacked plate satellite spin-stabilization separation method and system

Abstract

This invention discloses a method and system for the spin-and-jet separation of stacked flat-panel satellites. The system includes a rocket final stage body, flat-panel satellites, stacking satellite locking devices, and stacking satellite guide support columns. A satellite adapter is connected to the end of the rocket final stage body. Multiple stacking satellite locking devices are connected to the satellite adapter. The flat-panel satellites are enclosed within the area formed by these devices and locked in place. When the locking devices are released, the flat-panel satellites detach from them. Multiple rows of flat-panel satellites are stacked in parallel within the system. Each row is nested and guided by the stacking satellite guide support columns, and the rows can be separated and connected. This method enables the stacking and spin-and-jet separation of flat-panel satellites without collisions during the separation process, significantly improving the near-field separation safety of the stacked satellites and protecting their safety.

Description

Technical Field

[0001] This invention relates to the field of satellite launch technology, and in particular to a method for separating stacked flat-panel satellites by spin-throwing. Background Technology

[0002] Separation technology for stacked flat-panel satellites is crucial for their successful launch into their designated orbits, with near-field safety being the most critical aspect. During separation, because the flat-panel satellites rotate around their center of mass without a dedicated guidance mechanism, they are prone to collisions, jeopardizing their safety. Therefore, this invention provides a spin-and-projectile separation technology for stacked flat-panel satellites that avoids collisions during the separation process, which is of significant importance. Summary of the Invention

[0003] This invention provides a stacked flat-plate satellite spin-and-release system, comprising: a rocket final stage body 1, a flat-plate satellite 2, a stacked satellite locking device 3, and a stacked satellite guide support column 4. A satellite adapter 5 is connected to the end of the rocket final stage body. Multiple stacked satellite locking devices 3 are connected to the satellite adapter 5. The flat-plate satellite 2 is enclosed within the area formed by the multiple stacked satellite locking devices 3 and locked by the stacked satellite locking devices 3. When the stacked satellite locking devices 3 are released, the flat-plate satellite 2 disengages from the stacked satellite locking devices 3. Multiple rows of flat-plate satellites are stacked in parallel within the flat-plate satellite 2. Each row of flat-plate satellites is nested and guided by the stacked satellite guide support column 4, and each row of flat-plate satellites can be detached and connected.

[0004] As described above, a stacked flat-plate satellite spin-throw separation system is provided, wherein movable stacked satellite locking devices 3 are connected to the satellite adapter 5 in all four directions (up, down, left, and right), and the stacked satellite locking devices 3 lock the flat-plate satellite 2 inside.

[0005] As described above, a stacked flat satellite spin-and-spin separation system is provided inside the rocket's final stage body 1. The unlocking device is controlled by the rocket's internal controller. When the unlocking device is unlocked, the stacked satellite locking device 3 on the control satellite adapter is released, the flat satellite 2 separates from the stacked satellite locking device 3, and the parallel satellite leaves the rocket body.

[0006] As described above, a stacked flat-panel satellite spin-throw separation system is provided, wherein stacked satellite guide support columns 4 are installed between two adjacent rows of parallel satellites. The stacked satellite guide support column 4 consists of a separable nested part and a grooved part. When the flat-panel satellite is locked, the nested part is inserted into the grooved part. When the flat-panel satellite is unlocked, the nested part is separated from the grooved part, thereby realizing the separation between the parallel satellites.

[0007] The present invention also provides a method for separating stacked flat-panel satellites by spin-throwing, comprising:

[0008] Once the rocket's final stage 1 reaches its deployment location for the flat-panel satellite 2, and the launch vehicle enters orbit, the thrusters of the final stage 1 induce steady-state rotation in the pitch or yaw direction, controlling the final stage 1 to rotate at a slow angular velocity. Rotate;

[0009] When the unlocking device is released, the stacked satellite locking device 3 is released, and the stacked flat satellite 2 gradually leaves the rocket body under the action of steady-state rotational angular velocity;

[0010] The flat-panel satellites 2 are nested and guided by the stacked satellite guide support columns 4. Under the action of rotational angular velocity, the stacked satellites separate from each other due to the velocity difference formed by the difference in inertia.

[0011] As described above, in a stacked flat-plate satellite spin-throw separation method, during the spin-throw separation process, the rocket's final stage body and the flat-plate satellite are simultaneously subjected to a steady-state angular velocity and the satellite is unlocked and ejected, specifying the exact rotation method and rotation speed.

[0012] In the stacked flat-plate satellite spin-projection separation method described above, the tangential velocity at the separation moment of the nth flat-plate satellite is calculated during the spin-projection separation process. and normal velocity ; Tangential velocity , Rn is the angular velocity induced by the final stage of the rocket during separation; Rn is the distance between the nth flat-plate satellite and the final stage of the rocket; normal velocity. , .

[0013] As described above, in a method for separating stacked flat-plate satellites by spin-throwing, the support columns are nested and their strokes are... The groove depth of the recessed part and the nesting stroke of the load-bearing column. .

[0014] The beneficial effects achieved by this invention are as follows:

[0015] (1) This method can realize the stacking and spin-throw separation of flat satellites, which greatly reduces the mass of the separation mechanism compared with the traditional method.

[0016] (2) By designing the nested stroke of the support columns of the stacked satellite guide support columns, the satellites do not collide with each other during the spin-throw separation process, which greatly improves the near-field separation safety of the stacked satellites and protects the safety of the satellites. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0018] Figure 1 This is a structural diagram of a stacked flat-panel satellite spin-throw separation system provided in Embodiment 1 of the present invention;

[0019] Figure 2 This is a schematic diagram of the stacked flat-plate satellite spin-throw separation provided in an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the calculation process for the spin-jet separation. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] Example 1

[0023] See Figure 1 Embodiment 1 of the present invention provides a stacked flat satellite spin-and-spin separation system, including a rocket final stage body 1, a flat satellite 2, a stacked satellite locking device 3, and a stacked satellite guide support column 4. The end of the rocket final stage body is connected to a satellite adapter 5. Multiple stacked satellite locking devices 3 are connected to the satellite adapter 5. The flat satellite 2 is wrapped in the area enclosed by the multiple stacked satellite locking devices 3 and locked by the stacked satellite locking devices 3. When the stacked satellite locking devices 3 are released, the flat satellite 2 is detached from the stacked satellite locking devices 3. Multiple rows of flat satellites are stacked in parallel in the flat satellite 2. Each row of flat satellites is nested and guided by the stacked satellite guide support column 4. Each row of flat satellites can be detached and connected.

[0024] Specifically, movable stacking satellite locking devices 3 are connected to the satellite adapter 5 in all four directions (up, down, left, and right), and the flat satellite 2 is locked inside the stacking satellite locking devices 3. An unlocking device is installed inside the rocket's final stage body 1. The unlocking device is controlled by the rocket's internal controller. When the unlocking device unlocks, it releases the stacking satellite locking devices 3 on the satellite adapter, causing the flat satellite 2 to separate from the stacking satellite locking devices 3, and the parallel satellite leaves the rocket body.

[0025] Stacked satellite guide support columns 4 are installed between two adjacent rows of parallel satellites. The stacked satellite guide support column 4 consists of a separable nested part and a grooved part. Optionally, the nested part is connected to the lower end of the upper row of parallel satellites, and the grooved part is connected to the upper end of the lower row of parallel satellites. When the flat satellite is locked, the nested part is inserted into the grooved part. When the flat satellite is unlocked, the nested part is separated from the grooved part, thereby realizing the separation between the parallel satellites.

[0026] Example 2

[0027] Embodiment 2 of the present invention provides a method for separating stacked flat-panel satellites by spin-throwing, comprising:

[0028] Step 310: The final stage of the rocket 1 reaches the deployment position for the flat-panel satellite 2. After the launch vehicle enters orbit, the thrusters of the final stage of the rocket 1 induce steady-state rotation of the final stage of the rocket 1 in the pitch or yaw direction, controlling the final stage of the rocket 1 to rotate at a slow angular velocity. Rotate;

[0029] Figure 2 At time T0, the final stage of the rocket 1 has reached (or is about to reach) the deployment location for the flat-panel satellite 2. This deployment location can be at or near the predetermined orbital plane or orbital path of the flat-panel satellite 2. Specifically, after the launch vehicle enters orbit at time T0, the thrusters of the final stage of the rocket 1 induce a steady-state rotation of the final stage of the rocket 1 in the pitch or yaw direction, controlling the final stage of the rocket 1 to rotate at a slow angular velocity. Rotation enables the rocket's final stage body 1 to rotate around its center of mass.

[0030] Step 320: When the unlocking device is released, the stacked satellite locking device 3 is released, and the stacked flat satellites 2 gradually leave the rocket body under the action of steady-state rotational angular velocity;

[0031] Figure 2 At time T1, the rocket's final stage 1 releases the flat-plate satellite 2 by unlocking the stacked satellite locking device 3. Specifically, at time T1, the rocket's unlocking device is released, the stacked satellite locking device 3 is released, and the flat-plate satellites are nested and guided by the stacked satellite guide support column 4, while the flat-plate satellites continue to rotate around a fixed center of mass.

[0032] Step 330: The flat satellites 2 are nested and guided by the stacked satellite guide support column 4. Under the action of rotational angular velocity, the stacked satellites separate from each other due to the velocity difference formed by the difference in inertia.

[0033] Figure 2At time T2, under the influence of steady-state rotational angular velocity, the stacked flat-plate satellite 2 will gradually separate from the rocket body, using the velocity difference formed by the inertia difference of the stacked satellites under the influence of rotational angular velocity to separate them. During the spin-jet separation process, the rocket's final stage body and the flat-plate satellite combination are simultaneously subjected to steady-state angular velocity and unlocked to eject the satellites, with specific rotation methods and speeds defined. Furthermore, to avoid launch collisions between satellites during the spin-jet separation process, the nesting stroke of the stacked satellite guide support columns is designed. .

[0034] Figure 3 In the process of spin-projectile separation, the tangential velocity at the moment of separation of the nth flat-panel satellite is calculated. and normal velocity ; Tangential velocity , R is the angular velocity induced by the rocket's final stage body during separation. n The distance between the nth flat-panel satellite and the final stage of the rocket; normal velocity. , .

[0035] To avoid nested travel of the stacked satellite guide support columns during the spin-throw separation process. Nested stroke of load-bearing columns The groove depth of the recessed part and the nesting stroke of the load-bearing column. As can be seen from the formula, The larger the stacked flat-panel satellites are, the higher their normal velocity when they separate from each other. The larger the distance between the flat-panel satellites, the greater the distance between them. During the rotation and separation process, the satellites will always maintain a safe distance to avoid collisions.

[0036] For example, for satellites with a single flat-panel mass of less than 300 kg, when stacking at least 18 satellites, the rotational angular velocity induced by the rocket's final stage body during separation is: The selection range is (0.5~2.5)° / s, and its magnitude mainly affects the separation time. The nesting stroke of the stacked satellite guide support columns. The value should be selected between 250mm and 300mm.

[0037] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made on the basis of the technical solution of the present invention should be included within the scope of protection of the present invention.

Claims

1. A stacked planar satellite spin-stabilized separation system, characterized by, include: The rocket's final stage body (1), flat satellite (2), stacked satellite locking device (3), and stacked satellite guide support column (4) are connected to the end of the rocket's final stage body. A satellite adapter (5) is connected to the satellite adapter (5). Multiple stacked satellite locking devices (3) are connected to the satellite adapter (5). The flat satellite (2) is wrapped in the area enclosed by multiple stacked satellite locking devices (3) and locked by the stacked satellite locking devices (3). When the stacked satellite locking devices (3) are released, the flat satellite (2) is released from the stacked satellite locking devices (3). Multiple rows of flat satellites are stacked in parallel in the flat satellite (2). Each row of flat satellites is nested and guided by the stacked satellite guide support column (4). Each row of flat satellites can be separated and connected. The rocket's final stage (1) reaches the deployment location for the flat-panel satellite (2). After the launch vehicle enters orbit, the thrusters of the rocket's final stage (1) induce a steady-state rotation of the rocket's final stage (1) in the pitch or yaw direction, controlling the rocket's final stage (1) to rotate at a slow angular velocity. Rotate; When the unlocking device is released, the stacked satellite locking device (3) is released, and the stacked flat satellites (2) gradually leave the rocket body under the action of steady-state rotational angular velocity; The flat satellites (2) are nested and guided by the stacked satellite guide support column (4). Under the action of rotational angular velocity, the stacked satellites separate from each other due to the velocity difference formed by the difference in inertia. During the spin-throw separation process, the rocket's final stage body (1) and the flat satellite (2) are combined to apply a steady-state angular velocity and unlock to throw out the satellite, thus clarifying the specific rotation method and rotation speed; Calculate the tangential velocity at the moment of separation of the nth flat-panel satellite. and normal velocity ; Tangential velocity , R is the angular velocity induced by the rocket's final stage body during separation. n The distance between the nth flat-panel satellite and the final stage of the rocket; normal velocity. , ; To prevent collisions between satellites during the spin-and-splitter separation process and ensure a safe distance between them, a nested stroke for the stacked satellite guide support columns is designed. Nested stroke of load-bearing columns The groove depth of the recessed part and the nesting stroke of the load-bearing column. .

2. A stacked satellite spin-stabilized separation system as in claim 1 wherein, The satellite adapter (5) is connected to movable stackable satellite locking devices (3) in all four directions (up, down, left, right) and the stackable satellite locking devices (3) lock the flat satellite (2) inside.

3. A stacked PSS spin-stabilization separation system as in claim 1, wherein, An unlocking device is installed inside the rocket's final stage body (1). The unlocking device is controlled by the rocket's internal controller. When the unlocking device is unlocked, the stacked satellite locking device (3) on the control satellite adapter is released, the flat satellite (2) separates from the stacked satellite locking device (3), and the parallel satellite leaves the rocket body.

4. A stacked PSS spin-stabilization separation system as in claim 1, wherein, Stacked satellite guide support columns (4) are installed between two adjacent rows of parallel satellites. The stacked satellite guide support column (4) consists of a separable nested part and a grooved part. When the flat satellite is locked, the nested part is inserted into the grooved part. When the flat satellite is unlocked, the nested part is separated from the grooved part, thereby realizing the separation between the parallel satellites.

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