A simple rope-tethered satellite ejection and release mechanism

Abstract

The present invention discloses a simple rope-tethered satellite ejection and release mechanism for the movement and release of a sub-satellite. This mechanism is installed on the main satellite. The mechanism includes a guiding mechanism (1), a pre-tightening and release mechanism (2), and a sub-satellite connection mechanism (3). The sub-satellite connection mechanism (3) is arranged in the rectangular through-hole of the guiding mechanism (1) and is separated by the restraint of a spring. The pre-tightening and release mechanism (2) consists of a wire cutter bracket (2A), a wire cutter (2B), a spring push plate (2C), a spring (2D), and a pulling wire (2E). The wire cutter (2B) is installed on the wire cutter bracket (2A), and the wire of the wire cutter (2B) passes through the spring (2D); the spring (2D) is installed between the spring push plate (2C) and the AC fixing bracket (1C), and the pulling wire (2E) is installed on the wire cutter (2B) and the AC fixing bracket (1C). This mechanism has a simple and compact structure, can limit the displacement of the sub-satellite in all directions before the release instruction, and can respond quickly during the release. It is especially suitable for the release tasks of small-scale rope-tethered satellite systems in universities and small-scale atmospheric sails and solar sails for experiments.

Description

Technical Field

[0001] The present invention relates to the technical field of space tethered satellite systems, and particularly relates to a simple tethered satellite ejection and release mechanism. Background Art

[0002] In the field of tethered satellite systems, spring compression and release devices are widely used in the release operation of sub-satellites. Before the release operation of the sub-satellite, the spring compression and release device can compress the release spring and fix the sub-satellite on the main satellite. After receiving the release signal, the restraint of the sub-satellite and the spring by the spring compression and release device is released, relative displacement can occur between the sub-satellite and the main satellite, the compressed spring automatically returns to its original length, and the elastic potential energy of the spring is converted into the kinetic energy of the sub-satellite to complete the release of the sub-satellite.

[0003] Currently, for tethered satellite systems, spring compression and release devices are mostly realized by mechanical structures for compression. Especially for universities, in experimental small-scale tethered satellite systems, such as small atmospheric sails and small solar sails, using mechanical structures to achieve compression is too cumbersome and redundant, which is not conducive to the simplification and lightweight of small-scale tethered satellite systems, and at the same time reduces the reliability of system release.

[0004] Currently, for small experimental tethered satellite systems, specific spring compression and release devices need to be independently designed for specific tasks, and there is a lack of a spring compression and release product that is simple to apply and has a wide range of applications on the market. Summary of the Invention

[0005] The technical solution adopted by the present invention is to provide a spring compression and release mechanism for a small-scale tethered satellite system. The spring compression and release mechanism of the present invention is installed on the main satellite through fixing brackets (1A, 1B). The spring compression and release mechanism of the present invention is assembled into an integrated body through a pre-tightening and release mechanism (2) and a sub-satellite connection mechanism (3). The spring compression and release mechanism of the present invention includes a guiding mechanism (1), a pre-tightening and release mechanism (2), and a sub-satellite connection mechanism (3). The guiding mechanism (1) is fixedly connected to the main satellite through fixing brackets (1A, 1B) and plays a guiding role in the release of the sub-satellite. The pre-tightening and release mechanism (2) is assembled through a pull wire (2E) and an AC fixing bracket (1C), and it plays the role of pre-compressing the release spring and releasing the sub-satellite. The sub-satellite connection mechanism (3) is installed in the rectangular through-hole type guide rail of the guiding mechanism (1) and contacts the wire cutting bracket (2A) of the pre-tightening and release mechanism (2). The sub-satellite connection base (3A) of the sub-satellite connection mechanism (3) is fixedly connected to the sub-satellite through bolts to realize the fixation of the sub-satellite and the transmission of the release action.

[0006] The present invention is a simple tethered satellite ejection and release mechanism, which includes a guiding mechanism (1), a pre-tightening and release mechanism (2), and a sub-satellite connection mechanism (3);

[0007] The guiding mechanism (1) is provided with an AA fixing bracket (1A), an AB fixing bracket (1B), an AC fixing bracket (1C) and a bottom panel (1D); the AA fixing bracket (1A), the AB fixing bracket (1B) and the AC fixing bracket (1C) are arranged on the bottom panel (1D);

[0008] The front end of the bottom panel (1D) is provided with an AE through hole (1D1) for installing with the main star connecting plate;

[0009] The structures of the AA fixing bracket (1A) and the AB fixing bracket (1B) are the same;

[0010] The AA fixing bracket (1A) is provided with an AA type bracket (1A1), an AA lug panel (1A2) and an AB lug panel (1A3);

[0011] The joint of the AA type bracket (1A1) with the AA lug panel (1A2) and the AB lug panel (1A3) forms an AA rectangular hole (1A11); the AA rectangular hole (1A11) is for the front end of the sub - star connecting arm (3B) of the sub - star connecting mechanism (3) to pass through;

[0012] The AA lug panel (1A2) is provided with an AA through hole (1A21) for installing with the main star connecting plate;

[0013] The AB lug panel (1A3) is provided with an AB through hole (1A31) for installing with the main star connecting plate;

[0014] The AB fixing bracket (1B) is provided with an AB type bracket (1B1), an AC lug panel (1B2) and an AD lug panel (1B3);

[0015] The joint of the AB type bracket (1B1) with the AC lug panel (1B2) and the AD lug panel (1B3) forms an AB rectangular hole (1B11); the AB rectangular hole (1B11) is for the front end of the sub - star connecting arm (3B) of the sub - star connecting mechanism (3) to pass through;

[0016] The AC lug panel (1B2) is provided with an AC through hole (1B21) for installing with the main star connecting plate;

[0017] The AD lug panel (1B3) is provided with an AD through hole (1B31) for installing with the main star connecting plate;

[0018] The AC fixing bracket (1C) is provided with a vertical plate (1C1) and a hollow convex cylinder (1C2), and the hollow convex cylinder (1C2) is arranged outside the vertical plate (1C1); the central through hole (1C3) is for placing the wire (2E) of the pre - tightening and releasing mechanism (2);

[0019] The pre-tightening and releasing mechanism (2) consists of a wire cutter bracket (2A), a wire cutter (2B), a spring push plate (2C), a spring (2D), and a pull wire (2E); the wire cutter (2B) is powered by the main star power supply;

[0020] The wire cutter bracket (2A) is provided with a front panel (2A1), a rear panel (2A2), and an arc plate (2A3). The arc plate (2A3) is located between the front panel (2A1) and the rear panel (2A2), and the wire cutter (2B) is placed on the arc plate (2A3); the front panel (2A1) is provided with a BA through hole (2A11), and the BA through hole (2A11) is used for the BA wire (2B2) and BB wire (2B3) on the wire cutter (2B) to pass through;

[0021] The wire cutter (2B) is provided with a BB through hole (2B1), and the BB through hole (2B1) is used for the pull wire (2E) to pass through;

[0022] The spring push plate (2C) is provided with a BC through hole (2C1) for the BA wire (2B2) and BB wire (2B3) to pass through;

[0023] The spring (2D) is installed between the spring push plate (2C) and the vertical plate (1C1) of the AC fixing bracket (1C). One end of the spring (2D) is fixed to the spring push plate (2C), and the other end of the spring (2D) is fixed to the AC fixing bracket (1C) and is coaxially arranged with the axis direction of the sub-star connecting arm (3B);

[0024] One end of the pull wire (2E) is installed in the central through hole (1C3) of the hollow convex cylinder (1C2) of the AC fixing bracket (1C), and the other end of the pull wire (2E) is installed in the BB through hole (2B1) of the wire cutter (2B);

[0025] The sub-star connecting mechanism (3) is provided with a sub-star connecting base (3A) and a sub-star connecting arm (3B);

[0026] The sub-star connecting base (3A) is provided with a CA through hole (3A1), a CA threaded hole (3A2), a CB threaded hole (3A3), a CC threaded hole (3A4), and a CD threaded hole (3A5); a sub-star support rod (4) is installed in the CA through hole (3A1); after the sub-star support rod (4) is installed in the CA through hole (3A1), the sub-star support rod (4) is fixed to the sub-star connecting base (3A) by installing bolts in the CA threaded hole (3A2), CB threaded hole (3A3), CC threaded hole (3A4), and CD threaded hole (3A5) respectively;

[0027] The body of the sub-star connecting arm (3B) is provided with a weight reduction hole (3B2); the center of the sub-star connecting arm (3B) is a CA rectangular cavity (3B1);

[0028] Before the release of the sub - satellite connection mechanism (3), the sub - satellite connection mechanism (3) is restricted within the fixed frame of the guiding mechanism (1) under the action of the wire rope (2E); after the wire rope (2E) is cut, the restraint on the sub - satellite connection arm (3B) of the sub - satellite connection mechanism (3) in its axial direction is released, the spring (2D) returns to its original length, and under the push of the spring push plate (2C), the sub - satellite connection arm (3B) is ejected.

[0029] The beneficial effects of the spring - pressed release mechanism of the small tethered satellite system of the present invention are as follows: The guiding mechanism (1), pre - tightening and release mechanism (2), and sub - satellite connection mechanism (3) designed in the present invention are simple and compact in structure. They can limit the displacements of the sub - satellite in all directions before the release instruction and can respond quickly during the release. The spring - pressed release mechanism of the present invention has a wide range of applications. For tasks with sub - satellites of different masses and different release speeds, the specified release action can be completed by selecting different models of springs and wire ropes with different materials and different geometric dimensions. The sub - satellite connection mechanism is manufactured by 3D printing technology and can realize the fixation with sub - satellites of different geometric shapes. The spring - pressed release mechanism of the present invention has reliable effects and low manufacturing costs, and is especially suitable for the release tasks of small tethered satellite systems in universities, as well as small atmospheric sails and solar sails for experiments. Brief Description of the Drawings

[0030] Figure 1 is the structural diagram of the simple tethered satellite ejection release mechanism of the present invention.

[0031] Figure 1A is the structural diagram of another perspective of the simple tethered satellite ejection release mechanism of the present invention.

[0032] Figure 1B is Figure 1A the sectional structural diagram of

[0033] Figure 1C is the exploded view of the simple tethered satellite ejection release mechanism of the present invention.

[0034] Figure 2 is the structural diagram of the pre - tightening and release mechanism in the simple tethered satellite ejection release mechanism of the present invention.

[0035] Figure 2A is the assembly structural diagram of the wire cutter and the wire cutter bracket of the present invention.

[0036]

[0037] Detailed Embodiment

[0038] The present invention will be further described in detail below in conjunction with the drawings.

[0039] See Figure 1 ,Figure 1A , Figure 1B , Figure 1C As shown in Figure 1C , a simple cable - tied satellite ejection and release mechanism for sub - satellite movement release designed by the present invention includes a guiding mechanism 1, a pre - tightening and release mechanism 2, and a sub - satellite connection mechanism 3.

[0040] Guide mechanism 1

[0041] See Figure 1 , Figure 1A , Figure 1B , Figure 1C As shown in Figure 1 , Figure 1A , Figure 1B , and Figure 1C , in the present invention, the guiding mechanism 1 is an integrally formed structural member. The guiding mechanism 1 is provided with an AA fixing bracket 1A, an AB fixing bracket 1B, an AC fixing bracket 1C, and a bottom panel 1D. The AA fixing bracket 1A, the AB fixing bracket 1B, and the AC fixing bracket 1C are arranged on the bottom panel 1D.

[0042] The front end of the bottom panel 1D is provided with an AE through - hole 1D1. By placing a screw in the AE through - hole 1D1, the front end of the bottom panel 1D is fixed to the main - satellite connecting plate.

[0043] The AA fixing bracket 1A and the AB fixing bracket 1B have the same structure.

[0044] See Figure 1C As shown in Figure 1C , the AA fixing bracket 1A is provided with an AA - type frame 1A1, an AA lug panel 1A2, and an AB lug panel 1A3.

[0045] The engagement of the AA - type frame 1A1 with the AA lug panel 1A2 and the AB lug panel 1A3 forms an AA rectangular hole 1A11. The AA rectangular hole 1A11 is for the front end of the sub - satellite connection arm 3B of the sub - satellite connection mechanism 3 to pass through.

[0046] The AA lug panel 1A2 is provided with an AA through - hole 1A21. A screw passes through the AA through - hole 1A21 and mates with a threaded hole on the main - satellite connecting plate to realize the fixed installation of the guiding mechanism 1 and the main - satellite connecting plate.

[0047] See Figure 1A , Figure 1C As shown in Figure 1A and Figure 1C , the AB lug panel 1A3 is provided with an AB through - hole 1A31. A screw passes through the AB through - hole 1A31 and mates with a threaded hole on the main - satellite connecting plate to realize the fixed installation of the guiding mechanism 1 and the main - satellite connecting plate.

[0048] See Figure 1C As shown in Figure 1C , the AB fixing bracket 1B is provided with an AB - type frame 1B1, an AC lug panel 1B2, and an AD lug panel 1B3.

[0049] The engagement of the AB - type frame 1B1 with the AC lug panel 1B2 and the AD lug panel 1B3 forms the AB rectangular hole 1B11. The AB rectangular hole 1B11 is used for the front end of the sub - satellite connection arm 3B of the sub - satellite connection mechanism 3 to pass through.

[0050] The AC lug panel 1B2 is provided with an AC through - hole 1B21. A screw passes through the AC through - hole 1B21 and mates with the threaded hole on the main - satellite connection plate, realizing the fixed installation of the guiding mechanism 1 and the main - satellite connection plate.

[0051] See Figure 1A 、 Figure 1C As shown, the AD lug panel 1B3 is provided with an AD through - hole 1B31. A screw passes through the AD through - hole 1B31 and mates with the threaded hole on the main - satellite connection plate, realizing the fixed installation of the guiding mechanism 1 and the main - satellite connection plate.

[0052] See Figure 1C As shown, the AC fixing frame 1C is provided with a vertical plate 1C1 and a hollow convex cylinder 1C2. The hollow convex cylinder 1C2 is arranged on the outside of the vertical plate 1C1. The central through - hole 1C3 is used to place the wire 2E of the pre - tightening and releasing mechanism 2.

[0053] In the present invention, the guiding mechanism 1 is designed as a channel structure of a fixed frame (AA fixed frame 1A, AB fixed frame 1B) of two - segment separated "U" - shaped thin plates. The two fixed - frame thin plates are installed on the bottom panel 1D at a certain distance and coaxially, which is beneficial to the sliding of the sub - satellite connection arm 3B of the sub - satellite connection mechanism 3 during release.

[0054] In the present invention, the material of the guiding mechanism 1 is 2 - series or 7 - series aluminum alloy material.

[0055] Pre-tightening and releasing mechanism 2

[0056] See Figure 1 、 Figure 1A 、 Figure 1B 、 Figure 1C 、 Figure 2 、 Figure 2A As shown, in the present invention, the pre - tightening and releasing mechanism 2 is composed of a thread - cutting device bracket 2A, a thread - cutting device 2B, a spring push - plate 2C, a spring 2D, and a wire 2E. The thread - cutting device 2B is powered by the main - satellite power supply. In the present invention, the thread - cutting device 2B selects the AOXI model computerized sewing machine thread - cutting electromagnet of Taizhou Jiaojiang Chennuo Sewing Equipment Business.

[0057] The wire cutter bracket 2A is provided with a front panel 2A1, a rear panel 2A2, and an arc-shaped plate 2A3. The arc-shaped plate 2A3 is located between the front panel 2A1 and the rear panel 2A2, and a wire cutter 2B is placed on the arc-shaped plate 2A3. The front panel 2A1 is provided with a BA through-hole 2A11 for the BA wire 2B2 and the BB wire 2B3 on the wire cutter 2B to pass through. In the present invention, the BA wire 2B2 and the BB wire 2B3 are respectively connected to the spring restraint control signal terminals of the main star for receiving the instructions of the wire cutting and pulling wire 2E.

[0058] The wire cutter 2B is provided with a BB through-hole 2B1 for the pulling wire 2E to pass through.

[0059] The spring push plate 2C is provided with a BC through-hole 2C1 for the BA wire 2B2 and the BB wire 2B3 on the wire cutter 2B to pass through.

[0060] The spring 2D is installed between the spring push plate 2C and the vertical plate 1C1 of the AC fixed bracket 1C. One end of the spring 2D is fixed to the spring push plate 2C, and the other end of the spring 2D is fixed to the AC fixed bracket 1C and is coaxially arranged with the axis direction of the sub-star connection arm 3B. In the present invention, both ends of the spring 2D are fixedly connected to the spring push plate 2C and the vertical plate 1C1 in an adhesive form.

[0061] One end of the pulling wire 2E is installed in the central through-hole 1C3 of the hollow convex cylinder 1C2 of the AC fixed bracket 1C, and the other end of the pulling wire 2E is installed in the BB through-hole 2B1 of the wire cutter 2B.

[0062] In the present invention, the pulling wire 2E on the pre-tightening and releasing mechanism 2 is respectively installed on the AC fixed bracket 1C and the wire cutter 2B to limit the slippage of the pulling wire 2E in the axis direction of the sub-star connection arm 3B. The spring push plate 2C is used to pre-press the spring 2D and push the sub-star connection mechanism 3 to complete the release during the process of the spring 2D returning to its original length. The spring push plate 2C is a square plate structure with a hole in the middle, one side is fixedly connected to the spring 2D, and the other side is fixedly connected to the wire cutter bracket 2A for arranging the wire cutter 2B.

[0063] In the present invention, as shown in Figure 1A 、 Figure 1B One end of the pulling wire 2E passes through the central through-hole 1C3 of the hollow convex cylinder 1C2 of the AC fixed bracket 1C → the weight-reducing hole 3B2 (one side) on the sub-star connection arm 3B → the BB through-hole 2B1 of the wire cutter 2B → the weight-reducing hole 3B2 (the other side) on the sub-star connection arm 3B → and returns to the central through-hole 1C3 to form a closed rope segment. The closed pulling wire 2E can compress the spring 2D at a specified position. When the pulling wire 2E is cut, the spring 2D returns to its original length to realize the action release of the sub-star connection mechanism 3.

[0064] Sub-satellite connection mechanism 3

[0065] See Figure 1 、 Figure 1A 、 Figure 1B 、 Figure 1C As shown, in the present invention, the sub - satellite connection mechanism 3 is manufactured by 3D printing technology as an integrally formed structural member. The sub - satellite connection mechanism 3 is provided with a sub - satellite connection base 3A and a sub - satellite connection arm 3B. The material of the sub - satellite connection mechanism 3 is nylon carbon fiber.

[0066] The sub - satellite connection base 3A is provided with a CA through - hole 3A1, a CA threaded hole 3A2, a CB threaded hole 3A3, a CC threaded hole 3A4 and a CD threaded hole 3A5. A sub - satellite support rod 4 is installed in the CA through - hole 3A1. After the sub - satellite support rod 4 is installed in the CA through - hole 3A1, the sub - satellite support rod 4 is fixed to the sub - satellite connection base 3A by installing bolts in the CA threaded hole 3A2, the CB threaded hole 3A3, the CC threaded hole 3A4 and the CD threaded hole 3A5 respectively.

[0067] The body of the sub - satellite connection arm 3B is provided with a weight - reducing hole 3B2. The center of the sub - satellite connection arm 3B is a CA rectangular cavity 3B1. In the present invention, the sub - satellite connection arm 3B adopts a hollow design, which can reduce the weight of the sub - satellite connection mechanism 3.

[0068] In the present invention, the hollow - designed sub - satellite connection mechanism 3 slides in the AA rectangular hole 1A1A and the AB rectangular hole 1B1A of the guiding mechanism 1. Due to the limitation of the working environment, the airflow generated by the sliding will be lost through the gaps of the weight - reducing hole 3B2 and the CA rectangular cavity 3B1, making the sliding effect of the sub - satellite connection mechanism 3 on the guiding mechanism 1 better.

[0069] In the present invention, the sub - satellite connection mechanism 3 is a hollow thin - wall square - tube structure, and at the same time, a sub - satellite connection base 3A and a sub - satellite connection arm 3B are designed. It is fixedly connected to the bracket on the sub - satellite body as a whole through two bolts. The sub - satellite connection arm 3B of the sub - satellite connection mechanism 3 is installed in the AA rectangular hole 1A1A and the AB rectangular hole 1B1A of the guiding mechanism 1 and contacts with the spring push - plate 2C of the pre - tightening and releasing mechanism 2. Before the sub - satellite connection mechanism 3 is released, its movement in the axial direction of the sub - satellite connection arm 3B is restricted by a wire 2E.

[0070] In the present invention, before the release of the sub - satellite connection mechanism 3, the sub - satellite connection mechanism 3 is restricted within the fixed frame of the guiding mechanism 1 under the action of the pulling wire 2E; after the pulling wire 2E is cut, the restraint on the sub - satellite connection arm 3B of the sub - satellite connection mechanism 3 in its axial direction is released, the spring 2D returns to its original length, and under the push of the spring push plate 2C, the sub - satellite connection arm 3B is ejected. The sub - satellite support rod 4 is installed in the CA through - hole 3A1 of the sub - satellite connection base 3A and is fixedly connected by bolts. After the fixation, the sub - satellite connection mechanism 3 and the sub - satellite become an integral body. After the release is completed, the two are still connected together.

[0071] Working process of the simple tethered satellite ejection and release mechanism

[0072] (A), fix the spring 2D to the spring push plate 2C and the AC fixed frame 1C, install the wire cutter 2B at the arc - shaped plate 2A3 of the wire cutter support 2A. The wires (2B2, 2B3) on the wire cutter 2B pass through the BC through - hole 2C1 in the middle of the spring push plate 2C and the internal through - hole of the spring 32, and then are led out from the gap of the spring 2D, and then connected to the spring restraint control signal terminal of the main satellite to receive the spring restraint control signal of the main satellite.

[0073] Fix the guiding mechanism 1 to the main satellite by bolts. Fix the sub - satellite connection base 3A of the sub - satellite connection mechanism 3 to the sub - satellite by bolts.

[0074] Place the wire cutter support 2A in the pre - tightening and release mechanism 2 assembled into the sub - satellite connection arm 3B of the sub - satellite connection mechanism 3, and connect it to the AC fixed frame 1C of the guiding mechanism 1 through the pulling wire 2E to complete the assembly of the guiding mechanism 1 and the pre - tightening and release mechanism 2. At this point, just place the sub - satellite connection arm 3B of the sub - satellite connection mechanism 3 in the rectangular through - hole of the guiding mechanism 1 and compress the spring 2D.

[0075] After adjusting the wires (2B2, 2B3) on the wire cutter 2B to the appropriate positions, they can be fixedly connected to the vertical plate 1C1 with glue. After adjusting the spring 2D to be compressed to the predetermined position, pass the pulling wire 2E through the central through - hole of the AC fixed frame 1C on the guiding mechanism 1, and tie the head and tail ends of the pulling wire 2E. Connect the wires on the wire cutter 2B to the spring restraint control signal terminal of the main satellite. Thus, the assembly of the simple tethered satellite ejection and release mechanism is completed.

[0076] (B), when the wire cutter 2B receives the release signal, the wire cutter 2B cuts the pulling wire 2E, the restraint between the spring 2D and the sub - satellite connection mechanism 3 is released, the spring 2D returns to its original length, the spring push plate 2C pushes the sub - satellite connection arm 3B, and the sub - satellite connection arm 3B is ejected from the guiding mechanism 1, and the sub - satellite release task is thus completed.

[0077] The present invention designs a simple rope - tied satellite ejection and release mechanism for the release of sub - satellite actions. The problem to be solved is how to design a spring - pressed release device for a space rope - tied satellite system that can meet different mission requirements, and a spring - pressed release product that is compact in structure, has high release performance and reliability, and is lightweight, so as to realize a satellite that can meet various missions of the space rope - tied satellite system by applying a satellite ejection and release mechanism.

Claims

1. A simple rope - tied satellite ejection and release mechanism, characterized in that: It includes a guiding mechanism (1), a pre-tightening and releasing mechanism (2), and a sub-satellite connecting mechanism (3). The guiding mechanism (1) is provided with an AA fixing bracket (1A), an AB fixing bracket (1B), an AC fixing bracket (1C), and a bottom panel (1D); the AA fixing bracket (1A), the AB fixing bracket (1B), and the AC fixing bracket (1C) are arranged on the bottom panel (1D). At the front end of the bottom panel (1D), there is an AE through hole (1D1) for installing with the main satellite connecting plate. The structures of the AA fixing bracket (1A) and the AB fixing bracket (1B) are the same. The AA fixing bracket (1A) is provided with an AA type bracket (1A1), an AA lug panel (1A2), and an AB lug panel (1A3). The joint of the AA type bracket (1A1) with the AA lug panel (1A2) and the AB lug panel (1A3) forms an AA rectangular hole (1A11); the AA rectangular hole (1A11) is for the front end of the sub-satellite connecting arm (3B) of the sub-satellite connecting mechanism (3) to pass through. On the AA lug panel (1A2), there is an AA through hole (1A21) for installing with the main satellite connecting plate. On the AB lug panel (1A3), there is an AB through hole (1A31) for installing with the main satellite connecting plate. The AB fixing bracket (1B) is provided with an AB type bracket (1B1), an AC lug panel (1B2), and an AD lug panel (1B3). The joint of the AB type bracket (1B1) with the AC lug panel (1B2) and the AD lug panel (1B3) forms an AB rectangular hole (1B11); the AB rectangular hole (1B11) is for the front end of the sub-satellite connecting arm (3B) of the sub-satellite connecting mechanism (3) to pass through. On the AC lug panel (1B2), there is an AC through hole (1B21) for installing with the main satellite connecting plate. On the AD lug panel (1B3), there is an AD through hole (1B31) for installing with the main satellite connecting plate. The AC fixing bracket (1C) is provided with a vertical plate (1C1) and a hollow convex cylinder (1C2), and the hollow convex cylinder (1C2) is arranged outside the vertical plate (1C1); a central through hole (1C3) is for placing the pulling wire (2E) of the pre-tightening and releasing mechanism (2). The pre-tightening and releasing mechanism (2) is composed of a wire cutting device bracket (2A), a wire cutting device (2B), a spring push plate (2C), a spring (2D), and a pulling wire (2E); the wire cutting device (2B) is powered by the main satellite power supply. The wire cutting device bracket (2A) is provided with a front panel (2A1), a rear panel (2A2), and an arc-shaped plate (2A3). The arc-shaped plate (2A3) is located between the front panel (2A1) and the rear panel (2A2), and the wire cutting device (2B) is placed on the arc-shaped plate (2A3); on the front panel (2A1), there is a BA through hole (2A11), and the BA through hole (2A11) is for the BA wire (2B2) and the BB wire (2B3) on the wire cutting device (2B) to pass through. On the wire cutting device (2B), there is a BB through hole (2B1), and the BB through hole (2B1) is for the pulling wire (2E) to pass through. On the spring push plate (2C), there is a BC through hole (2C1) for the BA wire (2B2) and the BB wire (2B3) to pass through. The spring (2D) is installed between the spring push plate (2C) and the vertical plate (1C1) of the AC fixing bracket (1C), and one end of the spring (2D) is fixed to the spring push plate (2C), and the other end of the spring (2D) is fixed to the AC fixing bracket (1C) and is coaxially arranged with the axis direction of the sub - satellite connection arm (3B); One end of the wire (2E) is installed in the central through - hole (1C3) of the hollow convex cylinder (1C2) of the AC fixing bracket (1C), and the other end of the wire (2E) is installed in the BB through - hole (2B1) of the wire cutter (2B); The sub - satellite connection mechanism (3) is provided with a sub - satellite connection base (3A) and a sub - satellite connection arm (3B); The sub - satellite connection base (3A) is provided with a CA through - hole (3A1), a CA threaded hole (3A2), a CB threaded hole (3A3), a CC threaded hole (3A4) and a CD threaded hole (3A5); A sub - satellite support rod (4) is installed in the CA through - hole (3A1); After the sub - satellite support rod (4) is installed in the CA through - hole (3A1), the sub - satellite support rod (4) is fixed to the sub - satellite connection base (3A) by installing bolts in the CA threaded hole (3A2), the CB threaded hole (3A3), the CC threaded hole (3A4) and the CD threaded hole (3A5) respectively; The body of the sub - satellite connection arm (3B) is provided with a weight - reducing hole (3B2); The center of the sub - satellite connection arm (3B) is a CA rectangular cavity (3B1); Before the sub - satellite connection mechanism (3) is released, the sub - satellite connection mechanism (3) is restricted within the fixed bracket of the guiding mechanism (1) under the action of the wire (2E); After the wire (2E) is cut, the constraint of the sub - satellite connection arm (3B) of the sub - satellite connection mechanism (3) in its axial direction is released, the spring (2D) returns to its original length, and under the push of the spring push plate (2C), the sub - satellite connection arm (3B) is ejected.

2. The simple rope-tethered satellite ejection and release mechanism according to claim 1, characterized in that: Both ends of the spring (2D) are fixedly connected to the spring push plate (2C) and the vertical plate (1C1) in an adhesive form.

3. The simple rope-tethered satellite ejection and release mechanism according to claim 1, wherein: The spring push plate (2C) is used to pre - compress the spring (2D) and push the sub - satellite connection mechanism (3) to complete the release during the process of the spring (2D) returning to its original length.

4. The simple rope-tethered satellite ejection and release mechanism according to claim 1, characterized in that: The layout of the wire (2E) is that one end of the wire (2E) passes through the central through - hole (1C3) of the hollow convex cylinder (1C2) of the AC fixing bracket (1C) → the weight - reducing hole (3B2) on one side of the sub - satellite connection arm (3B) → the BB through - hole (2B1) of the wire cutter (2B) → the weight - reducing hole (3B2) on the other side of the sub - satellite connection arm (3B) → and returns to the central through - hole (1C3) to form a closed rope segment. This closed wire (2E) can compress the spring (2D) at a specified position. When the wire (2E) is cut, the spring (2D) returns to its original length to realize the action release of the sub - satellite connection mechanism (3).

5. The simple rope-tethered satellite ejection and release mechanism according to claim 1, characterized in that: The sub - satellite connection arm (3B) adopts a hollow design, which can reduce the weight of the sub - satellite connection mechanism (3).

6. The simple rope-tethered satellite ejection and release mechanism according to claim 1, characterized in that: For the spring compression and release of the space tethered satellite system.

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