A rope-tethered star-rocket separation device and separation method

Abstract

A tethered satellite-rocket separation device and method are disclosed for separating a spacecraft from the upper stage of a rocket during advanced space launch missions. The device features no pyrotechnics, minimal separation impact, and reusability. The separation device includes a bolt catcher, a load-bearing bolt, a shear sleeve, a spring thruster, a rope, a directional pulley, a rope drum, and a motor. The separation method utilizes a spring thruster to provide initial separation force, allowing the satellite to gain initial velocity and separate from the upper stage. A rope deployment / retraction mechanism (including a directional pulley, rope drum, and motor) releases the rope as the satellite moves. Under centrifugal force, the upper stage, in conjunction with the rope deployment / retraction mechanism, controls the rope length and tension to ensure the rope remains taut at all times. The rope deployment / retraction mechanism gradually releases the rope, allowing the satellite to gradually move away from the upper stage. Upon reaching the separation distance, the rope separates from the satellite, and the rope deployment / retraction mechanism retracts the rope, completing the separation process.

Description

Technical Field

[0001] This invention relates to a rope-tethered star-rocket separation device and method, belonging to the field of star-rocket separation technology. Background Technology

[0002] In recent years, space launch missions have become increasingly diversified, and the separation device, as a key component of various spacecraft, plays a crucial role in launch missions. Traditional pyrotechnic separation devices have advantages such as high load-bearing capacity, rapid separation, and high functional reliability. However, they also have significant drawbacks such as high separation impact, poor safety, non-repeatability, and other notable defects, making them unsuitable for next-generation spacecraft requiring low-impact separation. Therefore, it is necessary to develop non-pyrotechnic, low-impact separation devices for advanced space launch missions. Summary of the Invention

[0003] The technical problem solved by the present invention is to overcome the shortcomings of the prior art and provide a rope-tethered satellite-rocket separation device and separation method, which can achieve separation distance adjustment, satellite attitude control and orbit adjustment by controlling the rope length and rope tension.

[0004] The technical solution of this invention is:

[0005] on the one hand,

[0006] This invention proposes a tethered satellite-rocket separation device, comprising: a satellite, an upper stage, a spring thruster, and a tethered control system;

[0007] The spring thruster and cable control system are located on the upper stage. When the satellite separates from the upper stage, the spring thruster provides the initial separation force. Under the action of the separation force, the satellite gains an initial velocity and leaves the upper stage.

[0008] The rope control system releases ropes as the satellite moves. The satellite and the upper stage are connected by ropes. Under the action of centrifugal force field, the rope control system controls the rope length and tension to ensure that the rope is always taut.

[0009] Once the satellite reaches the separation distance, the cable separates from the satellite, the cable control system retracts the cable, and the separation ends.

[0010] Furthermore, after the satellite is ejected by the spring thruster, the upper stage is connected to the satellite by a rope, forming a tethered space system. The satellite and the upper stage rotate relative to each other, forming a stable spin system around the system's center of mass.

[0011] Furthermore, it also includes bolt catchers, load-bearing bolts, shear sleeves, sleeve connecting screws, and thruster supports;

[0012] The shear sleeve is installed on one side of the satellite via sleeve connecting screws; after the satellite-rocket docking is completed, the shear sleeve compresses the free end of the spring thruster to the maximum compression state; the bearing bolt passes through the shear sleeve, the spring thruster, and the thruster support, with the head and tail of the bearing bolt located on the satellite side and the upper stage side, respectively, and the tail of the bolt connected to the cable control system to achieve satellite-rocket connection; the bolt catcher is installed on one side of the bearing bolt head to capture the bearing bolt after satellite-rocket separation; the thruster support is installed on the upper stage side to support the fixed end of the spring thruster.

[0013] Furthermore, the rope control system includes a first steering pulley, a second steering pulley, a rope, a first rope drum, a second rope drum, a first motor, and a second motor;

[0014] The rope begins to wind around the first rope drum, turns upward through the first steering pulley, passes through the rope hole provided at the tail of the bearing bolt, turns downward through the second steering pulley, and ends winding around the second rope drum. This is used to tighten the bearing bolt and ensure the bearing capacity of the star-rocket connection device.

[0015] The first motor output shaft and the second motor output shaft are coaxially fixedly connected to the first rope drum and the second rope drum, respectively, for adjusting rope tension and rope length; the first rope drum and the second rope drum are respectively installed on the first motor output shaft and the second motor output shaft, for winding the two ends of the rope and controlling the rope's retraction and release; the first and second steering pulleys are fixedly installed on the upper stage side, respectively located on both sides of the bearing bolt, for steering the rope to the tail of the bearing bolt, ensuring that the rope can provide downward axial tension to the bearing bolt.

[0016] Furthermore, during star-rocket separation, as the bearing bolt moves away from the upper stage, the rope release mechanism releases the rope, which slides within the rope passage hole. The rope passage hole is a continuous, smooth curve, with the top of the curve curving towards the head of the bearing bolt. The hole diameter is slightly larger than the rope diameter, ensuring a smooth transition of the rope during separation without any bending.

[0017] Furthermore, the rope includes a first section of rope and a second section of rope; the first section of rope and the second section of rope are respectively the parts of the rope on both sides of the rope hole of the bearing bolt, wherein the end of the first section of rope is only wound on the first rope drum, and the end of the second section of rope is fixedly connected to the second rope drum.

[0018] Furthermore, satellite attitude control and orbit adjustment can be achieved by controlling the length of the rope and the rope tension.

[0019] Furthermore, the rope's breaking tensile strength is not less than 100KN, it does not curl after unloading, its diameter is not greater than 3mm, and it is made of ultra-high molecular weight polyethylene.

[0020] Secondly,

[0021] This invention also proposes a method for separating a satellite from a rocket, comprising:

[0022] S01: The first motor releases the torque holding mode, and the first rope drum is in a free state; at the same time, the spring thruster is activated, indirectly pushing the anti-shear sleeve to push the satellite away from the upper stage; the satellite drives the bearing bolt, the bearing bolt pulls the rope, and the rope slides in the rope hole within the bearing bolt; the first rope drum rotates under the pull of the rope; at this time, the first motor and the second motor are not working;

[0023] S02: When the bearing bolt is completely removed from the upper stage, if there is no separation distance, satellite attitude control, or orbit adjustment requirement, the designed rope length is sufficient to allow the first rope drum to completely release the rope and the second motor to control the second rope drum to retract the rope.

[0024] Once fully recovered, the separation process ends.

[0025] S03: If there are requirements for separation distance, satellite attitude control, and orbit adjustment, there is still rope wound on the first rope drum. The coordinated control of the first motor and the first rope drum, and the second motor and the second rope drum, realizes the separation distance, satellite attitude control, and orbit adjustment.

[0026] S04: After separation distance, satellite attitude control, and orbit insertion adjustment are completed, the designed rope length is sufficient to allow the first rope drum to fully unwind the rope, and the second motor controls the second rope drum to retract the rope.

[0027] Once fully recovered, the separation process ends.

[0028] The beneficial effects of this invention compared to the prior art are:

[0029] (1) The device of this invention achieves separation distance adjustment, satellite attitude control, and orbit insertion adjustment by controlling the length of the rope and the rope tension, thus ensuring the accuracy of satellite orbit insertion. It overcomes the shortcomings of traditional pyrotechnic separation devices, such as large separation impact and poor separation safety.

[0030] (2) This invention employs a single-rope folding scheme, enabling the rope to retract naturally after separation, without any damage to the rope during the entire separation process. Compared to the traditional method of cutting ropes with a thermal knife, this further reduces impact;

[0031] (3) The device of the present invention provides axial tension to the bearing bolt through a single rope to ensure the connection bearing capacity.

[0032] (4) During the separation process, the rope connects the satellite and the upper stage of the rocket. The separation distance between the satellite and the rocket can be adjusted by controlling the length of the rope released, thereby improving the separation safety.

[0033] (5) After separation, the device of the present invention forms a stable satellite-upper stage tethered space system, which can meet the requirements of separation distance, satellite attitude control and orbit adjustment. Attached Figure Description

[0034] Figure 1 This is a block diagram of the separation control process of the present invention;

[0035] Figure 2 This is a schematic diagram of the upper stage-satellite tethered space system of the present invention;

[0036] Figure 3 This is a schematic diagram of the rope separation system of the present invention;

[0037] Figure 4 This is a schematic diagram of the bolt-rope connection of the present invention. Detailed Implementation

[0038] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings.

[0039] This invention proposes a tethered satellite-rocket separation device, a non-fire-point separation device designed for multi-point connection applications. After the multi-point separation devices are simultaneously unlocked, a spring thruster provides the initial separation force. Under the action of the separation force, the satellite gains initial velocity and leaves the upper stage. The tether deployment mechanism releases the tether as the satellite moves. Under the action of a centrifugal force field, the upper stage, in coordination with the tether deployment mechanism, controls the tether length and tension to ensure the tether is always taut. The tether deployment mechanism gradually releases the tether, and the satellite gradually moves away from the upper stage. After reaching the separation distance, the tether separates from the satellite, and the tether deployment mechanism retracts the tether, ending the separation. The separation control process of the tethered separation device is described below. Figure 1 .

[0040] This invention has the following characteristics:

[0041] (1) Centrifugal force field: After the satellite is ejected by the spring thruster, the upper stage is connected to the satellite by a tether, forming a tethered space system, see Appendix. Figure 2 The two rotate around each other, forming a stable spin system around the system's center of mass.

[0042] (2) Rope Length / Tension Control: The rope winding and unwinding mechanism adopts a motor-drum system. The motor-drum system controls the rope winding and unwinding length and tension, keeping the rope constantly taut. Rope length / tension control is mainly used for separation distance adjustment, satellite attitude control, and orbit insertion adjustment.

[0043] (3) Rope System: The rope system consists of only a single rope, employing a single-rope folding design to provide axial tension on the bearing bolts, ensuring the load-bearing capacity of the satellite-rocket connection. The required rope length should be calculated based on separation distance requirements, satellite attitude control, and orbit insertion adjustment requirements, combined with the spring thruster parameters.

[0044] The single-rope retraction scheme, where the separation device uses only one rope to provide axial tension on the supporting bolt, ensures the load-bearing capacity of the star-rocket connection. This scheme allows the rope to retract naturally after separation, without any damage to the rope during the entire separation process. Compared to the traditional method of cutting the rope with a thermal knife, this further reduces impact.

[0045] (4) Spring thruster: The spring thruster should be able to meet the requirements of complete ejection and satellite separation speed.

[0046] (5) Rope-satellite connection scheme: The rope is directly connected to the bearing bolt. As the satellite moves away from the upper stage, the single rope slides within the bearing bolt.

[0047] Based on the above features, specifically, this invention proposes a tethered satellite-rocket separation device, comprising: a satellite 5, an upper stage 6, a spring thruster 7, and a tethered control system, as shown below. Figure 3 As shown.

[0048] The spring thruster 7 and the rope control system are mounted on the upper stage 6. When the satellite 5 separates from the upper stage 6, the spring thruster 7 provides the initial separation force. Under the action of the separation force, the satellite 5 gains an initial velocity and leaves the upper stage 6.

[0049] The rope control system releases ropes as the satellite 5 moves. The satellite 5 and the upper stage 6 are connected by ropes. Under the action of centrifugal force field, the rope control system controls the rope length and tension to ensure that the rope is always taut.

[0050] Once satellite 5 reaches the separation distance, the rope separates from satellite 5, the rope control system retracts the rope, and the separation ends.

[0051] After satellite 5 is ejected by spring thruster 7, upper stage 6 is connected to satellite 5 by rope, forming a rope-tied space system. Satellite 5 and upper stage 6 rotate around each other, forming a stable spin system around the system's center of mass.

[0052] Furthermore, the separation device of the present invention also includes a bolt catcher 1, a bearing bolt 2, a shear sleeve 3, a sleeve connecting screw 4, and a thruster support 8;

[0053] The shear sleeve 3 is installed on one side of the satellite 5 via the sleeve connecting screw 4; after the satellite-rocket docking is completed, the shear sleeve 3 compresses the free end of the spring thruster 7 to the maximum compression state; the bearing bolt 2 passes through the shear sleeve 3, the spring thruster 7 and the thruster support 8, with the head and tail of the bearing bolt 2 located on the side of the satellite 5 and the upper stage 6 respectively, and the tail of the bolt is connected to the rope control system to achieve satellite-rocket connection; the bolt catcher 1 is installed on one side of the head of the bearing bolt 2 to catch the bearing bolt 2 after the satellite-rocket separation; the thruster support 8 is installed on the side of the upper stage 6 to support the fixed end of the spring thruster 7.

[0054] like Figure 3 As shown, the rope control system includes a first steering pulley 9, a second steering pulley 10, a rope 11, a first rope drum 13, a second rope drum 14, a first motor 15, and a second motor 16.

[0055] Rope 11 starts to be wound around the first rope drum 13, turns upward through the first steering pulley 9, passes through the rope hole provided at the tail of the bearing bolt 2, turns downward through the second steering pulley 10, and ends to be wound around the second rope drum 14, which is used to tighten the bearing bolt 2 and ensure the bearing capacity of the star-rocket connection device.

[0056] The output shafts of the first motor 15 and the second motor 16 are coaxially fixed to the first rope drum 13 and the second rope drum 14, respectively, for adjusting the rope tension and rope length. The first rope drum 13 and the second rope drum 14 are respectively installed on the output shafts of the first motor 15 and the second motor 16, for winding the two ends of the rope 11 and controlling the retraction and release of the rope 11. The first steering pulley 9 and the second steering pulley 10 are fixedly installed on the side of the upper stage 6, respectively located on both sides of the bearing bolt 2, for steering the rope 11 to the tail of the bearing bolt 2, ensuring that the rope can provide downward axial tension to the bearing bolt 2.

[0057] During star-rocket separation, as the bearing bolt 2 moves away from the upper stage 6, the rope reeling mechanism releases rope 11. The rope slides within the rope passage hole; the rope passage hole is a continuous, smooth curve, with the top of the curve curving towards the head of the bearing bolt 2. The hole diameter is slightly larger than the rope diameter, ensuring a smooth transition of the rope during separation without any bends. Figure 4 As shown.

[0058] like Figure 3As shown, the rope 11 includes a first section 11-1 and a second section 11-2; the first section 11-1 and the second section 11-2 are the portions of the rope 11 on both sides of the rope hole of the bearing bolt 2, respectively. The end of the first section 11-1 is only wound around the first rope drum 13, while the end of the second section 11-1 is fixedly connected to the second rope drum 14. Satellite attitude control and orbital adjustment are achieved by controlling the rope's winding and unwinding length and rope tension.

[0059] Preferably, the breaking tensile strength of the rope 11 is not less than 100KN, there is no curling after unloading, the rope diameter is not greater than 3mm, and the material is ultra-high molecular weight polyethylene.

[0060] Based on the above separation device, the present invention also proposes a star-rocket separation method, comprising the following steps:

[0061] S01: The first motor 15 releases the torque holding mode, and the first rope drum 13 is in a free state; at the same time, the spring thruster 7 is activated, indirectly pushing the anti-shear sleeve 3 to push the satellite 5 away from the upper stage 6; the satellite 5 drives the bearing bolt 2, the bearing bolt 2 pulls the rope, and the rope slides in the rope hole within the bearing bolt 2; the first rope drum 13 rotates under the pull of the rope; at this time, the first motor 15 and the second motor 16 are not working;

[0062] S02: When the bearing bolt 2 is completely separated from the upper stage 6, if there is no separation distance, satellite attitude control, or orbit adjustment requirement, the designed rope length is sufficient to allow the first rope drum 13 to completely release the rope and the second motor 16 to control the second rope drum 14 to retract the rope 11.

[0063] Once fully recovered, the separation process ends.

[0064] S03: If there are requirements for separation distance, satellite attitude control, and orbit adjustment, there is still rope wound on the first rope drum 13. The coordinated control of the first motor 15 and the first rope drum 13, and the second motor 16 and the second rope drum 14 realizes separation distance, satellite attitude control, and orbit adjustment.

[0065] S04: After separation distance, satellite attitude control, and orbit insertion adjustment are completed, the designed rope length is sufficient to allow the first rope drum 13 to fully unwind the rope, and the second motor 16 controls the second rope drum 14 to retract the rope.

[0066] Once fully recovered, the separation process ends.

[0067] The core advantage of this invention is:

[0068] (1) The axial tension of the bearing bolt is provided by a single rope to ensure the bearing capacity of the connection;

[0069] (2) The inherent characteristics of the rope, such as not cutting the rope and the rope's inherent flexibility, can effectively reduce the impact of separation.

[0070] (3) After separation, a stable satellite-upper stage tethered space system is formed, which can meet the requirements of separation distance, satellite attitude control and orbit adjustment.

[0071] The parts of this invention not described in detail are common knowledge to those skilled in the art.

Claims

1. A rope-tethered star-rocket separation device, characterized in that... include: Satellite (5), upper stage (6), spring thruster (7), rope control system; The spring thruster (7) and the rope control system are mounted on the upper stage (6). When the satellite (5) separates from the upper stage (6), the spring thruster (7) provides an initial separation force. Under the action of the separation force, the satellite (5) gains an initial velocity and leaves the upper stage (6). The rope control system releases the rope as the satellite (5) moves. The satellite (5) and the upper stage (6) are connected by the rope. Under the action of the centrifugal force field, the rope control system controls the rope length and tension to ensure that the rope is always in a taut state. After the satellite (5) reaches the separation distance, the rope separates from the satellite (5), the rope control system retracts the rope, and the separation ends; The tethered satellite-rocket separation device also includes a bolt catcher (1), a bearing bolt (2), a shear sleeve (3), a sleeve connecting screw (4), and a thruster support (8); the shear sleeve (3) is installed on one side of the satellite (5) via the sleeve connecting screw (4); after the satellite-rocket docking is completed, the shear sleeve (3) compresses the free end of the spring thruster (7) to the maximum compression state; the bearing bolt (2) passes through the shear sleeve (3), the spring thruster (7), and the thruster support (8), with the head and tail of the bearing bolt (2) located on the satellite (5) side and the upper stage (6) side respectively, and the tail of the bolt is connected to the tethered control system to achieve satellite-rocket connection; the bolt catcher (1) is installed on one side of the head of the bearing bolt (2) for capturing the bearing bolt (2) after satellite-rocket separation; the thruster support (8) is installed on the upper stage (6) side for supporting the fixed end of the spring thruster (7); The rope control system includes a first steering pulley (9), a second steering pulley (10), a rope (11), a first rope drum (13), a second rope drum (14), a first motor (15), and a second motor (16). The rope (11) starts to wind around the first rope drum (13), turns upward through the first steering pulley (9), passes through the rope hole provided at the tail of the bearing bolt (2), turns downward through the second steering pulley (10), and ends to wind around the second rope drum (14), which is used to tighten the bearing bolt (2) and ensure the bearing capacity of the star-rocket connection device; The output shafts of the first motor (15) and the second motor (16) are coaxially fixed to the first rope drum (13) and the second rope drum (14) respectively, for adjusting the rope tension and rope length; the first rope drum (13) and the second rope drum (14) are respectively installed on the output shafts of the first motor (15) and the second motor (16), for winding the two ends of the rope (11) and controlling the retraction and release of the rope (11); the first steering pulley (9) and the second steering pulley (10) are fixedly installed on the side of the upper stage (6), respectively located on both sides of the bearing bolt (2), for the rope (11) to turn to the tail of the bearing bolt (2), ensuring that the rope can provide downward axial tension to the bearing bolt (2).

2. The rope-tethered star-rocket separation device according to claim 1, characterized in that: After the satellite (5) is ejected by the spring thruster (7), the upper stage (6) is connected to the satellite (5) by a rope, forming a rope-tied space system. The satellite (5) and the upper stage (6) rotate around each other, forming a stable spin system around the center of mass of the system.

3. The rope-tethered star-rocket separation device according to claim 1, characterized in that: When the star and rocket separate, as the bearing bolt (2) moves away from the upper stage (6), the rope release mechanism releases the rope (11), and the rope slides in the rope hole; the rope hole is a continuous smooth curve shape, with the top of the curve bending towards the head of the bearing bolt (2), and the hole diameter is slightly larger than the rope diameter, to ensure that the rope transitions smoothly during the separation process and that the rope does not bend.

4. The rope-tethered star-rocket separation device according to claim 3, characterized in that: The rope (11) includes a first section of rope (11-1) and a second section of rope (11-2); the first section of rope (11-1) and the second section of rope (11-2) are the parts of the rope (11) on both sides of the rope hole of the bearing bolt (2), wherein the end of the first section of rope (11-1) is only wound on the first rope drum (13), and the end of the second section of rope (11-1) is fixedly connected to the second rope drum (14).

5. The rope-tethered star-rocket separation device according to claim 4, characterized in that: Satellite attitude control and orbit adjustment are achieved by controlling the length of the rope and the rope tension.

6. A rope-tethered star-rocket separation device according to any one of claims 3-5, characterized in that: The breaking tensile strength of the rope (11) is not less than 100KN, there is no curling after unloading, the rope diameter is not greater than 3mm, and the material is ultra-high molecular weight polyethylene.

7. A method for separating a star and a rocket based on the rope-tethered star-rocket separation device as described in claim 3, characterized in that... include: S01: The first motor (15) releases the torque holding mode, and the first rope drum (13) is in a free state; At the same time, the spring thruster (7) is activated, and by indirectly pushing the shear sleeve (3), the satellite (5) is pushed away from the upper stage (6); the satellite (5) drives the bearing bolt (2), the bearing bolt (2) pulls the rope, and the rope slides in the rope hole in the bearing bolt (2); the first rope drum (13) rotates under the pull of the rope; at this time, the first motor (15) and the second motor (16) are not working; S02: When the bearing bolt (2) is completely separated from the upper stage (6), if there is no separation distance, satellite attitude control, or orbit adjustment requirement, the designed rope length is sufficient to allow the first rope drum (13) to completely release the rope and the second motor (16) to control the second rope drum (14) to retract the rope (11). Once fully recovered, the separation process ends. S03: If there are requirements for separation distance, satellite attitude control, and orbit adjustment, there is still a rope wound on the first rope drum (13). The coordinated control of the first motor (15) and the first rope drum (13), and the second motor (16) and the second rope drum (14) realizes separation distance, satellite attitude control and orbit adjustment. S04: After the separation distance, satellite attitude control, and orbit adjustment are completed, the designed rope length is sufficient to allow the first rope drum (13) to fully unwind the rope, and the second motor (16) controls the second rope drum (14) to retract the rope. Once fully recovered, the separation process ends.

8. The star-rocket separation method according to claim 7, characterized in that: The rope (11) includes a first section of rope (11-1) and a second section of rope (11-2); the first section of rope (11-1) and the second section of rope (11-2) are the parts of the rope (11) on both sides of the rope hole of the bearing bolt (2), wherein the end of the first section of rope (11-1) is only wound on the first rope drum (13), and the end of the second section of rope (11-1) is fixedly connected to the second rope drum (14).

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