A reusable launcher using a rope-type interstage separation device and method

Abstract

This invention discloses a rope-driven interstage separation device for repeated launches, mainly composed of an interstage section wall panel assembly, a drive retraction assembly, and a constraint unlocking assembly. The wall panels are divided into upper and lower sets, hinged together, and coordinated with fiber ropes, rope tensioners, electric pin pullers, and nitrogen springs to achieve linked operation. This device abandons the traditional hot and cold separation mode. After unlocking, the wall panels are pulled inward synchronously by rope traction, resulting in fast separation speed and simple action. It avoids the high-temperature combustion impact of hot separation and improves the problem of large attitude disturbance in traditional cold separation, ensuring stable operation. The wall panels are evenly distributed circumferentially and driven synchronously, resulting in uniform force distribution and avoiding structural deformation and interference, making it suitable for the large mass and long stroke separation conditions of heavy rockets. This device has reliable mechanical linkage and precise action. Its modular design can be adapted to multiple launch vehicles, effectively solving the technical problems of force imbalance and poor adaptability of traditional separation structures.

Description

Technical Field

[0001] This invention relates to the field of spacecraft separation technology, and more specifically to a rope-type interstage separation device for repeated launches. Background Technology

[0002] Interstage separation is a core technology in the flight process of launch vehicles, which directly determines the stability of the rocket's flight attitude and the success or failure of the launch mission. At present, the mainstream interstage separation methods of launch vehicles are mainly divided into two types: cold separation and hot separation. Both types of separation modes have inherent technical defects.

[0003] Cold separation technology relies on a thrust mechanism to separate the two stages of the rocket. The separation process is smooth and without the impact of high-temperature exhaust gases, but the overall separation time is relatively long, and the rocket body is in an unrestrained and uncontrolled state for a long time, which can easily interfere with the stability of the subsequent flight attitude. At the same time, the traditional cold separation thrust structure is difficult to ensure uniform stress on the end face of the interstage section, and the stress imbalance problem is prone to occur during the separation process, resulting in structural interference between the interstage section and the tail section of the second stage after separation, which significantly reduces the reliability of separation. Hot separation technology relies on the thrust of engine exhaust gas to achieve rapid separation, and the separation efficiency is higher. However, during the separation process, the high-temperature and high-pressure exhaust gas will directly impact the fuel tank of the lower stage and the interstage section structure, requiring additional heat insulation and pressure-resistant protection structures. This not only increases the structural complexity of the rocket body, but also significantly increases the overall mass of the rocket body, which contradicts the design requirements of lightweight launch vehicles and high payload ratio.

[0004] With the rapid development of large and heavy launch vehicle technology, the size of the rocket body and the mass of the separated components have increased significantly, and the effective stroke of interstage separation has also increased significantly, further amplifying the shortcomings of traditional separation technologies. Conventional thrust-type separation structures cannot adapt to the separation conditions of large stroke and large mass, the difficulty of uniform force control has increased dramatically, and the risk of structural interference has increased significantly. Existing separation devices cannot simultaneously meet the requirements of separation efficiency, structural safety, and rocket body lightweighting, and cannot meet the requirements of interstage separation operations of large launch vehicles. Summary of the Invention

[0005] To address these issues, the present invention provides a rope-type interstage separation device for repeated launches, thereby solving the aforementioned problems in the prior art.

[0006] To achieve the above objectives, the present invention provides the following technical solution:

[0007] According to a first aspect of the invention, a reusable launch cable-driven interstage separation device includes an interstage section wall panel assembly, a drive retraction assembly, and a constraint unlocking assembly.

[0008] The interstage wall panel assembly includes a docking ring, a short shell, multiple wall panels (first and second);

[0009] Multiple wall panels are sequentially spliced ​​together to form a cylindrical structure. The upper part of the outer wall of each wall panel is rotatably connected to the lower part of the outer wall of the docking ring via a hinge.

[0010] Multiple wall panels are sequentially spliced ​​together to form a cylindrical structure. The lower part of the outer wall of each wall panel is rotatably connected to the upper part of the outer wall of the short shell through a hinge.

[0011] The number of multiple wall panels one and multiple wall panels two is the same. Each wall panel one is correspondingly disposed above each wall panel two. The lower part of the inner sidewall of each wall panel one is rotatably connected to the upper part of the inner sidewall of each wall panel two through a hinge three.

[0012] The drive retraction assembly includes a rope hook, a fiber rope, and a rope tensioner; the rope hook is disposed on the inner sidewall of the docking ring, the rope tensioner is disposed at the bottom of the inner sidewall of the short shell, one end of the fiber rope is connected to the rope tensioner, and the other end of the fiber rope is connected to the rope hook and kept taut by the rope tensioner.

[0013] The constraint unlocking assembly includes an electric pin puller and a nitrogen spring; both the electric pin puller and the nitrogen spring are disposed between the bottom of the outer wall of the first wall panel and the top of the outer wall of the second wall panel, and the electric pin puller is used to limit the initial unfolded position of the first wall panel and the second wall panel.

[0014] The first cylindrical structure and the second cylindrical structure are coaxial and have the same diameter.

[0015] Furthermore, the first wall panel and the second wall panel are the same in shape and size, both being arc-shaped plate structures.

[0016] Furthermore, the rope hooks are provided in multiples, and the multiple rope hooks are evenly arranged in a circumferential array along the inner sidewall of the docking ring;

[0017] The rope tensioner is provided in multiple ways, and the multiple rope tensioners are evenly arranged in a circumferential array along the inner sidewall of the short shell.

[0018] Each of the rope hooks is positioned directly above each of the rope tensioners.

[0019] Furthermore, hinge one, hinge two, and hinge three all adopt a hinge structure, and the axis of rotation of each hinge is arranged circumferentially, so that the wall plate one and the docking ring, the wall plate two and the short shell, and the wall plate one and the wall plate two respectively rotate relative to each other around their respective axes.

[0020] Furthermore, the electric pin puller is fixedly installed at the bottom of the outer wall of the first wall panel, and the nitrogen spring is fixedly installed at the top of the outer wall of the second wall panel; in the initial state, the locking pin of the electric pin puller is inserted into the corresponding limiting hole of the nitrogen spring to restrict the relative rotation of the first wall panel and the second wall panel.

[0021] Furthermore, the rope tensioner is a winding tensioner with a built-in pre-tensioning mechanism or an electric tensioner, and the fiber rope always maintains a preset tension. When the electric puller is unlocked, the fiber rope, under tension, pulls the docking ring and the short shell closer to each other, causing the first wall panel and the second wall panel to flip outward and fold and retract.

[0022] Furthermore, the fiber rope is made of high-strength aramid fiber or ultra-high molecular weight polyethylene fiber, and the surface of the fiber rope is covered with a wear-resistant protective layer.

[0023] Furthermore, the constraint unlocking assembly is provided in multiple sets along the circumference, and the multiple sets of electric pull pins and nitrogen springs operate synchronously to ensure that the first wall panel and the second wall panel are subjected to uniform force at the moment of unlocking, thereby achieving separation without off-center load.

[0024] Furthermore, the docking ring is connected to the secondary tail section via explosive bolts on the docking surface, and the short shell is fixedly connected to the primary rocket body structure.

[0025] According to a first aspect of the present invention, a separation method employing the aforementioned rope-type interstage separation device is characterized by comprising the following steps:

[0026] S1. When the launch vehicle flies to the predetermined separation window, the explosive bolts between the second stage tail section and the docking ring are detonated and unlocked. At the same time, the electric pin puller is energized to pull out the pin, releasing the limiting constraint between the first wall panel and the second wall panel.

[0027] S2. The nitrogen spring is launched to provide initial driving force for wall panel one. At the same time, the fiber rope is continuously tightened under the action of the rope tensioner, pulling wall panel one and wall panel two to rotate around the corresponding pin shaft, and the interstage section as a whole contracts radially.

[0028] S3. The fiber rope and rope tensioner work together to form axial tension, and the nitrogen spring outputs axial thrust. The two sets of forces work together to achieve smooth separation of the two-stage rocket body and avoid structural interference.

[0029] S4. The two stages of the arrow body form a relative separation motion, and the interstage section completes the interstage separation action after fully contracting.

[0030] S5. After recovering the interstage structure, check the wear condition of the fiber rope, replace the damaged or expired fiber rope, and reset the electric puller and nitrogen spring, it can be used for the next launch mission.

[0031] The present invention has the following advantages:

[0032] 1. This invention abandons the traditional cold separation method that relies on a slow, pushing mechanism for separation. Instead, it employs a hinged panel assembly structure combined with a rope tightening drive mechanism. After unlocking, the fiber ropes can quickly pull each panel assembly inward synchronously, rapidly releasing the constraint relationship between the upper and lower stages of the rocket and completing the interstage separation operation. Compared to the lengthy separation time of traditional cold separation, this device has a fast separation response and a simple operation process, greatly shortening the time of unrestrained loss of control during rocket interstage separation. This effectively reduces the interference of the separation process on the rocket's flight attitude, significantly improves the rocket's flight attitude stability, and avoids the core problem of large attitude disturbances in traditional cold separation. Furthermore, unlike hot separation which relies on engine exhaust gas impact, this method avoids high-temperature, high-pressure exhaust gas impact throughout the process, ensuring a stable and controllable separation process. It combines the high efficiency of hot separation with the low disturbance advantages of cold separation.

[0033] 2. This device employs a coaxial, equal-diameter splicing structure with multiple wall panels corresponding to each other. All wall panel units are evenly distributed along the circumference of the rocket body and are synchronously driven to contract via a unified fiber rope and rope tensioner. This enables synchronous unlocking, deformation, and separation of the interstage section in the radial entire domain. Compared to the single-point stress and eccentric load problems that are prone to occur in traditional push-type cold separation structures, this structure achieves uniform circumferential stress on the end face of the interstage section, avoiding problems such as wall panel deformation and misalignment caused by uneven stress. At the same time, during separation, the wall panels contract inward to avoid interference, actively expanding the separation space between the upper and lower stages of the rocket body. This completely eliminates the structural interference risk between the interstage section and the second-stage tail section from a structural perspective, significantly improving the reliability and stability of interstage separation under high-mass, long-stroke conditions, and perfectly adapting to the separation operation requirements of large heavy-lift launch vehicles.

[0034] 3. This invention eliminates the need for additional protective structures such as heat insulation layers, pressure-resistant protection, and ablation prevention required by thermal separation technology. The entire separation process relies on a mechanical hinge receiving and retracting structure, avoiding the problems associated with high-temperature gas impact structures and significantly simplifying the overall structural complexity of the rocket interstage section. Simultaneously, the device replaces traditional heavy-duty thrust mechanisms and protective structures with lightweight components such as lightweight panels, fiber ropes, electric pin pullers, and nitrogen springs, effectively reducing the structural weight of the interstage section and decreasing the proportion of ineffective payload on the rocket. This aligns with the core design requirements of lightweight and high payload ratio for launch vehicles, effectively improving the rocket's effective carrying capacity and demonstrating significant lightweight advantages compared to traditional thermal separation structures.

[0035] 4. This device employs a multi-stage hinged structure to achieve the rotation, opening, closing, retraction, and reset of the wall panels. Combined with a combined control mode featuring electric pin release for limiting, nitrogen spring auxiliary support, and constant tension drive from the rope tensioner, the mechanical structure exhibits strong linkage and precise, controllable action. The entire process of unlocking, retraction, and separation is stable, without jamming or failure risk. In the initial state, the electric pin release precisely locks the wall panel's unfolded position, ensuring the integrity and rigidity of the interstage cylindrical structure and meeting the structural load-bearing requirements during rocket flight. During separation, it quickly unlocks and retracts synchronously, resulting in efficient and reliable structural state switching. Furthermore, the coaxial, equal-diameter modular wall panel splicing structure allows for adjustment of the number and size of wall panels according to the rocket body dimensions, enabling it to adapt to different models and separation strokes of large and medium-sized launch vehicles, making it widely applicable and highly practical in engineering.

[0036] 5. Addressing the shortcomings of traditional separation structures in handling the large size and mass separation conditions of large rockets, such as difficulty in force control and poor separation stability, this invention utilizes a circumferentially uniformly distributed flexible rope drive structure. This structure enables large-span, long-stroke wall panel retraction and avoidance, achieving smooth and rapid separation of the large-mass rocket body without relying on a high-thrust mechanism. This effectively solves the technical problems of traditional thrust-type structures being unable to adapt to long-stroke separation and prone to force imbalance, completely compensating for the performance shortcomings of traditional separation technology in heavy-lift launch vehicle applications. Furthermore, this device itself is a purely mechanical articulated structure, with no disposable consumables or thermal ablation damage. Only the fiber rope is a consumable component, which can be replaced to repeatedly perform the separation function. Attached Figure Description

[0037] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings in the following description are merely exemplary, and those skilled in the art can derive other embodiments based on the provided drawings without creative effort.

[0038] The structures, proportions, sizes, etc. illustrated in this specification are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed herein, and are not intended to limit the conditions under which the present invention can be implemented. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size, without affecting the effects and objectives that the present invention can produce, should still fall within the scope of the technical content disclosed in the present invention.

[0039] Figure 1 An isometric view of a repetitive launch interstage separation device using a rope-type separation mechanism, provided for some embodiments of the present invention.

[0040] Figure 2A rope-type interstage separation device for repeated launch is provided in some embodiments of the present invention. Figure 1 Enlarged view of part C.

[0041] Figure 3 A rope-type interstage separation device for repeated launch is provided in some embodiments of the present invention. Figure 1 Enlarged view of part D.

[0042] Figure 4 A rope-type interstage separation device for repeated launch is provided in some embodiments of the present invention. Figure 1 Enlarged view of part E.

[0043] Figure 5 This is a cross-sectional view of a rope-type interstage separation device for repeated launch, provided for some embodiments of the present invention.

[0044] Figure 6 A front view of a rope-type interstage separation device for repeated launch, provided for some embodiments of the present invention.

[0045] Figure 7 A rope-type interstage separation device for repeated launch is provided in some embodiments of the present invention. Figure 6 Enlarged view of part A.

[0046] Figure 8 This is a front view of the initial tightening state of a rope-type interstage separation device used for repeated firing, provided for some embodiments of the present invention.

[0047] Figure 9 A rope-type interstage separation device for repeated launch is provided in some embodiments of the present invention. Figure 8 Enlarged view of part B.

[0048] Figure 10 A schematic diagram of the internal structure of a rope-type interstage separation device for repeated launch provided for some embodiments of the present invention. Figure 1 .

[0049] Figure 11 This is a front view of a rope-type interstage separation device used for repeated firing in the intermediate tightened state, as provided in some embodiments of the present invention.

[0050] Figure 12 A schematic diagram of the internal structure of a rope-type interstage separation device for repeated launch provided for some embodiments of the present invention. Figure 2 .

[0051] Figure 13 This is a front view of the extreme tightening state of a rope-type interstage separation device used for repeated firing, provided for some embodiments of the present invention.

[0052] In the diagram: 1. Rope hook; 2. Fiber rope; 3. Secondary tail section; 4. Hinge 1; 41. Hinge 1; 42. Pin 1; 43. Hinge 2; 5. Hinge 2; 51. Hinge 3; 52. Pin 2; 53. Hinge 4; 6. Hinge 3; 61. Hinge 5; 62. Pin 3; 63. Hinge 6; 7. Connecting ring; 8. Rope tensioner; 9. Panel 1; 10. Panel 2; 11. Electric pin puller; 12. Nitrogen spring; 13. Short shell. Detailed Implementation

[0053] The following specific embodiments illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. 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.

[0054] Example 1

[0055] like Figures 1 to 13 As shown, a rope-type interstage separation device for repeated launch in the first aspect embodiment of the present invention is composed of three main modules: an interstage section wall panel assembly, a drive retraction assembly, and a constraint unlocking assembly. Each component is assembled strictly according to the reference numerals in the attached drawings. The first cylindrical structure and the second cylindrical structure are arranged coaxially and with equal diameter.

[0056] The interstage section wall panel assembly includes a docking ring 7, a short shell 13, 18 wall panels 9 (first type), and 18 wall panels 10 (second type). The number, shape, and size of wall panels 9 (first type) and 10 (second type) are completely identical. They are all arc-shaped plate structures, and each arc-shaped plate matches the outer diameter of the rocket body.

[0057] Eighteen wall panels 9 are sequentially spliced ​​end to end to form the upper cylindrical structure 1. The upper part of the outer wall of each wall panel 9 is rotatably connected to the lower part of the outer wall of the docking ring 7 via a hinge 4. The hinge 4 includes a hinge 41, a pin 42, and a second hinge 43. The hinge 41 is fixed to the lower part of the outer wall of the docking ring 7, the second hinge 43 is fixed to the upper part of the outer wall of the wall panel 9, and the pin 42 passes through the two sets of hinges to achieve hinged assembly.

[0058] Eighteen wall panels 10 are joined end to end to form the lower cylindrical structure 2. The lower part of the outer wall of each wall panel 10 is rotatably connected to the upper part of the outer wall of the short shell 13 via a hinge 2 5. The hinge 2 5 includes a hinge 3 51, a pin 2 52, and a hinge 4 53. The hinge 3 51 is fixed to the upper part of the outer wall of the short shell 13, the hinge 4 53 is fixed to the lower part of the outer wall of the wall panel 10, and the pin 2 52 completes the hinge engagement.

[0059] Panel 9 and panel 10 are arranged vertically in a corresponding manner. The lower part of the inner wall of each panel 9 is rotatably connected to the upper part of the inner wall of the corresponding panel 10 via hinge 6. Hinge 6 includes hinge 61, pin 62, and hinge 63. Hinge 61 is fixed to the lower part of the inner wall of panel 9, hinge 63 is fixed to the upper part of the inner wall of panel 10, and pin 62 connects the two sets of hinges in series.

[0060] All hinge axes of hinge 4, hinge 5, and hinge 6 are arranged circumferentially along the cylindrical structure, ensuring that wall panel 9 can rotate freely around the corresponding pin relative to the mating ring 7, wall panel 10 relative to the short shell 13, and wall panel 9 relative to wall panel 10.

[0061] The upper end face of the docking ring 7 is connected to the secondary tail section 3 by explosive bolts; the bottom of the short shell 13 is fixedly welded to the primary rocket body structure.

[0062] The drive retraction assembly consists of a rope hook 1, a fiber rope 2, and a rope tensioner 8, which are evenly arranged in a circumferential array, with the number matching the number of wall panels (18 sets in total).

[0063] Eighteen rope hooks 1 are evenly fixed in a circumferential array along the inner sidewall of the docking ring 7, and eighteen rope tensioners 8 are evenly fixed in a circumferential array along the bottom of the inner sidewall of the short shell 13. Each rope hook 1 is directly opposite the corresponding rope tensioner 8 directly below it.

[0064] The rope tensioner 8 is a winding tensioner with a built-in pre-tensioning mechanism and a factory-preset constant tension. One end of the fiber rope 2 is connected to the rope tensioner 8, and the other end is hooked onto the rope hook 1, maintaining tension throughout the process.

[0065] The main body of fiber rope 2 is woven from high-strength aramid fibers, and the outer surface is covered with a polyurethane wear-resistant protective layer, which has wear-resistant, tensile-resistant and fatigue-resistant properties.

[0066] The constraint unlocking components consist of 18 sets, each corresponding to a wall panel unit, and are evenly distributed along the circumference of the arrow body. All components operate synchronously.

[0067] Each set includes one set of electric pin puller 11 and one nitrogen spring 12; the electric pin puller 11 is fixed to the bottom of the outer wall of wall panel 9, and the nitrogen spring 12 is fixed to the top of the outer wall of wall panel 10.

[0068] Initial state of rocket flight: The locking pin of the electric pin puller 11 is inserted into the top limiting hole of the nitrogen spring 12, which rigidly restricts the relative rotation of the first wall plate 9 and the second wall plate 10, ensuring that the interstage section is a rigid cylindrical structure and meets the flight load requirements.

[0069] All electric pin pullers 11 are connected to the same control circuit, and all nitrogen springs 12 have the same parameters, so that the unlocking and ejection actions are completely synchronized, ensuring uniform circumferential force and no off-center load.

[0070] Working principle: During rocket flight, the electric pin puller 11 locks the wall panels, maintaining the complete cylindrical shape of the interstage section. After the separation command is issued, the electric pin puller 11 simultaneously pulls out of the locking pin, releasing the mechanical limit. The nitrogen spring 12 extends instantaneously, providing the initial flipping driving force for the wall panels; at the same time, the rope tensioner 8 continuously winds up the fiber rope 2, and the axial tension pulls the docking ring 7 and the short shell 13 closer to each other. Wall panels 1-9 and 2-10, respectively, rely on the pins and hinges of hinge 1-4, hinge 2-5, and hinge 3-6 to flip outward around their respective axes and fold radially. After the wall panels retract, they actively avoid the separation space, and together with the axial tension of the fiber rope and the axial thrust of the nitrogen spring, drive the first-stage rocket body and the second-stage rocket body to separate smoothly.

[0071] The separation steps using the device in this embodiment are as follows:

[0072] S1. Synchronous unlocking: When the launch vehicle reaches the preset separation window, the explosive bolts between the second stage tail section 3 and the docking ring 7 are simultaneously detonated and unlocked; at the same time, the control system sends an energizing signal to all electric pin pullers 11, and the locking pins are pulled out uniformly, releasing the limiting constraints of wall panel 9 and wall panel 10.

[0073] S2, Panel contraction: Each group of nitrogen springs 12 is simultaneously extended to provide initial rotational power for the panel assembly; the rope tensioner 8 simultaneously winds up the fiber rope 2, which pulls panel one 9 and panel two 10 under tension. Relying on the hinges and pins of hinge one 4, hinge two 5, and hinge three 6, the entire inter-stage section contracts radially inward.

[0074] S3. Rocket body separation: Fiber rope 2 and rope tensioner 8 form axial tension, nitrogen spring 12 outputs axial thrust. The two sets of forces work together to drive the first and second stage rocket bodies to make axial relative movements. The wall panel shrinks to form an avoidance space, completely avoiding structural interference.

[0075] S4. Separation complete: The two stages of the rocket continue to move relative to each other, the interstage wall reaches its limit of contraction, the rocket completely separates, and the entire interstage separation action ends.

[0076] S5. After recovering the interstage structure, check the wear and tear of the fiber rope, replace the damaged or expired fiber rope, and reset the electric pull pin and nitrogen spring. It can then be used for the next launch mission.

[0077] The technical effect achieved by this embodiment is as follows:

[0078] 1. It eliminates the defects of traditional cold and hot separation, eliminates the impact of high-temperature gas, has a fast separation speed, and greatly reduces the attitude disturbance of the rocket body;

[0079] 2. Multiple circumferential structures move synchronously, resulting in uniform stress distribution, no eccentric loading, and no structural deformation, making it suitable for the separation conditions of heavy rockets with large mass and long stroke.

[0080] 3. The fully mechanical articulated and cable-driven structure features clearly defined articulated components that are stable to assemble, eliminating the need for additional heat insulation or ablation protection components. This results in a lightweight structure and increased rocket payload.

[0081] 4. The mechanical linkage is precise and reliable, and the modular structure has strong versatility, making it compatible with multiple launch vehicles.

[0082] 5. This device itself is a purely mechanical hinge structure, with no disposable consumables and no thermal ablation damage. Only the fiber rope is a consumable part, which can be replaced to perform the separation function repeatedly.

[0083] Example 2

[0084] like Figures 1 to 13 As shown, this embodiment provides another reusable launch device using a rope-type interstage separation device, the structure of which includes all the contents of Embodiment 1. Only the different parts are described below.

[0085] Replace the winding tensioner with a built-in pre-tightening mechanism in Example 1 with an electric tensioner, while keeping the other installation positions and arrangements unchanged.

[0086] The electric tensioner has a built-in tension detection module that can maintain the preset tension of the fiber rope 2 in real time; after unlocking, it relies on the motor drive to complete the rope winding, and the winding speed and tension can be precisely adjusted according to the rocket's working conditions.

[0087] The technical effects achieved by this embodiment are: the electric tensioner has higher control precision, can be adapted to different separation speed requirements, and is suitable for small and medium-sized launch vehicles and multi-condition variable parameter separation scenarios.

[0088] Example 3

[0089] This embodiment provides another reusable launch device using a rope-type interstage separation mechanism, the structure of which includes all the contents of Embodiment 1. Only the different parts are described below.

[0090] The material of fiber rope 2 has been changed from aramid fiber to ultra-high molecular weight polyethylene fiber. The surface is still covered with a wear-resistant protective layer. This fiber rope is lighter, has higher specific strength, and has excellent low-temperature resistance, making it suitable for interstage separation of launch vehicles in high-altitude and low-temperature environments.

[0091] Example 4

[0092] like Figures 1 to 13 As shown, this embodiment provides another reusable launch device using a rope-type interstage separation device, the structure of which includes all the contents of Embodiment 1. Only the different parts are described below.

[0093] This embodiment is a modular adaptation solution. The core structure, connection relationship, and working principle are the same as those in Embodiment 1. Only the number of wall panels and supporting components is adjusted to reflect the modular design characteristics of the device.

[0094] For small-diameter medium-sized launch vehicles, the number of wall panels 9 and 10 is reduced from 18 to 10; 10 sets of rope hooks 1, 10 rope tensioners 8, 10 sets of electric pin pullers 11 and 10 sets of nitrogen springs 12 are installed simultaneously.

[0095] All components remain evenly arranged in a circumferential array. The structural composition of hinge 1 (4), hinge 2 (5), and hinge 3 (6) remains unchanged: hinge 1 (4) consists of hinge 1 (41), pin 1 (42), and hinge 2 (43); hinge 2 (5) consists of hinge 3 (51), pin 2 (52), and hinge 4 (53); and hinge 3 (6) consists of hinge 5 (61), pin 3 (62), and hinge 6 (63). All hinge shafts remain arranged circumferentially along the cylinder.

[0096] The constraint unlocking component and the driving component continue to operate synchronously to ensure uniform circumferential force and achieve unbiased separation.

[0097] The technical effect achieved by this embodiment is that it can adapt to different rocket diameters and different models of launch vehicles by increasing or decreasing the number of wall panels and supporting components, thus improving the adaptability to different operating conditions.

[0098] Example 5

[0099] This embodiment provides a rope-type interstage separation method, which uses the rope-type interstage separation device of any one of Embodiments 1 to 4.

[0100] In this embodiment, the method includes the following steps:

[0101] During normal rocket flight, the explosive bolts lock the second stage tail section 3 to the docking ring 7; the electric pin puller 11 locks the first wall plate 9 and the second wall plate 10; the fiber rope 2 maintains a preset tension under the action of the rope tensioner 8, and the interstage section is a rigid whole. The wall plates are hinged to the docking ring, the short shell, and the wall plates respectively through hinge 4, hinge 5, and hinge 6, ensuring the overall structural stability.

[0102] Step 1 Unlocking Phase: The rocket enters the designated separation airspace, and the onboard control system simultaneously outputs two commands: the explosive bolts detonate, releasing the mechanical connection between the second stage tail section 3 and the docking ring 7; all electric pin pullers 11 are energized to pull out the pins, releasing the rotation limit between the panels.

[0103] Step S2 Radial contraction of the wall panel: Multiple sets of nitrogen springs 12 are pushed out synchronously, pushing the wall panel assembly to generate an initial rotation angle; the rope tensioner 8 continuously winds up the fiber rope 2, and the tension drives all wall panels 1 9 and 2 10 to rotate around the pins of hinge 1 4, hinge 2 5 and hinge 3 6 respectively, and the entire inter-stage section radially contracts.

[0104] Step S3 Axial Separation and Interference Prevention: The axial tension of the fiber rope and the axial thrust of the nitrogen spring together form a separation force, pushing the first-stage and second-stage rocket bodies away from each other along the axial direction; the radial contraction of the wall panel forms a clearance space, completely avoiding scratches and interference between the interstage section and the rocket body.

[0105] Step S4 Separation Termination: The two stages of the rocket reach the preset separation distance, the interstage wall plate moves to the extreme contraction position, the entire interstage separation process is completed, and the rocket enters the next flight stage.

[0106] Although the present invention has been described in detail above with general descriptions and specific embodiments, modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, all such modifications or improvements made without departing from the spirit of the present invention fall within the scope of protection claimed by the present invention.

[0107] The terms such as "upper," "lower," "left," "right," and "middle" used in this specification are merely for clarity of description and are not intended to limit the scope of the invention. Any changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of the invention.

Claims

1. A rope-type interstage separation device for repeated launches, characterized in that, include: Interstage panel assembly, drive retraction assembly, and constraint unlocking assembly; The interstage wall panel assembly includes a docking ring (7), a short shell (13), a multi-panel first (9), and a multi-panel second (10); Multiple wall panels (9) are sequentially spliced ​​together to form a cylindrical structure. The upper part of the outer wall of each wall panel (9) is rotatably connected to the lower part of the outer wall of the docking ring (7) through a hinge. Multiple wall panels (10) are sequentially spliced ​​to form a cylindrical structure. The lower part of the outer wall of each wall panel (10) is rotatably connected to the upper part of the outer wall of the short shell (13) through a hinge. The number of multiple wall panels one (9) and multiple wall panels two (10) is the same. Each wall panel one (9) is correspondingly disposed above each wall panel two (10). The lower part of the inner sidewall of each wall panel one (9) is rotatably connected to the upper part of the inner sidewall of each wall panel two (10) through a hinge three. The drive retraction assembly includes a rope hook (1), a fiber rope (2), and a rope tensioner (8); the rope hook (1) is disposed on the inner wall of the docking ring (7), the rope tensioner (8) is disposed at the bottom of the inner wall of the short shell (13), one end of the fiber rope (2) is connected to the rope tensioner (8), and the other end of the fiber rope (2) is connected to the rope hook (1) and kept taut by the rope tensioner (8); The constraint unlocking assembly includes an electric puller (11) and a nitrogen spring (12); the electric puller (11) and the nitrogen spring (12) are both disposed between the bottom of the outer wall of the first wall panel (9) and the top of the outer wall of the second wall panel (10); the electric puller (11) is used to limit the initial unfolded position of the first wall panel (9) and the second wall panel (10); The first cylindrical structure and the second cylindrical structure are coaxial and have the same diameter.

2. The cable-type interstage separation device for repeated launches according to claim 1, characterized in that, The first wall panel (9) and the second wall panel (10) are the same in shape and size, and are both arc-shaped plate structures.

3. The cable-type interstage separation device for repeated launches according to claim 1, characterized in that, The rope hooks are provided in multiples, and the multiple rope hooks (1) are evenly arranged in a circular array along the inner sidewall of the docking ring (7); The rope tensioner is provided in multiple ways, and the multiple rope tensioners (8) are evenly arranged in a circular array along the inner sidewall of the short shell (13). Each of the rope hooks (1) is positioned directly above each of the rope tensioners (8).

4. A rope-type interstage separation device for repeated launches according to claim 1, characterized in that, The hinge component one, hinge component two and hinge component three all adopt a hinge structure, and the axis of rotation of each hinge is arranged around the circumference of the cylindrical structure one or the cylindrical structure two, so that the wall plate one (9) and the docking ring (7), the wall plate two (10) and the short shell (13), and the wall plate one (9) and the wall plate two (10) rotate relative to each other around their respective axes.

5. A rope-type interstage separation device for repeated launches according to claim 1, characterized in that, The electric pin puller (11) is fixedly installed at the bottom of the outer wall of the first wall panel (9), and the nitrogen spring (12) is fixedly installed at the top of the outer wall of the second wall panel (10). In the initial state, the locking pin of the electric pin puller (11) is inserted into the corresponding limiting hole of the nitrogen spring (12) to restrict the relative rotation between the first wall panel (9) and the second wall panel (10).

6. A rope-type interstage separation device for repeated launches according to claim 1, characterized in that, The rope tensioner (8) is a winding tensioner with a built-in pre-tensioning mechanism or an electric tensioner. The fiber rope (2) always maintains a preset tension. When the electric puller (11) is unlocked, the fiber rope (2) pulls the docking ring (7) and the short shell (13) closer to each other in the tensioned state, causing the first wall panel (9) and the second wall panel (10) to flip outward and fold and retract.

7. A rope-type interstage separation device for repeated launches according to claim 1, characterized in that, The fiber rope (2) is made of high-strength aramid fiber or ultra-high molecular weight polyethylene fiber, and the surface of the fiber rope (2) is covered with a wear-resistant protective layer.

8. A rope-type interstage separation device for repeated launches according to claim 1, characterized in that, The constraint unlocking assembly is provided in multiple sets along the circumference. The multiple sets of electric pull pins (11) and nitrogen springs (12) operate synchronously to ensure that the first wall panel (9) and the second wall panel (10) are subjected to uniform force at the moment of unlocking, so as to achieve separation without off-center load.

9. A rope-type interstage separation device for repeated launches according to claim 1, characterized in that, The docking ring (7) and the secondary tail section (3) are connected by explosive bolts on the docking surface, and the short shell (13) is fixedly connected to the primary rocket body structure.

10. A separation method using the rope-type interstage separation device according to any one of claims 1-9, characterized in that, Includes the following steps: S1. When the launch vehicle flies to the predetermined separation window, the explosive bolt between the second stage tail section (3) and the docking ring (7) is detonated and unlocked. At the same time, the electric pin puller (11) is energized to pull out the pin and release the limiting constraint between the first wall panel (9) and the second wall panel (10). S2, nitrogen spring (12) is launched to provide initial driving force for wall panel one (9), while fiber rope (2) is continuously tightened under the action of rope tensioner (8), pulling wall panel one (9) and wall panel two (10) to rotate around the corresponding pin shaft, and the interstage section as a whole shrinks radially; S3, the fiber rope (2) and the rope tensioner (8) work together to form an axial tension, and the nitrogen spring (12) outputs an axial thrust. The two sets of forces work together to achieve smooth separation of the two-stage rocket body and avoid structural interference. S4. The two stages of the arrow body form a relative separation motion, and the interstage section completes the interstage separation action after fully contracting. S5. After recovering the interstage structure, check the wear condition of the fiber rope (2), replace the damaged or used fiber rope (2), and reset the electric pull pin (11) and nitrogen spring (12) before it can be used for the next launch mission.

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