An externally towed cold launch device and method of use thereof

Abstract

The application provides an external traction type cold launching device and a use method thereof, and the cold launching device comprises a power cabin, a turbine propulsion mechanism, a traction rope, a tray, a launching cylinder and a solid propellant; a bottom cabin and a top cabin of the power cabin are communicated through a flow guide pipe; the solid propellant is arranged in the bottom cabin, and the turbine propulsion mechanism is arranged in the top cabin; the bottom surface of the launching cylinder is fixedly connected with the power cabin; the tray is arranged in the launching cylinder, and the tray is used for mounting a launching load; one end of the traction rope is connected with the tray, and the other end of the traction rope is stretched out of the launching cylinder and connected with the turbine propulsion mechanism; high-pressure gas generated by the solid propellant can enter the top cabin through the flow guide pipe and push the turbine propulsion mechanism to drive the tray to move in the launching cylinder through the traction mechanism; the scheme provided by the application has the advantages of powerful power, stable thrust and high device reusability, so as to meet the launching task requirements of various types of solid rockets and other types of aircrafts at the present stage.

Description

Technical Field

[0001] This invention belongs to the field of external traction cold launch technology, specifically relating to an external traction cold launch device and its usage method. Background Technology

[0002] With the continuous advancement of my country's aerospace science and technology, higher demands are being placed on the safe, efficient, and low-optical-signature launch propulsion of solid rockets. Existing solid rockets mainly employ hot launch and cold launch methods such as gas, compressed air, and gas-steam. While these methods can achieve the intended launch mission objectives, they suffer from numerous practical problems, including severe ablation and corrosion, low equipment reusability, bulky and immobile launch equipment, and insufficient power limits, introducing uncertainty into the safe launch of solid rockets. For example, cold launch systems using compressed air as the working medium are primarily suitable for spacecraft weighing less than 250 kg. Launching solid rockets exceeding this weight requires a significant increase in compressed air volume, substantially impacting the manufacturing process of high-pressure gas cylinders, platform weight reduction, and cost control.

[0003] Given the technical problems existing in solid rocket launches, there are currently no relevant solutions; therefore, there is an urgent need to find effective solutions to address these issues. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of the aforementioned technologies by proposing an externally traction-type cold launch device and its usage method, aiming to solve the launch problems of existing solid rockets.

[0005] This invention provides an externally towed cold launch device, comprising a power compartment, a turbine propulsion mechanism, a tow rope, a tray, a launch tube, and solid propellant. The power compartment includes a bottom compartment and a top compartment, which are connected by a guide pipe. The solid propellant is disposed in the bottom compartment. The turbine propulsion mechanism is disposed in the top compartment. The bottom surface of the launch tube is fixedly connected to the power compartment. The tray is disposed inside the launch tube and can reciprocate along the axial direction of the launch tube. The tray is used to mount the launch payload. One end of the tow rope is connected to the tray, and the other end of the tow rope extends outside the launch tube and is connected to the turbine propulsion mechanism. The high-pressure gas generated by the solid propellant can enter the top compartment through the guide pipe and drive the turbine propulsion mechanism to move the tray inside the launch tube via the tow rope, thereby launching the launch payload.

[0006] Furthermore, the bottom compartment and the top compartment are both rectangular structures, and the interiors of the bottom compartment and the top compartment are not interconnected; the guide pipe is located outside the power compartment and is connected to the bottom compartment and the top compartment respectively; a thermal activator is located at the center of the bottom of the solid propellant; the gas outlet of the solid propellant is connected to one end of the guide pipe; a tailpipe is also provided on the top compartment, one end of which is connected to the interior of the top compartment, and the other end of which extends to the exterior of the top compartment.

[0007] Furthermore, the power compartment includes a support chamber, which is a cylindrical structure, and the launch tube is a cylindrical structure. The top of the support chamber is provided with a flange face, and the flange face is provided with multiple flange face bolt holes at equal intervals around its circumference. The flange face and the bottom surface of the launch tube are fixedly connected by clamping bolts passing through the flange face bolt holes.

[0008] Furthermore, the turbine propulsion mechanism includes a rope pulley, a turbine shaft, and turbine blades; the turbine shaft is rotatably mounted in the top compartment, and both ends of the turbine shaft extend outwards from the top compartment; multiple turbine blades are fixedly mounted on the turbine shaft inside the top compartment and can rotate together with the turbine shaft; the rope pulleys are fixedly mounted at both ends of the turbine shaft extending outwards from the top compartment and rotate together with the turbine shaft; the traction rope includes a first traction rope and a second traction rope; one end of the first traction rope is connected to one side of the tray, and the other end of the first traction rope extends outwards from the launch tube and is connected to the rope pulley at one end of the turbine shaft; one end of the second traction rope is connected to the other side of the tray, and the other end of the second traction rope extends outwards from the launch tube and is connected to the rope pulley at the other end of the turbine shaft.

[0009] Furthermore, the traction rope is a carbon fiber rope. Multiple sets of wall-mounted pulleys are symmetrically arranged on both sides of the outer wall of the launch tube along its axis, and a set of tube-mouth pulleys are symmetrically arranged on both sides of the launch tube outlet along its axis. A set of rope-locking blocks and a set of limiters are symmetrically arranged on the inner wall of the launch tube. The limiters are used to prevent the tray from detaching from the launch tube. Large tray pulleys and small tray pulleys are symmetrically arranged on both sides of the tray. One end of the carbon fiber rope is fixed to the rope pulley, and the other end of the carbon fiber rope passes through multiple sets of wall-mounted pulleys, tube-mouth pulleys, small tray pulleys, and large tray pulleys in sequence, and is finally fixedly connected to the rope-locking block.

[0010] Furthermore, the carbon fiber rope is made of carbon fiber with a carbon content of over 95% and high specific modulus and specific strength.

[0011] Furthermore, the turbine shaft is provided with shoulders on both ends of the top compartment. The shoulders are located in through holes on the side walls of the top compartment, and rope pulleys are fixed to the outside of the shoulders. The turbine shaft located in the top compartment is provided with an inverted trapezoidal mounting groove. Multiple sets of turbine blades are mounted on the turbine shaft. Each set of turbine blades is engaged with the inverted trapezoidal mounting groove, thereby restricting the turbine blades from rotating circumferentially along the turbine shaft.

[0012] Furthermore, the solid propellant has a cylindrical structure, consisting of multiple cylindrical solid propellant units, with adjacent solid propellant units separated by a coating layer.

[0013] Furthermore, the coating layer is made of silica and silicone rubber.

[0014] Furthermore, the materials used to prepare the solid propellant unit include ammonium perchlorate, hydroxyl-terminated polybutadiene, and nitramine.

[0015] Accordingly, in conjunction with the above-described solution, the present invention also provides a method of using the externally traction-type cold-launch device described above, the method comprising the following steps: S1: Determine the power parameters of the cold launch device based on the target launch mission specifications; S2: Calculate the solid propellant formulation, type and mass ratio, turbine blade configuration and quantity, and heating power of the thermal exciter based on the power parameters, and design the installation dimensions of the power compartment, cable pulley, turbine shaft, tray and launch tube components. S3: Assemble the processed power compartment, rope pulley, turbine shaft, carbon fiber rope, tray and launch tube, and connect the carbon fiber rope to assemble a cold launch device. S4: Check the rationality of the assembly of each component of the cold emission device and the stability of the carbon fiber rope; S5: Install the solid rocket simulator on the tray and put it into the launch tube. First, use high-pressure cold air to carry out a cold launch simulation experiment to check the transmission performance of various types of fixed pulleys and rope pulleys, and the strength performance of carbon fiber ropes. S6: Replace the high-pressure cold gas with solid propellant, conduct an ignition and launch test, and monitor the pressure in the power compartment, the motion acceleration and velocity changes of the solid rocket simulator; S7: If there are abnormalities in the pressure in the power compartment, the motion acceleration and velocity changes of the solid rocket simulator, or the transmission performance of each component of the cold launch device does not meet the design requirements, repeat steps S1 to S6 until the performance indicators of the cold launch device meet the expected requirements. S8: Install the solid rocket on the tray and insert it into the launch tube to conduct a live-fire cold launch experiment; collect data on the internal pressure of the power compartment, the rotational speed of the cable wheel, the acceleration and velocity curve of the solid rocket, and obtain cold launch experiment data.

[0016] The solution provided by this invention has the following technical effects: First, the solution proposed in this invention is based on modular design thinking. It uses different configurations, formulations and mass ratios of solid propellants to control the total launch power, so as to match the launch power with the launch mission of various types of solid rockets and provide technical support for the multi-scenario launch of different types of solid rockets in the future battlefield. Secondly, the proposed solution adopts a split turbine drive method, which transmits gas power to carbon fiber rope through turbine shaft, pulling the solid rocket out of the tube quickly. During the launch process, the high-temperature gas is located inside the power compartment and does not come into contact with the components inside the launch tube, thus avoiding the ablation of solid rocket components by high-temperature and corrosive gas, effectively improving the reusability of the device and the reliability and safety of the launch mission. Third, the solution proposed in this invention has a simple structure, is easy to process and install, and has low maintenance costs. It can be customized according to the launch mission requirements, solving the problems of high cost, poor launch efficiency and low reusability of traditional gas launch or compressed air launch methods. Attached Figure Description

[0017] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0018] The present invention will be further described below with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the overall structure of an externally traction-type cold launch device according to a specific embodiment of the present invention; Figure 2 This is a schematic diagram of the solid propellant structure in a specific embodiment of the present invention; Figure 3 This is a cross-sectional view of the power compartment symmetry plane in a specific embodiment of the present invention; Figure 4 This is a cross-sectional view of the assembly symmetry plane of the turbine blades, turbine shaft, and power nacelle in a specific embodiment of the present invention. Figure 5 This is a schematic diagram of the assembly of the carbon fiber rope, solid rocket, tray, and tray-sized fixed pulley in a specific embodiment of the present invention; Figure 6 This is a schematic diagram illustrating the synchronous movement of the solid rocket with the tray in a specific embodiment of the present invention; Figure 7 This is a schematic diagram of the movement of the solid rocket after it separates from the tray in a specific embodiment of the present invention.

[0019] In the diagram: 1—Power compartment; 2—Guide pipe; 3—Rope pulley; 4—Turbine shaft; 5—Carbon fiber rope; 6—Large fixed pulley on the tray; 7—Small fixed pulley on the tray; 8—Wall fixed pulley; 9—Locking block; 10—Cylinder opening fixed pulley; 11—Solid propellant; 12—Thermal exciter; 13—Tail exhaust pipe; 14—Turbine blade; 15—Pressure bolt; 16—Tray; 17—Launch tube; 18—Solid rocket; 19—Limiter; 1a—Bottom compartment; 1b—Top compartment; 1c—Support compartment; 1d—Flange bolt hole; 4a—Shoulder; 4b—Inverted trapezoidal mounting slot; 11a—Covering layer; 11b—Solid propellant unit. Detailed Implementation

[0020] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0021] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0022] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.

[0023] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0024] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0025] As shown in Figure 1 to Figure 7 As shown in the figure, a specific embodiment of the present invention provides an externally towed cold launch device, which includes a power compartment 1, a turbine propulsion mechanism, a towing rope, a tray 16, a launch tube 17, and a solid propellant 11; wherein, the power compartment 1 includes a bottom compartment 1a, a top compartment 1b, and a support compartment 1c, and the bottom compartment 1a and the top compartment 1b are connected by a guide pipe 2; the solid propellant 11 is disposed in the bottom compartment 1a, and the high-pressure gas of the solid propellant 11 can enter the top compartment 1b through the guide pipe 2; further, the turbine propulsion mechanism is disposed in the top compartment 1b; the bottom surface of the launch tube 17 is fixedly connected to the power compartment 1, specifically to the support compartment 1c of the power compartment 1; further, the tray 16 is disposed in the launch tube 17 and can reciprocate along the axial direction of the launch tube 17, thereby driving the launch payload to launch; further, the tray 16 is used to install the launch payload, and the launch payload is preferably... The solid rocket 18 is selected; further, one end of the traction rope is connected to the tray 16, and the other end of the traction rope extends outside the launch tube 17 and is connected to the turbine propulsion mechanism; the solid propellant 11 is provided with a thermal exciter 12 at the bottom, which can excite the solid propellant 11 to generate high-pressure gas; specifically, the high-pressure gas generated by the solid propellant 11 can enter the top compartment 1b through the guide pipe 2 and drive the turbine propulsion mechanism to rotate, thereby causing the turbine propulsion mechanism to move the tray 16 inside the launch tube 17 through the traction rope, thereby launching the launch payload; the external traction cold launch device provided in the specific embodiment of the present invention is suitable for solid rocket launch, can solve the uncertainty brought about by the launch process of traditional hot launch and existing cold launch system, and has the advantages of strong power, stable thrust, and high device reusability, so as to meet the launch mission requirements of various types of solid rockets and other types of aircraft at this stage.

[0026] Preferably, in combination with the above scheme, as shown in Figures 1 to 12, the following methods are used: Figure 7As shown, the bottom compartment 1a and the top compartment 1b are both cuboid structures, and their interiors are not interconnected. Furthermore, the guide pipe 2 is located outside the power compartment 1 and connects to the sides of both the bottom compartment 1a and the top compartment 1b, thereby supplying high-pressure gas to the top compartment 1b along the side of the power compartment 1 to drive the turbine propulsion mechanism. Further, a thermal igniter 12 is located at the center of the bottom of the solid propellant 11. This design ignites the solid propellant through the thermal igniter 12 to generate high-temperature, high-pressure gas, driving the turbine blades and turbine shaft of the turbine propulsion mechanism to rotate at high speed. The device, in conjunction with rope pulleys, traction ropes, and various types of fixed pulleys, pulls the tray 16 and solid rocket 18 along the launch tube 17, controlling the work process of the launch device to complete the solid rocket launch mission. This achieves the launch objectives of adjustable power, stable thrust, low ablation rate, and high reusability. The gas outlet of the solid propellant 11 is connected to one end of the guide pipe 2. Furthermore, a tailpipe 13 is welded onto the top compartment 1b. One end of the tailpipe 13 is connected to the inside of the top compartment 1b, and the other end extends to the outside of the top compartment 1b, thereby enabling exhaust and controlling the gas pressure inside the top compartment 1b.

[0027] Preferably, in combination with the above scheme, as shown in Figures 1 to 12, the following methods are used: Figure 7 As shown, the power compartment 1 includes a bottom compartment 1a, a top compartment 1b, and a support compartment 1c. The support compartment 1c is located on top of the top compartment 1b. The support compartment 1c has a cylindrical structure, and the launch tube 17 has a cylindrical structure. The top of the support compartment 1c is provided with a flange face, and the flange face has multiple flange bolt holes 1d at equal intervals around its circumference. This allows the flange face to be fixedly connected to the bottom surface of the launch tube 17 by means of clamping bolts 15 passing through the flange bolt holes 1d, achieving high-strength fixation.

[0028] Preferably, in combination with the above scheme, as shown in Figures 1 to 12, the following methods are used: Figure 7As shown, the turbine propulsion mechanism includes a cable pulley 3, a turbine shaft 4, and turbine blades 14. The turbine shaft 4 is rotatably mounted within the top compartment 1b, with both ends extending outwards from the outer sides of the top compartment 1b. Specifically, the turbine shaft 4 is fitted onto the central axis of the top compartment 1b of the power module 1, and the turbine blades 14 are mounted on the turbine shaft 4 via an interference fit. Further, multiple turbine blades 14 are fixedly mounted on the turbine shaft 4 within the top compartment 1b and are capable of rotating together with the turbine shaft 4. Specifically, the number of turbine blades 14 is determined based on the cold launch... The power parameters of the device are determined; the rope pulleys 3 are respectively fixedly installed at both ends of the turbine shaft 4 extending out of the top compartment 1b, and rotate together with the turbine shaft 4; the rope pulleys 3 are installed at both ends of the turbine shaft 4 by positioning through the shaft shoulder 4a; further, the traction rope symmetrically pulls the tray 16 on both sides of the outer side of the launch tube 17 to move it; specifically, the traction rope includes a first traction rope and a second traction rope, which are symmetrically arranged along the axis of the launch tube 17; wherein, one end of the first traction rope is connected to one side of the tray 16, and the other end of the first traction rope extends out of the launch tube 17. The outer side of the launch tube 17 is connected to the rope pulley 3 at one end of the turbine shaft 4; correspondingly, one end of the second traction rope is connected to the other side of the tray 16, and the other end of the second traction rope extends out of the outer side of the launch tube 17 and is connected to the rope pulley 3 at the other end of the turbine shaft 4; the external traction cold launch device provided by the present invention ignites the solid propellant 11 through the thermal energy exciter 12 to generate high temperature and high pressure gas, which drives the turbine blades 14 and turbine shaft 4 of the turbine propulsion mechanism to rotate at high speed, in conjunction with the rope pulley 3, carbon fiber rope 5, wall fixed pulley 8, tube mouth fixed pulley 10, and tray large fixed pulley. 6. The tray pulley 7 and other devices pull the tray 16 and solid rocket 18 along the axis of the launch tube 17. By controlling the work process of the launch device, the solid rocket launch mission is completed, achieving the launch objectives of adjustable power, stable thrust, low device ablation rate, and high reusability. It can solve the problems of weak power adjustment, poor thrust stability, high device ablation rate, and low reusability of existing cold launch technology. It has the advantages of strong power, stable thrust, and high device reusability, and is suitable for solid rockets of different loads and configurations as well as various types of underwater unmanned vehicle launch systems.

[0029] Preferably, in combination with the above scheme, as shown in Figures 1 to 12, the following methods are used: Figure 7As shown, in this embodiment: the traction rope is a carbon fiber rope 5; multiple sets of wall-mounted pulleys 8 are symmetrically arranged on both sides of the outer wall of the launching tube 17 along its axial direction, preferably three sets of wall-mounted pulleys 8; a set of tube-mouth pulleys 10 are symmetrically arranged on both sides of the outlet of the launching tube 17 along its axial direction; a set of rope-locking blocks 9 and a set of limiters 19 are symmetrically arranged on the inner wall of the launching tube 17, the limiters 19 being used to restrict the tray 16 from detaching from the launching tube 17; a large tray pulley 6 and a small tray pulley 7 are symmetrically arranged on both sides of the tray 16; furthermore, One end of the carbon fiber rope 5 is fixed to the rope pulley 3, and the other end of the carbon fiber rope 5 passes through multiple sets of wall fixed pulleys 8, cylinder mouth fixed pulleys 10, tray small fixed pulleys 7, and tray large fixed pulleys 6 in sequence, and is finally fixedly connected to the rope locking block 9; specifically, the rope locking block 9 is welded to the side wall of the launch tube 17; specifically, the bottom of the solid rocket is fitted onto the tray 16, and the two move along the launch tube 17 under the pull of the carbon fiber rope 5. The upper limit of the movement of the tray 16 is stopped by the limiter 19, which is welded to the side wall at the port of the launch tube 17.

[0030] Preferably, in combination with the above scheme, as shown in Figures 1 to 12, the following methods are used: Figure 7 As shown, the carbon fiber rope 5 is made of carbon fiber rope with a carbon content of over 95% and high specific modulus and specific strength, which can achieve strong tensile strength and meet the emission strength requirements.

[0031] Preferably, in conjunction with the above scheme, as shown in Figure 5, the bottom of the solid rocket 18 is fitted with a circular groove at one end of the tray 16. Two sets of large fixed pulleys 6 and small fixed pulleys 7 are symmetrically and staggered on both sides of the tray 16. The staggered installation of the large fixed pulleys 6 and small fixed pulleys 7 allows the carbon fiber rope 5 to better pull the tray 16 and distribute the force more evenly. The carbon fiber rope 5 first passes through the lower large fixed pulley 6 and then through the upper small fixed pulley 7. The large fixed pulleys 6 and small fixed pulleys 7 move synchronously with the tray 16.

[0032] Preferably, in combination with the above scheme, as shown in Figures 1 to 12, the following methods are used: Figure 7 As shown, the turbine shaft 4 has shoulders 4a on both ends of the top compartment 1b, and the shoulders 4a are set in through holes on the side wall of the top compartment 1b, and rotate with the through holes; further, the rope pulley 3 is sleeved and fixed on the outside of the shoulders 4a; further, the turbine shaft 4 located in the top compartment 1b has an inverted trapezoidal mounting groove 4b; specifically, multiple sets of turbine blades 14 are sleeved on the turbine shaft 4, and each set of turbine blades 14 is engaged with the inverted trapezoidal mounting groove 4b, thereby restricting the turbine blades 14 from rotating around the circumference of the turbine shaft 4; specifically, the central through hole of the turbine blade 14 is sleeved on the turbine shaft 4, and the inverted trapezoidal boss in the central through hole engages with the inverted trapezoidal mounting groove 4b, thereby restricting the turbine blades 14 from rotating around the circumference of the turbine shaft 4, that is, ensuring that the turbine blades 14 rotate together with the turbine shaft 4, thereby improving the transmission efficiency.

[0033] Preferably, in combination with the above scheme, as shown in Figures 1 to 12, the following methods are used: Figure 7 As shown, please refer to the following for details. Figure 2 As shown, the solid propellant 11 has a cylindrical structure and is composed of multiple cylindrical solid propellant units 11b. Adjacent solid propellant units 11b are separated by a coating layer 11a. Specifically, the coating layer 11a is made of silica and silicone rubber, which can improve the separation effect, avoid interference and influence between adjacent solid propellant units 11b, and help the thermal ignition generator.

[0034] Preferably, in combination with the above scheme, as shown in Figures 1 to 12, the following methods are used: Figure 7 As shown, please refer to the following for details. Figure 2 As shown, the materials used to prepare the solid propellant unit 11b include ammonium perchlorate, hydroxyl-terminated polybutadiene, and nitramine, which can meet the power requirements and reduce the ablation of the power compartment 1 by the solid propellant 11.

[0035] Specifically, in conjunction with the above schemes, as shown in Figures 1 to 12, Figure 7 As shown, the externally traction-type cold launch device provided by this invention can achieve the goals of adjustable power, stable thrust, and controllable ablation rate during the solid rocket launch process; its working principle and process are as follows: First, the thermal igniter 12 in the bottom compartment 1a of the power module 1 is activated, igniting the solid propellant 11 to generate high-temperature, high-pressure gas. Then, the gas enters the top compartment 1b of the power module along the guide pipe 2, driving the turbine blades 14 and turbine shaft 4 to rotate at high speed, and then exits the power module 1 from the tailpipe 13. The rope pulley 3, rotating synchronously with the turbine shaft 4, collects the gas through the wall-mounted pulley 8, the tube-mouth pulley 10, the tray small pulley 7, the tray large pulley 6, and the carbon fiber rope 5 of the tray 16, thereby pulling the tray 16 and the solid rocket 18 to move synchronously along the launch tube 17, as detailed below. Figure 6 As shown; in this process, the tray 16 and the solid rocket 18 move synchronously to the limit switch 19, where the tray 16 brakes and stops, separating from the solid rocket 18. Finally, the solid rocket 18 flies out of the launch tube 17, completing the launch process, as shown. Figure 7 As shown, by changing the configuration, formula, mass ratio of solid propellant 11, the size of rope wheel 3, and the configuration and number of turbine blades 14, the launch operation of solid rocket 18 with adjustable power, stable thrust, and low device ablation rate can be achieved.

[0036] Accordingly, in conjunction with the above schemes, as shown in Figures 1 to 12, Figure 7 As shown in the figure, a specific embodiment of the present invention also provides a method for using the externally traction-type cold launch device described above; specifically, the method for using the cold launch device includes the following steps: S1: Determine the power parameters of the cold launch device based on the target launch mission indicators. The power parameters include the total launch power and the maximum traction force. Specifically, based on the payload mass, launch speed and acceleration indicators, calculate the total launch power and the maximum traction force required by the launch system using mass conservation, energy conservation and pulley system efficiency equations. Furthermore, the total launch power E = ( m g L +1 / 2 mv 2 min ) / η1, where: m is the load mass; g is the gravitational acceleration; L The length of the launch tube; v min η1 is the minimum exit velocity of the load; η1 is the kinetic energy conversion rate, taken as 0.2~0.5; further, the maximum traction force of the solid rocket launch. F = ma max In the formula: a max The maximum acceleration; the two satisfy E≥2 FnL In the formula: n is the number of pulley groups of the large fixed pulley 6 on the tray; Furthermore, the efficiency calculation formula is as follows: η =Gh / (Fs), where: G is the weight of the load, h is the height to which the load is lifted, F is the traction force, and s is the distance the free end of the carbon fiber rope is stretched. S2: Calculate the formula, type and mass ratio of solid propellant 11, configuration and quantity of turbine blades 14, heating power of thermal exciter 12 based on power parameters, and design the installation dimensions of each component of power compartment 1, rope wheel 3, turbine shaft 4, tray 16 and launch tube 17. Specifically, based on the solid rocket's mass m and maximum launch acceleration a, the maximum traction force for launch is determined. F = ma ≥Q×v,v=[2D(P1-P2) / ( ρ g λL)]^(1 / 2), where ρ g Where ρ is the gas density, Q is the flow rate, v is the flow velocity, P1 and P2 represent the pressures at both ends of the guide pipe 2 and the tailpipe 13, ρ represents the fluid density, λ represents the pipe internal resistance coefficient, L is the equivalent length from guide pipe 2 to tailpipe 13, and D represents the equivalent inner diameter of the pipe; Turbine blade configuration and quantity parameters: Number of turbine blades 14 Z = Q / (π D β H), where Z represents the number of blades; Q represents the flow rate; D represents the turbine blade diameter; β represents the ratio of the flow path width of guide tube 2 to the turbine blade diameter; H represents the blade height, determined by the turbine blade configuration; the flow rate Q is determined by the propellant burning rate: Q = r b A ρ b ,in, r b and ρ b These are the propellant burning rate and density, determined by the propellant formulation and mass ratio; A is the propellant burning surface, determined by the propellant type, and the propellant loading configuration is limited by the size of the power compartment 1; the size of the launch tube 17 is limited by the size of the solid rocket 18, and the size of the tray 16 is slightly smaller than the inner diameter of the launch tube 17; the size of the turbine shaft 4 is 1 / 5 of the blade height; the diameter of the cable pulley 3 is approximately 1 / 10 of the diameter of the tray 16; the total propellant mass is determined by the total launch power. S3: Assemble the processed power compartment 1, rope wheel 3, turbine shaft 4, carbon fiber rope 5, tray 16 and launch tube 17, and connect the carbon fiber rope 5 to assemble a cold launch device. S4: Check the rationality of the assembly of each component of the cold emission device and the stability of the carbon fiber rope 5. S5: Install the solid rocket simulator on the tray 16 and put it into the launch tube 17. First, use high-pressure cold air to carry out a cold launch simulation experiment to check the transmission performance of various types of fixed pulleys and rope wheels 3, and the strength performance of carbon fiber rope 5. S6: Replace the high-pressure cold gas with solid propellant 11, conduct an ignition and launch test, and monitor the pressure in the power compartment 1, the motion acceleration and velocity changes of the solid rocket simulator. S7: If there are abnormalities in the pressure inside the power compartment 1, the motion acceleration and velocity changes of the solid rocket simulator, or the transmission performance of each component of the cold launch device does not meet the design requirements, repeat steps S1 to S6 until the performance indicators of the cold launch device meet the expected requirements. S8: Install the solid rocket 18 on the tray 16 and insert it into the launch tube 17 to conduct a live-fire cold launch experiment; collect the internal pressure (pt) of the power compartment 1, the rotational speed (rt) of the rope wheel 3, and the motion acceleration (at) and velocity (vt) curves of the solid rocket 18 to obtain cold launch experiment data.

[0037] The solution provided by this invention has the following technical effects: First, the solution proposed in this invention is based on modular design thinking. It uses different configurations, formulations and mass ratios of solid propellants to control the total launch power, so as to match the launch power with the launch mission of various types of solid rockets and provide technical support for the multi-scenario launch of different types of solid rockets in the future battlefield. Secondly, the proposed solution adopts a split turbine drive method, which transmits gas power to carbon fiber rope through turbine shaft, pulling the solid rocket out of the tube quickly. During the launch process, the high-temperature gas is located inside the power compartment and does not come into contact with the components inside the launch tube, thus avoiding the ablation of solid rocket components by high-temperature and corrosive gas, effectively improving the reusability of the device and the reliability and safety of the launch mission. Third, the solution proposed in this invention has a simple structure, is easy to process and install, and has low maintenance costs. It can be customized according to the launch mission requirements, solving the problems of high cost, poor launch efficiency and low reusability of traditional gas launch or compressed air launch methods.

[0038] The above description is merely a preferred embodiment of the present invention and does not constitute any limitation on the present invention. Any person skilled in the art can make many possible variations and modifications to the technical solution of the present invention, or modify it into equivalent embodiments, without departing from the scope of the present invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technology of the present invention without departing from the scope of the present invention are within the protection scope of the present invention.

Claims

1. An externally traction-type cold-launch device, characterized in that, The cold launch device includes a power compartment (1), a turbine propulsion mechanism, a traction rope, a tray (16), a launch tube (17), and a solid propellant (11); the power compartment (1) includes a bottom compartment (1a) and a top compartment (1b), which are connected by a guide pipe (2); the solid propellant (11) is disposed in the bottom compartment (1a); the turbine propulsion mechanism is disposed in the top compartment (1b); the bottom surface of the launch tube (17) is fixedly connected to the power compartment (1); the tray (16) is disposed in the launch tube (17) and can reciprocate along the axial direction of the launch tube (17); the tray (16) The traction rope is used to install the launch payload; one end of the traction rope is connected to the tray (16), and the other end of the traction rope extends outside the launch tube (17) and is connected to the turbine propulsion mechanism; the high-pressure gas generated by the solid propellant (11) can enter the top compartment (1b) through the guide pipe (2) and drive the turbine propulsion mechanism to move the tray (16) inside the launch tube (17) through the traction rope, thereby launching the launch payload; the bottom compartment (1a) and the top compartment (1b) are both rectangular structures, and the interiors of the bottom compartment (1a) and the top compartment (1b) are not interconnected; the guide pipe 2 is set at the... The power compartment (1) is located outside the power compartment (1) and is connected to the bottom compartment (1a) and the top compartment (1b) respectively; a thermal exciter (12) is provided at the center of the bottom of the solid propellant (11); the gas outlet of the solid propellant (11) is connected to one end of the guide pipe (2); a tailpipe (13) is also provided on the top compartment (1b), one end of the tailpipe (13) is connected to the inside of the top compartment (1b), and the other end of the tailpipe (13) extends to the outside of the top compartment (1b); the turbine propulsion mechanism includes a cable pulley (3), a turbine shaft (4) and turbine blades (14); the turbine shaft (4) is rotatably mounted on the top compartment (1b). The turbine shaft (4) extends outward from the top compartment (1b) at both ends; multiple turbine blades (14) are fixedly mounted on the turbine shaft (4) inside the top compartment (1b) and can rotate together with the turbine shaft (4); rope pulleys (3) are fixedly mounted on both ends of the turbine shaft (4) extending outward from the top compartment (1b) and rotate together with the turbine shaft (4); the traction rope includes a first traction rope and a second traction rope; one end of the first traction rope is connected to one side of the tray (16), and the other end of the first traction rope extends outward from the launch tube (17) and is connected to the rope pulley (3) at one end of the turbine shaft (4);One end of the second traction rope is connected to the other side of the tray (16), and the other end of the second traction rope extends out of the outside of the launch tube (17) and is connected to the rope pulley (3) at the other end of the turbine shaft (4); the traction rope is a carbon fiber rope (5), and multiple sets of wall fixed pulleys (8) are symmetrically arranged on both sides of the outer wall of the launch tube (17) along its axial direction, and a set of tube mouth fixed pulleys (10) are symmetrically arranged on both sides of the outlet of the launch tube (17) along its axial direction; a set of rope locking blocks (9) and a set of rope locking blocks (9) are symmetrically arranged on the inner wall of the launch tube (17). A set of limiters (19) is used to restrict the tray (16) from detaching from the launching tube (17); the tray (16) is symmetrically provided with a large fixed pulley (6) and a small fixed pulley (7) on both sides; one end of the carbon fiber rope (5) is fixed to the rope wheel (3), and the other end of the carbon fiber rope (5) passes sequentially through the multiple sets of wall fixed pulleys (8), the tube opening fixed pulley (10), the small fixed pulley (7) of the tray, and the large fixed pulley (6) of the tray, and is finally fixedly connected to the locking rope block (9).

2. The externally traction-type cold-launch device according to claim 1, characterized in that, The power compartment (1) includes a support chamber (1c), which is a cylindrical structure, and the launch tube (17) is a cylindrical structure. The top of the support chamber (1c) is provided with a flange face, and the flange face is provided with multiple flange face bolt holes (1d) at equal intervals around its circumference. The flange face and the bottom surface of the launch tube (17) are fixedly connected by clamping bolts (15) passing through the flange face bolt holes (1d).

3. The externally traction-type cold-launch device according to claim 1, characterized in that, The carbon fiber rope (5) is made of carbon fiber rope with a carbon content of more than 95% and high specific modulus and specific strength.

4. The externally traction-type cold-launch device according to claim 1, characterized in that, The turbine shaft (4) is provided with shoulders (4a) on both ends of the top compartment (1b). The shoulders (4a) are located in through holes on the side wall of the top compartment (1b). The rope pulley (3) is sleeved and fixed to the outside of the shoulders (4a). The turbine shaft (4) located in the top compartment (1b) is provided with an inverted trapezoidal mounting groove (4b). Multiple sets of turbine blades (14) are sleeved on the turbine shaft (4). Each set of turbine blades (14) is engaged with the inverted trapezoidal mounting groove (4b) to restrict the turbine blades (14) from rotating circumferentially along the turbine shaft (4).

5. The externally traction-type cold-launch device according to claim 1, characterized in that, The solid propellant (11) has a cylindrical structure and is composed of multiple cylindrical solid propellant units (11b). Two adjacent solid propellant units (11b) are separated by a coating layer (11a).

6. The externally traction-type cold launch device according to claim 5, characterized in that, The coating layer (11a) is made of silica and silicone rubber; and / or the solid propellant unit (11b) is made of ammonium perchlorate, hydroxyl-terminated polybutadiene, and nitramine.

7. A method of using the externally traction-type cold-launch device according to claim 1, characterized in that, The method of use includes the following steps: S1: Determine the power parameters of the cold launch device based on the target launch mission specifications; S2: Calculate the formula, type and mass ratio of solid propellant (11), configuration and quantity of turbine blades (14), heating power of thermal exciter (12) based on the power parameters, and design the installation dimensions of each component of power compartment (1), rope wheel (3), turbine shaft (4), tray (16) and launch tube (17). S3: Assemble the processed power compartment (1), rope wheel (3), turbine shaft (4), carbon fiber rope (5), tray (16) and launch tube (17), and connect the carbon fiber rope (5) to form the cold launch device. S4: Check the rationality of the assembly of each component of the cold emission device and the stability of the carbon fiber rope (5); S5: Install the solid rocket simulation projectile on the tray (16) and put it into the launch tube (17). First, use high-pressure cold air to carry out a cold launch simulation experiment to check the transmission performance of various types of fixed pulleys and rope wheels (3) and the strength performance of the carbon fiber rope (5). S6: Replace the high-pressure cold gas with the solid propellant (11), conduct an ignition and launch test, and monitor the pressure in the power compartment (1), the motion acceleration and velocity changes of the solid rocket simulator; S7: If the pressure in the power compartment (1), the motion acceleration and velocity change of the solid rocket simulator are abnormal, or the transmission performance of each component of the cold launch device does not meet the design requirements, repeat steps S1 to S6 until the performance indicators of the cold launch device meet the expected requirements. S8: Install the solid rocket (18) on the tray (16) and put it into the launch tube (17) to conduct a live cold launch experiment; collect the internal pressure (pt) of the power compartment (1), the rotational speed (rt) of the rope wheel (3), the motion acceleration (at) and velocity (vt) curve of the solid rocket (18) to obtain cold launch experiment data.

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