Rocket power capturing net launching device and rocket marshalling flight control method
Through the rocket power net capture launch device, the rocket traction missile is used to drive the net to expand, solving the problems of limited range of the existing net capture launch device and increased equipment weight, achieving higher range and capture probability, and improving the safety and simplicity of the system.
Patent Information
- Application Number
- CN202510177564.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-18
- Publication Date
- 2025-06-06
AI Technical Summary
The existing net capture launcher has limited range. The higher the initial velocity, the greater the excitation energy is required, which leads to an increase in the weight of the equipment. The huge downwind resistance of the high initial velocity may lead to a tear of the net, which is high in cost and a smaller area of the net.
The rocket power net capture launch device is used to provide power through the rocket engine, driving a larger area of net capture to achieve higher probability capture. The device includes a rocket traction bomb, net capture, flight attitude control line and storage/release box resistance umbrella module. It drives the rocket traction bomb to take off through the rocket engine, and the traction bomb drives the net to unfold and fly forward.
The range of the trapping net is increased to more than 200 meters, which enhances the capture probability, is not high in system cost, is simple in operation and is safe, and can effectively avoid the dangers caused by the trapping net approaching the launcher under the action of inertia.
Smart Images
Figure CN120101580A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of rocket-powered net-catching launch, and in particular to a rocket-powered net-catching launch device and a rocket formation flight control method. Background Art
[0002] Most of the other existing net-launching devices use compressed air or gunpowder combustion gas as power to drive several heavy metal traction heads to fly outward at a certain opening angle at the same time. After the traction head drives a net to open at a preset angle, it uses the inertia of the mass of the metal traction head multiplied by the initial velocity to fly. The overall operation steps are as follows: 1. The gas releases energy; 2. The traction head is pushed to reach a higher initial velocity; 3. After the net is opened, the inertia gradually decreases during flight; 4. The net falls to the ground after the inertia is consumed.
[0003] The range of this type of launch device is generally not far, rarely exceeding 30 meters, and very rarely up to 50 meters. If you want to further increase the initial velocity to obtain a longer range, you will encounter some problems. Problem 1: The higher the initial velocity, the greater the excitation energy required, and the corresponding compressed gas cylinder pressure bearing capacity or the gunpowder explosion guide tube pressure bearing capacity must be higher, resulting in a heavier equipment weight, which is very unfavorable for storage and carrying. If the gunpowder gas generating device is also faced with high jet energy, the resulting recoil will be greater, which will exceed the personnel's tolerance. Problem 2: When the initial velocity is high to a certain extent, for example, the initial velocity of the traction block and the capture net is higher than the speed of sound, the traction head and the capture net are like flying in a storm. The huge energy of wind resistance will risk tearing the capture net into pieces, and the higher the requirements for the sturdiness of the capture net, the more likely it is to lead to high costs and a reduction in the capture net area. Therefore, it is difficult to increase the range of the capture net device that relies on the initial velocity + inertia principle under this technical limitation. Summary of the invention
[0004] 1. Technical issues to be resolved
[0005] In view of the deficiencies in the prior art, the present invention provides a rocket-powered net-capturing launch device and a rocket formation flight control method, which have the advantages of a large rocket engine power and can drive a larger area of the net to achieve a higher probability of capture, and solve the problem that the existing launch device generally has a short range, rarely exceeding 30 meters, and very rarely up to 50 meters. If you want to further increase the initial velocity to obtain a longer range, you will encounter some problems. Problem 1: The higher the initial velocity, the greater the excitation energy required, and the corresponding pressure bearing capacity of the compressed gas cylinder or the gunpowder explosion guide tube will be higher, resulting in a heavier device weight, which is very unfavorable for storage and carrying. If the gunpowder gas generating device is also faced with high jet energy, the resulting recoil is large and will exceed the bearing capacity of personnel. Problem 2: When the initial velocity is high to a certain extent, for example, the initial velocity of the traction block and the net is higher than the speed of sound, the traction head and the net are like flying in a storm, and the huge wind resistance energy will have the risk of tearing the net into pieces, so the higher the requirement for the sturdiness of the net, it is easy to lead to problems such as high cost and reduced net area.
[0006] (II) Technical solution In order to achieve the purpose that the above-mentioned rocket engine has greater power and can drive a larger area of the capture net to achieve a higher probability of capture, the present invention provides the following technical solutions: a rocket-powered capture net launching device, including a protective cover, a rocket bracket and a flame-blocking cloth bracket, a fixing ring, a battery box and a launch button module, a movable ring, a barrel and a rear cover, a flame-blocking cloth, a rocket traction bomb, a capture net, a flight attitude control line and a storage / release box drag parachute module, one end of the barrel and the rear cover is provided with a fixing ring, one end of the barrel and the rear cover is provided with a flame-blocking cloth, and one end of the flame-blocking cloth away from the barrel and the rear cover is provided with a flame-blocking cloth. A fixing ring is provided, and a protective cover is provided at the other end of the fixing ring; a rocket bracket and a flame shield cloth bracket connected to the fixing ring are provided on the outer side of the barrel and the rear cover; a battery box and a launch button module are provided on the outside of the barrel and the rear cover; a movable ring is provided on the outside of the barrel and the rear cover and located at the lower side of the fixing ring; a rocket traction bomb is provided on the rocket bracket and the flame shield cloth bracket, a catching net is provided inside the rocket traction bomb, a flight attitude control line is provided on the rocket traction bomb, and the other end of the flight attitude control line is connected to a storage / release box drag parachute module.
[0007] Furthermore, the protective cover includes a tube cover, a cover-throwing spring, a telescopic guide rod, a pin-closing protrusion, a safety pin hole and a safety pin. Two telescopic guide rods are arranged inside the tube cover, and the outsides of the two telescopic guide rods are both sleeved with a cover-throwing spring. The inner side of the tube cover is provided with a pin-closing protrusion, and the outer side of the tube cover is provided with a safety pin hole, and the safety pin hole is connected to the safety pin hole.
[0008] Furthermore, the rocket bracket and flame-blocking cloth bracket include a rocket positioning bracket, a flame-blocking cloth bracket, a support arm, a positioning hole and a torsion spring, a latch and a torsion spring and a storage groove. The rocket positioning bracket is connected to the flame-blocking cloth bracket through the latch and the torsion spring. A support arm is provided on the side of the rocket positioning bracket away from the flame-blocking cloth bracket. A positioning hole and a torsion spring are provided at the bottom of the rocket positioning bracket. A storage groove is provided on the side of the rocket positioning bracket away from the support arm.
[0009] Furthermore, the fixing ring comprises a fixing ring body, an inclined groove, a safety pin insertion hole and a bracket positioning groove. The fixing ring body is provided with an inclined groove, and four bracket positioning grooves are provided on the outer side of the fixing ring body.
[0010] Furthermore, the battery box and launch button module includes a battery box and a battery, a rocket ignition wire terminal, a buzzer, a power-on safety button, a wiring groove and a launch button. Four rocket ignition wire terminals are arranged on the side of the battery box and the battery, a buzzer is arranged on the front side of the battery box and the battery, a power-on safety button is arranged on the bottom of the battery box and the battery, a wiring groove is opened on the battery box and the battery, and a launch button is arranged on the bottom of the battery box and the battery.
[0011] Furthermore, the movable ring is provided with four positioning grooves, the top of the movable ring is provided with an impact protrusion, and the movable ring is provided with an electric wire trough channel.
[0012] Furthermore, the barrel and the rear cover comprise a barrel, a rear cover and a shoulder strap ring. The rear cover is disposed at the bottom of the barrel, and the shoulder strap ring is disposed on the outside of the rear cover.
[0013] Furthermore, a resistance stabilization line hole is provided on the rocket traction bomb, a center of gravity load line hole is provided on the rocket traction bomb, a launcher positioning plate is provided on the outside of the rocket traction bomb, a rocket engine compartment is provided on the inside of the rocket traction bomb, and a counterweight compartment is provided on the top of the rocket traction bomb.
[0014] Furthermore, the wire storage / release box resistance parachute module includes a wire storage / release box and a resistance parachute, and the interior of the wire storage / release box is provided with four wire storage / release box compartments, and the bottom of the wire storage / release box is connected to the wire storage / release box back cover by threads, and the wire storage / release box back cover is provided with a resistance ring and a positioning groove.
[0015] A rocket group flight control method for a rocket-powered net-catching launcher, the operation steps are as follows: Step 1: After the operator manually pulls out the safety pin, the locking protrusion built into the cylinder cover can move along the inclined groove under the lifting action of the cover-throwing spring, and the protective cover will be ejected and thrown away after being unlocked; Step 2: As the protective cover is discarded, the rocket bracket loses the restraint of the protective cover, that is, the four sets of rocket positioning brackets are opened under the action of the positioning holes and torsion springs and the catches and torsion springs, and the flame shield is unfolded; Step 3: As the rocket positioning bracket opens, the four torsion springs will drive the movable ring to move forcefully toward the fixed ring. During this process, the impact protrusion will hit the power-on safety button, releasing the battery box and battery from the safety state, and energizing the buzzer and the LED indicator light of the launch button, indicating that the launch button is in the ready-to-launch state with sound and light. Step 4: If the launch button is pressed, the rocket ignition wire at the rocket ignition wire terminal will pass current, causing the ignition head embedded inside the rocket engine to ignite synchronously, starting the rocket engine and driving the rocket traction missile to take off synchronously; Step 5: The rocket-towed missile is driven by the thrust of the rocket engine and takes off along the preset launcher track. During takeoff, the high-temperature gas ejected from the tail of the rocket will be blocked by the flame shield so as not to injure the launcher; Step 6: Once the rocket-towed missile is driven forward, the tail resistance stabilization line hole is affected by the resistance of the flight attitude control line from the damping rubber in the storage / release box. This resistance stipulates that the engine nozzle of the rocket-towed missile must point to the source of resistance. When the rocket engines of the four traction missiles are all pointing to the same source of resistance, the heads of the four traction missiles will take the direction of the launch tube as the central axis and fly forward radially; Step 7: At the same time, the net is connected as an effective load near the center of gravity of the rocket towing projectile, that is, at the center of gravity load line hole, so the center of gravity is near the center of gravity of the towing projectile. The weight of the net and the aerodynamic drag will only act as an inertial drag on the rocket towing projectile in the form of load, but will not affect the angle and posture of the towing projectile. Step 8: When the net is fully extended, the traction missiles cannot be further extended and will maintain the maximum extended posture, flying in the direction of the combined force of the rockets; Step nine: When all the flight attitude control lines are completely released from the storage / release box, they are completely straightened, and together they pull the storage / release box and the drag parachute out of the storage tube. The aerodynamic drag generated by the storage / release box and the drag parachute is backward, and the propulsion direction of each traction bomb is a virtual ray formed from the center of the resistance source to the center of gravity of each traction bomb. The combined force makes the entire net fully unfold like an inverted pyramid, and accelerates forward until the fuel is consumed, maintaining inertial flight and then landing. In this process, the net will entangle when it encounters a target until the capture is successful, and the launcher can discard the launcher part at will.
[0016] (III) Beneficial effects Compared with the prior art, the present invention provides a rocket-powered net-catching launch device and a rocket formation flight control method, which have the following beneficial effects: 1. The rocket-powered net-launching device and rocket formation flight control method have a long range, which increases the range of the net to more than 200 meters, greatly improving the practical value. The operation is simple, and ordinary people can master the use method after 5 minutes of explanation. The reaction speed is fast. The overall design is that the packaging tube and the launch tube are integrated. It only takes 0.1 seconds to switch from the storage state to the launch state, and a quick response can be made.
[0017] 2. The rocket-powered net-capturing launch device and rocket formation flight control method have a high capture probability and are capable of driving a large-area net to greatly improve the capture probability by relying on sufficient power. The entire system is not costly, is conducive to mass production, and can be stored for a long period of time. The launch tube is discarded after launch, which improves the operator's flexibility and has high safety. If the net encounters a target when it is close to the launcher, due to the large amount of remaining fuel in the rocket, the powerful continuous thrust will pull the powerless target away or deviate from its original route, preventing it from approaching the launcher under the action of inertia, thereby avoiding danger. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 It is an exploded view of the overall structure of the present invention; Figure 2 It is a schematic diagram of the storage state of the present invention; Figure 3 It is a schematic diagram of the ready-to-launch state of the present invention; Figure 4 This is a structural diagram of the net flight control of the present invention; Figure 5 It is a schematic diagram of the protective cover of the present invention; Figure 6 It is a schematic diagram of the rocket bracket and the stuffing-blocking cloth bracket of the present invention; Figure 7 It is a schematic diagram of the fixing ring of the present invention; Figure 8 A schematic diagram of the battery and the transmitting button module of the present invention; Fig. 9 It is a schematic diagram of the movable ring of the present invention; Fig.10 It is a schematic diagram of the barrel and the rear cover of the present invention; Fig.11 This is a schematic diagram of the structure of a rocket-drawn bomb of the present invention; Fig.12 It is a schematic diagram of the storage / wire box of the present invention.
[0019] In the figure: 1. Protective cover; 101. Cylinder cover; 102. Cover spring; 103. Telescopic guide rod; 104. Closed pin protrusion; 105. Safety pin hole; 106. Safety pin; 2. Rocket bracket and flame shield bracket; 201. Rocket positioning bracket; 202. Flame shield bracket; 203. Support arm; 204. Positioning hole and torsion spring; 205. Clip and torsion spring; 206. Storage slot; 3. Fixed ring; 301. Fixed ring body; 302. Inclined groove; 203. Safety pin jack; 204. Bracket positioning slot; 4. Battery box and launch button module; 401. Battery box and battery; 402. Rocket ignition wire terminal; 403. Buzzer; 404. Power-on safety button; 405. Wiring Slot; 406, launch button; 5, movable ring; 501, positioning slot; 502, impact convex shoot; 503, wire slot channel; 6, barrel and back cover; 601, barrel; 602, back cover; 603, shoulder strap ring; 7, flame shield; 8, rocket traction bomb; 801, resistance stabilization line hole; 802, center of gravity load line hole; 803, launcher positioning plate; 804, counterweight compartment; 805, rocket engine compartment; 9, capture net; 10, flight attitude control line; 11, storage / release box drag parachute module; 1101, storage / release box; 1102, drag parachute; 1103, storage / release box compartment; 1104, storage / release box back cover; 1105, damping ring and positioning slot; 1106, thread. DETAILED DESCRIPTION
[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.
[0021] See also Figure 1-12A rocket-powered net-catching launch device comprises a protective cover 1, a rocket support and a flame-blocking cloth support 2, a fixing ring 3, a battery box and a launching button module 4, a movable ring 5, a barrel and a rear cover 6, a flame-blocking cloth 7, a rocket traction bomb 8, a net 9, a flight attitude control line 10 and a storage / release box drag parachute module 11, a fixing ring 3 is arranged at one end of the barrel and the rear cover 6, a flame-blocking cloth 7 is arranged at one end of the barrel and the rear cover 6, a fixing ring 3 is arranged at one end of the flame-blocking cloth 7 away from the barrel and the rear cover 6, and a protective cover is arranged at the other end of the fixing ring 3. Cover 1, a rocket bracket and a flame shield cloth bracket 2 connected to the fixing ring 3 are arranged on the outside of the barrel and the rear cover 6, a battery box and a firing button module 4 are arranged outside the barrel and the rear cover 6, a movable ring 5 is arranged outside the barrel and the rear cover 6 and located on the lower side of the fixing ring 3, a rocket traction bomb 8 is arranged on the rocket bracket and the flame shield cloth bracket 2, a catching net 9 is arranged inside the rocket traction bomb 8, a flight attitude control line 10 is arranged on the rocket traction bomb 8, and the other end of the flight attitude control line 10 is connected to a storage / release box drag parachute module 11.
[0022] In the embodiment, the protective cover 1 includes a cylinder cover 101, a cover spring 102, a telescopic guide rod 103, a locking pin protrusion 104, a safety pin hole 105 and a safety pin 106. Figure 5 As shown, two telescopic guide rods 103 are arranged inside the cylinder cover 101, and the outer parts of the two telescopic guide rods 103 are sleeved with a cover spring 102. A locking pin convex shoot 104 is arranged on the inner side of the cylinder cover 101, and a safety pin hole 105 is arranged on the outer side of the cylinder cover 101, and a safety pin 106 is connected to the safety pin hole 105. After the operator manually pulls out the safety pin 106, the locking projection 104 built into the cylinder cover 101 can move along the inclined groove 302 under the lifting action of the cover-throwing spring 102, and the protective cover 1 is ejected and discarded as a whole after being unlocked.
[0023] In the case implementation, the rocket bracket and flame shield bracket 2 include a rocket positioning bracket 201, a flame shield bracket 203, a support arm 203, a positioning hole and a torsion spring 204, a latch and a torsion spring 205 and a storage slot 206, as shown in FIG. Figure 6 As shown, the rocket positioning bracket 201 is connected to the filling cloth bracket 202 through the latch and the torsion spring 205, and a support arm 203 is arranged on the side of the rocket positioning bracket 201 away from the filling cloth bracket 202, and a positioning hole and a torsion spring 204 are arranged on the bottom of the rocket positioning bracket 201. The rocket bracket 2 loses the restraint of the protective cover 1, that is, the four sets of rocket positioning brackets 201 are opened under the action of the positioning hole and the torsion spring 204 and the latch and the torsion spring 205, and the flame-blocking cloth 7 is unfolded, and a storage groove 206 is opened on the side of the rocket positioning bracket 201 away from the support arm 203.
[0024] In the embodiment, the fixing ring 3 includes a fixing ring body 301, an inclined groove 302, a safety pin insertion hole 303 and a bracket positioning groove 304. Figure 7 As shown, an inclined groove 302 is formed on the fixing ring body 301, and four bracket positioning grooves 304 are formed on the outer side of the fixing ring body 301; By opening the rocket positioning bracket 201 , the four torsion springs will drive the movable ring 5 to move forcefully toward the fixed ring 3 .
[0025] In the case implementation, the battery box and launch button module 4 includes a battery box and battery 401, a rocket ignition wire terminal 402, a buzzer 403, a power-on safety button 404, a wiring groove 405, and a launch button 406. Figure 8 As shown, the side of the battery box and battery 401 is provided with four rocket ignition wire terminals 402, and the front side of the battery box and battery 401 is provided with a buzzer 403. By hitting the protruding shoot 502 to hit the power-on safety button 404, the battery box and battery 401 are released from the safety state, and the buzzer 403 and the LED prompt light of the launch button 406 are powered on, and the sound and light prompt is in the ready state. The bottom of the battery box and battery 401 is provided with a power-on safety button 404, the battery box and battery 401 is provided with a wiring groove 405, and the bottom of the battery box and battery 401 is provided with a launch button 406; The launch button 406 is a luminous button. When the launch button 406 is pressed, current flows through the rocket ignition wire at the rocket ignition wire terminal 402, causing the ignition head embedded in the rocket engine to ignite synchronously, starting the rocket engine and driving the rocket traction missile to take off synchronously.
[0026] In the case implementation, Fig. 9 As shown, four positioning grooves 501 are provided on the movable ring 5, and a striking protrusion 502 is provided on the top of the movable ring 5, so as to facilitate striking the power-on safety button 404 through the striking protrusion 502. An electric wire groove channel 503 is provided on the movable ring 5 to facilitate the routing of electric wires.
[0027] In the embodiment, the barrel and rear cover 6 include a barrel 601, a rear cover 602 and a strap ring 603. Fig.10 As shown, a rear cover 602 is provided at the bottom of the barrel 601 , and a shoulder strap ring 603 is provided outside the rear cover 602 . Multiple components can be accommodated through the barrel 601 , the rear cover 602 and the shoulder strap ring 603 .
[0028] In the case implementation, Fig.11As shown, a resistance stabilizing line hole 801 is provided on the rocket traction bomb 8. Once the rocket traction bomb 8 is driven forward, the resistance stabilizing line hole 801 at the tail is affected by the resistance of the damping glue in the storage / release line box 11 of the flight attitude control line 10. This resistance stipulates that the engine nozzle of the rocket traction bomb 8 must be pointed to the source of resistance. A center of gravity load line hole 802 is provided on the rocket traction bomb 8. A launcher positioning piece 803 is provided on the outside of the rocket traction bomb 8. A rocket engine compartment 805 is provided inside the rocket traction bomb 8. A counterweight compartment 804 is provided on the top of the rocket traction bomb 8. By setting the center of gravity load line hole 802, the catching net 9 is connected as an effective load near the center of gravity of the rocket traction projectile 8, that is, the center of gravity load line hole 802. Therefore, the center of gravity is near the center of gravity of the traction projectile. The weight of the catching net 9 and the aerodynamic resistance will only have an inertial slowing effect on the rocket traction projectile 8 in the form of load, and will not affect the angle and posture of the traction projectile.
[0029] In the case implementation, the storage / release box resistance parachute module 11 includes a storage / release box 1101 and a resistance parachute 1102. The storage / release box 1101 is provided with four storage / release box compartments 1103. The bottom of the storage / release box 1101 is connected to a storage / release box rear cover 1104 through a thread 1106. The storage / release box rear cover 1104 is provided with a resistance ring and a positioning groove 1105. By setting up the storage / release box 1101 and the drag parachute 1102, when all the flight attitude control lines 10 are completely released from the storage / release box 1101, they are completely straightened, and together pull the storage / release box 1101 and the drag parachute 1102 to fly out of the storage tube. The aerodynamic drag jointly generated by the storage / release box 1101 and the drag parachute 1102 is backward, and the propulsion force of each traction bomb is on a virtual ray formed from the center of the resistance source to the center of gravity of each traction bomb. The resulting force makes the entire capture net 9 fully unfolded like an inverted pyramid shape, and accelerates forward until the fuel is consumed, and it maintains inertial flight and then lands.
[0030] A rocket group flight control method for a rocket-powered net-catching launcher, the operation steps are as follows: Step 1: After the operator manually pulls out the safety pin 106, the locking protrusion 104 built into the cylinder cover 101 can move along the inclined groove 302 under the lifting action of the cover ejection spring 102, and the protective cover 1 is ejected and discarded as a whole after being unlocked; Step 2: As the protective cover 1 is discarded, the rocket bracket 2 loses the restraint of the protective cover 1, that is, under the action of the positioning hole and the torsion spring 204 and the catch and the torsion spring 205, the four sets of rocket positioning brackets 201 are opened, and the flame shield 7 is unfolded; Step 3: As the rocket positioning bracket 201 opens, the four torsion springs drive the movable ring 5 to move forcefully toward the fixed ring 3. During this process, the impact projection 502 will impact the power-on safety button 404, so that the battery box and the battery 401 are released from the safety state, and the buzzer 403 and the LED prompt light of the launch button 406 are powered on, and the sound and light prompt is in the ready state; Step 4: If the launch button 406 is pressed, the rocket ignition wire at the rocket ignition wire terminal 402 will pass current, causing the ignition head embedded in the rocket engine to ignite synchronously, starting the rocket engine and driving the rocket traction missile to take off synchronously; Step 5: The rocket traction missile 8 is driven by the thrust of the rocket engine and takes off along the preset launcher track. During takeoff, the high-temperature gas ejected from the tail of the rocket will be blocked by the flame shield 7 so as not to injure the launcher; Step 6: Once the rocket traction bomb 8 is driven forward, the tail resistance stabilization line hole 801 is affected by the resistance of the flight attitude control line 10 from the damping rubber in the storage / release box 11. This resistance stipulates that the engine nozzle of the rocket traction bomb 8 must be pointed to the source of resistance. When the rocket engines of the four traction bombs are all pointed to the same source of resistance, the heads of the four traction bombs will take the direction of the launch tube as the central axis and fly forward radially; Step 7: At the same time, the capture net 9 is connected as an effective load near the center of gravity of the rocket traction projectile 8, that is, the center of gravity load line hole 802, so that the center of gravity is near the center of gravity of the traction projectile. The weight of the capture net 9 and the aerodynamic resistance will only play an inertial slowing effect on the rocket traction projectile 8 in the form of load, and will not affect the angle and posture of the traction projectile; Step 8: When the capture net 9 is fully extended to the maximum, each traction bomb cannot be further extended, and will maintain the maximum extended posture, and fly in the direction of the combined force of each rocket; Step nine: When all the flight attitude control lines 10 are completely released from the storage / release box 1101, they are completely straightened, and together pull the storage / release box 1101 and the drag parachute 1102 to fly out of the storage tube. The aerodynamic resistance jointly generated by the storage / release box 1101 and the drag parachute 1102 is toward the rear, and the propulsion force of each traction bomb is on a virtual ray formed from the center of the resistance source to the center of gravity of each traction bomb. The formed center makes the entire capture net 9 fully unfolded like an inverted pyramid shape, and accelerates forward until the fuel is consumed, maintaining inertial flight and then landing. In this process, the capture net 9 will entangle when encountering a target until the capture is successful, and the launcher can throw away the launcher part at will.
[0031] To sum up, the rocket-powered net launching device and rocket formation flight control method have a long range, which increases the range of the net to more than 200 meters, greatly improving the practical value. The operation is simple, and ordinary people can master the use method after 5 minutes of explanation. The reaction speed is fast. The overall design is that the packaging tube and the launch tube are integrated. It only takes 0.1 second to switch from the storage state to the launch state, and a quick response can be made.
[0032] Moreover, the capture probability is high, and it is capable of driving a large area of the capture net by relying on sufficient power, which greatly improves the capture probability. The cost of the entire system is not high, which is conducive to mass production and can be stored for a long period of time. The launch tube is discarded after launch, which improves the operator's flexibility and high safety. If the capture net encounters a target when it is close to the launcher, due to the large amount of remaining fuel in the rocket, the powerful continuous thrust will pull the powerless target away or deviate from its original route, preventing it from approaching the launcher under the action of inertia, thereby avoiding danger.
[0033] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.
[0034] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A rocket-powered net-catching launch device, comprising a protective cover (1), a rocket support and a flame-blocking cloth support (2), a fixing ring (3), a battery box and a firing button module (4), a movable ring (5), a barrel and a rear cover (6), a flame-blocking cloth (7), a rocket-pulling bomb (8), a net (9), a flight attitude control line (10), and a storage / release box drag parachute module (11), characterized in that: A fixing ring (3) is provided at one end of the barrel and the rear cover (6), a flame-blocking cloth (7) is provided at one end of the barrel and the rear cover (6), a fixing ring (3) is provided at one end of the flame-blocking cloth (7) away from the barrel and the rear cover (6), a protective cover (1) is provided at the other end of the fixing ring (3), a rocket bracket and a flame-blocking cloth bracket (2) connected to the fixing ring (3) are provided on the outside of the barrel and the rear cover (6), a battery box and a firing button module (4) are provided on the outside of the barrel and the rear cover (6), a movable ring (5) is provided on the outside of the barrel and the rear cover (6) and located below the fixing ring (3), a rocket traction bomb (8) is provided on the rocket bracket and the flame-blocking cloth bracket (2), a capture net (9) is provided inside the rocket traction bomb (8), a flight attitude control line (10) is provided on the rocket traction bomb (8), and the other end of the flight attitude control line (10) is connected to a storage / release box drag parachute module (11).
2. A rocket powered net launching device according to claim 1, characterized in that: The protective cover (1) comprises a tube cover (101), a cover-throwing spring (102), a telescopic guide rod (103), a locking pin protrusion (104), a safety pin hole (105) and a safety pin (106); two telescopic guide rods (103) are arranged inside the tube cover (101); the outer sides of the two telescopic guide rods (103) are sleeved with a cover-throwing spring (102); the inner side of the tube cover (101) is provided with a locking protrusion (104); the outer side of the tube cover (101) is provided with a safety pin hole (105); and the safety pin hole (105) is connected to the safety pin hole (106).
3. A rocket powered net launching device according to claim 1, characterized in that: The rocket support and flame-blocking cloth support (2) comprise a rocket positioning support (201), a flame-blocking cloth support (203), a support arm (203), a positioning hole and a torsion spring (204), a latch and a torsion spring (205), and a storage groove (206); the rocket positioning support (201) is connected to the flame-blocking cloth support (202) via the latch and the torsion spring (205); a support arm (203) is provided on a side of the rocket positioning support (201) away from the flame-blocking cloth support (202); a positioning hole and a torsion spring (204) are provided at the bottom of the rocket positioning support (201); and a storage groove (206) is provided on a side of the rocket positioning support (201) away from the support arm (203).
4. A rocket powered net launching device according to claim 1, characterized in that: The fixing ring (3) comprises a fixing ring body (301), an inclined groove (302), a safety pin insertion hole (302) and a bracket positioning groove (304); the fixing ring body (301) is provided with an inclined groove (302); and four bracket positioning grooves (304) are provided on the outer side of the fixing ring body (301).
5. A rocket powered net launching device according to claim 1, characterized in that: The battery box and firing button module (4) comprises a battery box and a battery (401), a rocket ignition wire terminal (402), a buzzer (403), a power-on safety button (404), a wiring groove (405), and a firing button (406). Four rocket ignition wire terminals (402) are arranged on the side of the battery box and the battery (401), a buzzer (403) is arranged on the front side of the battery box and the battery (401), a power-on safety button (404) is arranged on the bottom of the battery box and the battery (401), a wiring groove (405) is opened on the battery box and the battery (401), and a firing button (406) is arranged on the bottom of the battery box and the battery (401).
6. A rocket powered net launching device according to claim 1, characterized in that: The movable ring (5) is provided with four positioning grooves (501), the top of the movable ring (5) is provided with a striking protrusion (502), and the movable ring (5) is provided with an electric wire trough channel (503).
7. A rocket powered net launching device according to claim 1, characterized in that: The barrel body and rear cover (6) comprises a barrel body (601), a rear cover (602) and a shoulder strap ring (603); the rear cover (602) is arranged at the bottom of the barrel body (601), and the shoulder strap ring (603) is arranged outside the rear cover (602).
8. A rocket powered net launching device according to claim 1, characterized in that: The rocket traction projectile (8) is provided with a resistance stabilization line hole (801), the rocket traction projectile (8) is provided with a center of gravity load line hole (802), the rocket traction projectile (8) is provided with a launcher positioning piece (803) on the outside, the rocket traction projectile (8) is provided with a rocket engine compartment (805) on the inside, and the top of the rocket traction projectile (8) is provided with a fairing / counterweight compartment (804).
9. A rocket powered net launching device according to claim 1, characterized in that: The wire storage / release box resistance parachute module (11) comprises a wire storage / release box (1101) and a resistance parachute (1102); four wire storage / release box compartments (1103) are arranged inside the wire storage / release box (1101); the bottom of the wire storage / release box (1101) is connected to a wire storage / release box rear cover (1104) via a thread (1106); and a resistance ring and a positioning groove (1105) are arranged on the wire storage / release box rear cover (1104).
10. A rocket formation flight control method for a rocket-powered net-catching launcher, comprising the rocket-powered net-catching launcher according to claims 1-8, characterized in that: The steps are as follows: Step 1: After the operator manually pulls out the safety pin (106), the locking projection (104) built into the cylinder cover (101) can move along the inclined groove (302) under the lifting action of the cover ejection spring (102), and after being released from the lock, the protective cover (1) is ejected and discarded as a whole; Step 2: As the protective cover (1) is discarded, the rocket bracket (2) loses the restraint of the protective cover (1), that is, under the action of the positioning hole and the torsion spring (204) and the catch and the torsion spring (205), the four sets of rocket positioning brackets (201) are opened, and the flame shield (7) is unfolded; Step 3: As the rocket positioning bracket (201) opens, the four torsion springs drive the movable ring (5) to move forcefully in the direction of the fixed ring (3). During this process, the impact protrusion (502) impacts the power-on safety button (404), so that the battery box and the battery (401) are released from the safety state, and the buzzer (403) and the LED prompt light of the launch button (406) are powered on, and the sound and light prompt that the launch state is ready; Step 4: If the launch button (406) is pressed, the rocket ignition wire at the rocket ignition wire terminal (402) will pass current, causing the ignition head embedded in the rocket engine to ignite synchronously, starting the rocket engine and driving the rocket traction missile to take off synchronously; Step 5: The rocket-towed missile (8) is driven by the thrust of the rocket engine and takes off along the preset launcher track. During takeoff, the high-temperature gas ejected from the tail of the rocket will be blocked by the flame shield (7) so as not to injure the launcher; Step 6: Once the rocket traction projectile (8) is driven forward, the tail resistance stabilizing line hole (801) is affected by the resistance of the flight attitude control line (10) from the damping rubber in the storage / release box (11). This resistance stipulates that the engine nozzle of the rocket traction projectile (8) must be pointed to the source of resistance. When the rocket engines of the four traction projectiles are all pointed to the same source of resistance, the heads of the four traction projectiles will take the direction of the launch tube as the central axis and fly forward in a radial shape. Step 7: At the same time, the capture net (9) is connected as an effective load near the center of gravity of the rocket towing projectile (8), that is, at the center of gravity load line hole (802), so that the center of gravity is near the center of gravity of the towing projectile. The weight and aerodynamic resistance of the capture net (9) will only have an inertial slowing effect on the rocket towing projectile (8) in the form of load, and will not affect the angle and posture of the towing projectile; Step 8: When the capture net (9) is fully extended to its maximum, the traction missiles cannot be further extended and will maintain this maximum extended posture, flying in the direction of the combined force of the rockets; Step 9: When all the flight attitude control lines (10) are completely released from the storage / release box (1101), they are completely stretched straight, and together pull the storage / release box (1101) and the drag parachute (1102) to fly out of the storage tube. The aerodynamic drag jointly generated by the storage / release box (1101) and the drag parachute (1102) is toward the rear, and the propulsion force and arrow direction of each traction bomb are on a virtual ray formed from the center of the drag source to the center of gravity of each traction bomb. The formed center makes the entire capture net (9) fully unfold like an inverted pyramid shape, and accelerate forward until the fuel is consumed, and then maintain inertial flight and land. In this process, the capture net (9) will entangle when encountering a target until the capture is successful, and the launcher can throw away the launcher part at will.