Portable cold launching modularized sounding rocket launching system

Abstract

The invention relates to the technical field of rocket cold launching, and particularly discloses a portable cold launching modular sounding rocket launching system which comprises a launching cylinder, a rocket body installed in the launching cylinder, a control assembly and a launching assembly, and the control assembly and the launching assembly are installed on the launching cylinder. The control assembly comprises a mounting frame, a control module is mounted on the mounting frame, the control assembly further comprises an ignition module, a top cover is arranged at the top of the launching cylinder, a connecting rod is mounted at the bottom of the top cover, and the tail end of the connecting rod is mounted on a controller; compressed air or gas generated by chemical reaction is stored through the high-pressure gas tank to replace firer explosives, safe and environment-friendly launching is achieved, open fire and harmful gas are not generated in the launching process, meanwhile, light-weight structures such as engineering plastics and carbon fibers are adopted, and the quick-release design is adopted; therefore, the system can meet all-terrain deployment requirements and support multi-scene operation.

Description

Technical Field

[0001] The present application belongs to the field of rocket cold launch technology, and specifically relates to a portable cold launch modular sounding rocket launch system. Background Art

[0002] Sounding rockets are used for environmental exploration, scientific research, and technological testing in near-Earth space. They are a common tool for studying the stratosphere and ionosphere, as well as for transitioning through Earth's atmosphere into outer space. Sounding rockets typically consist of a payload, a rocket engine, a body structure, and a stabilization system.

[0003] Its payload carries various devices tailored to the specific exploration objectives, such as sensors for measuring atmospheric temperature, pressure, density, and composition, as well as instruments for ionospheric exploration. As a key tool for atmospheric and near-space exploration, sounding rockets play an irreplaceable role in meteorological data collection, space environment research, and emergency communications relay.

[0004] However, traditional sounding rocket launch systems generally rely on thermal launch technology. The open flames and harmful gases generated during the launch process place strict demands on the launch platform and operating environment. In addition, traditional thermal launch systems are bulky and have long deployment cycles, making them difficult to adapt to remote areas or emergency mission scenarios. Summary of the Invention

[0005] The purpose of this application is to provide a portable cold-launch modular sounding rocket launching system to solve the problems raised in the above-mentioned background technology.

[0006] To achieve the above objectives, this application provides the following technical solutions:

[0007] A portable cold-launch modular sounding rocket launch system comprising:

[0008] A launch tube and a rocket body mounted inside the launch tube, as well as a control assembly and a launch assembly mounted on the launch tube;

[0009] The control assembly includes a mounting frame, which is fixed on a portable launch frame. A control module is installed on the mounting frame. The control assembly also includes an ignition module. A top cover is provided on the top of the launch tube, a connecting rod is installed at the bottom of the top cover, and the end of the connecting rod is installed on the controller.

[0010] Preferably, the launching assembly includes a high-pressure gas cylinder, a regulating valve is installed on the top of the high-pressure gas cylinder, and a second solenoid valve is installed on the top of the regulating valve.

[0011] Preferably, the launch assembly also includes a constant temperature heater, a storage box 1 is installed on the top of the constant temperature heater, a rotary valve is installed on the top of the storage box 1, a storage box 2 is installed on the top of the rotary valve, a pressure gauge is installed on one side of the storage box 2, a sealing cover is installed on the top of the storage box 2, and a solenoid valve 1 is installed on the top of the sealing cover.

[0012] Preferably, a portable launching stand is installed at the bottom of the launching tube, and a battery pack is installed on the mounting stand.

[0013] Preferably, the first storage box is filled with an oxidant, and the second storage box is filled with an organic acid.

[0014] Preferably, the interior of the rocket body is provided with a fairing, an aerial camera, a parachute opening device, an avionics sounding compartment, a cargo compartment, an engine and a tail section.

[0015] Preferably, S1: select a compressed air carrier and charge; calculate the thrust required to push the rocket body out of the launch tube (pushing 0.5 meters away) based on the launch mass, and select an appropriate high-pressure air storage device;

[0016] S2: Select the appropriate module to be carried by the rocket body: Select the corresponding module according to the mission requirements and install the module into the rocket body;

[0017] S3: Launching device installation: Install the portable launcher at the bottom of the launch tube, then place the rocket body and high-pressure gas storage device into the launch tube, and finally install the portable launcher and launch tube;

[0018] S4: Launch the rocket body; the launch assembly is controlled by the control assembly, and compressed air or gas produced by chemical reaction is used to push the rocket body inside the launch tube. After being pushed out, the rocket body starts and the cold launch of the rocket body is completed.

[0019] Compared with the prior art, the present invention has the following advantages:

[0020] (1) Compressed air or gas generated by chemical reactions is stored in high-pressure gas tanks to replace pyrotechnic explosives, achieving safe and environmentally friendly launches. No open flames or harmful gases are generated during the launch process. At the same time, the use of lightweight structures such as engineering plastics and carbon fiber and quick-disassembly designs enables the system to meet all-terrain deployment requirements and support multi-scenario operations.

[0021] (2) The system is endowed with powerful multi-scenario operational capabilities through the integration of a modular mission cabin. The mission cabin adopts a standardized interface design and can be quickly replaced according to different operational requirements. For example, it can be equipped with communication equipment for signal relay, equipped with detection instruments for environmental monitoring, and loaded with fire extinguishing equipment for firefighting tasks. The modular design not only improves the versatility and scalability of the system, but also reduces maintenance costs and difficulty. Users can flexibly configure the mission cabin according to actual needs, realizing multiple uses of one machine. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A perspective view of the launch tube for this application;

[0023] Figure 2 A three-dimensional diagram of the battery pack of this application;

[0024] Figure 3 A perspective view of the controller of this application;

[0025] Figure 4 A perspective view of the high-pressure gas storage cylinder for this application;

[0026] Figure 5 A perspective view of the constant temperature heater of this application;

[0027] Figure 6 A three-dimensional diagram of the rocket body for this application;

[0028] Figure 7 for Figure 6 A three-dimensional view of the interior of the rocket body;

[0029] In the figure: 1. Launch tube; 2. Portable launch rack; 3. Mounting rack; 4. Control module; 5. Ignition module; 6. Top cover; 7. Battery pack; 8. Controller; 9. Connecting rod; 10. High-pressure gas cylinder; 11. Regulating valve; 12. Constant temperature heater; 13. Storage box one; 14. Rotary valve; 15. Storage box two; 16. Pressure gauge; 17. Sealing cover; 18. Solenoid valve one; 19. Rocket body; 20. Fairing; 21. Aerial camera; 22. Parachute opening device; 23. Avionics sounding compartment; 24. Cargo compartment; 25. Engine; 26. Tail section; 27. Solenoid valve two. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0031] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0032] Example 1:

[0033] See also Figure 1 As shown, a portable cold launch modular sounding rocket launch system includes:

[0034] A launch tube 1 and a rocket body 19 mounted inside the launch tube 1, as well as a control assembly and a launch assembly mounted on the launch tube 1;

[0035] As can be seen from the above, when in use, the rocket body 19 is placed inside the launch tube 1, and the launch assembly is controlled by the control assembly to operate, so that the rocket body 19 is pushed out of the launch tube 1 by a cold launch method.

[0036] Specifically, regarding the above-mentioned launch components, refer to Figure 1-3 As shown, the control assembly includes a mounting frame 3, which is fixed to a portable launcher 2. A control module 4 is mounted on the mounting frame 3. The control assembly also includes an ignition module 5. A top cover 6 is provided on the top of the launch tube 1. A connecting rod 9 is installed at the bottom of the top cover 6. The end of the connecting rod 9 is mounted on a controller 8.

[0037] As can be seen from the above, during launch, the control module 4 and the ignition module 5 control the operation of the device, so that the controller 8 drives the connecting rod 9 to open the top cover 6. At this time, the launch assembly is running, and the rocket body 19 is pushed out of the launch tube 1 through the launch assembly.

[0038] Preferably, a portable launching frame 2 is installed at the bottom of the launching tube 1, and a battery pack 7 is installed on the mounting frame 3;

[0039] As can be seen from the above, the launch tube 1 is made of engineering plastics and aviation duralumin materials, the tube weight is ≤2kg, the temperature resistance range is -50℃ to 200℃, and the thrust resistance is up to 1.2GPa; the portable launcher 2 supports 25° slope leveling, and the wind resistance level is improved to level 6; the lightweight structure and quick-disassembly design of the launch tube 1 and the portable launcher 2 meet the requirements of all-terrain deployment; the battery pack 7 provides power for the operation of the device.

[0040] Specifically, regarding the above-mentioned launch components, refer to Figure 4 As shown, the launch assembly includes a high-pressure gas cylinder 10, a regulating valve 11 is installed on the top of the high-pressure gas cylinder 10, and a solenoid valve 27 is installed on the top of the regulating valve 11;

[0041] As can be seen from the above, the pressure of the gas output from the high-pressure gas cylinder 10 is controlled by the regulating valve 11, and the subsequent solenoid valve 27 is opened, so that the high-pressure gas inside the high-pressure gas cylinder 10 pushes the rocket body 19 out of the launch tube 1.

[0042] Preferably, the rocket body 19 is provided with a fairing 20, an aerial camera 21, a parachute opening device 22, an avionics sounding compartment 23, a cargo compartment 24, an engine 25 and a tail section 26;

[0043] As can be seen from the above, the fairing 20 and the tail section 26 facilitate the flight stability and payload safety of the rocket, the parachute device 22 facilitates the subsequent recovery of the rocket body 19, and the avionics sounding compartment 23 and the cargo compartment 24 facilitate the carrying of the fire extinguishing module (CO2 gas cylinder + trace starting medicine), the weather monitoring module (micro weather station + laser dust monitor), the artificial rainfall module (silver iodide sowing device + temperature and humidity sensor), the hail prevention module (air explosion device + radar hail detector) and the lighting module, thereby meeting different mission requirements;

[0044] Example 2:

[0045] refer to Figure 5 As shown, regarding the above-mentioned launch assembly, the launch assembly also includes a constant temperature heater 12, a storage box 13 is installed on the top of the constant temperature heater 12, a rotary valve 14 is installed on the top of the storage box 13, a storage box 2 15 is installed on the top of the rotary valve 14, a pressure gauge 16 is installed on one side of the storage box 2 15, a sealing cover 17 is installed on the top of the storage box 2 15, and a solenoid valve 18 is installed on the top of the sealing cover 17;

[0046] As can be seen from the above, during launch, the rotary valve 14 is controlled to open, so that the chemical reagents in the storage box 13 and the storage box 2 15 react with each other, thereby generating a large amount of gas. At this time, the thrust inside the device is detected by the pressure gauge 16, and finally the solenoid valve 18 is used to control the discharge of the generated gas, so that the generated gas is pushed out of the rocket body 19 inside the launch tube 1; the above components can be replaced with the high-pressure gas cylinder 10 and the regulating valve 11 in Example 1, and the replacement is calculated according to the mass of the module carried during launch.

[0047] Preferably, the storage box 1 13 is filled with an oxidant, and the storage box 2 15 is filled with an organic acid;

[0048] As can be seen from the above, a chemical reaction occurs between the oxidant and the organic acid in the device, thereby generating gas to propel the rocket body 19 for cold launch.

[0049] Example 3:

[0050] refer to Figure 1-Figure 7 As shown, a portable cold launch modular sounding rocket launch system includes the following steps:

[0051] S1: Select the compressed air carrier and charge; calculate the thrust required to push the rocket body 19 out of the launch tube 1 (pushing 0.5 meters) based on the launch mass, and select an appropriate high-pressure gas storage device (the high-pressure gas storage device is the high-pressure gas cylinder 10 in Example 1 and the gas reaction device in Example 2, and the two can be replaced in actual use);

[0052] S2: Select appropriate modules to be carried by the rocket body 19: Select corresponding modules to be carried according to the mission requirements and install the modules into the rocket body 19 (refer to the description of the modules in the second embodiment, such as the fire extinguishing module, weather monitoring module, artificial rainfall module, hail prevention module and lighting module);

[0053] S3: Setting up the launch device; install the portable launcher 2 on the bottom of the launch tube 1, then place the rocket body and the high-pressure gas storage device into the launch tube 1, and finally set up the portable launcher 2 and the launch tube 1;

[0054] S4: Launch the rocket body 19; control the launch assembly through the control assembly, use compressed air or gas produced by chemical reaction to push the rocket body 19 inside the launch tube 1, and after being pushed out, the rocket body 19 starts, completing the cold launch of the rocket body 19.

[0055] The following is the launch test data of Example 3 of a portable cold-launch modular sounding rocket launch system of this application:

[0056]

[0057] 1. Wind environment test: The launch was completed under wind conditions of 35-40 km / h, the system was deployed within 3 minutes, and the rocket accurately launched the sounding air quality detection avionics module to the target altitude and returned.

[0058] 2. Cold environment test: Under -25℃ conditions, the module startup time is less than 10s.

[0059] Although the embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A portable cold-launch modular sounding rocket launch system, characterized in that: include: A launch tube (1), a rocket body (19) installed inside the launch tube (1), and a control component and a launch component installed on the launch tube (1); The control assembly comprises a mounting frame (3), the mounting frame (3) being fixed on a portable launch frame (2), a control module (4) being mounted on the mounting frame (3), and an ignition module (5). The top of the launch tube (1) is provided with a top cover (6), a connecting rod (9) being mounted on the bottom of the top cover (6), and the end of the connecting rod (9) being mounted on a controller (8).

2. A portable cold-launch modular sounding rocket launch system according to claim 1, characterized in that: The launching assembly comprises a high-pressure gas cylinder (10), a regulating valve (11) is installed on the top of the high-pressure gas cylinder (10), and a second solenoid valve (27) is installed on the top of the regulating valve (11).

3. The portable cold-launch modular sounding rocket launch system according to claim 1, characterized in that: The launch assembly also includes a constant temperature heater (12), a storage box (13) is installed on the top of the constant temperature heater (12), a rotary valve (14) is installed on the top of the storage box (13), a storage box (15) is installed on the top of the rotary valve (14), a pressure gauge (16) is installed on one side of the storage box (15), a sealing cover (17) is installed on the top of the storage box (15), and a solenoid valve (18) is installed on the top of the sealing cover (17).

4. The portable cold-launch modular sounding rocket launch system according to claim 1, characterized in that: A portable launching frame (2) is installed at the bottom of the launching tube (1), and a battery pack (7) is installed on the mounting frame (3).

5. The portable cold-launch modular sounding rocket launch system according to claim 3, characterized in that: The storage box 1 (13) is filled with an oxidant, and the storage box 2 (15) is filled with an organic acid.

6. The portable cold-launch modular sounding rocket launch system according to claim 1, characterized in that: The rocket body (19) is internally provided with a fairing (20), an aerial camera (21), a parachute opening device (22), an avionics sounding compartment (23), a cargo compartment (24), an engine (25) and a tail section (26).

7. The portable cold-launch modular sounding rocket launch system according to claim 1, characterized in that: The following steps are involved: S1: Select the compressed air carrier and the amount of compressed air; calculate the thrust required to push the rocket body (19) out of the launch tube (1) (pushing away 0.5 meters) according to the launch mass, and select an appropriate high-pressure gas storage device; S2: Select a suitable module for the rocket body (19): select a corresponding module according to the mission requirements, and install the module into the rocket body (19); S3: Setting up the launch device; installing the portable launch frame (2) at the bottom of the launch tube (1), placing the rocket body and the high-pressure gas storage device into the launch tube (1), and finally setting up the portable launch frame (2) and the launch tube (1); S4: Launching the rocket body (19); controlling the launch assembly to operate through the control assembly, using compressed air or gas produced by a chemical reaction to push out the rocket body (19) inside the launch tube (1), after which the rocket body (19) is started, completing the cold launch of the rocket body (19).

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