Launching assembly and parachute launching rocket device

Abstract

The utility model discloses a launch subassembly and parachute launch rocket device relates to aircraft recovery technical field, including shell and fuel, be equipped with combustion chamber in the shell, fuel includes first grain and second grain, the first grain is equipped with through first combustion hole, the second grain is located in the first combustion hole, and the combustion chamber is equipped with through second combustion hole. The second grain is provided with a through second combustion hole, and the hole wall of the second combustion hole and the hole wall of the first combustion hole are both coated with ignition layers. The hole wall of a first combustion hole formed in the first grain and the hole wall of a second combustion hole formed in the second grain are both coated with ignition layers, and the second grain is located in the first combustion hole. Compared with an existing parachute shooting rocket device which is only provided with one grain, the combustion area of the ignition layer is enlarged to a great extent, after the ignition layer is ignited, the first grain and the second grain can be combusted at the same time, the combustion efficiency is high, the second grain is added, the content of comburent is increased, and the combustion efficiency is improved. And more sufficient power can be provided for the parachute shooting rocket device during combustion.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft recovery, in particular to a launching component and a parachute rocket device. Background Art

[0002] With the continuous development of my country's aviation technology, various aircraft are being used more and more frequently and in a wider range. In the application process of aircraft, aircraft recovery is a very important process and a very complicated process, which requires very strict control and operation, otherwise it will cause serious damage to people or objects in the aircraft. Therefore, more and more research is being conducted on aircraft recovery technology.

[0003] The prior art with announcement number CN 207809795U discloses a parachute rocket device for rapid parachute opening, which includes a rocket body assembly, a nozzle assembly and a tail connection assembly. The nozzle assembly is arranged at the head of the rocket device and the nozzle is inverted, and a connecting belt is arranged between the rocket device and the top of the parachute. The main powder column in the shell of the rocket device burns to generate high-temperature and high-pressure combustion gas to drive the rocket to move, and then the parachute is quickly pulled out of the parachute cabin through the connecting belt to achieve rapid opening of the parachute.

[0004] However, the existing parachute rocket device still has defects. For example, the combustion chamber has only one propellant column, which has only one hollow hole, and the combustion area is not large enough. After the ignition box is ignited, the propellant column cannot burn quickly, resulting in insufficient initial power for opening the parachute of the parachute rocket device. Utility Model Content

[0005] The purpose of the utility model is to overcome the above-mentioned technical deficiencies and to propose a launching assembly and a parachute rocket device, so as to solve the technical problem that the combustion chamber of the parachute rocket device in the prior art has only one propellant column, the propellant column has only one hollow hole, the combustion area is not large enough, and after the ignition cartridge is ignited, the propellant column cannot burn quickly, resulting in insufficient initial power for opening the parachute of the parachute rocket device.

[0006] In order to achieve the above technical purpose, the utility model adopts the following technical solutions:

[0007] In a first aspect, the utility model provides a launching assembly for guiding a parachute-shooting rocket device to open a parachute, the launching assembly comprising:

[0008] a casing having a combustion chamber therein; and

[0009] Fuel is arranged in the combustion chamber, and the fuel includes a first charge and a second charge. The first charge is provided with a first combustion hole extending therethrough, the second charge is located in the first combustion hole, the second charge is provided with a second combustion hole extending therethrough, and the hole walls of the second combustion hole and the hole walls of the first combustion hole are both coated with an ignition layer.

[0010] In some embodiments, the first charge and the second charge are both cylindrical, and the second charge is spaced apart from the hole wall of the first combustion hole.

[0011] In some embodiments, a plurality of third combustion holes are formed on the circumference of the first charge around the first combustion hole, and the plurality of third combustion holes all penetrate the first charge.

[0012] In some embodiments, a plurality of fourth combustion holes are formed on the circumference of the second combustion hole around the second combustion hole, and the plurality of fourth combustion holes all penetrate the second combustion hole.

[0013] In some embodiments, the hole wall of the third combustion hole and the hole wall of the fourth combustion hole are both coated with an ignition layer.

[0014] In some embodiments, the fuel further includes a third charge, the third charge is located in the second combustion hole, and the third charge is spaced apart from a hole wall of the second combustion hole.

[0015] In some embodiments, the launching assembly further includes an ignition box and an electric squib, wherein the ignition box is disposed at the bottom of the combustion chamber, the ignition box is connected to the first charge column and the second charge column, one end of the electric squib is connected to the ignition box, the electric squib is used to connect to a control device, and can ignite the ignition box under the control of the control device.

[0016] In some embodiments, the launch assembly further includes a plurality of injection members, which are evenly arranged around the circumference of the shell, and each of the injection members is connected to the combustion chamber and external air.

[0017] In some embodiments, the launching assembly further comprises a rotating ring, which is rotatably connected to the shell and can be switched between a folded state and an extended state. The rotating ring is used to connect to a transfer strap of the parachute and can be rotated to an extended state under the pulling of the transfer strap.

[0018] In a second aspect, the utility model also provides a parachute shooting rocket device, comprising a parachute shooting tube and the above-mentioned launching assembly, wherein the shell is slidably connected to the parachute shooting tube and can slide away from the parachute shooting tube when the fuel is burning.

[0019] Compared with the prior art, the launch assembly provided by the utility model includes a first charge and a second charge at the same time. The wall of the first combustion hole opened by the first charge and the wall of the second combustion hole opened by the second charge are both coated with an ignition layer, and the second charge is located in the first combustion hole. Compared with the existing parachute rocket device that only has one charge, the present application greatly expands the combustion area of ​​the ignition layer. After the ignition layer is ignited, the first charge and the second charge can burn at the same time, with high combustion efficiency, and guide the parachute to open quickly. In addition, the second charge is added, so that the content of the combustible material is increased, which can provide more sufficient power for the parachute rocket device during combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic structural diagram of the rotating ring of the launch assembly provided by an embodiment of the utility model in a folded state;

[0021] Figure 2 It is a schematic diagram of the structure of the rotating ring of the launch assembly provided by the embodiment of the utility model in the extended state;

[0022] Figure 3 This is a schematic diagram of disassembling a launch assembly provided by an embodiment of the utility model;

[0023] Figure 4 It is a structural schematic diagram of an embodiment of the fuel provided by the embodiment of the utility model;

[0024] Figure 5 It is a structural schematic diagram showing another embodiment of the fuel provided by the embodiment of the utility model;

[0025] Figure 6 It is a structural schematic diagram showing another embodiment of the fuel provided by the embodiment of the utility model;

[0026] Figure 7 It is a structural schematic diagram of an umbrella shooting tube provided by an embodiment of the utility model. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0028] In order to solve the technical problem that the combustion chamber of the parachute rocket device in the prior art has only one charge column, the charge column has only one hollow hole, the combustion area is not large enough, and after the ignition cartridge is ignited, the charge column cannot burn quickly, resulting in insufficient initial power for opening the parachute of the parachute rocket device, the utility model provides a launch assembly that can realize the simultaneous combustion of multiple charge columns, has high combustion efficiency, and guides the parachute to open quickly. In addition, the newly added second charge column increases the content of the combustion material, which can provide more sufficient power for the parachute rocket device during combustion.

[0029] It should be noted that the launching assembly described in the present invention is used for but not limited to parachute rocket devices, etc. For the convenience of explanation, in the present invention, only the launching assembly applied to a parachute rocket device is used as an example for explanation, and the principle of applying the launching assembly to other types of equipment is essentially the same as the principle applied to the parachute rocket device, and will not be described in detail here.

[0030] See also Figures 1 to 3 , Figure 1 The schematic diagram of the structure of the launch assembly 100 in one embodiment of the utility model is shown. The launch assembly 100 includes a shell 1 and a fuel 2. A combustion chamber 11 is provided in the shell 1. The fuel 2 is provided in the combustion chamber 11. When the fuel 2 is burned, it can drive the combustion chamber 11 to form a high temperature and high pressure, providing a power source for the launch assembly 100 to be launched. The fuel 2 includes a first charge 21 and a second charge 22. The first charge 21 is provided with a first combustion hole 211 extending therethrough. The second charge 22 is located in the first combustion hole 211. The second charge 22 is provided with a second combustion hole 221 extending therethrough. The hole wall of the second combustion hole 221 and the hole wall of the first combustion hole 211 are both coated with an ignition layer. The ignition layer can be, for example, a flammable material such as gunpowder, which is easy to burn to assist the combustion of the first charge 21 and the second charge 22. The charge can be a mixture formed by meshing a plurality of raw materials under high temperature and high pressure, and then the ignition layer is coated on its surface.

[0031] In one of the embodiments, the outer wall of the first charge 21 and the outer wall of the second charge 22 may also be coated with an ignition layer to increase the combustion area of ​​the charge and improve the combustion efficiency.

[0032] In one embodiment, see Figure 4 The first medicine column 21 and the second medicine column 22 are both cylindrical, and the cylindrical medicine column can burn evenly and can also adapt to the shape of the cylindrical combustion chamber 11, which is easy to install. In addition, the second medicine column 22 is spaced apart from the hole wall of the first combustion hole 211, so that a gap is left between the second medicine column 22 and the first medicine column 21, which is conducive to increasing the contact area with air and making the medicine column burn more fully. In other embodiments, a part of the second medicine column 22 can also be attached to the hole wall of the first combustion hole 211, so that the first medicine column 21 and the second medicine column 22 can be connected together, so as to facilitate quick installation.

[0033] In one embodiment, see Figure 5 The first charge 21 is provided with a plurality of third combustion holes 212 around the first combustion hole 211, and the plurality of third combustion holes 212 all penetrate the first charge 21, so that the contact area between each third combustion hole 212 and the air is maximized, and the first charge 21 burns more fully and with higher combustion efficiency. Compared with the previous embodiment, the third combustion hole 212 is newly added in this embodiment, which further increases the contact area between the first charge 21 and the air, has higher combustion efficiency, and improves the parachute opening efficiency of the parachute rocket device.

[0034] In one embodiment, see Figure 6 The second charge 22 is provided with a plurality of fourth combustion holes 222 around the second combustion hole 221, and the plurality of fourth combustion holes 222 all penetrate the second charge 22, so that the contact area between each fourth combustion hole 222 and the air is maximized, and the second charge 22 burns more fully and with higher combustion efficiency. Compared with the previous embodiment, the fourth combustion hole 222 is newly added in this embodiment, which further increases the contact area between the second charge 22 and the air, has higher combustion efficiency, and improves the parachute opening efficiency of the parachute rocket device.

[0035] In one embodiment, the hole wall of the third combustion hole 212 and the hole wall of the fourth combustion hole 222 are coated with an ignition layer, which is a flammable material that will burn when encountering an open flame, such as gunpowder. When the first charge 21 and the second charge 22 are ignited, the ignition layers of the hole wall of the third combustion hole 212 and the hole wall of the fourth combustion hole 222 can burn, which is conducive to improving the combustion efficiency of the first charge 21 and the second charge 22, thereby improving the parachute opening efficiency of the parachute rocket device.

[0036] In one embodiment, the fuel 2 further includes a third charge (not shown in the figure), the third charge is located in the second combustion hole 221, and the third charge is spaced from the hole wall of the second combustion hole 221, which is conducive to increasing the air area between the third charge and the hole wall of the second combustion hole 221, and improving the combustion efficiency. In this embodiment, by adding the third charge, not only the content of the charge is increased, but also the combustion area is increased, so that the fuel 2 can further improve the combustion efficiency and further improve the parachute opening efficiency of the parachute rocket device. It can be understood that in other embodiments, the third charge can also be provided with a through combustion hole, and another charge can be arranged in the combustion hole, and so on. The number of charge is not limited, and can be arranged layer by layer according to actual needs.

[0037] In one embodiment, see Figure 3The launching assembly 100 further includes an ignition cartridge 3 and an electric squib (not shown in the figure). The ignition cartridge 3 is arranged at the bottom of the combustion chamber 11. The ignition cartridge 3 is connected to the first charge 21 and the second charge 22. One end of the electric squib is connected to the ignition cartridge 3. The electric squib is used to connect to a control device (not shown in the figure) and can ignite the ignition cartridge 3 under the control of the control device. The control device can be, for example, a wireless remote controller. The operator can operate the wireless remote controller to control the electric squib to ignite the ignition cartridge 3, so that the ignition cartridge 3 ignites the first charge 21 and the second charge 22. When the first charge 21 and the second charge 22 are burned, the combustion chamber 11 is driven to generate high temperature and high pressure, providing a power source for the launch of the parachute rocket device.

[0038] In one embodiment, see Figure 2 The launch assembly 100 also includes a plurality of injection members 4, which are evenly arranged around the circumference of the shell 1. Each injection member 4 is connected to the combustion chamber 11 and the external air. The high temperature and high pressure generated by the combustion of the fuel 2 in the combustion chamber 11 are ejected through the injection members 4, providing a power source for the launch assembly 100 to be launched, thereby guiding the parachute to open.

[0039] In one embodiment, see Figure 3 The shell 1 includes a middle shell 12, a top shell 13, a bottom shell 14, a gasket 15, a limit plate 16, and a clamp 17, wherein the top shell 13 and the bottom shell 14 are connected to the top and the bottom of the middle shell 12 respectively, and the inside of the middle shell 12 is hollow to form the above-mentioned combustion chamber 11. The gasket 15 is arranged on the top of the fuel 2, and the side of the gasket 15 facing away from the fuel 2 abuts against the limit plate 16, and the bottom of the fuel 2 abuts against the ignition cartridge 3. Under the clamping of the ignition cartridge 3 and the gasket 15, the fuel 2 is fixed so that the fuel 2 can abut against the ignition cartridge 3, and the ignition cartridge 3 can stably ignite the fuel 2. The clamp 17 is sleeved on the outer wall of the middle shell 12, and the clamp 17 is provided with a positioning protrusion 171, and the positioning protrusion 171 is used to play a guiding role so that the launch assembly 100 can slide along a fixed direction.

[0040] Second, see Figure 1 and Figure 7 The utility model also provides a parachute rocket device, including a parachute tube 101 and the above-mentioned launching assembly 100. The shell 1 of the launching assembly 100 is slidably connected to the parachute tube 101 and can slide away from the parachute tube 101 when the fuel 2 is burned, so as to guide the parachute to open and provide auxiliary effect for the landing of the aircraft.

[0041] In one embodiment, see Figure 2The launching assembly 100 further includes a rotating ring 5, which is rotatably connected to the housing 1 and can switch between a folded state and an extended state. The rotating ring 5 is used to connect the parachute adapter belt and can be rotated to the extended state ( Figure 2 After the parachute adapter belt is connected to the rotating ring 5, it is thrown upward from the exit of the parachute shooting tube 101 along the gap between the parachute shooting tube 101 and the shell 1, and connected to the parachute in the parachute cabin of the aircraft. The rotating ring 5 located inside the parachute shooting tube 101 is in a folded state ( Figure 1 As shown in the figure, when the aircraft ignites the fuel 2 to drive the launching assembly 100 to rise and separate from the parachute shooting tube 101, the rotating ring 5 pulls the parachute to separate from the parachute cabin of the aircraft. Under the air resistance of the parachute, the parachute pulls the rotating ring 5 through the adapter belt, driving the rotating ring 5 to rotate to the extended state. Therefore, before the launching assembly 100 is launched from the parachute shooting tube 101, the rotating ring 5 is in a folded state, which can save the length space inside the parachute shooting tube 101, which is conducive to reducing the length of the parachute shooting tube 101 and saving costs.

[0042] A launching chamber 6 is provided in the shooting tube 101, and a positioning groove 61 is provided on the inner wall of the launching chamber 6. The positioning groove 61 is used for sliding connection with the positioning protrusion 171 of the launching assembly 100, so that the launching assembly 100 can slide in and out of the launching chamber 6. When the fuel 2 burns, the launching assembly 100 can stably slide out of the launching chamber 6 along the length direction of the positioning groove 61.

[0043] The outer wall of the parachute shooting tube 101 is provided with a mounting bracket 7, and the mounting bracket 7 can be connected to the aircraft by screws or welding. After the launching assembly 100 is launched, the parachute shooting tube 101 is still fixed on the aircraft.

[0044] In order to better understand the present invention, the following Figures 1 to 7 The technical solution of the utility model is described in detail:

[0045] Before use, the parachute rocket device needs to be installed first, one end of the parachute adapter belt is connected to the rotating ring 5, and the rotating ring 5 is rotated to a folded state, the launching assembly 100 is slid into the launching cavity 6 of the parachute shooting tube 101, the excess part of the parachute adapter belt is thrown out from the gap between the parachute shooting tube 101 and the shell 1, and the other end of the parachute adapter belt is connected to the parachute of the aircraft parachute cabin.

[0046] When the aircraft needs to land after completing the mission, the operator uses a wireless remote control to control the electric squib to ignite the ignition box 3. The ignition box 3 drives the fuel 2 to burn when burning. Since the fuel 2 also contains the first charge 21 and the second charge 22, the power provided by the combustion is greater and the combustion efficiency is higher. After the jets are ejected through multiple injection parts 4, greater power can be provided for the launch assembly 100. The launch assembly 100 guides the parachute to launch and open, assisting the aircraft to land.

[0047] The specific implementation methods of the utility model described above do not constitute a limitation on the protection scope of the utility model. Any other corresponding changes and modifications made according to the technical concept of the utility model should be included in the protection scope of the claims of the utility model.

Claims

1. A launching assembly, characterized in that: The transmitting assembly comprises: a casing having a combustion chamber therein; and Fuel is arranged in the combustion chamber, and the fuel includes a first charge and a second charge. The first charge is provided with a first combustion hole extending therethrough, the second charge is located in the first combustion hole, the second charge is provided with a second combustion hole extending therethrough, and the hole walls of the second combustion hole and the hole walls of the first combustion hole are both coated with an ignition layer.

2. The launch assembly according to claim 1, characterized in that: The first charge and the second charge are both cylindrical, and the second charge is spaced apart from the hole wall of the first combustion hole.

3. The launch assembly according to claim 1, characterized in that: A plurality of third combustion holes are formed on the circumference of the first charge around the first combustion hole, and the plurality of third combustion holes all penetrate the first charge.

4. The launch assembly according to claim 3, characterized in that: The second charge has a plurality of fourth combustion holes formed around the second combustion hole, and the plurality of fourth combustion holes all penetrate the second charge.

5. The launch assembly according to claim 4, characterized in that: The hole wall of the third combustion hole and the hole wall of the fourth combustion hole are both coated with an ignition layer.

6. The launch assembly according to claim 1, characterized in that: The fuel further includes a third charge, which is located in the second combustion hole and spaced apart from a hole wall of the second combustion hole.

7. The launch assembly according to claim 1, characterized in that: The launching assembly also includes an ignition box and an electric squib. The ignition box is arranged at the bottom of the combustion chamber, the ignition box is connected to the first and second charge columns, one end of the electric squib is connected to the ignition box, the electric squib is used to connect to a control device, and can ignite the ignition box under the control of the control device.

8. The launch assembly according to claim 1, characterized in that: The emission assembly further comprises a plurality of injection members, which are evenly arranged around the circumference of the shell, and each of the injection members is connected to the combustion chamber and external air.

9. The launch assembly according to claim 1, characterized in that: The launching assembly also includes a rotating ring, which is rotatably connected to the shell and can be switched between a folded state and an extended state. The rotating ring is used to connect to a transfer belt of the parachute and can be rotated to an extended state under the pulling of the transfer belt.

10. A parachute rocket device, characterized in that: It comprises an umbrella-shooting tube and a launching assembly as claimed in any one of claims 1 to 9, wherein the shell is slidably connected to the umbrella-shooting tube and can slide away from the umbrella-shooting tube when the fuel is burned.

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