WO2024091197A1 - A launching system - Google Patents

A launching system Download PDF

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Publication number
WO2024091197A1
WO2024091197A1 PCT/TR2022/051760 TR2022051760W WO2024091197A1 WO 2024091197 A1 WO2024091197 A1 WO 2024091197A1 TR 2022051760 W TR2022051760 W TR 2022051760W WO 2024091197 A1 WO2024091197 A1 WO 2024091197A1
Authority
WO
WIPO (PCT)
Prior art keywords
launching
gas
hydrogen gas
plug
combustion
Prior art date
Application number
PCT/TR2022/051760
Other languages
French (fr)
Inventor
Halil BAĞIBAN
Alper GÖRGÜLÜ
Mustafa Mutlu ÇOBAN
Halil İbrahim ÇOBAN
Original Assignee
Gürbağ Elektromekani̇k Savunma Ve Haberleşme Teknoloji̇leri̇ Anoni̇m Şi̇rketi̇
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from TR2022/016375 external-priority patent/TR2022016375A1/en
Application filed by Gürbağ Elektromekani̇k Savunma Ve Haberleşme Teknoloji̇leri̇ Anoni̇m Şi̇rketi̇ filed Critical Gürbağ Elektromekani̇k Savunma Ve Haberleşme Teknoloji̇leri̇ Anoni̇m Şi̇rketi̇
Publication of WO2024091197A1 publication Critical patent/WO2024091197A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers

Definitions

  • the present invention relates to a launching system (1) that uses hydrogen energy instead of fuel energy using propulsion in the launching systems in the military field or other areas where the related technique is required.
  • Pyrotechnics is the science of using substances capable of independently sustaining exothermic chemical reactions so as to produce heat, light, gas, smoke and/or sound. Pyrotechnics meets the ignition, pressure and mechanical impact requirements in subsystems of military munitions, cruise missiles, spacecraft, manned and unmanned aerial vehicles.
  • missile or launch systems One of the areas where pyrotechnics is used is missile or launch systems.
  • One of them is catapult launch.
  • a catapult launch is a device that allows an aircraft to take off from a very limited amount of space, such as the deck of a ship. It is most commonly used on aircraft carriers, but in rare cases it can be mounted on land-based landing fields.
  • the front wheels of the aircraft are connected to the drawbar of the catapult in the operating system of the catapult launch.
  • the weight, derrick, gunpowder, flywheel, air pressure, hydraulic or steam power that will provide thrust from the catapult cylinders is suddenly released and the thrust gained from the same is transferred to the aircraft by the drawbar of the catapult.
  • Pneumatic systems are systems in which motion and power are provided by using compressed air in a controlled manner.
  • a compressor is used so as to compress the gas.
  • the compressed gas can be transferred directly or to a storage tank for later use depending on the mechanism to be used. Once the gas is compressed, it now has potential energy and is ready to be used.
  • Single-acting or double-acting pistons are used so as to use the compressed air.
  • the potential energy transforms into kinetic energy and provides motion during the use of gas.
  • the air sent to the system is transmitted to the piston cylinder mechanism by using directional control valves and motion is provided.
  • Another launch system operates with magnetic launch.
  • the inventive launching system canister uses hydrogen energy instead of the fuel energy that provides the propulsion power.
  • the inventive launching system canister allows use for launching rockets, ammunition and drones, especially in air defense systems and it allows multiple launches according to the need in the military and civilian areas with the use of hydrogen energy.
  • Hydrogen gas with high energy potential is used in the inventive system.
  • a launching system canister using hydrogen energy is not encountered.
  • the aim of the present invention is to realize a launching system canister that enables portable launching systems to be reused.
  • Another aim of the present invention is to realize a launching system canister that provides multiple launching possibilities by integrating the launching system into the vehicle.
  • Another aim of the present invention is to realize a launching system canister that exhibits maximum performance with hydrogen energy.
  • Another aim of the present invention is to realize a launching system canister that provides cost minimization.
  • Another aim of the present invention is to realize a launching system canister that does not require post-launching maintenance and repair and is ready for a new launch in a much shorter time than previous systems.
  • a launching system canister realized to achieve the aim of the present invention is shown in the attached figures, in which;
  • Figure 1 is a perspective view of the launching system canister.
  • Figure 2. is an exploded view of the launching system canister.
  • Figure 3. is a perspective view of the multi-launching system.
  • Figure 4. is a plan view of the multi-launching system.
  • the present invention is a launching system canister (1) that uses hydrogen energy instead of fuel energy using propulsion in the launching systems in the military field, characterized by comprising of the following; connecting the delrin plug (2) to the aluminum plug (3) and using the same for centering, placing the aluminum plug (3) on the shaft (4) and using the same for sealing, placing the shaft (4) on the base of the launching tube (5) and fixing the combustion area, launching the object as a result of pressurizing the hydrogen gas of the launching tube (5), measuring the velocity of the object pushed out of the launcher during launching by means of the proximity sensor (6), triggering the ignition process from the right side so as to burn the hydrogen gas by means of the right spark plug (7), measuring the temperature in the combustion areas by means of the temperature sensor (8), triggering the ignition process from the left side so as to bum the hydrogen gas by means of the left spark plug (9), flange (10) being the base under the launching tube (5), sealing the combustion area and being the part where the hydrogen gas is conveyed into the launching tube
  • the hydrogen gas which is pressurized into the launching tube (5) in the inventive launching system (1), enables ejecting the object placed inside the launcher by means of the piston.
  • the launching process in the inventive launching system (1) is carried out as follows. There is a shaft (4) connected to the flange (10) at the bottom of the launching tube (5). The top of the shaft (4) is closed and compressed with aluminum and delrin plugs (3, 2). The combustion process takes place in this section at the bottom of said launching tube (5). The object to be launched is placed on the delrin plug (2). The amount of hydrogen, oxygen and nitrogen in the gas transmitted to the launching tube (5) via the gas measurement sensor (14) is measured and sent to the combustion area.
  • the pressure created by the combustion of the gas ensures the launching of the object in the launching tube (5).
  • the pressure and the velocity of the object are detected by the pressure and proximity sensors (13, 6) placed in the launching tube (5). After the launching process is performed, a new object can be placed on the piston in the launching tube (5) and multiple launches can be made.
  • the shaft (4) is connected to the launching tube (5) by means of the flange (10) on the base.
  • the top of the shaft (4) is closed with aluminum plug (3) and delrin plug (2).
  • Right spark plug (7), left spark plug (9) and temperature sensor (8) are connected to this section, which is compressed with aluminum plug (3) and delrin plug (2).
  • the proximity sensor (6) is connected to the top of the launching tube (5) so as to detect the speed of the object to be launched.
  • the object to be launched is placed on the delrin plug (2) inside the launching tube (5).
  • the delivery of hydrogen gas is initiated via the gas measurement sensor (14) located under the flange (10) located at the bottom of the launching tube (5).
  • the amount of the delivered gas is measured by means of this gas measurement sensor (14).
  • the valve (12) located at the bottom of the launching system (1) is closed, and the flow of hydrogen gas to the section compressed with the aluminum plug (3) and delrin plug (2) is interrupted.
  • the combustion of hydrogen gas is provided by the right spark plug (7) and the left spark plug (9).
  • the value of the pressure formed before and after combustion is measured by means of the pressure sensor (13).
  • the object is ejected out of the launcher in the launching tube (5) with the thrust of the pressure.
  • the velocity of the launched object is measured by means of the proximity sensor (6).
  • the object to be launched is positioned on the aluminum plug (3) and delrin plug (2) so as to make the same ready to be ejected again.
  • the inventive launching system (1) offers multiple launching possibilities. No harmful waste is generated after launching. There is no need for maintenance and repair after each launching.
  • Launching tubes (5) are placed in single-launch system cavities (15.1) in said multi-launching system (15).
  • multi-launching can be performed using the multi-launching system (15).

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

The present invention relates to a launching system (1) that uses hydrogen energy instead of fuel energy using propulsion in the launching systems in the military 5 field or other areas where the related technique is required.

Description

A LAUNCHING SYSTEM
Field of the Invention
The present invention relates to a launching system (1) that uses hydrogen energy instead of fuel energy using propulsion in the launching systems in the military field or other areas where the related technique is required.
Prior Art
Pyrotechnics is the science of using substances capable of independently sustaining exothermic chemical reactions so as to produce heat, light, gas, smoke and/or sound. Pyrotechnics meets the ignition, pressure and mechanical impact requirements in subsystems of military munitions, cruise missiles, spacecraft, manned and unmanned aerial vehicles. One of the areas where pyrotechnics is used is missile or launch systems. There are different types of launching methods and systems. One of them is catapult launch. A catapult launch is a device that allows an aircraft to take off from a very limited amount of space, such as the deck of a ship. It is most commonly used on aircraft carriers, but in rare cases it can be mounted on land-based landing fields. The front wheels of the aircraft are connected to the drawbar of the catapult in the operating system of the catapult launch. When the aircraft is ready to take off, the weight, derrick, gunpowder, flywheel, air pressure, hydraulic or steam power that will provide thrust from the catapult cylinders is suddenly released and the thrust gained from the same is transferred to the aircraft by the drawbar of the catapult.
Other launching systems are pneumatic systems. Pneumatic systems are systems in which motion and power are provided by using compressed air in a controlled manner. A compressor is used so as to compress the gas. The compressed gas can be transferred directly or to a storage tank for later use depending on the mechanism to be used. Once the gas is compressed, it now has potential energy and is ready to be used. Single-acting or double-acting pistons are used so as to use the compressed air. The potential energy transforms into kinetic energy and provides motion during the use of gas. The air sent to the system is transmitted to the piston cylinder mechanism by using directional control valves and motion is provided. Another launch system operates with magnetic launch.
It creates difficulties such as the fact that our law enforcement officers work with one-shot launch systems in difficult conditions such as off-road, these systems need maintenance-repair activities at the factory level after each launching, existing system generate waste and many disadvantages occur due to these difficulties. In systems in the state of the art, fixed launching systems and portable launching systems are used for launching drones, rockets and similar systems. In particular, portable launching systems require maintenance and repair at the factory level, as they create waste after each launching. This situation causes our military forces to carry the launching system repeatedly or leave it in the field after the launching. Therefore, our forces, which are exposed to difficult conditions, have to spend an extra effort. Furthermore, said launching system may cause extra costs when it has to be left on the field. This situation can cause a negative situation both for our forces and for the state treasury. Launching is carried out with the use of air or different gases in the state of the art.
The inventive launching system canister uses hydrogen energy instead of the fuel energy that provides the propulsion power. The inventive launching system canister allows use for launching rockets, ammunition and drones, especially in air defense systems and it allows multiple launches according to the need in the military and civilian areas with the use of hydrogen energy. Hydrogen gas with high energy potential is used in the inventive system. In the state of the art, there is no explanation regarding the technical features and the technical effects provided by the invention of the present application. In current applications, a launching system canister using hydrogen energy is not encountered.
Aims of the Invention
The aim of the present invention is to realize a launching system canister that enables portable launching systems to be reused.
Another aim of the present invention is to realize a launching system canister that provides multiple launching possibilities by integrating the launching system into the vehicle.
Another aim of the present invention is to realize a launching system canister that exhibits maximum performance with hydrogen energy.
Another aim of the present invention is to realize a launching system canister that provides cost minimization.
Another aim of the present invention is to realize a launching system canister that does not require post-launching maintenance and repair and is ready for a new launch in a much shorter time than previous systems.
Detailed Description of the Invention
A launching system canister realized to achieve the aim of the present invention is shown in the attached figures, in which;
Figure 1. is a perspective view of the launching system canister.
Figure 2. is an exploded view of the launching system canister. Figure 3. is a perspective view of the multi-launching system.
Figure 4. is a plan view of the multi-launching system.
The parts in the figure are enumerated one by one and the parts correspond to these numbers are given in the following.
1. Launching system
2. Delrin plug
3. Aluminum plug
4. Shaft
5. Launching tube
6. Proximity sensor
7. Right spark plug
8. Temperature sensor
9. Left spark plug
10. Flange
11. Reduction
12. Valve
13. Pressure sensor
14. Gas measurement sensor
15. Multi-launching system
15.1. Single-launching system
The present invention is a launching system canister (1) that uses hydrogen energy instead of fuel energy using propulsion in the launching systems in the military field, characterized by comprising of the following; connecting the delrin plug (2) to the aluminum plug (3) and using the same for centering, placing the aluminum plug (3) on the shaft (4) and using the same for sealing, placing the shaft (4) on the base of the launching tube (5) and fixing the combustion area, launching the object as a result of pressurizing the hydrogen gas of the launching tube (5), measuring the velocity of the object pushed out of the launcher during launching by means of the proximity sensor (6), triggering the ignition process from the right side so as to burn the hydrogen gas by means of the right spark plug (7), measuring the temperature in the combustion areas by means of the temperature sensor (8), triggering the ignition process from the left side so as to bum the hydrogen gas by means of the left spark plug (9), flange (10) being the base under the launching tube (5), sealing the combustion area and being the part where the hydrogen gas is conveyed into the launching tube (5), providing the connection of the valve (12) and the flange (10) by means of the reducer (11), valve (12) providing or cutting the flow of hydrogen gas with the openingclosing process and preventing the pressure generated by the combustion of the gas from being transmitted back, pressure sensor (13) ensuring the measurement of the pressure created by the gas sent into the launching tube (5) before and after combustion, gas measurement sensor (14) enabling the hydrogen gas to be delivered to the system and enabling the hydrogen, oxygen and nitrogen amount of the delivered gas to be measured, providing multiple launches by placing a plurality of launching systems (1) on multi-launching systems (15).
The hydrogen gas, which is pressurized into the launching tube (5) in the inventive launching system (1), enables ejecting the object placed inside the launcher by means of the piston. The launching process in the inventive launching system (1) is carried out as follows. There is a shaft (4) connected to the flange (10) at the bottom of the launching tube (5). The top of the shaft (4) is closed and compressed with aluminum and delrin plugs (3, 2). The combustion process takes place in this section at the bottom of said launching tube (5). The object to be launched is placed on the delrin plug (2). The amount of hydrogen, oxygen and nitrogen in the gas transmitted to the launching tube (5) via the gas measurement sensor (14) is measured and sent to the combustion area. The pressure created by the combustion of the gas ensures the launching of the object in the launching tube (5). The pressure and the velocity of the object are detected by the pressure and proximity sensors (13, 6) placed in the launching tube (5). After the launching process is performed, a new object can be placed on the piston in the launching tube (5) and multiple launches can be made.
In an embodiment of the invention, the shaft (4) is connected to the launching tube (5) by means of the flange (10) on the base. The top of the shaft (4) is closed with aluminum plug (3) and delrin plug (2). Right spark plug (7), left spark plug (9) and temperature sensor (8) are connected to this section, which is compressed with aluminum plug (3) and delrin plug (2). The proximity sensor (6) is connected to the top of the launching tube (5) so as to detect the speed of the object to be launched. The object to be launched is placed on the delrin plug (2) inside the launching tube (5). The delivery of hydrogen gas is initiated via the gas measurement sensor (14) located under the flange (10) located at the bottom of the launching tube (5). The amount of the delivered gas is measured by means of this gas measurement sensor (14). After the gas measurement sensor (14) detects it, the valve (12) located at the bottom of the launching system (1) is closed, and the flow of hydrogen gas to the section compressed with the aluminum plug (3) and delrin plug (2) is interrupted. The combustion of hydrogen gas is provided by the right spark plug (7) and the left spark plug (9). The value of the pressure formed before and after combustion is measured by means of the pressure sensor (13). The object is ejected out of the launcher in the launching tube (5) with the thrust of the pressure. The velocity of the launched object is measured by means of the proximity sensor (6). The object to be launched is positioned on the aluminum plug (3) and delrin plug (2) so as to make the same ready to be ejected again. Therefore, the inventive launching system (1) offers multiple launching possibilities. No harmful waste is generated after launching. There is no need for maintenance and repair after each launching. In one embodiment of the present invention, there is a multi-launching system (15). Launching tubes (5) are placed in single-launch system cavities (15.1) in said multi-launching system (15). Thus, multi-launching can be performed using the multi-launching system (15).

Claims

CLAIMS A launching system canister (1) that uses hydrogen energy instead of fuel energy using propulsion in the launching systems in the military field, characterized by comprising of the following; connecting the delrin plug (2) to the aluminum plug (3) and using the same for centering, placing the aluminum plug (3) on the shaft (4) and using the same for sealing, placing the shaft (4) on the base of the launching tube (5) and fixing the combustion area, launching the object as a result of pressurizing the hydrogen gas of the launching tube (5), measuring the velocity of the object pushed out of the launcher during launching by means of the proximity sensor (6), triggering the ignition process from the right side so as to burn the hydrogen gas by means of the right spark plug (7), measuring the temperature in the combustion areas by means of the temperature sensor (8), triggering the ignition process from the left side so as to burn the hydrogen gas by means of the left spark plug (9), flange (10) being the base under the launching tube (5), sealing the combustion area and being the part where the hydrogen gas is conveyed into the launching tube (5), providing the connection of the valve (12) and the flange (10) by means of the reducer (11), valve (12) providing or cutting the flow of hydrogen gas with the openingclosing process and preventing the pressure generated by the combustion of the gas from being transmitted back, pressure sensor (13) ensuring the measurement of the pressure created by the gas sent into the launching tube (5) before and after combustion, gas measurement sensor (14) enabling the hydrogen gas to be delivered to the system and enabling the hydrogen, oxygen and nitrogen amount of the delivered gas to be measured, providing multiple launches by placing a plurality of launching systems (1) on multi-launching systems (15).
PCT/TR2022/051760 2022-10-29 2022-12-31 A launching system WO2024091197A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2022/016375 TR2022016375A1 (en) 2022-10-29 A LAUNCH SYSTEM
TR2022016375 2022-10-29

Publications (1)

Publication Number Publication Date
WO2024091197A1 true WO2024091197A1 (en) 2024-05-02

Family

ID=90831497

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2022/051760 WO2024091197A1 (en) 2022-10-29 2022-12-31 A launching system

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WO (1) WO2024091197A1 (en)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101275817A (en) * 2007-03-30 2008-10-01 北京航天发射技术研究所 Object emitting device with compressed gas as energy sources
US20120205488A1 (en) * 2011-02-16 2012-08-16 Sparton Corporation Unmanned aerial vehicle launch system
WO2015127178A1 (en) * 2014-02-21 2015-08-27 Lockheed Martin Corporation Payload launcher and autonomous underwater vehicle

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101275817A (en) * 2007-03-30 2008-10-01 北京航天发射技术研究所 Object emitting device with compressed gas as energy sources
US20120205488A1 (en) * 2011-02-16 2012-08-16 Sparton Corporation Unmanned aerial vehicle launch system
WO2015127178A1 (en) * 2014-02-21 2015-08-27 Lockheed Martin Corporation Payload launcher and autonomous underwater vehicle

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