JPH0318657A - Rocket motor - Google Patents

Abstract

PURPOSE:To obtain a rocket motor easy and speedy in firing preparation as well as economical without requiring a storage facility by injecting liquid-fuel from an injector toward solid oxidizer and at that time igniting the liquid-fuel, thus jetting high temperature-pressure gas generated under combustion reaction between the gasified oxygen and liquid-fuel from a rocket nozzle. CONSTITUTION:A motor case 1 is provided with a rocket nozzle at its lower end and an ignition burner 5 at the center of its upper end. A liquid-fuel injector 6 provided with injectors 7 is disposed concentrically in a combustion chamber 3, and its upper end is communicated with discharge opening of a fuel pump in a pump chamber 8. A tank 11 for liquid inert material is provided above a tank 10, a pipe 12 communicated with the bottom part of the tank 11 is communicated with an inert material pump in the pump chamber 8, the liquid inert material in the tank 11 is supplied to the combustion chamber 3 from the injector 6 at need by a control unit to be gasified at combustion temperature, and the gasification of solid oxidizer 2 is suppressed by this gasified inert gas, thus controlling combustion.

Description

[Detailed Description of the Invention] [Industrial Field of Application] This invention relates to a rocket motor consisting of a liquid and a solid. [Prior Art] A well-known rocket motor is a hybrid rocket motor. This hybrid rocket motor is equipped with an injector in the combustion chamber provided at the center of the solid fuel, and the liquid oxidizer injected from the injector is brought into contact with the solid fuel and ignited, causing the solid fuel to burn. It generates thrust by ejecting high-temperature, high-pressure gas from a rocket nozzle. [Problem to be solved by the invention] Since the conventional hybrid rocket motor as described above uses solid fuel, it requires less piping and piping than a two-liquid type liquid fuel rocket motor that uses liquid fuel and liquid oxidizer. Although it has the advantage of simplifying the control system, it poses major problems in terms of storage and handling because the oxidizing agent is a dangerous liquid such as liquid oxygen that must be stored at low temperatures. One problem of this invention is to solve the problems of conventional rocket motors as described above by creating a rocket motor that uses a solid oxidizer, allows the fuel to be stored at room temperature, and also enables combustion control. It is to provide. (Means for Solving the Problem) In order to solve the above problems, the present invention provides a solid oxidizer that can be stored at room temperature and has a combustion chamber that runs through the center, a liquid fuel tank that can be stored at room temperature, and a liquid fuel tank that can be stored at room temperature. It consists of an active substance tank and a fuel injector that protrudes into the combustion chamber. Liquid fuel is injected from the injector toward the solid oxidizer and ignited to cause a combustion reaction between the oxygen vaporized from the solid oxidizer and the liquid fuel. To provide a rocket motor in which the high-temperature, high-pressure gas generated by the above-mentioned combustion engine is jetted out from a rocket nozzle, and if necessary, an inert substance is vaporized and jetted into a combustion chamber. To explain its operation, the liquid fuel in the fuel tank is forced into the injector using an appropriate pump, and is injected in the form of a spray toward the inner surface of the surrounding solid oxidizer. An ignition burner is installed at the back of the chamber, and by ejecting an ignition flame toward the combustion chamber, the solid oxidizer vaporizes and the liquid fuel begins to burn.

The high-temperature, high-pressure gas generated in this way is ejected from the rocket nozzle and generates thrust. [Example] In the example shown in the drawings, 1 is a motor case made of a titanium alloy or the like, and 2 is a solid oxidizing agent fixed inside the case. Potassium perchlorate, ammonium peroxide, ammonium nitrate, etc. The inner cavity passing through the center of the agent 2 is defined as the combustion chamber 3. A rocket nozzle 4 is provided at the lower end of the motor case 1, and an ignition burner 5 is provided at the center of the upper end of the case 1. Reference numeral 6 denotes a liquid fuel injector, which has a large number of small holes, that is, injectors 7, and is installed concentrically in the combustion chamber 3, and its upper end is connected to the discharge port of the fuel pump in the pump chamber 8. ．． Reference numeral 10 denotes a liquid fuel tank provided at the upper part of the pump chamber 8, in which liquid fuel such as alcohol, kerosene, hydrazine, etc. is loaded, and the bottom thereof communicates with the suction port of the fuel pump in the bomb chamber 8. Further, a liquid inert substance tank 11 is further provided at the top of the tank 10, and a pipe 12 connected to the bottom of the tank 11 is connected to an inert substance pump in the pump chamber 8 (not shown). Tank 1
The liquid inert substance in 1 is replenished from the injector 6 to the combustion chamber 3 as needed and vaporized at the combustion temperature, and the vaporized inert gas suppresses the vaporization of the solid oxidizer 2 to control combustion. Force. The pump in the pump chamber 8 is driven by power such as an electric motor or a gas turbine, but an electric motor requires a power source, and a turbine requires a fuel tank 13 for it. 14 in the figure is a fuel tank for the ignition burner 5. In the fuel tanks 13 and 14, a liquid or gaseous fuel and an oxidizing agent are stored separately under pressure and supplied to the prime mover as needed. In addition, igniters using gunpowder may also be used. Next, to explain the operation of the above embodiment, under the condition that rocket launch preparation is completed, the ignition burner 5 is started and ignited, and at the same time, the fuel pump in the bomb chamber 8 is started to transfer the fuel in the tank 10 to the injector 6. When the fuel is injected from each injector 7, the fuel that comes into contact with the vaporized oxygen from the solid oxidizer 2 heated by the flame from the ignition burner 5 starts to burn and becomes a high-temperature, high-pressure gas, which is ejected from the rocket nozzle 4. Generates thrust. In addition, in order to control the combustion of fuel in the combustion chamber 3, an inert substance is sent from the tank 11 through the pipe 12 to an inert substance bomb in the pump chamber 8, and the flow rate of the fuel and the liquid inert substance are controlled. The injection state of the high-temperature, high-pressure gas from the rocket nozzle 4 is controlled by appropriately controlling the flow rate using a flow rate regulating valve, etc., and controlling the combustion state by changing the mixture ratio of fuel and inert material. to control the rocket's flight speed. [Effects of the Invention] As described above, the rocket mower of the present invention includes a solid oxidizer that can be stored at room temperature and has a combustion chamber that runs through the center, a liquid fuel tank that can be stored at room temperature, a tank for liquid inert material, and the above-mentioned combustion chamber. It consists of a fuel injector that protrudes into the room, and the injector injects liquid fuel toward the solid oxidizer and ignites it, releasing high-temperature, high-pressure gas generated by the combustion reaction between the oxygen vaporized from the solid oxidizer and the liquid fuel. It is injected from a rocket nozzle and, if necessary, vaporizes inert substances to suppress the vaporization of the solid oxidant and control combustion. This is far more advantageous than a rocket motor that burns the fuel. In other words, in this invention, since the oxidizer is solid and the fuel is a liquid that can be stored at room temperature, storage equipment for ultra-low temperature liquefied gas such as rockets using liquid oxygen is not required, making it economical and easy to prepare for launch. And it can be done quickly.

In addition, since the fuel is liquid, it is easy to control the injection state and the injection speed of high-temperature, high-pressure gas from the rocket nozzle, and it is also equipped with a liquid inert material tank to direct the inert gas to the combustion chamber. It is extremely safe because it can be injected, the combustion state can be controlled, and combustion can be stopped, and the flight speed can be easily controlled.

[Brief explanation of the drawing]

FIG. 1 is a longitudinal sectional front view showing an embodiment of the rocket motor of the present invention. 2... Solid oxidizer, 3... Combustion chamber, 6... Fuel injector, 10... Liquid fuel tank, 11... tanks for inert substances,
14... Burner fuel tank for ignition.

Claims (1)

[Claims] (1) Consists of a solid oxidizer that can be stored at room temperature and has a combustion chamber that runs through the center, a liquid fuel tank that can be stored at room temperature, a liquid inert substance tank, and a fuel injector that protrudes into the combustion chamber. The liquid fuel is injected from the container toward the solid oxidizer, ignited, and the high-temperature, high-pressure gas generated by the combustion reaction between the oxygen vaporized from the solid oxidizer and the liquid fuel is ejected from the rocket nozzle. A rocket motor that vaporizes and ejects it into the combustion chamber.