阅读说明：本技术 一种无火工品气固混合火箭发动机 (Initiating explosive-free gas-solid hybrid rocket engine ) 是由 胡松启 刘林林 刘雪莉 王印 于 2020-04-29 设计创作，主要内容包括：本发明公开了一种无火工品气固混合火箭发动机,由火花塞、发动机壳体、喷注器、爆破片、固体推进剂、喷管、高压空气腔室和燃烧室组成。发动机采用火花塞点火,避免使用含火工品的点火头点火产生的安全隐患。高压空气可通过喷注器与碳粉充分接触,在火花塞启动时可保证碳粉被可靠点燃,从而冲破爆破片；碳粉燃烧产生的高温产物及空气进入燃烧室引燃固体推进剂并维持其持续燃烧,产生的高温燃气经过喷管喷出后产生推力。发动机工作前采用爆破片密闭高压空气腔室内气体,可减少发动机中的线路设计。高压气体在运输和存储过程中均不具有危险性；固体推进剂直接装填在燃烧室中,可提高发动机的空间利用率,保证发动机的安全性。(The invention discloses a fireless gas-solid hybrid rocket engine, which consists of a spark plug, an engine shell, an injector, a rupture disk, a solid propellant, a spray pipe, a high-pressure air chamber and a combustion chamber. The engine adopts the spark plug to ignite, avoids using the potential safety hazard that the ignition head that contains the initiating explosive device igniteed and produces. The high-pressure air can be fully contacted with the carbon powder through the injector, and the carbon powder can be reliably ignited when the spark plug is started, so that the rupture disk is broken; high-temperature products and air generated by burning the carbon powder enter a combustion chamber to ignite the solid propellant and maintain the solid propellant to be continuously burnt, and generated high-temperature fuel gas is sprayed out through a spray pipe to generate thrust. The explosion piece is adopted to seal the gas in the high-pressure air cavity before the engine works, so that the circuit design in the engine can be reduced. The high-pressure gas is not dangerous in the transportation and storage processes; the solid propellant is directly filled in the combustion chamber, so that the space utilization rate of the engine can be improved, and the safety of the engine is ensured.)

1. A gas-solid hybrid rocket engine without initiating explosive devices comprises a spark plug, a top cover, an engine shell, an injector, carbon powder, a rupture disk, a heat insulation layer, a solid propellant, a spray pipe, a high-pressure air chamber, a combustion chamber and a one-way valve, and is characterized in that the engine shell is of two concentric cylindrical barrel structures with the step surfaces at one side end connected into a whole, a hollow boss is arranged at the front end of the inner cylindrical barrel, threads are arranged on the circumferential direction of the inner wall of the boss, the injector is in threaded connection with the boss of the inner cylindrical barrel of the engine shell, the rupture disk is positioned in a groove formed between the boss of the inner cylindrical barrel of the engine shell and the injector, and the carbon powder is placed in a cavity formed by the injector and the rupture disk; the other side end of the engine shell is open, the end part of the engine shell is provided with internal threads, the top cover is in threaded connection with the open end of the engine shell, and the top cover, the engine shell and the injector form a high-pressure air chamber;

the center part of the top cover is provided with a screw hole for mounting a spark plug, and the spark plug is connected with the injector; the check valve is positioned at the lower part of the central screw hole of the top cover, and the circle center of the central screw hole of the top cover is positioned on the axis of the concentric circle of the shell;

the injector is a T-shaped structure formed by a coaxial disc and a circular tube, the disc is provided with a central hole, a plurality of circular holes are distributed in the circumferential direction at equal angles according to the central hole and communicated with a circular tube cavity, and external threads are arranged in the circumferential direction of the circular tube;

the combustion chamber is composed of a cylindrical barrel body and a spray pipe inside the engine shell, the solid propellant and the heat insulation layer are bonded and placed in the combustion chamber and fixed through the spray pipe, and the spray pipe is fixedly connected with the engine shell through bolts.

2. The initiating explosive-free gas-solid hybrid rocket engine according to claim 1, wherein the central screw hole of the top cover is positioned on the same axis with the central lines of the engine shell and the injector.

Technical Field

The invention relates to the technical field of gas-solid hybrid rocket engines, in particular to a gas-solid hybrid rocket engine without initiating explosive devices.

Background

With the development of the aerospace science and technology industry, more and more small-sized or micro rockets are applied to daily lives of people who weather rain enhancement, hail suppression, cloud elimination, frost prevention, high-altitude fire extinguishment and the like, and even a small-sized rocket model capable of being launched appears in the market, so that the rocket engine is required to be simpler in structure, more convenient to operate, and most importantly, high in safety and reliability.

The invention patent 200920125865.5 proposes an engine for forest fire extinguishing bomb, in which the structure of the engine is optimized only, but the safety hazard existing when solid powder is applied to the high temperature environment of forest fire is not considered, because the solid powder has self-sustaining combustion property, once ignited in abnormal state, the solid powder can cause irreversible damage to the environment or human body. In the invention 201821468891.3, an air pump type rocket engine, although the safety of the engine of the model airplane advancing in the air is considered, the structural defects are that both gasoline and air need to be injected into a combustion chamber for combustion through an external auxiliary action when the air pump type rocket engine is used, and the operation process and the structure of the engine are complex.

Disclosure of Invention

In order to avoid the defects in the prior art, the invention provides a gas-solid hybrid rocket engine without initiating explosive devices. The engine adopts the spark plug for ignition, so that potential safety hazards caused by ignition by using an ignition head containing initiating explosive devices are avoided; the high-pressure air can be fully contacted with the carbon powder through the injector, and the carbon powder can be reliably ignited when the spark plug is started, so that the rupture disk is broken; before the engine works, the high-pressure air is sealed by the rupture disk, so that the circuit design in the engine can be reduced; the high-pressure air is not dangerous in the transportation and storage processes; the solid fuel is directly filled in the combustion chamber, so that the space utilization rate of the engine is improved.

The invention solves the technical problem by adopting the technical scheme that the explosion-proof device comprises a spark plug, a top cover, an engine shell, an injector, carbon powder, a rupture disk, a heat insulating layer, a solid propellant, a spray pipe, a high-pressure air chamber, a combustion chamber and a one-way valve, and is characterized in that the engine shell is of two concentric cylindrical barrel structures which are connected into a whole by a step surface at one side end, a hollow boss is arranged at the front end of an internal cylindrical barrel, threads are arranged on the circumferential direction of the inner wall of the boss, the injector is in threaded connection with the boss of the internal cylindrical barrel of the engine shell, the rupture disk is positioned in a groove formed between the boss of the internal cylindrical barrel of the engine shell and the injector, and the carbon powder is placed in a cavity formed; the other side end of the engine shell is open, the end part of the engine shell is provided with internal threads, the top cover is in threaded connection with the open end of the engine shell, and the top cover, the engine shell and the injector form a high-pressure air chamber;

the center part of the top cover is provided with a screw hole for mounting a spark plug, and the spark plug is connected with the injector; the check valve is positioned at the lower part of the central screw hole of the top cover, and the circle center of the central screw hole of the top cover is positioned on the axis of the concentric circle of the shell;

the injector is a T-shaped structure formed by a coaxial disc and a circular tube, the disc is provided with a central hole, a plurality of circular holes are distributed in the circumferential direction at equal angles according to the central hole and communicated with a circular tube cavity, and external threads are arranged in the circumferential direction of the circular tube;

the combustion chamber is composed of a cylindrical barrel body and a spray pipe inside the engine shell, the solid propellant and the heat insulation layer are bonded and placed in the combustion chamber and fixed through the spray pipe, and the spray pipe is fixedly connected with the engine shell through bolts.

The central screw hole of the top cover is positioned on the same axis with the central lines of the engine shell and the injector.

Advantageous effects

According to the initiating explosive-free gas-solid hybrid rocket engine, the engine is ignited by adopting the spark plug, so that potential safety hazards caused by ignition by using an ignition head containing initiating explosive are avoided; the high-pressure air can be fully contacted with the carbon powder through the injector, and the carbon powder can be reliably ignited when the spark plug is started, so that the rupture disk is broken; before the engine works, the high-pressure air is sealed by the rupture disk, so that the circuit design in the engine can be reduced; the high-pressure air has low reactivity and is not dangerous in the transportation and storage processes; solid fuel is directly filled in the combustion chamber, so that the space utilization rate of the engine is improved; the solid fuel does not contain an oxidant and has no self-sustaining combustion capability, so that the safety of the engine is improved.

Drawings

The invention will be described in detail with reference to the accompanying drawings and embodiments.

FIG. 1 is a schematic diagram of a gas-solid hybrid rocket engine without initiating explosive devices.

FIG. 2 is a schematic top cover view of the gas-solid hybrid rocket engine without initiating explosive devices.

FIG. 3 is a top cover sectional view of the gas-solid hybrid rocket engine without initiating explosive device of the present invention.

FIG. 4 is a side view of the case of the gas-solid hybrid rocket engine without initiating explosive device of the present invention.

FIG. 5 is a sectional view of the case of the gas-solid hybrid rocket engine without initiating explosive device of the present invention.

FIG. 6 is a side view of the injector of the fireless gas-solid hybrid rocket engine of the present invention.

FIG. 7 is a cross-sectional view of the injector of the fireless gas-solid hybrid rocket engine of the present invention.

FIG. 8 is a side view of a nozzle of the gas-solid hybrid rocket engine without initiating explosive device according to the present invention.

FIG. 9 is a sectional view of a nozzle of the gas-solid hybrid rocket engine without initiating explosive device according to the present invention.

In the drawings

1. Spark plug 2, top cover 3, engine shell 4, injector 5, carbon powder 6, rupture disk 7, heat insulating layer 8, solid propellant 9, jet pipe 10, high-pressure air chamber 11, combustion chamber 12 and one-way valve

Detailed Description

The embodiment is a gas-solid hybrid rocket engine without initiating explosive devices.

Referring to fig. 1 to 9, the initiating explosive-free gas-solid hybrid rocket engine of the embodiment comprises a spark plug 1, a top cover 2, an engine shell 3, an injector 4, carbon powder 5, a rupture disk 6, a heat insulation layer 7, a solid propellant 8, a spray pipe 9, a high-pressure air chamber 10, a combustion chamber 11 and a one-way valve 12; the engine shell 3 is of two concentric cylindrical structures, the step surfaces of one side end of the engine shell are connected into a whole, a hollow boss is arranged at the front end of the internal cylindrical structure, threads are formed in the circumferential direction of the inner wall of the boss, the injector 4 is in threaded connection with the boss of the internal cylindrical structure of the engine shell 3, the rupture disk 6 is located in a groove formed between the boss of the internal cylindrical structure of the engine shell 3 and the injector 4, and carbon powder 5 is placed in a cavity formed by the injector 4 and the rupture disk 6; the other side end of the engine shell 3 is open, the end part is provided with internal threads, the top cover 2 is in threaded connection with the open end of the engine shell 3, and the top cover 2, the engine shell 3 and the injector 4 are combined into a high-pressure air chamber 10.

The center of the top cover 2 is provided with a screw hole for installing the spark plug 1, and the spark plug 1 is connected with the injector 4 through threads. The check valve 12 is arranged at the lower part of a central screw hole of the top cover 2, and the circle center corresponding to the central screw hole of the top cover 2 is positioned on the inner diameter of a concentric circle of the shell. The central screw hole of the top cover 2 is positioned on the same axis with the engine shell 3 and the injector 4.

The injector 4 is a T-shaped structure formed by a coaxial disc and a circular tube, the disc is provided with a central hole, and a plurality of circular holes are distributed in the circumferential direction at equal angles according to the central hole and communicated with the cavity of the circular tube. The central bore of the injector 4 in this embodiment is 1/10 disks in diameter and 8 bores are evenly spaced around the inner bore.

The combustion chamber 11 is composed of an engine shell 3 and a spray pipe 9, the solid propellant 8 and the heat insulation layer 7 are placed in the combustion chamber and fixed through the spray pipe 9, a protruding flange is arranged at the joint of the spray pipe 9, a plurality of screw holes are evenly distributed in the flange, and the spray pipe 9 is fixedly connected with the engine shell 3 through bolts. The solid fuel and the heat insulating layer are physically bonded to form a non-detachable fuel cartridge, and the fuel cartridge is fixed to the engine shell through the spray pipe.

In the embodiment, the rupture disk 6 is placed in a groove formed between a boss of a cylindrical barrel in the engine shell 3 and the injector 4, and the carbon powder 5 is placed in a cavity formed by the injector 4 and the rupture disk 6; carbon powder 5 is placed on the left side of the rupture disk, the injector 4 is connected with the engine shell 3 through threads, the rupture disk 6 is fixed, and the middle of the injector 4A center hole with a diameter of 4mm and 8 holes with a diameter of 3mm around the center hole, a top cover 3 fixed on the engine housing 3 by screw threads, a spark plug fixed at the center of the top cover 2 by screw threads, a check valve 12 fixed at the screw hole of the top cover near the edge by screw threads, and a density of 1.03kg/m³Paraffin-containing solid fuel 8 with the length of 100mm and the outer diameter of 60 mm is connected with a heat insulating layer 7 with the thickness of 4mm in a physical bonding mode to form a fuel charge column, the fuel charge column is freely filled in a cavity formed by a round tube in the engine shell 3, a spray pipe 9 is connected with the engine shell 3 through 8M 4 × 10 screws with the strength of 12.9, the roar diameter of the spray pipe is 6.8mm, a high-pressure air pipeline is connected with a one-way valve 12 through threads, air is filled into a high-pressure air chamber 10, the air tightness of the whole device is checked, when the pressure of high-pressure air reaches 5MPa, ventilation is stopped, a power supply connected with a spark plug 1 is opened, the spark plug 2 ignites and ignites carbon powder 5, the pressure on the left side of the explosion piece 6 is increased, the explosion piece 6 is broken, high-temperature products generated by combustion of the carbon powder 5 and air enter a combustion chamber 11 to ignite the solid fuel 8 and maintain continuous combustion of the solid fuel 8, and generated high-temperature gas.