Static detonation engine

Abstract

The design is a static detonation engine, the principle is that after mixed gas is input into a gas inlet and then ignited by an ignition device in a detonation engine cavity, the gas is detonated to generate pushing force, power can be provided for various spacecrafts, or pushing force can be provided for devices needing pushing force, and the structure of the static detonation engine comprises a gas inlet device and an engine front cavity. The engine is composed of an engine rear cavity, an ignition device, a tail control device, a gas inlet fuel detection device, an in-cavity fuel gas concentration detection device, a cooling device and a front and rear cavity isolation device.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of detonation engine structural design, belongs to the field of mechanical engineering and aerospace propulsion technology, and in particular to a static detonation engine system with multi-stage regulation function. The engine has no high-speed rotating components, can effectively improve the reliability of the detonation engine, and can be widely applied to various aviation equipment and other devices requiring thrust to provide power support. BACKGROUND

[0002] At present, detonation engines have been researched and applied at home and abroad. There are hydrogen-oxygen rotary detonation rocket engines in China, Half-X dual-mode ramjet engines have been developed in the United States, and some countries such as Germany and Japan have also explored in this field. However, the existing technologies in this field generally have the problems of complex structure and poor reliability. At the same time, the cost of aviation fuel is high, which makes it difficult to popularize the use of civil equipment, so that aircraft cannot be popularized to ordinary people. The existing detonation engine also has problems such as insufficient combustion stability, low thrust regulation precision, and limited heat management efficiency. Based on this, the present application realizes jet work according to the principle of gas explosion, uses commonly available low-cost fuel, greatly simplifies the engine structure, thereby greatly reducing the use and maintenance cost, manufacturing difficulty and cost of the engine, and improving the stability and safety of the product, which is expected to make flight products like cars available to ordinary people. SUMMARY

[0003] (I) Technical problems to be solved The present application aims to solve the problems of complex structure, poor reliability, high use cost, insufficient combustion stability, low thrust regulation precision, and limited heat management efficiency of the existing detonation engine, and to provide a static detonation engine with simple structure, low cost, high stability and safety. (II) Technical solutions To achieve the above-mentioned purpose, the present application provides a static detonation engine, which is a completely new design and can use low-cost fuel for operation. The engine adopts an oval spherical design and mainly includes a front cavity (202), a rear cavity (203), an air inlet device (101), an ignition device (204), an air inlet fuel detection device (102), a cavity gas concentration detection device (205), an isolation device (201), a tail control device (401), and a cooling device (301). The air inlet system adopts a multi-point air inlet way and is provided with an air inlet (101), which can provide low-cost fuel for the engine through high-pressure compressed gas bottles or supercharged air. The air inlet system is one of the structures that need to be protected. The ignition system is a multi-point ignition mechanism (204) similar to a spark plug, which is arranged at a specific position of the front-rear cavity isolation device (201). The isolation device (201) is used for separating the front cavity (202) and the rear cavity (203), the tail control device (401) is connected with the rear cavity (203), and is used for discharging the gas to generate thrust. The cooling device (301) is used for cooling each part of the engine, and ensures normal operation of the engine. The intake fuel detection device (102) is used for detecting the related parameters of the fuel in the intake, and the cavity gas concentration detection device (205) is used for detecting the concentration of the gas in the front cavity (202) and the rear cavity (203), so that the engine can work safely and stably. The static engine structure of the application is the core content to be protected, through the above structure design, the engine is simplified, the cost is reduced, and the reliability and safety are improved. (Three) beneficial effects Compared with the prior art, the application has the following beneficial effects: Simplified structure: the engine has no high-speed rotating parts, the structure is greatly simplified, the manufacturing difficulty and cost are reduced, and the use and maintenance are facilitated. Low cost: the commonly available low-cost fuel is used, and the fuel use cost is further reduced through the high-pressure compressed gas cylinder or the supercharged intake system, so that the engine can be popularized on civil equipment. Improved reliability and safety: the simplified structure reduces the failure points and improves the stability of the product; at the same time, the intake fuel detection device (102) and the cavity gas concentration detection device (205) and the cooling device (301) can effectively guarantee the safe operation of the engine. Improved combustion stability and thrust control accuracy: through the multi-point ignition device (204) and reasonable intake design, the combustion stability is improved, and the design of the tail control device (401) helps to improve the thrust control accuracy. Beneficial to popularization: the above advantages greatly reduce the cost of flight products, and are expected to benefit ordinary people like cars, and promote the popularization of aircraft. BRIEF DESCRIPTION OF DRAWINGS

Figure 1

Claims

1. A stationary detonation engine system, characterized in that, include: The integrated intake unit is composed of an intake device (101) and a fuel detection device (102) working together to monitor the composition of the gas mixture and regulate the flow rate in real time; The split-chamber combustion structure includes an engine front chamber (202) and a rear chamber (203) separated by an isolation device (201). The front chamber (202) receives premixed gas and triggers detonation through an ignition device (204). The rear chamber (203) is equipped with a gas concentration detection device (205) to optimize combustion efficiency. An active thermal management system, with a cooling device (301) integrated into the outer wall of the combustion chamber, suppresses heat load through closed-loop temperature control; The dynamic thrust control module is dynamically adjusted by the tail control device (401) based on combustion parameters to achieve thrust vector output.

2. The stationary detonation engine system according to claim 1, characterized in that: The isolation device (201) is a high-temperature resistant composite material component. Its opening and closing state is linked with the gas concentration detection device (205). When the pressure in the current chamber (202) reaches the threshold, the isolation opening area is automatically adjusted.

3. The stationary detonation engine system according to claim 1, characterized in that: The cooling device (301) includes a microchannel cooling layer (302) and a phase change material layer (303). The circulating coolant in the microchannel is regulated by the feedback of the temperature sensor (304), and the phase change material layer (303) absorbs instantaneous thermal shock.

4. The stationary detonation engine system according to claim 1, characterized in that: The fuel detection device (102) and the gas concentration detection device (205) achieve data fusion through the control chip (501) and dynamically adjust the intake air-fuel mixture ratio and ignition timing to improve combustion efficiency.

5. The stationary detonation engine system according to claim 1, characterized in that: The tail control device (401) includes a deformable nozzle (402) and an actuator array (403), which adjusts the nozzle expansion ratio and deflection angle in real time based on the pressure data of the rear chamber (203) to output vector thrust.

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