11 results about "Pulse detonation engine" patented technology

This invention proposes a closed-cycle power unit and its operation method for a submarine-to-air cross-mode vehicle based on an elliptical rotor engine and a pulse detonation engine, relating to the fields of aerospace and underwater propulsion. It addresses the problems of short battery life, low-temperature degradation and thermal runaway, high noise and pollution from traditional internal combustion engines (due to reliance on intake air and pollution), and the tendency for hydrogen-oxygen combustion to detonate. It also addresses the difficulty of using a single power source to simultaneously achieve underwater cruising and high thrust for cross-mode applications. In this invention, the elliptical rotor engine, without an intake duct and with direct-injection hydrogen-oxygen fuel for a rich combustion profile, serves as the core power source. The pulse detonation propulsion reuses its exhaust gas and supplemental fuel injection. Integrated control uses sensors and algorithms to switch between four modes, achieving cross-mode power supply for submarine-to-air applications. This invention extends the underwater endurance of the submarine-to-air cross-mode vehicle to several hours; enables stable and efficient operation at -20°C; provides rapid refueling without low-temperature degradation; suppresses hydrogen-oxygen detonation; improves thermal efficiency and power-to-weight ratio; reduces noise and contamination; provides sufficient cross-mode thrust; and achieves zero emissions.

To solve the problems of the complex structure of the mechanical valve type reverse transmission suppression mechanism of the air-breathing pulse detonation engine and the difficulties in valve driving and opening / closing control, the present invention proposes a pulse detonation combustion chamber with an air guiding device and an air-breathing pulse detonation engine. On the basis of the traditional pulse detonation combustion chamber, an air guiding transmission device and a transmission spring for rebounding and resetting the air guiding transmission device when it is depressurized are added to each detonation combustion device. Each air guiding transmission device is driven by a part of the energy gas led out from its corresponding detonation combustion device, compresses the transmission spring and generates an axial displacement; the output ends of all the air guiding transmission devices are cooperatively connected with the mechanical rotary valve, and convert their axial displacements into the circumferential rotation of the mechanical rotary valve. The present invention can adaptively realize the oncoming flow filling and reverse transmission isolation, without additionally arranging a driving motor, a signal acquisition unit and a motor control unit for the valve, and has a simpler structure, lower cost and higher reliability.

The application discloses a shock wave focusing detonation initiation device and a control method thereof, and belongs to the technical field of detonation combustion initiation. The first air inlet on the air inlet rotating disc is periodically connected and cut off with the second air inlet on the shock wave focusing cavity by rotating the air inlet rotating disc. When connected, under the action of the internal and external gas pressure difference, the external gas enters the shock wave focusing cavity through each set of connected first air inlets and second air inlets, and a stable and reliable unsteady shock wave is generated in the shock wave focusing cavity. The generated multiple unsteady shock waves propagate to the downstream detonation combustion chamber according to a certain trajectory under the constraint of the horn-shaped shell, and are focused at the air outlet of the shock wave focusing cavity, thereby avoiding the pressure reversal phenomenon at the first air inlet, effectively overcoming the shock wave diffraction loss, reducing the shock wave focusing energy loss, and improving the reliability and working condition adaptability of the pulse detonation engine ignition initiation.

The invention discloses a pulse detonation engine for multi-directional attitude adjustment of a rocket. The pulse detonation engine comprises a detonating pipe section, a branch pipe, a spray pipe and the like. The engine is arranged on the transverse plane of the rocket body, the working modes are changed through the switching valves in the branch pipes, clockwise and anticlockwise self-rotation attitude adjustment around the axial direction of the rocket and overall pitching attitude adjustment of the rocket body can be achieved in different working modes, and the engine has the advantages of being fast in thrust response, accurate in pulse response, large in specific impulse, high in reliability and the like. And the rocket attitude adjusting device is suitable for various rocket flight attitude adjusting tasks.

The application relates to the field of aerospace propulsion technology, and discloses a multi-mode cluster shock-absorbing pulse detonation engine with intelligent gap control; the engine comprises multiple explosion tube bodies in a concentric circle layout, a hydraulic sealing system, a fuel supply system, an electric arc igniter, an integrated thermal management system and an intelligent control system. The core lies in: the sealing reliability is ensured through intelligent dynamic gap control; a wide-range flight is adapted through multi-mode gas supply; precise ignition control is realized through multi-sensor fusion; waste heat is recycled and thrust gain is generated through integrated thermal management; and vibration and noise are inhibited through cluster detonation interference with a specific layout. The application has the dual-mode intelligent switching capability of high-frequency large thrust and low-frequency high efficiency, integrates health monitoring, and forms an advanced propulsion system solution scheme with high reliability, wide-range self-adaptation and low vibration.

The application discloses a vertical take-off and landing fixed-wing aircraft based on a pulse detonation engine and relates to the technical fields of the pulse detonation engine and the aircraft. The aircraft comprises a detonation tube steering adjusting actuator which is composed of an electric push rod, a rocker arm, various hinge shafts and a protection connecting rod mechanism and the like; and a pulse detonation engine with thrust vector control which is composed of a fixed detonation tube, a movable detonation tube, a connecting tube device, a mixing tube and the detonation tube steering adjusting actuator. When the aircraft is in a level flight working condition, the included angle between the axis of the movable detonation tube and the fixed detonation tube is 5 degrees; when the aircraft is in a vertical take-off and landing working condition, the detonation tube steering adjusting actuator drives the movable detonation tube to rotate downwards, and the maximum included angle between the movable detonation tube and the axis of the fixed detonation tube can reach 100 degrees, so as to provide a vertical lifting force and realize thrust vector adjustment.

The invention relates to jet engines, and more particularly to pulse detonation engines. The desired technical result, namely increased energy efficiency and reliability, is achieved in an engine having a combustion chamber configured in the form of a detonation resonator that opens into an exhaust nozzle. The resonator is an aspherical reflector that is symmetrical about the axis of the engine. A gaseous fuel and a gaseous oxidizer are used in the engine, together with a single-step combustion process. If a hydrocarbon fuel is to be used, the fuel duct is provided with a pyrolysis chamber. Pyrolysis is achieved as a result of the fuel flow coming into contact with the heated rear side of the reflector. A mixture of fuel and oxidizer is fed into the combustion chamber through an annular supersonic injection system. To initiate detonation, the engine can be provided with a detonation initiator in the form of a tube which is blind at the distal end and open at the end disposed in the combustion chamber, said tube lying along the axis of the engine. The detonation products flowing through the exhaust nozzle generate a thrust which propels the engine in the opposite direction. This pulse detonation engine design is simple and reliable and provides for the highly efficient generation of propulsive thrust force by maintaining cyclic resonant detonation at a frequency of around 10 kHz.

The invention provides a closed cycle power device of an air-submerged transboundary aircraft based on an elliptical rotor machine and a pulse detonation engine and an operation method of the closed cycle power device, relates to the field of aerospace and underwater propulsion, and aims to solve the problems of short battery endurance, low-temperature attenuation and thermal runaway, high noise of a traditional internal combustion engine, pollution caused by dependence on air intake, easiness in detonation caused by oxyhydrogen combustion, low energy consumption and the like. And the problem that underwater cruise and transboundary large thrust are difficult to consider at the same time through single power is solved. The elliptical rotor machine is not provided with an air inlet channel, and hydrogen and oxygen are directly injected in a cylinder to keep rich combustion as core power; pulse detonation propulsion reuses waste gas and reinjection fuel; the four modes of integrated control are switched through a sensor and an algorithm, and air-submerged cross-medium power supply is achieved. According to the invention, the underwater endurance of the submarine-to-air transboundary aircraft is prolonged to several hours; stable and efficient operation can be achieved at-20 DEG C, filling is fast, and low-temperature attenuation is avoided; hydrogen-oxygen detonation is inhibited, and the heat efficiency and the power-to-weight ratio are improved Noise and wake are reduced, the transboundary thrust is sufficient, and zero emission is achieved.

The invention relates to the technical field of pulse detonation engines, and discloses a pulse detonation combustion chamber and a control method.The pulse detonation combustion chamber comprises an injection mixing section, a concave cavity combustion chamber, an equal straight section combustion chamber and a combustion product outlet which are sequentially arranged in the axial direction; the concave cavity combustion chamber is formed by connecting a plurality of concave cavity structures in series in the axial direction of the concave cavity combustion chamber, the concave cavity structures are formed by extending channel wall bodies of the concave cavity combustion chamber outwards in the radial direction, and then the resistance of the combustion chamber under the high-speed incoming flow condition is greatly reduced. The injection mixing section is provided with a main flow flame ignition area, and an ion probe and a concave cavity ignition area are arranged in the concave cavity structure; through the promotion effect of the multiple cavity configurations and the cavity ignition areas in the different cavity configurations on flame acceleration and detonation, the detonation distance is shortened, the detonation time is shortened, the robustness of the control system is improved, and the detonation detonation success rate is increased. And stable and reliable short-distance rapid detonation is realized by comprehensively utilizing the flame stabilizing and turbulent flow effects of the concave cavity and the energy synergistic effect of multi-point ignition.

The invention discloses a water-jet propulsion pump combined with a pulse detonation engine, which belongs to the technical field of underwater propulsion, and comprises a water-jet propulsion pump shell, a water-jet propulsion pump, a water-jet propulsion pump spray pipe, an annular bracket, a water inlet and a pulse detonation engine unit, and the water-jet propulsion pump spray pipe is fixed at the rear end of the water-jet propulsion pump shell; the water-jet propulsion pump extends into the water-jet propulsion pump shell from front to back, a propulsion pump water inlet flow channel is formed between the water-jet propulsion pump and the inner wall of the water-jet propulsion pump shell, and the space in the water-jet propulsion pump spray pipe is called as a propulsion pump water outlet flow channel; a cavity of which the front end face is closed and the rear end face is communicated with a water outlet runner of the water spraying propulsion pump is formed in the circumferential side wall of the water spraying propulsion pump shell; and the pulse detonation engine unit is fixed in the cavity. The high-efficiency thrust generation capacity of the pulse detonation engine is effectively utilized, extra thrust is provided for the water jet propulsion pump, the propulsion efficiency and thrust output are remarkably improved, and the pulse detonation engine is suitable for the propulsion requirements of high-speed ships under special working conditions.

The present application relates to the technical field of pulse detonation engine, and discloses a pulse detonation combustion chamber and a control method, comprising a jet mixing section, a cavity combustion chamber, an equal-straight section combustion chamber and a combustion product outlet arranged in sequence along the axial direction; the cavity combustion chamber is composed of a plurality of cavity configurations connected in series along the axial direction of the cavity combustion chamber, and the cavity configurations are formed by extending the channel wall of the cavity combustion chamber radially outward, thereby greatly reducing the resistance of the combustion chamber under high-speed airflow conditions; the jet mixing section is provided with a main flow flame ignition area, and the cavity configurations are provided with an ion probe and a cavity ignition area; through the promotion effect of the plurality of cavity configurations and the cavity ignition areas in different cavity configurations on flame acceleration and detonation initiation, the detonation initiation distance and time are shortened, and the robustness of the control system and the success rate of detonation initiation are increased. The energy synergy effect of flame stabilization, flow disturbance and multi-point ignition of the cavity is comprehensively utilized to realize stable and reliable short-distance rapid initiation.