Explosion engine

Abstract

An explosion engine with its air inlet end not connected with a fixed combustion chamber, comprising an air inlet channel, a bearing, a shaft, an aircraft, characterized in that the explosion engine further comprises a machine shell, a rotary cylinder, a fixed combustion chamber, end walls at both ends of the rotary cylinder, a rotary cylinder partition, an inner circular wall of the rotary cylinder, an uninterrupted fuel injector, an igniter, a jet channel, and a gas exhaust channel; the oncoming flow entering from the air inlet channel pushes the rotor to rotate at high speed, after the rotary cylinder rotates through the position of the uninterrupted fuel injector and receives the injected fuel, the rotary cylinder continues to rotate to the position connected with the fixed combustion chamber, the explosion shock wave in the fixed combustion chamber will cause the explosive compression of the mixture of fuel and air in the rotary cylinder, so that the explosion of the mixture of fuel and air produces an explosion shock wave which is ejected from the jet channel, after the rotary cylinder rotates to the position not connected with the fixed combustion chamber, the exhaust gas remaining in the rotary cylinder is exhausted into the next working cycle.

Description

I. TECHNICAL FIELD

[0001] The present technology belongs to the field of engines II. BACKGROUND

[0002] The existing three-way jet engines such as turbojet engines, turbofan engines and ramjet engines are connected to the air intake end and the jet end through the combustion chamber, and the pressure in the front part of the combustion chamber must be much greater than the pressure in the rear part to work normally. If the gas pressure in the combustion chamber is too high, the air compressor cannot push the air into the combustion chamber, so it is impossible to use the method of making the jet port much smaller than the air intake port to make the jet port jet several tens or hundreds of Mach gas flow, that is, the aircraft using the three-way jet engine as the thruster cannot achieve hypersonic flight, and the combustion effect is not good. The defect of the rocket is that it needs to carry its own oxidizer, and the working medium of the rocket lacks nitrogen for the reverse thrust. III. SUMMARY

[0003] In view of the defects of the above-mentioned technology, the present application designs a deflagration engine whose air intake end is not connected to a fixed combustion chamber.

[0004] The technical scheme adopted by the present application is as follows:

[0005] The application discloses a deflagration engine which is not connected with a fixed combustion chamber at an air inlet end and has a pressure at a rear part of the combustion chamber much higher than that at a front part of the combustion chamber. The deflagration engine comprises an air inlet channel, a gas guide, a bearing, a shaft and an aircraft and the like existing technologies, and is characterized in that the deflagration engine further comprises a machine shell, a rotating cylinder, a fixed combustion chamber, end walls at two ends of the rotating cylinder, rotating cylinder partition plates, an inner circular wall of the rotating cylinder, an uninterrupted fuel injector, an igniter, a jet channel, a blocking plate and a gas discharge channel. The inner circular wall of the rotating cylinder is fixedly connected to the shaft through the end walls at two ends of the rotating cylinder to form an annular groove, and the annular groove is equally divided into 12 identical rotating cylinders through 12 rotating cylinder partition plates. The two ends of the rotating cylinder partition plates are sealingly and fixedly connected with the end walls at two ends of the rotating cylinder, the inner side of the rotating cylinder partition plates is sealingly and fixedly connected with the inner circular wall of the rotating cylinder, the rotating cylinder partition plates are hollow plates, that is, the rotating cylinder partition plates have interlayer spaces, there is a blocking plate between the left space and the right space in the inner circular wall, the left space in the inner circular wall is connected with the interlayer space on the left side of the rotating cylinder partition plate, the right space in the inner circular wall is connected with the interlayer space on the right side of the rotating cylinder partition plate, cooling air enters the left space in the inner circular wall of the rotating cylinder from the air hole in the end wall at the left end of the rotating cylinder, then enters the interlayer space of the rotating cylinder partition plate to cool the rotating cylinder partition plate, and then is discharged to the outside through the right space in the inner circular wall of the rotating cylinder and the air hole in the end wall at the right end of the rotating cylinder. The rotor is composed of the shaft, the end walls at two ends of the rotating cylinder, the inner circular wall of the rotating cylinder and the rotating cylinder partition plates, the movement track of the rotor when rotating is cut by the inner wall of the machine shell, that is, the gap between the inner wall of the machine shell and the rotor is very small, but the inner wall of the machine shell does not hinder the rotation of the rotor, and the bearings at two ends of the rotor are limited by the corresponding bearing sleeves on the machine shell. The bearing sleeve, the machine shell, the air inlet channel, the fixed combustion chamber, the jet channel and the gas discharge channel are a fixedly connected whole, the fixedly connected whole is fixedly installed on the aircraft, the air inlet channel is a gas passage through which the speed difference ram air flow of the aircraft flying enters the deflagration engine, whether an air diffuser is arranged in the gas passage needs to be determined through experiments, whether an air guide is arranged in the fixed combustion chamber also needs to be determined through experiments, the uninterrupted fuel injector comprises all devices for realizing the function of the uninterrupted fuel injector, the nozzle of the uninterrupted fuel injector is fixed on the fixed combustion chamber, fuel is sprayed from a slit of the uninterrupted fuel injector, the whole surface of the rotating cylinder facing the slit sprays the fuel after rotating through the uninterrupted fuel injector, the gas in the rotating cylinder of the uninterrupted fuel injector is subjected to a strong impact force, a rebound force and a centrifugal force within one hundredth of a second, the gas in the cylinder is subjected to a strong movement and forms a strong movement air flow vortex, the gas is mixed with the fuel on the whole surface of the rotating cylinder instantaneously and uniformly, the igniter is fixed on the fixed combustion chamber, the igniter comprises other components for realizing the function of the igniter, and the igniter does not need to be ignited again after the ignition of the igniter is successful, and the jet channel is a gas passage through which the deflagration gas in the fixed combustion chamber is blasted to the outside.The air escape channel is a gas channel through which the high-pressure gas left in the rotary cylinder is discharged backward after the rotary cylinder is rotated to be not communicated with the fixed combustion chamber. When the flight speed of the aircraft equipped with the explosion engine is greater than 120 kilometers per hour, the oncoming flow entering from the air inlet channel, that is, the ramjet flow, can enter the rotary cylinder and make the rotor rotate at high speed by pushing the rotary cylinder partition. When the rotary cylinder is rotated to the position of the uninterrupted fuel injector, the outer edge of the rotary cylinder is in contact with the inner wall of the shell, and the internal space is not communicated with the outside. The fuel injected by the uninterrupted fuel injector is mixed with the air in the rotary cylinder uniformly. When the rotary cylinder continues to rotate to the position that the internal space is communicated with the fixed combustion chamber, the explosion shock wave in the fixed combustion chamber will cause the explosive compression of the mixture of fuel and air in the rotary cylinder, so that the mixture of fuel and air explodes into the fixed combustion chamber. Subsequently, the explosion shock wave ignites the mixture of fuel and air in the rear rotary cylinder to explode. The explosion engine is ignited by explosion, and the explosion is connected to produce a high-pressure gas flow at a speed of tens or hundreds of Mach from the jet nozzle to the rear of the aircraft, thereby generating a huge propulsive force to push the aircraft to fly at a hypersonic speed or a supersonic speed. If necessary, the aircraft can also be set to fly at a subsonic speed. When the rotary cylinder continues to rotate to be not communicated with the fixed combustion chamber and only communicated with the air escape channel, the remaining burned gas in the rotary cylinder is discharged from the air escape channel. When the rotary cylinder continues to rotate to be communicated with the air escape channel and the air inlet channel, the ramjet flow entering from the air inlet channel enters the rotary cylinder to clean the rotary cylinder, so that the exhaust gas left in the rotary cylinder flows out of the air escape channel. When the rotary cylinder continues to rotate to be communicated with the air inlet channel, the ramjet flow reenters the rotary cylinder and makes the rotor rotate at high speed to enter the next working cycle.

[0006] The explosion engine has the following advantages: 1. The mixture of air and fuel is uniformly mixed, and then the mixture is subjected to

[0007] The explosion engine has the following advantages: 1. The mixture of air and fuel is uniformly mixed, and then the mixture is subjected to

[0008] 2, The air inlet end of the explosion engine is not connected with the fixed combustion chamber, and the air in the air inlet end is transported to the fixed combustion chamber cylinder by cylinder through the rotating cylinder, so no matter how high the pressure in the fixed combustion chamber is, it will not affect the effective entry of the air in the air inlet end into the fixed combustion chamber, so the jet nozzle of the explosion engine can be made very small, which can be as small as one tenth of the air inlet, so that a huge pressure can be generated in the fixed combustion chamber, and the jet flow speed of the jet nozzle can reach tens or hundreds of Mach, so that the explosion engine can drive the aircraft to achieve hypersonic flight, and the energy generated by the explosion engine can be efficiently converted into propulsion energy.

[0009] 3, As long as the speed of the aircraft where the explosion engine is located reaches 120 kilometers per hour, the explosion engine can be started, so the aircraft where the explosion engine is located can fly at hypersonic speed, supersonic speed, and subsonic speed; if the explosion engine is used as an aircraft propeller, a downhill runway should be set up on the airport, and an electromagnetic catapult or other propulsion mechanism should be used to push the aircraft downhill at a speed of 120 kilometers per hour to start the explosion engine, and the aircraft can take off when the speed of the aircraft driven by the explosion engine on the horizontal runway reaches the take-off speed.

[0010] 4, The explosion engine has a simple structure and working principle, and the energy utilization efficiency is particularly high. Except for the oil supply mechanism, the remaining mechanisms can be manufactured by general machinery manufacturers, and the manufacturing cost is less than 1 / 10 of that of a turbofan engine. The thrust-to-weight ratio of the explosion engine can exceed 100, which is beyond the reach of any other jet engine. The explosion engine can jet tens or hundreds of Mach airflow. The explosion engine has many implementation ways, and can be made into an explosion jet engine with zero forward speed or an explosion engine specially designed to generate rotary power. The explosion engine can be applied to many fields.

[0011] 5, The sandwich space inside the rotor of the explosion engine can be effectively cooled by cooling gas, so that the maximum temperature that can be withstood inside the rotor of the explosion engine can be increased. Four, Brief Description of Drawings

[0012] Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 、 Figure 6 、 Figure 7 、 Figure 8 、 Figure 9 、 Figure 10 、 Figure 11 、 Figure 12 、 Figure 13 、 Figure 14 、 Figure 15 、Figure 16 , Figure 17 , Figure 18 , Figure 19 , Figure 20 , Figure 21 , Figure 22 is the structural diagram of the design of the explosive engine. In Figure 1 , 77 - aircraft, 50a - air inlet, 78 - uninterrupted fuel injector, 1 - casing, 89 - air guide, 17 - rotary cylinder, 11a - shaft, 35a - jet, 44a - fixed combustion chamber, 25 - inner wall of rotary cylinder, 18 - rotary cylinder partition, 45a - igniter, 51a, 51b - air outlet. In Figure 2 , 50a - air inlet, 1 - casing, 10a, 10b - bearing, 44a - fixed combustion chamber, 18 - rotary cylinder partition, 88 - blocking plate, 25 - inner wall of rotary cylinder, 52a, 52b - end wall of rotary cylinder, 35a - jet, 11a - shaft. In Figure 3 , 1 - casing, 13 - fixed baffle, 16a, 16b - air inlet, 11a - shaft. In Figure 4 , 1 - casing, 27a - outer wall of rotary cylinder, 17 - rotary cylinder, 18 - rotary cylinder partition, 11a - shaft, 25 - inner wall of rotary cylinder. In Figure 5 , 1 - casing, 35a, 35b - jet, 29a, 29b - explosive communication port, 11a - shaft, 30a, 30b - fuel injection port, 34a, 34b - air outlet, 28 - explosive baffle. In Figure 6 , 3 - transmission shaft, 47 - air compressor fan, 81 - mechanism for injecting fuel from fuel injection port into rotary cylinder, 46 - diffuser, 43 - attachment, 13 - fixed baffle, 37a, 37b - bevel gear, 10a, 10b - bearing, 1 - casing, 80 - annular partition, 27a, 27b - outer wall of rotary cylinder, 79a, 79b - connecting plate, 29a, 29b - explosive communication port, 28 - explosive baffle, 17 - rotary cylinder, 25 - inner wall of rotary cylinder, 45a, 45b - igniter, 42a, 42b - inner wall of fixed combustion chamber, 44a, 44b - fixed combustion chamber, 35a, 35b - jet, 11a - shaft. In Figure 7 , 28 - explosive baffle, 54a, 54b - cooling gas passage, 1 - casing, 29a - explosive communication port, 55 - cooling gas inlet, 11a - shaft, 16a - air inlet, 30a - fuel injection port. In Figure 8 , 17 - rotary cylinder, 56 - rotor jet, 54a, 54b - cooling gas passage, 35a - jet, 1 - casing, 18 - rotary cylinder partition, 27a, 27b - outer wall of rotary cylinder, 25 - inner wall of rotary cylinder, 11a - shaft.Figure 9 In the figure: 57a, 57b - bottom housing plates of the right end of the rotary cylinder, 58a, 58b - cooling gas outlets, 11a - shaft. In the figure: Figure 10 In the figure: 54a, 54b - cooling gas channels, 1 - housing, 11a - shaft. In the figure: Figure 11 In the figure: 54a, 54b - cooling gas channels, 62 - compressor, 27a, 27b - outer cylindrical wall of the rotary cylinder, 25 - inner cylindrical wall of the rotary cylinder, 81 - means for injecting fuel into the rotary cylinder from the fuel injection inlet, 29a - explosion communication port, 17 - rotary cylinder, 44a - fixed combustion chamber, 28 - explosion baffle, 60 - thrust bearing, 57a, 57b - bottom housing plates of the right end of the rotary cylinder, 35a - jet duct, 10b - bearing, 11a - shaft, 59 - bearing support with bearing sleeve, 16a - air inlet communication port. In the figure: Figure 12 In the figure: 9a - end wall of the flat rotary rotor, 1 - housing, 6a, 6b, 6c, 6d - flat rotary shaft, 2 - fixed shaft. In the figure: Figure 13 In the figure: 1 - housing, 21a, 21b - exhaust port, 22a, 22b, 22c, 22d - flow blocking plug, 5a, 5b, 5c, 5d - flat rotary piston, 86a, 86b - flat rotary cylinder, 6a, 6b, 6c, 6d - flat rotary shaft, 20a, 20b - air inlet, 2 - fixed shaft, 24a, 24b - choke, 8 - divider, 68 - flat rotary compressor. In the figure: Figure 14 In the figure: 1 - housing, 6a, 6b, 6c, 6d - flat rotary shaft, 7a, 7b, 7c, 7d - flat rotary gear, 15a, 15b, 15c, 15d - transmission gear, 4a, 4b, 4c, 4d - transmission gear shaft, 26 - fixed gear, 11b - shaft. In the figure: Figure 15 In the figure: 1 - housing, 2 - fixed shaft, 4a, 4c - transmission gear shaft, 5a, 5c - flat rotary piston, 6a, 6c - flat rotary shaft, 7a, 7b - flat rotary gear, 8 - divider, 9a, 9b - end wall of the flat rotary rotor, 10a, 10b - bearing, 11a, 11b - shaft, 15a, 15c - transmission gear, 16a - air inlet communication port, 17 - rotary cylinder, 23a, 23b - gas storage cooling tank, 25 - inner cylindrical wall of the rotary cylinder, 26 - fixed gear, 27a, 27b - outer cylindrical wall of the rotary cylinder, 28 - explosion baffle, 29a - explosion communication port, 35a - jet duct, 44a - fixed combustion chamber, 54b - cooling gas channel, 57a, 57b - bottom housing plates of the right end of the rotary cylinder, 59 - bearing support with bearing sleeve, 60 - thrust bearing, 68 - flat rotary compressor. In the figure: Figure 16In the figure: 1 - casing, 2 - fixed shaft, 5a, 5b, 5c, 5d - flat piston, 6a, 6b, 6c, 6d - flat shaft, 8 - divider, 20a, 20b - air inlet, 21a, 21b - air outlet, 22a, 22b, 22c, 22d - flow plug, 24a - gap, 86a, 86b - flat cylinder, 69 - flat engine. In Figure 17 In the figure: 1 - casing, 11b - shaft, 17 - rotary cylinder, 18 - rotary cylinder partition, 25 - inner wall of rotary cylinder, 27a - outer wall of rotary cylinder. In Figure 18 In the figure: 1 - casing, 11b - shaft, 16a - air inlet communication port, 28 - deflagration baffle, 29a - deflagration communication port, 30a - fuel injection port, 34a - air outlet. In Figure 19 In the figure: 1 - casing, 2 - fixed shaft, 4a, 4c - transmission gear shaft, 5a, 5c - flat piston, 6a, 6c - flat shaft, 7a, 7b - flat gear, 8 - divider, 9a, 9b - flat rotor end wall, 10a, 10b - bearing, 11a, 11b - shaft, 15a, 15c - transmission gear, 16a - air inlet communication port, 17 - rotary cylinder, 25 - inner wall of rotary cylinder, 26 - fixed gear, 27a, 27b - outer wall of rotary cylinder, 28 - deflagration baffle, 29a - deflagration communication port, 44a - fixed combustion chamber, 57a - bottom shell plate of right end of rotary cylinder, 60 - thrust bearing, 66 - deflagration communication port, 69 - flat engine. In Figure 20 In the figure: 86a, 86b - flat cylinder, 1 - casing, 2 - fixed shaft, 5a, 5b, 5c, 5d - flat piston, 6a, 6b, 6c, 6d - flat shaft, 8 - divider, 21a, 21b - air outlet, 22a, 22b, 22c, 22d - flow plug, 24a, 24b - gap, 68 - flat compressor, 50b - air inlet. In Figure 21 In the figure: 1 - casing, 11a - shaft, 17 - rotary cylinder, 18 - rotary cylinder partition, 25 - inner wall of rotary cylinder, 35a - air injection port, 40 - high-pressure gas inlet, 44a - fixed combustion chamber, 45a - igniter, 50a - air inlet, 51a, 51b - air outlet, 53 - oxygen inlet, 78 - uninterrupted fuel injector. In Figure 22In the middle: 1-casing, 2-fixed shaft, 4b, 4d-transmission gear shaft, 5b, 5d-parallel rotating piston, 6b, 6d-parallel rotating shaft, 7c, 7d-parallel rotating gear, 8-separator, 9a, 9b-parallel rotating rotor end wall, 10a, 10b, 10c-bearing, 11a, 11b-shaft, 15b, 15d-transmission gear, 18-rotary cylinder partition, 25-inner circular wall of rotary cylinder, 26-fixed gear, 35a-jet duct, 44a-fixed combustion chamber, 50, 50b-intake duct, 52a, 52b-end walls at both ends of rotary cylinder, 68-parallel rotating compressor, 43-auxiliary unit. V. Detailed Implementation Methods

[0013] 1. A fan-pressure detonation engine that starts at zero forward speed, the specific structure of which is as follows: Figure 3 , Figure 4 , Figure 5 , Figure 6The fan compression deflagration engine comprises an organic shell 1, bearings 10a, 10b, a transmission shaft 3, connecting plates 79a, 79b, bevel gears 37a, 37b, igniters 45a, 45b, a compression fan 47, a diffuser 46, a mechanism 81 for spraying fuel from a fuel injection port into a rotating cylinder, an auxiliary machine 43, a shaft 11a, characterized in that the fan compression deflagration engine further comprises fixed baffles 13, air inlet communication ports 16a, 16b, outer circular walls 27a, 27b of the rotating cylinder, rotating cylinder partitions 18, an annular partition 80, a rotating cylinder 17, inner circular walls 25 of the rotating cylinder, deflagration baffles 28, deflagration communication ports 29a, 29b, jet nozzles 35a, 35b, fuel injection ports 30a, 30b, air discharge ports 34a, 34b, inner circular walls 42a, 42b of the fixed combustion chamber, and fixed combustion chambers 44a, 44b.The inner circular wall 25 of the rotary cylinder is fixedly connected to the shaft 11a by the connecting plates 79a, 79b fixed to the shaft 11a, the outer circular wall 27a, 27b of the rotary cylinder is fixedly connected to the inner circular wall 25 of the rotary cylinder by the 15 rotary cylinder partitions 18 fixed to the inner circular wall 25 of the rotary cylinder, the 15 rotary cylinder partitions divide the annular space between the inner circular wall 25 of the rotary cylinder and the outer circular wall 27a, 27b of the rotary cylinder into 15 rotary cylinders, the fixed connection body and the bevel gear 37a fixed to the shaft 11a, the annular partition 80 and the air pressure fan 47 combine to form the rotor of the engine, the interlayer space of a rotary cylinder partition 18 is divided into left and right spaces by a rectangular steel plate, cooling air enters the left space of the annular partition 80 from the shaft hole, then enters the interlayer space of the outer circular wall of the rotary cylinder through the left interlayer space of the rotary cylinder partition 18 and moves to the right, the cooling air moving to the right then enters the right space of the annular partition 80 through the right interlayer space of the rotary cylinder partition behind it, and then is discharged to the outside through the shaft hole, thereby effectively cooling the parts needed to be cooled inside the rotor, ensuring that the rotor will not be damaged due to excessive temperature inside the rotor. The air pressure fan is the fan of the turbofan engine, but it is greatly scaled down. The bearing sleeve in the middle of the diffuser, which is integrated with the diffuser, is sleeved on the bearing 10a, the bearing 10a is sleeved on the shaft 11a, the outer edge of the diffuser is fixedly connected to the casing, the outer edge of the fixed baffle 13 at the front end of the rotary cylinder is fixedly connected to the casing, two bearing sleeves are also fixedly connected to the fixed baffle 13 to limit two bearings on the transmission shaft, so that the bevel gear 37b fixedly connected to the transmission shaft and the bevel gear 37a fixed to the shaft are in meshing engagement, ensuring that the rotary power generated by the accessory 43 can be effectively transmitted to the rotor. The fixed baffle at the front end of the rotary cylinder has air inlet communication ports 16a, 16b and an axial hole that can pass through the shaft 11a. The outer edge of the deflagration baffle 28 between the rotary cylinder and the fixed combustion chamber is fixedly connected to the casing, and the axial hole in the middle is sleeved on the shaft 11a. The deflagration baffle also has deflagration communication ports 29a, 29b, fuel injection ports 30a, 30b, and air release ports 34a, 34b. When the rotor rotates, the left end of each component of the rotary cylinder engages with the fixed baffle 13 at the air inlet end, and the right end engages with the deflagration baffle 28. The engagement is small and the components rub against each other.The fan compression explosion engine works, the intake end is not communicated with the fixed combustion chamber, is by rotating cylinder one cylinder one cylinder the compressed air produced by the fan is transported to the fuel injection port position to accept the fuel injection, then is transported to the position communicated with the fixed combustion chamber to accept the explosion shock wave of the fixed combustion explosion compression, the fuel and air mixture body subjected to explosion compression is only explosion injection into the fixed combustion chamber and is ejected from the jet nozzle behind the fixed combustion chamber, so as to obtain great thrust to drive the aircraft where the fan compression explosion engine is located to hypersonic or supersonic flight, the rotating cylinder is not communicated with the fixed combustion chamber, the exhaust gas left in the rotating cylinder will be discharged to the outside through the air passage communicated with the exhaust port, the rotating cylinder is communicated with the intake port after the exhaust, the compressed air produced by the fan is received again, and the next working cycle is entered, because the fan compression explosion engine has the auxiliary machine 43 and the sub-air fan 44, therefore, the fan compression explosion engine is started under the condition that the aircraft where the fan compression explosion engine is located has zero forward speed.

[0014] 2. A explosion rotation injection engine, the specific structure of the mode is as follows Figure 7 、 Figure 8 、 Figure 9 、 Figure 10 、 Figure 11The shown explosive rotary jet engine comprises a machine shell 1, a bearing 10b, a shaft 11a, a compressor 62, a mechanism 81 for spraying fuel into the rotary cylinder from the fuel injection port, characterized in that the explosive rotary jet engine further comprises an explosive baffle 28, cooling gas passages 54a, 54b, an explosive communication port 29a, a cooling gas inlet 55, a fuel injection port 30a, an air inlet communication port 16a, a jet duct 35a, a rotor jet port 56, a rotary cylinder 17, a rotary cylinder partition plate 18, an inner circular wall 25 of the rotary cylinder, an outer circular wall 27a, 27b of the rotary cylinder, a bottom shell plate 57a, 57b at the right end of the rotary cylinder, a cooling gas outlet 58a, 58b, a fixed combustion chamber 44a, a thrust bearing 60, and a bearing support 59 integrated with the bearing sleeve; the compressor 62 can be a low-pressure compressor part of a turbofan engine or other compressors, including a starting motor, and the compressor can share the shaft 11a and support the shaft 11a with a bearing support, and the compressor does not need to generate too much gas pressure, the bottom shell plate 57a, 57b at the right end of the rotary cylinder is first fixedly connected to the shaft 11a, then the inner circular wall 25 of the rotary cylinder and the outer circular wall 27a, 27b of the rotary cylinder are fixedly connected to the bottom shell plate at the right end of the rotary cylinder, and then the 10 rotary cylinder partition plates 18 are fixedly connected to the annular groove between the inner circular wall 25 of the rotary cylinder and the outer circular wall 27a, 27b of the rotary cylinder, and the 10 rotary cylinder partition plates divide the annular groove into 10 rotary cylinders with the same shape, the above-mentioned fixed connection body connected together and the parts in the compressor 62 that should be fixedly connected to the shaft 11a form a rotor of the explosive rotary jet engine, when the rotor rotates, the left end of the part forming the rotary cylinder is in contact with the explosive baffle, the hole in the middle of the explosive baffle 28 is sleeved on the shaft 11a, the outer edge is fixedly connected to the machine shell, the outer edge of the bearing support 59 integrated with the bearing sleeve is fixedly connected to the machine shell, the middle bearing sleeve is sleeved on the bearing 10b, the cooling gas enters the annular space between the inner circular wall 25 of the rotary cylinder and the shaft 11a from the cooling gas inlet 55, then enters the interlayer space of the outer circular wall 27a, 27b of the rotary cylinder through the interlayer space of the rotary cylinder partition plate 18, and then flows out from the cooling gas outlet 58a, 58b, and each outer circular wall of the rotary cylinder is provided with a rotor jet port 56, if the explosive rotary jet engine is used to generate rotary power, the rotor jet port should be tangentially jetted, and the gas outlet of the jet duct 35a should be larger, if the explosive rotary jet engine is used as a jet engine, the intersection angle between the center line of the rotor jet port and the radius should be about 130 degrees, and the gas outlet of the jet duct 35a should be smaller, and the explosive rotary jet engine can be started by the starting motor in the state without forward speed, after the explosive rotary jet engine is started, the compressed air generated by the compressor 62 will enter the rotary cylinder from the air inlet communication port 16a, when the rotary cylinder of the explosive rotary jet engine rotates to communicate with the air inlet communication port 16a,The compressed air after being pressurized by the compressor 62 will quickly enter the rotating cylinder, when the rotating cylinder continues to rotate to the position of the fuel injection port 30a after leaving the intake port, the rotating cylinder starts to communicate with the fixed combustion chamber, the explosion in the fixed combustion chamber enters the rotating cylinder from one side, and the fuel and air mixture in the rotating cylinder is explosively compressed and burned, then constant volume heating, when the rotating cylinder rotates to the position that the opening of the rotating cylinder is completely opposite to the fixed combustion chamber, the burned fuel and air mixture in the rotating cylinder explodes and expands into the fixed combustion chamber, and is injected into the jet pipe from the rotor jet port communicating with the fixed combustion chamber, so as to obtain the rotating thrust to drive the rotor to rotate, at the same time, the explosion gas injected into the jet pipe is sprayed backward from the jet pipe, so as to obtain a great propulsive force to drive the aircraft where the rotating explosion jet engine is located to fly at a hypersonic speed, when the rotating cylinder continues to rotate to the position that the rotating cylinder does not communicate with the fixed combustion chamber, the gas left in the rotating cylinder continues to be sprayed from the rotor jet port, when the rotating cylinder rotates to the position that the rotor jet port is blocked by the inner wall of the casing, the gas in the rotating cylinder is basically sprayed out, when the rotating cylinder rotates to the position that the rotating cylinder communicates with the intake port 16a, the compressed air after being pressurized by the compressor 62 quickly enters the rotating cylinder again, and enters the next working cycle.

[0015] 3. A flat explosion engine, the specific structure of this mode is as follows Figure 12 、 Figure 13 、 Figure 14 、 Figure 7 、 Figure 8 、 Figure 9 、 Figure 15The flat rotary engine is shown, including organic shell 1, flat rotary rotor end wall 9a, 9b, fixed shaft 2, flat rotary cylinder 86a, 86b, flat rotary shaft 6a, 6b, 6c, 6d, flat rotary gear 7a, 7b, 7c, 7d, transmission gear 15a, 15b, 15c, 15d, transmission gear shaft 4a, 4b, 4c, 4d, fixed gear 26, cooling gas passage 54a, 54b, shaft 11a, 11b, cooling gas inlet 55, deflagration baffle 28, deflagration communication port 29a, air intake communication port 16a, fuel injection port 30a, rotary cylinder 17, rotor air injection port 56, air injection channel 35a, rotary cylinder partition 18, rotary cylinder outer circular wall 27a, 27b, rotary cylinder inner circular wall 25, rotary cylinder right end bottom shell plate 57a, 57b, cooling gas outlet 58a, 58b, bearing 10a, 10b, fixed combustion chamber 44a, bearing support 59 integrated with bearing sleeve, thrust bearing 60, flat rotary compressor 68, characterized in that the flat rotary engine further includes air inlet 20a, 20b, air outlet 21a, 21b, flow blocking plug 22a, 22b, 22c, 22d, gap 24a, 24b, flat rotary piston 5a, 5b, 5c, 5d, divider 8, gas storage cooling groove 23a, 23b.The gear defines the pivot shaft and the pivot piston can only rotate in parallel, that is, the direction of the upper edge of the pivot piston during rotation is always unchanged, the pivot gear 7a, the pivot shaft 6a and the pivot piston 5a are a fixed connection body, the flow blocking plug 22a, 22b, 22c, 22d is fixed between the pivot rotor end wall 9a and the pivot rotor end wall 9b, the pivot rotor end wall 9a, 9b is fixedly connected to the shaft 11a, the divider is fixedly connected to the shell through the fixed shaft, and the narrowest passage between the divider and the shell is called the aperture 24a, 24b, which only allows the pivot piston, the pivot shaft and the flow blocking plug to pass through, and does not allow gas to pass through. When the flat compression and explosion engine rotates, the air entering the pivot cylinder 86b from the air inlet 20a is compressed by the pivot piston 5c and then enters the gas storage cooling groove 23a, 23b through the gas passage connected with the exhaust port 21b. The air entering the pivot cylinder 86a from the air inlet 20b is compressed by the pivot piston 5a and then enters the gas storage cooling groove 23a, 23b through the gas passage connected with the exhaust port 21a. When the rotating cylinder rotates to be connected with the gas storage cooling groove through the air inlet communication port 16a, the compressed gas in the gas storage cooling groove will quickly enter the rotating cylinder through the air inlet communication port. When the rotating cylinder continues to rotate, leaves the air inlet communication port and reaches the position of the fuel injection port 30a to receive fuel injected from the fuel injection port, the rotating cylinder starts to communicate with the fixed combustion chamber, and the explosion of the mixed fuel and air in the rotating cylinder is compressed and burned to heat the mixed fuel and air. When the rotating cylinder rotates to the position where the opening of the rotating cylinder is completely opposite to the fixed combustion chamber, the mixed combustion gas in the rotating cylinder expands and explodes into the fixed combustion chamber, and then is injected into the jet duct through the rotor jet port connected with the fixed combustion chamber, so that rotary power is obtained to drive the rotor to rotate. At the same time, the explosion gas injected into the jet duct is ejected from the jet duct, so that a large propulsive force is obtained to drive the aircraft where the flat compression and explosion engine is located to fly at hypersonic speed. The rotating cylinder continues to rotate to the position where the jet port of the rotor jet port is blocked by the inner wall of the shell, and the gas in the rotating cylinder is basically exhausted, and then reaches the position of the air inlet communication port 16a to receive the compressed gas in the gas storage cooling groove for the next working cycle.

[0016] 4. A rotating power explosion flat rotation engine, the specific structure of the mode is as follows Figure 12 、 Figure 16 、 Figure 14 、 Figure 18 、 Figure 17 、 Figure 9 、 Figure 19As shown, the flat-rotating explosion engine comprises a housing 1, flat-rotating rotor end walls 9a, 9b, a fixed shaft 2, flat-rotating pistons 5a, 5b, 5c, 5d, flat-rotating shafts 6a, 6b, 6c, 6d, a divider 8, air inlets 20a, 20b, air outlets 21a, 21b, block flow plugs 22a, 22b, 22c, 22d, a narrow opening 24a, flat-rotating cylinders 86a, 86b, flat-rotating gears 7a, 7b, 7c, 7d, transmission gears 15a, 15b, 15c, 15d, transmission gear shafts 4a, 4b, 4c, 4d, bearings 10a, 10b, a fixed gear 26, a fixed combustion chamber 44a, an air communication opening 16a, an explosion baffle 28, an explosion communication opening 29a, shafts 11a, 11b, a fuel injection opening 30a, an air outlet 34a, a rotary cylinder 17, a rotary cylinder partition 18, an inner circular wall 25 of the rotary cylinder, a thrust bearing 60, outer circular walls 27a, 27b of the rotary cylinder, bottom shell plates 57a, 57b at the right end of the rotary cylinder, and cooling gas outlets 58a, 58b. The flat-rotating explosion engine further comprises an explosion communication opening 66 and a flat-rotating engine 69. A flat-rotating piston, a flat-rotating shaft and a flat-rotating gear form a fixed connection body, which can only rotate in parallel through gear transmission. When the flat-rotating explosion engine rotates, air entering the flat-rotating cylinder 86b from the air inlet 20b is pushed by the flat-rotating piston 5a to become compressed air and is then discharged from the air outlet 21a. The compressed air discharged from the air outlet 21a enters the rotary cylinder through a gas passage connected with the air outlet 21a and the air communication opening 16a. When the rotary cylinder, which has already entered the compressed air, rotates to the position of the fuel injection opening 30a to receive fuel injected from the fuel injection opening, the rotary cylinder gradually communicates with the fixed combustion chamber. The mixture of compressed air and fuel in the rotary cylinder is ignited and exploded by the explosion of the fixed combustion chamber, generating an explosion shock wave. The explosion shock wave enters the flat-rotating cylinder 86a through a gas passage between the explosion communication opening 66 and the air inlet 20a, pushing the flat-rotating piston to rotate in parallel and doing work to the outside world. After the gas doing work to push the flat-rotating piston to rotate in parallel is completed, the gas is discharged from the air outlet 21b. After the mixture in the rotary cylinder is ignited, the rotary cylinder continues to rotate away from the fixed combustion chamber. After the gas remaining in the rotary cylinder is discharged from the air outlet 34a to the outside world, the rotary cylinder receives the compressed air pushed by the flat-rotating piston again, entering the next working cycle.

[0017] 5. An explosion engine, the specific structure of which is shown in Figure 12 、 Figure 20 、 Figure 14 、 Figure 21 、 Figure 22The shown engine includes organic shell 1, flat rotating rotor end wall 9a, 9b, flat rotating shaft 6a, 6b, 6c, 6d, fixed shaft 2, flat rotating cylinder 86a, 86b, flat rotating piston 5a, 5b, 5c, 5d, divider 8, exhaust port 21a, 21b, block flow plug 22a, 22b, 22c, 22d, narrow opening 24a, 24b, flat rotating compressor 68, air inlet 50a, 50b, flat rotating gear 7a, 7b, 7c, 7d, transmission gear 15a, 15b, 15c, 15d, transmission gear shaft 4a, 4b, 4c, 4d, rotating cylinder 17, rotating cylinder partition 18, inner circular wall of rotating cylinder 25, jet channel 35a, fixed combustion chamber 44a, igniter 45a, air exhaust channel 51a, 51b, uninterrupted fuel injector 78, bearing 10a, 10b, 10c, shaft 11a, 11b, fixed gear 26, end wall 52a, 52b at both ends of rotating cylinder, accessory 43, characterized in that the engine further includes high pressure gas inlet 40, oxygen inlet 53; a flat rotating piston, a flat rotating shaft and a flat rotating gear form a fixed connection body, which is limited to parallel rotation of the flat rotating piston through gear transmission, the gas switch on the oxygen inlet 53 is closed in normal time, and is opened only when the gas entering the rotating cylinder cannot meet the needs of deflagration, so that oxygen enters the rotating cylinder to assist combustion, and is closed when oxygen is not needed to assist combustion, the high pressure air discharged from the exhaust port 21a and the exhaust port 21b enters the rotating cylinder through the gas passage from the high pressure gas inlet 40, when the engine drives a hypersonic aircraft, the openings of the air inlet 50a, 50b face forward, the incoming flow enters the rotating cylinder from the air inlet 50a, the incoming flow enters the flat rotating cylinder 86a, 86b from the air inlet 50b, the gas entering the flat rotating cylinder 86a, 86b is pushed by the flat rotating piston 5a, 5c to become high pressure gas, and then enters the rotating cylinder through the gas passage to mix with the gas entering from the air inlet 50a, so that there is sufficient high pressure gas in the rotating cylinder, when the rotating cylinder rotates to receive the injected fuel through the uninterrupted fuel injector 78, the rotating cylinder gradually communicates with the fixed combustion chamber 44a, the explosion of the fixed combustion chamber compresses and detonates the mixture of high pressure gas and fuel in the rotating cylinder, the deflagration of the mixture of high pressure gas and fuel produces a violent shock wave from the jet channel 35a, thereby obtaining a huge propulsive force to drive the aircraft where the engine is located to fly at hypersonic speed or supersonic speed, when the rotating cylinder continues to rotate to leave the fixed combustion chamber, the exhaust gas remaining in the rotating cylinder is discharged from the air exhaust channel 51a, 51b, and then the rotating cylinder receives the incoming flow from the air inlet to enter the next working cycle, because the engine includes an accessory and a flat rotating compressor, the engine can be started without forward speed.

Claims

1. A detonation engine with its intake end not connected to a fixed combustion chamber and the pressure at the rear of the combustion chamber being much greater than the pressure at the front, comprising an intake duct (50a), an air guide (89), bearings (10a, 10b), and a shaft (11a), wherein the detonation engine is mounted on an aircraft (77), characterized in that... The explosion engine further comprises an organic shell (1), a rotating cylinder (17), a fixed combustion chamber (44a), end walls (52a, 52b) at both ends of the rotating cylinder, rotating cylinder partitions (18), an inner circular wall (25) of the rotating cylinder, an uninterrupted fuel injector (78), an igniter (45a), a jet channel (35a), a blocking plate (88), and air release channels (51a, 51b); the inner circular wall of the rotating cylinder is fixedly connected to the shaft through the end walls at both ends of the rotating cylinder to form an annular groove, and the annular groove is equally divided into 12 identical rotating cylinders through 12 rotating cylinder partitions; the two ends of the rotating cylinder partitions are sealingly and fixedly connected to the end walls at both ends of the rotating cylinder, and the inner side is sealingly and fixedly connected to the inner circular wall of the rotating cylinder; the rotating cylinder partitions are hollow plates, i.e., the rotating cylinder partitions have sandwiched spaces; cooling air enters the left space inside the inner circular wall of the rotating cylinder from the air holes in the end wall at the left end of the rotating cylinder, then enters the sandwiched space of the rotating cylinder partitions to cool the rotating cylinder partitions, and then passes through the right space inside the inner circular wall of the rotating cylinder and the air holes in the end wall at the right end of the rotating cylinder to be discharged to the outside; the rotor is composed of the shaft, the end walls at both ends of the rotating cylinder, the inner circular wall of the rotating cylinder, and the rotating cylinder partitions; the movement track of the rotor when rotating is tangent to the inner wall of the shell, i.e., the gap between the inner wall of the shell and the rotor is particularly small, but the rotation of the rotor is not hindered by the inner wall of the shell; the bearings at both ends of the rotor are limited on the shell by the corresponding bearing sleeves.The bearing sleeve, the casing, the air inlet, the fixed combustion chamber, the jet and the air outlet are a fixed connection whole, which is fixedly installed on the aircraft. When the flight speed of the aircraft installed with the explosion engine is greater than 120 kilometers per hour, the oncoming flow entering from the air inlet, that is, the ramjet flow, can enter the rotating cylinder and push the rotor to rotate at high speed by pushing the rotating cylinder partition. When the rotating cylinder rotates to the position of the uninterrupted fuel injector, the outer edge of the rotating cylinder is tangent to the inner wall of the casing, and the internal space is not connected with the outside world. The fuel injected by the uninterrupted fuel injector is mixed with the air in the rotating cylinder uniformly. When the rotating cylinder continues to rotate to the position that the internal space is connected with the fixed combustion chamber, the explosion shock wave in the fixed combustion chamber can explode and compress the mixture of fuel and air in the rotating cylinder, so that the mixture of fuel and air explodes and burns in the fixed combustion chamber. Subsequently, the explosion shock wave ignites the mixture of fuel and air in the rear rotating cylinder, and the explosion engine is ignited and exploded in this way, so as to generate great propulsive force to drive the aircraft to fly at hypersonic speed or supersonic speed, and the aircraft can also fly at subsonic speed if necessary. When the rotating cylinder continues to rotate to the position that it is not connected with the fixed combustion chamber, but is connected with the air outlet, the remaining burned gas in the rotating cylinder is discharged from the air outlet. When the rotating cylinder continues to rotate to the position that it is connected with the air outlet and the air inlet, the ramjet flow entering from the air inlet enters the rotating cylinder to clean the rotating cylinder, so that the waste gas remaining in the rotating cylinder flows out of the air outlet. When the rotating cylinder continues to rotate to the position that it is connected with the air inlet, the ramjet flow reenters the rotating cylinder and pushes the rotor to rotate at high speed, and enters the next working cycle. The explosion engine is mixed with the fuel uniformly, and then the mixture is compressed by the explosion shock wave and mixed with the explosion flame, and then explodes. The air inlet of the explosion engine is not connected with the fixed combustion chamber, and the air in the air inlet is transported to the fixed combustion chamber by the rotating cylinder one cylinder by one cylinder, so that the jet of the explosion engine can be very small, and can be as small as one tenth of the air inlet.

2. A zero advance speed starting fan-staged deflagration engine comprising a housing (1), bearings (10a, 10b), a drive shaft (3), connecting plates (79a, 79b), bevel gears (37a, 37b), igniters (45a, 45b), a compression fan (47), a diffuser (46), a mechanism (81) for injecting fuel from a fuel injection port into a rotating cylinder, an attachment (43), a shaft (11a), characterized in that The fan compression explosion engine also includes fixed baffle (13), air inlet communication port (16a, 16b), rotating cylinder outer wall (27a, 27b), rotating cylinder partition (18), annular partition (80), rotating cylinder (17), rotating cylinder inner wall (25), explosion baffle (28), explosion communication port (29a, 29b), jet (35a, 35b), fuel injection port (30a, 30b), air vent (34a, 34b), fixed combustion chamber inner wall (42a, 42b), fixed combustion chamber (44a, 44b); the inner wall (25) of the rotating cylinder is fixedly connected to the shaft (11a) through the connecting plate (79a, 79b) fixed to the shaft (11a), the outer wall (27a, 27b) of the rotating cylinder is fixedly connected to the inner wall (25) of the rotating cylinder through the 15 rotating cylinder partitions (18) fixedly connected to the inner wall (25) of the rotating cylinder, the 15 rotating cylinder partitions divide the annular space between the inner wall (25) of the rotating cylinder and the outer wall (27a, 27b) of the rotating cylinder into 15 rotating cylinders, the fixed connection body is combined with the bevel gear (37a) fixed to the shaft (11a), the annular partition (80) and the air compression fan (47) to form the rotor of the engine: when the fan compression explosion engine works, the air inlet end is not communicated with the fixed combustion chamber, and the compressed air generated by the air compression fan is transported to the position of the fuel injection port to receive the injected fuel, and then transported to the position communicated with the fixed combustion chamber to receive the explosion compression of the explosion shock wave of the fixed combustion, only the fuel and air mixture subjected to the explosion compression can explode and inject into the fixed combustion chamber and be injected out of the jet behind the fixed combustion chamber, so as to obtain great thrust to drive the aircraft where the fan compression explosion engine is located to fly at hypersonic speed or supersonic speed, when the rotating cylinder is not communicated with the fixed combustion chamber, the exhaust gas remaining in the rotating cylinder will be discharged to the outside through the air duct communicated with the air vent, when the rotating cylinder is communicated with the air inlet communication port, the compressed air generated by the air compression fan is received again to enter the next working cycle.

3. A deflagration engine comprising a housing (1), a bearing (10b), a shaft (11a), a compressor (62), a mechanism (81) for injecting fuel from a fuel injection port into a rotating cylinder, characterized in that The engine also comprises deflagration baffle (28), cooling gas passage (54a, 54b), deflagration communication port (29a), cooling gas inlet (55), fuel injection port (30a), air intake communication port (16a), jet duct (35a), rotor jet port (56), rotary cylinder (17), rotary cylinder partition (18), inner circular wall of rotary cylinder (25), outer circular wall of rotary cylinder (27a, 27b), bottom shell plate of rotary cylinder right end (57a, 57b), cooling gas outlet (58a, 58b), fixed combustion chamber (44a), thrust bearing (60), bearing support (59) integrated with bearing sleeve; first, the bottom shell plate of rotary cylinder right end (57a, 57b) is fixedly connected to shaft (11a), then the inner circular wall of rotary cylinder (25) and the outer circular wall of rotary cylinder (27a, 27b) are fixedly connected to the bottom shell plate of rotary cylinder right end, and then 10 rotary cylinder partitions (18) are fixedly connected to the annular groove between the inner circular wall of rotary cylinder and the outer circular wall of rotary cylinder, and the 10 rotary cylinder partitions divide the annular groove into 10 rotary cylinders with the same shape; the fixed connection body connected above is combined with the components in the compressor (62) that should be fixedly connected to the shaft (11a) to form the rotor of the engine; the engine can be started by starting motor in the state without forward speed; after the engine is started, the compressed air generated by the compressor (62) enters the rotary cylinder through the air intake communication port (16a); when the rotary cylinder of the engine rotates to the position communicated with the air intake communication port (16a), the compressed air after being pressurized by the compressor (62) enters the rotary cylinder quickly; when the rotary cylinder continues to rotate to the position of fuel injection port (30a) to receive the fuel injected from the fuel injection port, the rotary cylinder starts to communicate with the fixed combustion chamber, the deflagration in the fixed combustion chamber enters the rotary cylinder from one side to explosively compress and burn the fuel and air mixture in the rotary cylinder, and then constant volume heating is performed; when the rotary cylinder rotates to the position where the opening of the rotary cylinder is completely opposite to the fixed combustion chamber, the burned fuel and air mixture in the rotary cylinder expands and explodes into the fixed combustion chamber, and then is injected into the jet duct from the rotor jet port communicated with the fixed combustion chamber, so that rotary thrust is obtained to drive the rotor to rotate; at the same time, the deflagration gas injected into the jet duct is sprayed backward from the jet duct, so that great propulsion is obtained to drive the aircraft where the engine is located to fly at hypersonic speed; when the rotary cylinder continues to rotate to the position where the rotary cylinder is not communicated with the fixed combustion chamber, the gas remaining in the rotary cylinder continues to be sprayed from the rotor jet port; when the rotary cylinder rotates to the position where the rotor jet port is blocked by the inner wall of the shell, the gas in the rotary cylinder is basically sprayed; when the rotary cylinder rotates to the position communicated with the air intake communication port (16a), the compressed air after being pressurized by the compressor (62) enters the rotary cylinder quickly, and the next working cycle starts.

4. A flat compression deflagration engine comprising a housing (1), flat rotating rotor end walls (9a, 9b), a fixed shaft (2), flat rotating cylinders (86a, 86b), flat rotating shafts (6a, 6b, 6c, 6d), flat rotating gears (7a, 7b, 7c, 7d), transmission gears (15a, 15b, 15c, 15d), transmission gear shafts (4a, 4b, 4c, 4d), fixed gears (26), cooling gas channels (54a, 54b), shafts (11a, 11b), cooling gas inlets (55), deflagration baffles (28), deflagration communication ports (29a), air intake communication ports (16a), fuel injection inlets (30a), rotating cylinders (17), rotor air injection ports (56), air injection channels (35a), rotating cylinder partitions (18), rotating cylinder outer circular walls (27a, 27b), rotating cylinder inner circular walls (25), rotating cylinder right end bottom housing plates (57a, 57b), cooling gas outlets (58a, 58b), bearings (10a, 10b), fixed combustion chambers (44a), bearing supports (59) integrated with bearing sleeves, thrust bearings (60), flat rotating compressors (68), characterized in that The flat compression explosion engine also includes air inlet (20a, 20b), exhaust port (21a, 21b), block flow plug (22a, 22b, 22c, 22d), gap (24a, 24b), flat rotating piston (5a, 5b, 5c, 5d), divider (8), gas storage cooling tank (23a, 23b); through the gear limit flat rotating shaft and flat rotating piston can only parallel rotation, that is, the direction of the upper edge of the flat rotating piston during rotation is always unchanged, flat rotating gear (7a), flat rotating shaft (6a) and flat rotating piston (5a) are a fixed connection body, block flow plug (22a, 22b, 22c, 22d) is fixed between flat rotating rotor end wall (9a) and flat rotating rotor end wall (9b), flat rotating rotor end wall (9a, 9b) is fixedly connected on shaft (11a), the divider is fixedly connected on the shell through the fixed shaft, the narrowest channel between the divider and the shell is called gap (24a, 24b), which only allows flat rotating piston, flat rotating shaft and block flow plug to pass through, and does not allow gas to pass through, when the flat compression explosion engine rotates, the air entering the flat rotating cylinder (86b) from the air inlet (20a) is compressed by the flat rotating piston (5c) and then enters the gas storage cooling tank (23a, 23b) through the gas passage connected with the exhaust port (21b), the air entering the flat rotating cylinder (86a) from the air inlet (20b) is compressed by the flat rotating piston (5a) and then enters the gas storage cooling tank (23a, 23b) through the gas passage connected with the exhaust port (21a), when the rotating cylinder rotates to be connected with the gas storage cooling tank through the air inlet communication port (16a), the compressed gas in the gas storage cooling tank will quickly enter the rotating cylinder through the air inlet communication port, when the rotating cylinder continues to rotate, leaves the air inlet communication port and reaches the position of the fuel injection port (30a) to receive the fuel injected from the fuel injection port, the rotating cylinder starts to communicate with the fixed combustion chamber, the explosion of the fixed combustion chamber in the mixed fuel and air mixture in the rotating cylinder is compressed and burned, when the rotating cylinder rotates to its opening completely facing the fixed combustion chamber, the mixed combustion gas in the rotating cylinder expands and explodes into the fixed combustion chamber, and then is injected into the jet pipe from the rotor jet port connected with the fixed combustion chamber, so that rotary power is obtained to drive the rotor to rotate, at the same time, the explosion gas injected into the jet pipe is injected out of the jet pipe, so that great propulsion is obtained to drive the aircraft where the flat compression explosion engine is located to fly at hypersonic speed, the rotating cylinder continues to rotate to the position where the jet port of the rotor jet port is blocked by the inner wall of the shell, and after the internal gas is basically injected, it reaches the position of the air inlet communication port (16a) to receive the compressed gas in the gas storage cooling tank for the next working cycle.

5. A rotary power production engine of deflagration, comprising a housing (1), a flat rotating rotor end wall (9a, 9b), a fixed shaft (2), a flat rotating piston (5a, 5b, 5c, 5d), a flat rotating shaft (6a, 6b, 6c, 6d), a divider (8), an air inlet (20a, 20b), an air outlet (21a, 21b), a flow blocking plug (22a, 22b, 22c, 22d), a gap (24a), a flat rotating cylinder (86a, 86b), a flat rotating gear (7a, 7b, 7c, 7d), a transmission gear (15a, 15b, 15c, 15d), a transmission gear shaft (4a, 4b, 4c, 4d), a bearing (10a, 10b), a fixed gear (26), a fixed combustion chamber (44a), an air inlet communication port (16a), a deflagration baffle (28), a deflagration communication port (29a), a shaft (11a, 11b), a fuel injection port (30a), a gas exhaust port (34a), a rotating cylinder (17), a rotating cylinder partition (18), an inner circular wall of the rotating cylinder (25), a thrust bearing (60), an outer circular wall of the rotating cylinder (27a, 27b), a bottom shell plate at the right end of the rotating cylinder (57a, 57b), a cooling gas outlet (58a, 58b), characterized in that The present explosive flat rotation engine also includes an explosion communication port (66), the flat rotation engine (69): a flat rotation piston, a flat rotation shaft and a flat rotation gear constitute a fixed connection body, through gear transmission to limit the fixed connection body can only parallel rotation, the present explosive flat rotation engine rotates, the air entering the flat rotation cylinder (86b) from the air inlet (20b) is pushed by the parallel rotating flat rotation piston (5a) into compressed air and then discharged from the exhaust port (21a), the compressed air discharged from the exhaust port (21a) enters the rotating cylinder through the gas passage communicated with the exhaust port (21a) and the air inlet communication port (16a), when the rotating cylinder has entered the compressed air rotates to the position of the fuel injection port (30a) to accept the fuel injected from the fuel injection port, the rotating cylinder gradually communicates with the fixed combustion chamber, the compressed air and fuel mixture in the rotating cylinder is subjected to explosive compression by the explosion of the fixed combustion chamber to produce an explosion shock wave, the explosion shock wave enters the flat rotation cylinder (86a) through the gas passage between the explosion communication port (66) and the air inlet (20a) to push the flat rotation piston to rotate parallel to the outside, after the gas pushing the flat rotation piston to rotate parallel does work, it is discharged from the exhaust port (21b), after the mixture in the rotating cylinder is detonated, the rotating cylinder continues to rotate away from the fixed combustion chamber, the gas left in the rotating cylinder is discharged from the exhaust port (21b), after the gas left in the rotating cylinder is discharged from the exhaust port (21b), the rotating cylinder receives the gas compressed by the flat rotation piston again, and enters the next working cycle.

6. A deflagration engine comprising a housing (1), a flat rotating rotor end wall (9a, 9b), a flat rotating shaft (6a, 6b, 6c, 6d), a fixed shaft (2), a flat rotating cylinder (86a, 86b), a flat rotating piston (5a, 5b, 5c, 5d), a divider (8), an exhaust port (21a, 21b), a choke plug (22a, 22b, 22c, 22d), a choke (24a, 24b), a flat rotating compressor (68), an intake port (50a, 50b), a flat rotating gear (7a, 7b, 7c, 7d), a drive gear (15a, 15b, 15c, 15d), a drive gear shaft (4a, 4b, 4c, 4d), a rotating cylinder (17), a rotating cylinder partition (18), a rotating cylinder inner circular wall (25), a jet port (35a), a fixed combustion chamber (44a), an igniter (45a), a bleeder port (51a, 51b), a continuous fuel injector (78), a bearing (10a, 10b, 10c), a shaft (11a, 11b), a fixed gear (26), a rotating cylinder end wall (52a, 52b), an attachment (43), characterized in that The engine also includes a high-pressure gas inlet (40), an oxygen inlet (53), a flat rotating piston, a flat rotating shaft and a flat rotating gear, which are combined into a fixed connection body, and the flat rotating piston can only rotate in parallel through gear transmission. The gas switch on the oxygen inlet (53) is closed in normal time, and only when the gas entering the rotating cylinder cannot meet the needs of deflagration, the gas switch on the oxygen inlet is opened to let oxygen enter the rotating cylinder to assist combustion, and when oxygen is not needed to assist combustion, the gas switch on the oxygen inlet is closed. The high-pressure air discharged from the exhaust port (21a) and the exhaust port (21b) enters the rotating cylinder through the gas passage from the high-pressure gas inlet (40). When the aircraft is flying at hypersonic speed, the opening of the air inlet (50a, 50b) is directed to the front, and the incoming flow enters the rotating cylinder from the air inlet (50a), and the incoming flow enters the flat rotating cylinder (86a, 86b) from the air inlet (50b). The gas entering the flat rotating cylinder (86a, 86b) is pushed by the flat rotating piston (5a, 5c) to become high-pressure gas and then enters the rotating cylinder through the gas passage to mix with the gas entering from the air inlet (50a), so that there is sufficient high-pressure gas in the rotating cylinder. When the rotating cylinder rotates through the uninterrupted fuel injector (78) to receive the injected fuel, the rotating cylinder gradually communicates with the fixed combustion chamber (44a), the explosion of the fixed combustion chamber explosively compresses and detonates the mixture of high-pressure gas and fuel in the rotating cylinder, and the deflagration of the mixture of high-pressure gas and fuel produces a violent shock wave from the jet nozzle (35a), thereby obtaining a huge propulsive force to drive the aircraft where the engine is located to fly at hypersonic or supersonic speed. When the rotating cylinder continues to rotate away from the fixed combustion chamber, the exhaust gas remaining in the rotating cylinder is discharged from the exhaust port (51a, 51b), and the rotating cylinder receives the incoming flow from the air inlet to enter the next working cycle. Because the engine includes an auxiliary machine and a flat rotating compressor, the engine can start without forward speed.

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