Universal aircraft for vertical take-off and landing
Through high -voltage and high -density controlled combustion and pulse combustion technology, the problem of insufficient power and low efficiency of existing aircraft has been solved, and efficient advancement and continuous flight have been realized, and the ability to fly in Star.
Patent Information
- Application Number
- CN202411661881.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-20
- Publication Date
- 2025-01-21
AI Technical Summary
Existing aircraft have problems such as insufficient power, low efficiency, poor safety and inability to achieve long-term continuous combustion propulsion, especially under the demand for interstellar flight.
Using high-pressure and high-density controllable combustion as the main power, high-temperature and high-pressure gas is generated through pulse combustion, and is stored and continuously boosted. The injection is controlled through specific injection channels as needed to achieve stable output and efficient propulsion.
In the case of the consumption of the same energy fuel, the gas jet speed and thrust have been increased several times, extending the flight time, and have the ability to fly in interstellar flight.
Smart Images
Figure CN119329752A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aircraft, and relates to a vertical take-off and landing general aircraft. Background Art
[0002] Since the invention of airplanes, human beings have never stopped their desire for free flight, but they have always stopped at the research of primary flight technology. The basic principles of aircraft have not changed qualitatively, and the way to get rid of the earth's gravity has not changed much, almost not as good as birds. In particular, flight away from the earth is still limited to the circular centrifugal method.
[0003] Generally, fixed-wing aircraft use the difference in surface curvature between the wing and the fuselage to achieve different airflow speeds on the upper and lower surfaces of the wing and fuselage to generate a pressure difference and achieve lift. However, its efficiency is low and it cannot achieve large-scale takeoff loads. It also has low efficiency and poor safety.
[0004] Jet aircraft use the power generated by the engine combustion chamber to drive the compressor to operate. The inhaled air is pressurized and then enters the combustion chamber to mix with the fuel for combustion. This is a semi-open physical process. The pressure that the compressor can reach becomes the basic pressure of the combustion chamber. The heat generated by the combustion causes the gas volume to expand and do work. The pressure increase generated is subject to the structure and is not as good as the sealing condition. The compressor's boost is subject to the material and structural mode. It is currently difficult to reach 30 times. The gas pressure entering the combustion chamber does not exceed 3MPa. After the combustion heat is generated, the gain multiple is almost difficult to exceed 10 times, which limits the maximum pressure that the engine jet can reach to 30M, resulting in a jet speed that is difficult to exceed 3000 meters / second, limiting the thrust of the aircraft.
[0005] Due to insufficient power, the lifting force of the wings and fuselage needs to be generated by moving the aircraft to a certain speed. The aircraft needs a runway and a specific site to take off and land, which limits the usage scenarios and is also limited to the air density range, making it difficult to utilize the upper space of the air layer.
[0006] Rockets generally use oxygen and fuel to burn directly in the combustion chamber, which is much more efficient than using air combustion. Since the combustion chamber generally used is semi-open, the high-temperature gas generated by the combustion is directly ejected to form thrust. The general temperature cannot exceed 3000 degrees Celsius, and the injection speed is difficult to exceed 3000 meters per second. The fuel utilization rate is very low. It is impossible to form long-term continuous combustion propulsion and it is difficult to adapt to the needs of interstellar flight. The combustion of rockets is similar to the technical weaknesses of jet aircraft. It is semi-open combustion, with almost no control over the combustion state. The gas pressure is insufficient, resulting in insufficient injection speed, insufficient jet propulsion force, and low fuel efficiency. It is not suitable for long-term continuous power.
[0007] Rotorcraft use blades that rotate rapidly at a specific angle to pressurize gas downward and backward to generate thrust. This is extremely inefficient, has limited lifting force, and cannot achieve ideal and efficient movement. Summary of the invention
[0008] In order to solve the above technical problems, the present invention provides a general-purpose vertical take-off and landing aircraft, which adopts high-pressure and high-density controlled combustion as the main power, and stores the high-temperature and high-pressure gas generated by the combustion for continuous boost, and then injects it at a certain flow rate through a set channel as needed, which can create a stable temperature of more than 3000 degrees Celsius and a continuous pressure of more than 170MPa, achieve stable output, and the injection flow rate can be stably controlled at more than 7000 meters / second.
[0009] The technical solution adopted by the present invention is:
[0010] A general-purpose aircraft for vertical take-off and landing comprises a sealed shell, wherein an equipment cabin is arranged in the sealed shell, wherein the equipment cabin comprises an air storage tank for providing high-pressure air, a primary gas storage tank, a secondary gas storage tank, a generator, a burner assembly, an oxygen storage tank, a fuel storage tank, and an injection assembly, wherein the burner assembly is respectively connected with the oxygen storage tank, the fuel storage tank, the generator, and the primary gas storage tank, wherein the air storage tank and the primary gas storage tank can both be connected with the secondary gas storage tank, wherein the secondary gas storage tank is connected with the injection assembly, wherein the injection assembly comprises a lift jet and an upper jet for injection during the take-off and landing phase, a propulsion jet, a deceleration and braking jet, and a steering jet for injection during the flight phase, wherein the lift jet and the upper jet are arranged vertically opposite to each other, wherein the propulsion jet and the deceleration and braking jet are arranged horizontally opposite to each other, and wherein the steering jet is arranged horizontally, wherein during the take-off and landing phase, the air storage tank is connected with the secondary gas storage tank to conduct normal temperature compressed air to contract and expand the corresponding jet, and during the flight phase, the primary gas storage tank is connected with the secondary gas storage tank to conduct power high-pressure gas to contract and expand the corresponding jet.
[0011] Furthermore, the burner assembly is a variable pressure and variable density burner assembly, including a combustion chamber, the combustion chamber adopts a pulse combustion method, a cooling system is arranged outside the combustion chamber, and the combustion chamber is connected to a recovery and reuse system.
[0012] Furthermore, the first-level gas storage tank is connected to the second-level gas storage tank through a power gas pipeline, and a thermal insulation component is provided on the power gas pipeline.
[0013] Furthermore, the air storage tank is connected to an air intake chamber and an air intake unit which can supply pressurized air or inhale external air for supplementation.
[0014] Furthermore, the combustion exhaust gas discharged by the generator and the waste gas generated in each compartment of the closed shell are pressurized and then output to the secondary gas storage tank.
[0015] Furthermore, the secondary fuel gas storage tank is connected to the non-fuel particulate matter storage tank, and the added particulate matter is ejected along with the power gas, thereby increasing the thrust under the condition of equal fuel consumption.
[0016] Furthermore, a floor support system is provided at the bottom of the closed housing.
[0017] Furthermore, a heat exchange coil for heating and cooling the water medium is arranged in the closed shell, pump valves are arranged at the nodes of the heat exchange coil, and the heat exchange coil is provided with a water return structure.
[0018] Furthermore, the enclosed shell is provided with an operating cabin, a payload cabin, a vertical lifting machine and a moving passage; the operating cabin and the equipment cabin are provided with a protective cabin for entering and exiting the aircraft; and the moving passage is provided with a permanent magnet suction cup.
[0019] Furthermore, the aircraft is also provided with a battery assembly and a control system assembly. The control system assembly includes a navigation system, an autopilot system, and a detection system. The navigation system adopts passive navigation with reference to distant stars when performing space flight, and adopts conventional radar navigation when flying close to the target.
[0020] The beneficial effects of the present invention are as follows: Under the condition of the same energy and fuel consumption, the gas jet can achieve several times more speed and form several times more thrust. Under the condition of the same fuel and load, it can achieve huge thrust while achieving better continuous flight time, and can realize interstellar flight. BRIEF DESCRIPTION OF THE DRAWINGS
[0021] Figure 1 It is a schematic diagram of the internal structure of the present invention;
[0022] Figure 2 It is a side cross-sectional structural schematic diagram of the present invention;
[0023] Figure 3 It is a schematic diagram of the working principle of the present invention.
[0024] Among them, 1. Drinking water storage tank; 2. Protection cabin; 3. Sealed shell; 4. Steering jet port; 5. Jet flow valve; 6. Jet gas cabin; 7. Jet gas pipeline; 8. Insulation component; 9. Secondary gas storage tank; 10. Oxygen generator and pressurizing unit; 11. Air conditioning heating water pump assembly; 12. Refrigeration and cooling water supply unit; 13. Waste heat storage tank and waste heat generator set assembly; 14. Waste collection tank; 15. Carbon powder pump; 16. Waste treatment complete set; 17. Vertical inner channel; 18. Recovery tank; 19. Cooling water tank; 20. Cooling water pump; 21. Combustion chamber; 22. Oxygen pump valve; 23. Cooling water return pump valve; 24. Pressure control valve; 25. Primary gas storage tank; 27. Cooling water cavity; 3 0. Air storage tank; 31. Air pump valve; 32. High-pressure air pipeline; 33. Thermal insulation components; 34. Power gas pipeline; 36. Non-fuel particulate matter storage tank; 37. Internal elevator; 38. Fuel storage tank; 39. Oxygen storage tank; 40. Lift jet; 42. Power gas flow valve; 43. Internal elevator shaft; 44. Support wall components; 45. Thermal insulation components of the first-level gas storage tank; 47. The inner liner of the first-level gas storage tank; 48. The thermal insulation support components of the first-level gas storage tank; 49. The outer shell of the first-level gas storage tank; 50. The support components of the first-level gas storage tank; 55. The upper jet; 56. The propulsion jet; 57. The deceleration and braking jet; 58. The outer shell of the second-level gas storage tank; 59. The support components of the second-level gas storage tank. DETAILED DESCRIPTION
[0025] The present invention is further described below in conjunction with specific embodiments, but the present invention is not limited to these specific embodiments. Those skilled in the art should recognize that the present invention covers all possible alternatives, improvements and equivalents within the scope of the claims.
[0026] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "clockwise", "counterclockwise" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, the meaning of "multiple" is two or more, unless otherwise clearly defined.
[0027] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0028] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.
[0029] Referring to 1-3, this embodiment provides a general-purpose vertical take-off and landing aircraft, including a sealed shell 3. The sealed shell 3 can be in a butterfly shape, a boat shape, a cylindrical shape, a spherical shape, etc. This embodiment takes the butterfly shape as an example.
[0030] In the embodiment, the sealed housing 3 is provided with an equipment cabin, which includes an air storage tank 30 for providing high-pressure air, a primary gas storage tank 25, a secondary gas storage tank 9, a generator (not marked in the figure), a burner assembly, an oxygen storage tank 39, a fuel storage tank 38, and an injection assembly. The burner assembly is respectively connected to the oxygen storage tank 39, the fuel storage tank 38, the generator, and the primary gas storage tank 25. The air storage tank 30 and the primary gas storage tank 25 can be connected to the secondary gas storage tank 9, and the secondary gas storage tank 9 is connected to the injection assembly. The injection assembly includes a lift for injection during take-off and landing. The jet port 40 and the upper jet port 55, the propulsion jet port 56 for jetting in the flight phase, the deceleration and braking jet port 57 and the steering jet port 4, the lift jet port 40 and the upper jet port 55 are arranged vertically opposite to each other, the propulsion jet port 56 and the deceleration and braking jet port 57 are arranged horizontally opposite to each other, and the steering jet port 4 is arranged horizontally. During the take-off and landing phase, the air storage tank 30 is connected with the secondary gas storage tank 9 to conduct the normal temperature compressed air to shrink and expand the corresponding jet port. During the flight phase, the primary gas storage tank 25 is connected with the secondary gas storage tank 9 to conduct the power high-pressure air to shrink and expand the corresponding jet port. The combustion exhaust gas discharged by the generator and the exhaust gas generated in each cabin of the closed shell 3 are pressurized and then output to the secondary gas storage tank 9 for the take-off and landing phase.
[0031] The burner assembly described in this embodiment is a variable pressure and variable density burner assembly, including a combustion chamber 21, the combustion chamber 21 adopts a pulse combustion mode, a cooling system is arranged outside the combustion chamber 21, and the combustion chamber 21 is connected to a recycling and reuse system. The primary gas storage tank 25 is connected to the secondary gas storage tank 9 through a power gas pipeline 34, and a heat insulation component 33 is arranged on the power gas pipeline 34. A valve component and / or a pump component are arranged accordingly on each pipeline. When the power is started, the carbon powder pump 15 inputs carbon powder to the combustion chamber 21 at a set flow rate according to the set instruction, and the synchronous oxygen pump valve 22 inputs oxygen at a set pressure and flow rate in proportion, and the high-temperature and high-pressure gas generated by ignition in the combustion chamber 21 flows to the primary gas storage tank 25 through the pressure control valve 24. At the same time, the cooling water of the cooling water pool 19 is input into the external cooling cavity 27 of the combustion chamber 21 through the cooling water pump 20 to form a water bath cooling body, and part of the heat generated by combustion is transmitted through the combustion chamber maintenance wall and absorbed in the water bath cooling body to ensure that the combustion chamber 21 will not burn through at high temperature and maintain sustainable combustion. After the carbon powder and oxygen in the combustion chamber 21 are ignited and burned, high-temperature and high-pressure gas is generated. The input system stops inputting fuel due to pressure factors, and the combustion is suspended. After the high-temperature gas is output through the pressure control valve 24, the pressure of the combustion chamber 21 is reduced, and the input system re-inputs oxygen and carbon powder, ignites and burns again to output the high-temperature and high-pressure gas to the first-level gas storage tank 25 next time. Repeat this process to form pulse combustion. Several sets of burner assemblies can be set to operate synchronously. In this embodiment, four sets of burner assemblies are set, and the high-temperature and high-pressure gas is input into the first-level gas storage tank 25, and then input into the second-level gas storage tank 9 through the power gas pipeline 34 under the control of the power gas flow valve 42. Under the command of the central control system, the gas is sprayed according to the command to generate power.
[0032] The oxygen storage tank 39 of this embodiment is connected to the oxygen machine and the pressurizing unit 10 to supplement oxygen. The fuel in the fuel storage tank 38 can be solid carbon powder, gas, liquid fuel, or mixed fuel. Carbon powder is used in this embodiment. Auxiliary booster can also be used to mix solid non-combustion particles (including rocks, etc.) to increase the density of the jet gas and thus increase the thrust. For example, a non-fuel particle storage tank 36 is set, which can be a booster fine sand storage tank, and the non-fuel particle storage tank 36 is connected to the secondary gas storage tank 9.
[0033] The recycling and reuse system of this embodiment can be used as an auxiliary system for the burner assembly. Domestic and organic waste can be collected through the channel and sent to the waste collection pool 14, and then crushed and separated by the waste treatment complete set 16. The water collected in the cooling water pool 19 can be used for cooling the combustion chamber 21, and the carbon-containing waste can be sent to the combustion chamber 21 for combustion through the carbon powder pump 15. The remaining waste should be collected and stored in a centralized manner according to the characteristics of the corresponding objects and handled separately. The return water of the cooling system is guided back to the return water pool 18 through the cooling water return pump valve 23.
[0034] The air storage tank 30 described in this embodiment is connected to an air intake chamber and an air intake unit that can pressurize and deliver air or inhale external air for replenishment. Taking the earth's surface pressure as a reference, the air pressure in the cabin is consistent with that of the earth before takeoff. The higher the altitude from the ground, the pressure and temperature outside the aircraft cabin change. When the pressure drops, the air intake chamber and the air intake unit are started to replenish the air pressure in the air storage tank 30 to achieve a nearly constant pressure environment in the cabin. If the pressure rises, the air in the cabin can be collected and pressed into the recovery air chamber of the air storage tank 30 through the air intake chamber and the air intake unit to achieve pressure adjustment. The air storage tank 30 is connected to the secondary fuel gas storage tank 9 through a high-pressure air pipeline 32, and an air pump valve 31 is provided on the high-pressure air pipeline 32.
[0035] The primary gas tank 25 of this embodiment includes a primary gas tank liner 47 and a primary gas tank shell 49. The primary gas tank liner 47 is fixedly connected to the primary gas tank shell 49 via the primary gas tank liner support component 28. The primary gas tank shell 49 is installed in the closed shell 3 via the primary gas tank support component 50. The primary gas tank thermal insulation component 45 is arranged outside the primary gas tank shell 49.
[0036] The gas secondary storage tank 9 of this embodiment is connected with the jet gas cabin 6 through the jet gas pipeline 7. The jet gas pipeline 7 is provided with a heat preservation component 8. The jet gas cabin 6 is connected with the corresponding jet port and is provided with a jet flow valve 5. The gas secondary storage tank 9 is provided with a gas secondary storage tank shell 58 outside, and is installed in the closed shell 3 through the gas secondary storage tank support component 59. Each jet gas cabin 6 of this embodiment can be connected with a lift jet port 40 and an upper jet port 55, and several jet gas cabins 6 arranged on the left side can be connected with a propulsion jet port 56, and several jet gas cabins 6 arranged on the right side can be connected with a deceleration and brake jet port 57, and several jet gas cabins 6 arranged on the front and rear sides can be connected with a steering jet port 4, including a left steering jet port and a right steering jet port. This embodiment can realize vertical take-off, horizontal flight, steering flight, downward flight, deceleration flight, backward flight, landing, etc. through the control of each jet port.
[0037] During vertical takeoff, after the system automatically detects and completes, if the impact of high temperature on the environment needs to be considered, the air pump valve 31 is opened, the air storage tank 30 and the secondary gas storage tank 9 are connected, and high-pressure air enters the secondary gas storage tank 9. The lift jet 40 sprays normal temperature air according to the instruction to achieve lifting. When a certain height (such as 500 meters) is reached, the power gas can be connected and switched to power gas jet propulsion. After switching, the air can be supplemented from the air and pressed into the air storage tank 30 according to the instruction for use. If there is no requirement for the impact of high temperature on the environment, the power gas can be directly used to start according to the set program. According to the instructions of the central processor, the combustion chamber 21 is started, and the required pressure and flow are controlled by the instructions of the central processing system. The auxiliary units such as the oxygen, carbon powder, and cooling water delivery system are started synchronously to achieve normal combustion operation. The power gas (high temperature and high pressure) enters the secondary gas storage tank 9 through the primary gas storage tank 25, and is ejected from the lift jet 40 according to the set flow and pressure, forming an upward thrust, and continuing to push the aircraft upward. During horizontal flight, after the aircraft rises to a predetermined height, the propulsion jet 56 is started to continuously generate horizontal acceleration to achieve horizontal flight. When lift is formed or gravity is reduced, the lift jet 40 can be reduced or closed as needed. During turning flight, the power gas in the secondary gas tank 9 is ejected into the opposite direction of the required turning direction through the flow valve and pipeline through the turning jet 4 according to the set flow rate and pressure, generating a turning thrust to achieve a change of direction. During downward flight, the power gas in the secondary gas tank 9 is ejected into the upper jet 55 according to the set flow rate and pressure through the flow valve and pipeline, generating a downward thrust to achieve downward movement. If deceleration is required, the propulsion jet 56 is reduced or closed, and the deceleration and brake jet 57 is synchronously started to spray in the opposite direction. If backward movement is required, the propulsion jet 56 is closed, and the deceleration and brake jet 57 is started to spray in the opposite direction. After the speed is reduced to zero, the backward movement can be achieved. If it is necessary to land downward, the power gas in the secondary gas storage tank 9 will be sprayed upward through the flow valve and pipeline through the upper jet port 55 at the set flow rate and pressure to generate downward thrust to achieve downward movement, and after approaching the target, the upward spray gas will be reduced or stopped, and the reverse jet will be started synchronously to land according to the set process.
[0038] The bottom of the closed shell 3 described in this embodiment is provided with a landing support system, which can reduce shock and ground. After losing power, the parachute is activated to assist in deceleration, and the belly of the aircraft is used for shock reduction and lands safely, thus achieving loss of control safety protection.
[0039] This embodiment is also provided with a constant temperature system. A heat exchange coil for heating and cooling the water medium is provided in the closed shell 3. A pump valve is provided at the node of the heat exchange coil. According to the temperature information of the sensor, flow control is performed, and water of a certain temperature is input to exchange heat with the corresponding space gas environment and structural parts to achieve temperature control. The heat exchange coil is provided with a return water structure. The return water structure returns the residual water to the cooling water pool 19 or the return water pool 18 under the control of the return water pump valve assembly, and can regain heat through the waste heat storage tank and the waste heat generator assembly 13 for secondary circulation to achieve continuous control of temperature. The heat exchange coil is connected to the air conditioning heating water pump 11 and the refrigeration and cooling water supply unit 12 respectively. An air circulation fan can also be set as needed in the space of the aircraft, and a one-way flow control is performed according to the pipeline to achieve full ventilation of the internal air. The recycled air is purified and humidified and reused. If the recycled air cannot meet the breathing quality index, new air can be extracted from the air storage tank 30 and injected to improve the air quality in the cabin. An artificial climate agricultural cabin area may also be provided in the enclosed shell 3, which not only meets the artificial climate production needs of agricultural products, but also helps to improve the air quality in the cabin.
[0040] The enclosed shell 3 of this embodiment is also provided with an operating cabin, a load cabin, a vertical lifting machine and a moving passage, a vertical lifting machine, and stairs and passages for objects, personnel, etc. to enter and exit the cabin and move in the cabin. The operating cabin and the equipment cabin are provided with a protective cabin 2 for entering and exiting the aircraft, and a permanent magnet suction cup is provided in the moving passage. The vertical lifting machine can be an internal elevator 37, which is installed in the internal elevator shaft 43. The operating cabin, the load cabin, etc. can be separated and supported by a supporting wall assembly 44. The bottom of the foot can be configured with corresponding parts such as metal blocks such as iron and nickel that are easily attracted by magnets, and the permanent magnet suction cup can provide appropriate fixation of the human body or object during movement. The enclosed shell 3 is also provided with a drinking water storage tank 1. Some vertical internal channels 17 can also be provided in the enclosed shell 3.
[0041] The aircraft described in this embodiment is also provided with a battery assembly and a control system assembly, and the control system assembly includes a navigation system, an automatic driving system, a detection system, a communication system, a security system, a load system, etc. The navigation system uses passive navigation with distant stars as reference when performing space flight, and uses conventional radar navigation when flying close to the target. The detection system can detect the safe distance from surrounding objects, and if there is a safety risk, the position of the aircraft can be changed by adjusting the spray direction of the nozzle to avoid collision.
[0042] Before starting the aircraft, fuel (oxygen, carbon powder, water) should be injected into the corresponding storage tanks, and high-pressure air should be injected into the air storage tank 30. Perform a comprehensive safety and status inspection, and only start the aircraft for takeoff when it meets the start conditions.
[0043] A specific application example of the present invention is the aerospace flying boat XKFZ580A, which has the following appearance: dish-shaped, with a maximum circumferential diameter of 58 (m) and a top height of 14.8 (m); deadweight: less than 500 tons; maximum vertical thrust: 10,000 tons; maximum horizontal thrust: 10,000 tons; take-off and landing propulsion air reserve: 500 tons; maximum load capacity: 2,000 tons. Fuel reserve: (10-hour maximum power continuous combustion reserve) carbon powder, with a carbon content of more than 95%, 900 tons; oxygen reserve 2,430 tons, oxygen production capacity 60 tons / hour; water, pure, 1,000 tons. Fuel consumption (maximum power): carbon powder (95% pure), 90 tons / hour; oxygen 243 tons / hour. Flight acceleration, when fully loaded, is initially greater than 1.6 meters / second, and the acceleration can be gradually increased as the fuel is consumed. Cruising speed, calculated based on maximum fuel for round trip flight: 3-10 Mach in the air layer; maximum speed not less than 100 Mach; 100 Mach between the Earth and the Moon, maximum speed not less than 200 Mach; 400 Mach outside the Earth and the Moon, maximum speed not less than 1000 Mach. Belly landing, can be used for both water and land landings.
[0044] The power of the present invention comes from high-pressure gas. The power high-pressure gas generated by combustion is collected and stored in a collection tank, and is ejected along a set path according to a set flow rate and pressure to generate the required power. The power gas generated by combustion is stored to obtain a more stable power output, which is also conducive to the control of the power gas flow rate and the ability to adapt to power changes is enhanced. The initial pressure and fuel density of the combustion are controllable and adjustable. It is a variable pressure and variable density combustion, which is higher than the traditional combustion method, has high efficiency, stronger power, and less fuel consumption per unit power. The combustion specific impulse can reach more than 11,000 seconds, which is significantly better than the general rocket combustion specific impulse, which rarely exceeds 400 seconds. The combustion chamber adopts a water bath cooling method to keep the temperature of the external wall of the combustion chamber within a safe range. The high-pressure and high-density closed combustion in the combustion chamber generates power gas, which is input into the power gas storage tank according to the set channel, and is output from the power gas storage tank at a certain pressure and flow rate, and ejected at a specific nozzle to generate the required power. The aircraft can be used in the air layer or in interstellar space. In the scenario of air layer use, oxygen can be obtained by inhaling air for separation, and compressed air can be inhaled to supplement air. For interstellar space use scenarios, it is necessary to inhale air from the air layer for compressed storage before takeoff, separate air to obtain oxygen for compressed storage, or directly input oxygen for compressed storage. The aircraft shell uses water as a medium for heat exchange to achieve temperature control in the cabin. Water delivery and return water can be powered by active pumping or by temperature difference automatic type. Aircraft engine fuel includes but is not limited to carbon powder, and various fuels that burn and generate heat can be used. To ensure sustainable combustion, fuel storage and delivery devices are configured, and the amount of fuel can be configured according to the flight mission to better improve the efficiency of fuel load. The aircraft lands on its belly, and landing gear can also be added for landing. The aircraft's ejector assembly can be connected to multiple power gas pipelines, and the corresponding channels can be turned on or off according to instructions, and the flow and injection direction can be controlled according to the set instructions. A non-fuel particulate matter addition system can be set up, and the added particulate matter is ejected with the power gas to increase thrust under the same fuel consumption.
[0045] Under the condition of the same energy and fuel consumption, the gas jet of the present invention can achieve several times higher speed and generate several times higher thrust. Under the condition of the same fuel and load, it can achieve huge thrust and better continuous flight time, thus realizing interstellar flight.
Claims
1. A vertical take-off and landing general-purpose aircraft, comprising a sealed shell, wherein an equipment cabin is arranged in the sealed shell, characterized in that: The equipment cabin includes an air storage tank for providing high-pressure air, a primary gas storage tank, a secondary gas storage tank, a generator, a burner assembly, an oxygen storage tank, a fuel storage tank, and an injection assembly. The burner assembly is connected to the oxygen storage tank, the fuel storage tank, the generator, and the primary gas storage tank, respectively. The air storage tank and the primary gas storage tank can be connected to the secondary gas storage tank. The secondary gas storage tank is connected to the injection assembly. The injection assembly includes a lift jet and an upper jet for injection during the take-off and landing phase, a propulsion jet, a deceleration and braking jet, and a steering jet for injection during the flight phase. The lift jet and the upper jet are arranged vertically opposite to each other, the propulsion jet and the deceleration and braking jet are arranged horizontally opposite to each other, and the steering jet is arranged horizontally. During the take-off and landing phase, the air storage tank is connected to the secondary gas storage tank to conduct normal temperature compressed air to shrink and expand the corresponding jets. During the flight phase, the primary gas storage tank is connected to the secondary gas storage tank to conduct power high-pressure gas to shrink and expand the corresponding jets.
2. A vertical take-off and landing general purpose aircraft according to claim 1, characterized in that: The burner assembly is a variable pressure and variable density burner assembly, including a combustion chamber, the combustion chamber adopts a pulse combustion method, a cooling system is arranged outside the combustion chamber, and the combustion chamber is connected to a recovery and reuse system.
3. A vertical take-off and landing general purpose aircraft according to claim 1, characterized in that: The primary gas storage tank is connected to the secondary gas storage tank through a power gas pipeline, and a thermal insulation component is arranged on the power gas pipeline.
4. A vertical take-off and landing general purpose aircraft according to claim 1, characterized in that: The air storage tank is communicated with an air intake chamber and an air intake unit which can pressurize and deliver air or inhale external air for supplementation.
5. The vertical take-off and landing general purpose aircraft according to claim 1, characterized in that: The combustion tail gas discharged by the generator and the waste gas generated in each compartment of the closed shell are pressurized and then output to the secondary fuel gas storage tank.
6. A vertical take-off and landing general purpose aircraft according to claim 1, characterized in that: The secondary fuel gas storage tank is in communication with the non-fuel particulate matter storage tank.
7. The vertical take-off and landing general purpose aircraft according to claim 1, characterized in that: The bottom of the closed shell is provided with a floor support system.
8. A vertical take-off and landing general purpose aircraft according to any one of claims 1 to 7, characterized in that: The sealed shell is provided with a heat exchange coil for heating and cooling the water medium, the nodes of the heat exchange coil are provided with pump valves, and the heat exchange coils are all provided with a water return structure.
9. A vertical take-off and landing general purpose aircraft according to claim 8, characterized in that: An operating cabin, a load cabin, a vertical lifting machine and a moving passage are arranged in the enclosed shell; a protective cabin for entering and exiting the aircraft is arranged in the operating cabin and the equipment cabin; a permanent magnet suction cup is arranged in the moving passage.
10. The vertical take-off and landing general purpose aircraft according to claim 1, characterized in that: The aircraft is also provided with a battery assembly and a control system assembly. The control system assembly includes a navigation system, an autopilot system, and a detection system. The navigation system adopts passive navigation with reference to distant stars when performing space flight, and adopts conventional radar navigation when flying close to a target.