CN114715380B - Variant aircraft and driving method thereof - Google Patents
Variant aircraft and driving method thereof Download PDFInfo
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- CN114715380B CN114715380B CN202210419262.6A CN202210419262A CN114715380B CN 114715380 B CN114715380 B CN 114715380B CN 202210419262 A CN202210419262 A CN 202210419262A CN 114715380 B CN114715380 B CN 114715380B
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- 238000000034 method Methods 0.000 title claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 71
- 230000006835 compression Effects 0.000 claims description 14
- 238000007906 compression Methods 0.000 claims description 14
- 238000002485 combustion reaction Methods 0.000 claims description 11
- 239000002737 fuel gas Substances 0.000 claims description 11
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 230000004048 modification Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 238000004080 punching Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000007599 discharging Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/54—Varying in area
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a variant aircraft and a driving method thereof, wherein the aircraft comprises a fuselage and an engine, the variant aircraft further comprises a high aspect ratio aircraft structure and a low aspect ratio aircraft structure, the high aspect ratio aircraft structure is detachably arranged on the fuselage of the aircraft, so that the aircraft can throw off the high aspect ratio aircraft structure according to flight requirements, and the low aspect ratio aircraft structure is adopted as an aircraft flight structure. The technical scheme of the invention is implemented to improve the flying capacity of the variant aircraft.
Description
Technical Field
The present disclosure relates to an aeronautical device, and more particularly, to a variant aircraft and a method of driving the same.
Background
The variant aircraft refers to an aircraft which can change aerodynamic shapes such as wing areas, aspect ratios, sweepback angles and the like in flight so as to ensure that the aircraft keeps optimal performance under different flight conditions. Compared with the conventional fixed layout aircraft, the variant aircraft has wider flight envelope and higher fight efficiency, and can autonomously change the aerodynamic configuration according to the requirements of flight environment, flight profile, fight mission and the like, so as to optimize the flight performance. The wider flight envelope requirements of a variant aircraft present new challenges to the aeroengine capability, making it difficult for the flight capability of existing variant aircraft to meet the wider flight envelope requirements of a variant aircraft, and therefore, a variant aircraft that can improve the flight capability needs to be designed.
Meanwhile, the existing variant aircraft mainly adopts foldable wings and other forms, and the wing expansion ratio of the variant aircraft is adjusted by changing the wing form. The airplane has the problems that the airplane is not thoroughly changed, the airplane is driven by adopting the same power source under the condition of different wing expansion ratios, and the like, so that the acceleration performance and economy of the airplane are in a non-optimal state, and the technical advantages of the changed airplane can not be fundamentally embodied.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present invention provides a variant aircraft and a driving method thereof, so as to improve the flying capability of the variant aircraft.
In order to achieve the above purpose, the present disclosure adopts the following technical scheme: a variant aircraft comprising a fuselage and an engine, the variant aircraft further comprising a high aspect ratio aircraft structure and a low aspect ratio aircraft structure, the high aspect ratio aircraft structure being detachably disposed on the fuselage of the aircraft such that when the aircraft is thrown off the high aspect ratio aircraft structure as desired for flight, the low aspect ratio aircraft structure is employed as an aircraft flight structure.
Preferably, the low aspect ratio aircraft structure comprises a low aspect ratio wing and an engine high-pressure system, and the low aspect ratio wing and the high-pressure system are fixedly connected to the aircraft body;
The high-pressure system comprises a high-pressure shaft, a middle air inlet channel valve, a compression channel mode selection valve, a fuel gas channel mode selection valve, a middle tail pipe valve, a high-pressure compressor front runner, a high-pressure turbine rear runner and a high-pressure gas runner;
The high-pressure gas flow passage comprises an intermediate air inlet passage, a high-pressure gas compressor, a combustion chamber, a high-pressure turbine and an intermediate tail pipe which are sequentially arranged along the air flow direction, the high-pressure shaft is connected with the high-pressure gas compressor and the high-pressure turbine, an intermediate air inlet passage valve is arranged in the intermediate air inlet passage, a bypass high-pressure gas compressor front flow passage is arranged on the side surface of the high-pressure gas flow passage, which is arranged on the downstream side of the intermediate air inlet passage valve, along the air flow direction, a compression passage mode selection valve is arranged at the bypass position of the high-pressure gas compressor front flow passage and the high-pressure gas flow passage, the high-pressure gas turbine front flow passage is controlled to be communicated or not communicated with the high-pressure gas flow passage by controlling the opening or closing of the compression passage mode selection valve, the intermediate tail pipe is arranged on the downstream side of the turbine of the high-pressure gas flow passage, the intermediate tail pipe valve is arranged in the intermediate tail pipe, a bypass high-pressure turbine tail pipe valve is arranged between the high-pressure gas turbine tail pipe valve and the high-pressure gas flow passage, the bypass high-pressure gas turbine tail pipe is arranged at the bypass position of the high-pressure gas turbine tail pipe is not communicated with the high-pressure gas flow passage by controlling the opening or closing of the high-pressure gas passage;
The intermediate inlet valve is used for controlling whether gas enters the high-pressure compressor and the combustion chamber from the intermediate inlet pipe, and the intermediate tail pipe valve is used for controlling whether high-pressure gas is discharged from the intermediate tail pipe.
Preferably, the high aspect ratio aircraft structure comprises a high aspect ratio wing and an engine low-voltage system, wherein the low aspect ratio wing and the high aspect ratio wing are arranged on two sides of an aircraft body in an overlapping mode, the high aspect ratio wing is positioned below the low aspect ratio wing, and the high aspect ratio wing is fixedly connected with the low-voltage system;
the low-pressure system comprises a low-pressure shaft and a low-pressure gas flow passage, wherein the low-pressure gas flow passage comprises a side air inlet passage, a fan, an outer duct, a low-pressure turbine, a mixer and a tail nozzle which are sequentially arranged along the air flow direction, the low-pressure shaft is connected with the fan and the low-pressure turbine, an opening communicated with a front flow passage of the high-pressure turbine is formed in the side face, downstream of the fan, of the low-pressure gas flow passage along the air flow direction, and an opening communicated with a rear flow passage of the high-pressure turbine is formed in the side face, upstream of the low-pressure turbine, of the low-pressure gas flow passage along the air flow direction.
Preferably, the number of the low-voltage systems is an even number of more than two.
The aircraft with the combination of the jettisonable wing variant aircraft and the double low-pressure system variable cycle aeroengine provided by the disclosure has the advantages that the mode of the high aspect ratio wing aircraft is matched with the working mode of the equivalent turbofan engine, so that long-time subsonic cruising is realized; the low aspect ratio wing mode is matched with the working mode of the equivalent turbojet engine, so that the limit supersonic speed flight is realized. The variant aircraft in the present disclosure adopts a jettisonable wing form and a variable cycle aeroengine with a disposable dual low pressure system, and is a novel subversion of a flying fusion configuration.
The present disclosure also provides a method for driving a variant aircraft, including, when the aircraft is in a high aspect ratio structure, closing a middle air inlet valve and a middle tail pipe valve, opening a compression channel mode selection valve and a gas channel mode selection valve, after an air medium is sucked into a power device by a side air inlet, dividing the air medium into two parts by compression of a fan, respectively entering an outer duct and a front flow channel of a high-pressure compressor, enabling the air flow entering the outer duct to directly flow to a mixer and mix with the gas after a low-pressure turbine, and finally discharging the air by tail pipes at two sides; the gas flow entering the high-pressure compressor through the front flow passage of the high-pressure compressor passes through the combustion chamber to form high-temperature high-pressure gas, then the gas enters the high-pressure turbine to perform expansion work, and then enters the low-pressure turbine through the rear flow passage of the high-pressure turbine to be mixed with the gas flow of the outer duct.
Preferably, when the aircraft is in a low aspect ratio structure and flies, the high aspect ratio wing and the high aspect ratio additional driving system are abandoned, the middle air inlet channel valve and the middle tail pipe valve of the engine are opened, the compression channel mode selection valve and the fuel gas channel mode selection valve are closed, air medium is sucked into the power device by the middle air inlet channel and flows through the high-pressure air compressor, then flows through the combustion chamber to form high-temperature and high-pressure fuel gas, and then the fuel gas enters the high-pressure turbine to expand and do work, and is discharged by the tail pipe.
According to the technical scheme, a layer of low aspect ratio wing is additionally added on the basis of the traditional single-layer wing to form the double wings with the overlapped high aspect ratio, so that the aircraft can be guaranteed to have the high aspect ratio before modification, subsonic high-efficiency flight is realized, the aircraft can be guaranteed to have the low aspect ratio after modification, and supersonic low-resistance flight is realized.
The double low pressure system variable cycle aero-engine adopting the jettisonable low pressure system can be well matched with a variant aircraft. The engine is an equivalent turbofan engine before modification, has the characteristic of low subsonic cruising fuel consumption rate, is fused with an aircraft with a large aspect ratio, and greatly improves the endurance of the aircraft; the engine variant is followed by an equivalent turbojet engine, has the characteristic of high supersonic thrust, is fused with an airplane with a small aspect ratio, and greatly improves the limit speed of the airplane.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
FIG. 1 is a schematic illustration of a variant aircraft structure;
FIG. 2 is a schematic illustration of a high aspect ratio aircraft flight configuration;
FIG. 3 is a schematic illustration of a low aspect ratio aircraft flight configuration.
Detailed Description
The present disclosure is described in further detail below with reference to the drawings and the embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant content and not limiting of the present disclosure. It should be further noted that, for convenience of description, only a portion relevant to the present disclosure is shown in the drawings.
In addition, embodiments of the present disclosure and features of the embodiments may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Referring to fig. 1, a variant aircraft, which includes a fuselage 12 and an engine, has a high aspect ratio aircraft structural portion and a low aspect ratio aircraft structural portion.
Specifically, referring to fig. 2, the high aspect ratio aircraft structure includes a high aspect ratio wing 3 and an engine low pressure system, the low aspect ratio aircraft structure includes a low aspect ratio wing 4 and an engine high pressure system, the high aspect ratio wing 3 and the low aspect ratio wing 4 are disposed on both sides of the aircraft body 12 in an overlapping manner, the high aspect ratio wing 3 is disposed below the low aspect ratio wing 3, and the low aspect ratio wing 4 and the high pressure system are fixedly connected to the body 12; the high aspect ratio wing 3 is detachably arranged on the fuselage 12 of the aircraft, and the high aspect ratio wing 3 is fixedly connected with the engine low-pressure system, so that when the aircraft needs to be subjected to supersonic speed punching, the high aspect ratio wing 3 and the low-pressure system can be abandoned, the aircraft is deformed into the low aspect ratio wing and the high-pressure system drives the aircraft, and the punching capacity of the aircraft is improved.
In this embodiment, the engine low pressure system is two as many as the number of wings with large aspect ratio. The separation of the wings with large aspect ratio can be conveniently realized through the double-wing airplane configuration overlapped up and down; the double low-pressure system variable cycle aeroengine is used as power, so that the separation of the low-pressure system can be conveniently realized. The double low pressure system variable cycle engine is flat, so that the whole aerodynamic efficiency of the aircraft is higher. The matching of the airplane configuration with the large aspect ratio and the equivalent turbofan engine with low oil consumption provides a guarantee for subsonic long-endurance flight before the airplane variation; the design of the turbojet engine and the low aspect ratio wing of the low-pressure system can be abandoned, so that the supersonic speed punching capability of the aircraft can be improved.
In addition, the high-aspect-ratio wing and the engine low-pressure system fixedly connected with the high-aspect-ratio wing can be conveniently and quickly separated from the fuselage to discard the high-aspect-ratio wing and the engine low-pressure system, and the high-aspect-ratio wing can be detachably mounted on the aircraft fuselage in a known manner in aviation and aerospace technology, such as any form of separation mounting structure such as a detachable connecting mechanism of a traditional aerospace aircraft solid booster.
An aircraft high-pressure system that flies in a small aspect ratio mode has a high-pressure gas flow passage in which a middle intake passage 8, a high-pressure compressor 11, a combustion chamber 15, a high-pressure turbine 22, and an intermediate nozzle 18 are provided in this order in the direction of flow of the gas, a high-pressure shaft 1 connects the high-pressure compressor 11 and the high-pressure turbine 22 such that a rotor of the high-pressure compressor 11 rotates coaxially with the high-pressure turbine 22, a middle intake passage valve 9 is provided in the middle intake passage 8, a bypass high-pressure compressor front flow passage 10 is provided on a side of the high-pressure gas flow passage downstream of the middle intake passage valve 9 in the direction of flow of the gas, a compression passage mode selection valve 7 is provided at a bypass position of the high-pressure compressor front flow passage 10 and the high-pressure gas flow passage, an intermediate nozzle 18 is provided downstream of the high-pressure turbine 22 of the high-pressure gas flow passage, an intermediate nozzle valve 19 is provided in the intermediate nozzle 18, a bypass high-pressure turbine rear flow passage 20 is provided between the high-pressure nozzle valve 19 and the high-pressure turbine 22, and the bypass passage mode selection valve 17 is provided at a bypass position of the high-pressure turbine rear flow passage 20 and the intermediate nozzle 18.
As shown in fig. 1-2, the low pressure system of an aircraft flying in the large aspect ratio mode has a low pressure gas flow passage including a side air inlet duct 6, a fan 5, an outer duct 13, a low pressure turbine 14, a mixer 21, and a tail nozzle 16 which are disposed in this order in the air flow direction, the low pressure shaft 2 connecting the fan 5 and the low pressure turbine 14 such that the fan 5 rotates coaxially with the low pressure turbine 14, an opening communicating with the high pressure turbine front flow passage 10 being provided on a side of the low pressure gas flow passage downstream of the fan 5 in the air flow direction, and an opening communicating with the high pressure turbine rear flow passage 20 being provided on a side of the low pressure gas flow passage upstream of the low pressure turbine 14 in the air flow direction.
When the aircraft is operated in subsonic long endurance mode, a large aspect ratio structure is adopted, in the mode, the middle air inlet valve 9 and the middle tail pipe valve 19 of the engine are closed, and the compression channel mode selection valve 7 and the fuel gas channel mode selection valve 17 are opened. At this time, after being sucked into the power device by the air inlets 6 at both sides, the air medium is compressed by the fan 5 and divided into two paths, and the two paths enter the outer duct 13 and the front flow passage 10 of the high-pressure compressor respectively. The gas flow entering the outer duct 13 directly flows to the mixer 21 to be mixed with the gas after the low-pressure turbine 14, and finally is discharged from the tail nozzles 16 at both sides. The air flow entering the high-pressure compressor 11 through the high-pressure compressor front flow passage 10 passes through the combustion chamber 15 to form high-temperature high-pressure gas, then the gas enters the high-pressure turbine 22 to perform expansion work, and then enters the low-pressure turbines 14 on the two sides through the high-pressure turbine rear flow passage 20 to be mixed with the air flow of the outer duct 13. The aircraft flies in a high aspect ratio structural mode, and the aircraft has high aerodynamic efficiency, and at the moment, the aircraft engine is in operation due to the low-pressure system, namely the equivalent turbofan engine is formed, so that the aircraft has high fuel economy, and guarantees are provided for long-time subsonic cruising and cruising of the aircraft.
As shown in fig. 3, when the aircraft is operating in the supersonic sprint mode, the high aspect ratio wing and low pressure system is discarded, and the aircraft is in the low aspect ratio aircraft, in this mode, the intermediate inlet valve 9 and the intermediate outlet valve 19 of the engine are opened, and the compression passage mode selector valve 7 and the gas passage mode selector valve 17 are closed. The air medium is sucked into the power device by the middle air inlet channel 8 and flows through the high-pressure compressor 11, then flows through the combustion chamber 15 to form high-temperature and high-pressure fuel gas, and then enters the high-pressure turbine 22 to perform expansion work, and then is discharged from the tail nozzle 18. At the moment, the aircraft has high aerodynamic efficiency, and the aircraft engine only takes part in work due to the fact that a low-pressure system is removed, so that the aircraft engine is equivalent to a turbojet engine, has high thrust and provides guarantee for supersonic acceleration sprint of the aircraft.
In the description of the present specification, reference to the terms "one embodiment/manner," "some embodiments/manner," "example," "a particular example," "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/manner or example is included in at least one embodiment/manner or example of the application. In this specification, the schematic representations of the above terms are not necessarily for the same embodiment/manner or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/modes or examples described in this specification and the features of the various embodiments/modes or examples can be combined and combined by persons skilled in the art without contradiction.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present application, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
It will be appreciated by persons skilled in the art that the above embodiments are provided for clarity of illustration only and are not intended to limit the scope of the application. Other variations or modifications will be apparent to persons skilled in the art from the foregoing disclosure, and such variations or modifications are intended to be within the scope of the present application.
Claims (4)
1. A variant aircraft, the aircraft comprising a fuselage and an engine, characterized in that: the variant aircraft further comprises a high aspect ratio aircraft structure and a low aspect ratio aircraft structure, wherein the high aspect ratio aircraft structure is detachably arranged on the fuselage of the aircraft, so that the aircraft can throw off the high aspect ratio aircraft structure according to flight requirements, and the low aspect ratio aircraft structure is adopted as an aircraft flight structure; the low aspect ratio aircraft structure comprises a low aspect ratio wing and an engine high-voltage system, and the low aspect ratio wing and the high-voltage system are fixedly connected to the aircraft body;
The high-pressure system comprises a high-pressure shaft, a middle air inlet channel valve, a compression channel mode selection valve, a fuel gas channel mode selection valve, a middle tail pipe valve, a high-pressure compressor front runner, a high-pressure turbine rear runner and a high-pressure gas runner;
The high-pressure gas flow passage comprises an intermediate air inlet passage, a high-pressure gas compressor, a combustion chamber, a high-pressure turbine and an intermediate tail pipe which are sequentially arranged along the air flow direction, the high-pressure shaft is connected with the high-pressure gas compressor and the high-pressure turbine, an intermediate air inlet passage valve is arranged in the intermediate air inlet passage, a bypass high-pressure gas compressor front flow passage is arranged on the side surface of the high-pressure gas flow passage, which is arranged on the downstream side of the intermediate air inlet passage valve, along the air flow direction, a compression passage mode selection valve is arranged at the bypass position of the high-pressure gas compressor front flow passage and the high-pressure gas flow passage, the high-pressure gas flow passage is controlled to be communicated or not to be communicated with the high-pressure gas flow passage by controlling the opening or closing of the compression passage mode selection valve, the intermediate tail pipe is arranged on the downstream of the high-pressure turbine of the high-pressure gas flow passage, the intermediate tail pipe valve is arranged in the intermediate tail pipe, a bypass high-pressure turbine tail pipe valve is arranged between the high-pressure gas flow passage and the intermediate tail pipe valve, the bypass high-pressure gas flow passage is arranged at the bypass high-pressure gas turbine tail pipe valve, the high-pressure gas flow passage is not communicated with the high-pressure gas flow passage through the intermediate air passage or is controlled to be communicated with the high-pressure gas flow passage;
The intermediate inlet channel valve is used for controlling whether gas enters the high-pressure gas compressor and the combustion chamber from the intermediate inlet channel, and the intermediate tail pipe valve is used for controlling whether high-pressure gas is discharged from the intermediate tail pipe; the high aspect ratio aircraft structure comprises a high aspect ratio wing and an engine low-voltage system, wherein the low aspect ratio wing and the high aspect ratio wing are arranged on two sides of an aircraft body in an overlapping mode, the high aspect ratio wing is positioned below the low aspect ratio wing, and the high aspect ratio wing is fixedly connected with the low-voltage system;
the engine low pressure system comprises a low pressure shaft and a low pressure gas flow passage, wherein the low pressure gas flow passage comprises a side air inlet passage, a fan, an outer duct, a low pressure turbine, a mixer and a side tail nozzle which are sequentially arranged along the air flow direction, the low pressure shaft is connected with the fan and the low pressure turbine, an opening communicated with a front flow passage of the high pressure turbine is formed in the side face of the low pressure gas flow passage, which is arranged along the air flow direction, of the downstream of the fan, and an opening communicated with a rear flow passage of the high pressure turbine is formed in the side face of the low pressure gas flow passage, which is arranged along the air flow direction, of the upstream of the low pressure turbine.
2. The variant aircraft of claim 1, wherein: the number of the low-voltage systems is an even number of more than two.
3. A method of driving a variant aircraft according to any one of claims 1 or 2, wherein: when the aircraft is in a high aspect ratio structure and flies, the middle air inlet channel valve and the middle tail pipe valve are closed, the compression channel mode selection valve and the fuel gas channel mode selection valve are opened, air medium is sucked into the power device by the side air inlet channel and then is compressed by the fan to be divided into two paths, the two paths of air medium respectively enter the outer duct and the front flow channel of the high-pressure compressor, air flow entering the outer duct directly flows to the mixer and is mixed with air after the low-pressure turbine, and finally the air medium is discharged from the tail pipes at two sides; the gas flow entering the high-pressure compressor through the front flow passage of the high-pressure compressor passes through the combustion chamber to form high-temperature high-pressure gas, then the gas enters the high-pressure turbine to perform expansion work, and then enters the low-pressure turbine through the rear flow passage of the high-pressure turbine to be mixed with the gas flow of the outer duct.
4. A method of driving a variant aircraft according to claim 3, wherein: when the aircraft is in a low aspect ratio structure and flies, the high aspect ratio wing and the low pressure system are abandoned, the middle air inlet channel valve and the middle tail pipe valve of the engine are opened, the compression channel mode selection valve and the fuel gas channel mode selection valve are closed, air medium is sucked into the power device by the middle air inlet channel and then flows through the high pressure air compressor, then flows through the combustion chamber to form high-temperature and high-pressure fuel gas, and then the fuel gas enters the high pressure turbine to expand and do work, and is discharged from the tail pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210419262.6A CN114715380B (en) | 2022-04-20 | 2022-04-20 | Variant aircraft and driving method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210419262.6A CN114715380B (en) | 2022-04-20 | 2022-04-20 | Variant aircraft and driving method thereof |
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| CN114715380A CN114715380A (en) | 2022-07-08 |
| CN114715380B true CN114715380B (en) | 2024-07-02 |
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| CN114715380A (en) | 2022-07-08 |
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