IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0755365
(2010-04-06)
|
등록번호 |
US-8308104
(2012-11-13)
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발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
12 |
초록
▼
The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wing
The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wings of the aircraft and in communication with the rotating gas turbine engine to further control and stabilize flight of the aircraft. The gas turbine engine of the aircraft can comprise a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating more thrust from a single engine.
대표청구항
▼
1. An aircraft comprising: a main frame having a top domed section and a bottom domed section, wherein said bottom domed section is adapted for rotation;a plurality of wings, wherein said wings are distributed about said main frame in an approximately equiangular arrangement;a gas turbine engine hav
1. An aircraft comprising: a main frame having a top domed section and a bottom domed section, wherein said bottom domed section is adapted for rotation;a plurality of wings, wherein said wings are distributed about said main frame in an approximately equiangular arrangement;a gas turbine engine having an inlet positioned within said top domed section to admit air into said engine and at least one outlet positioned within said bottom domed section to eject products of combustion of said engine, wherein said gas turbine engine is at least partially attached with said bottom domed section and is adapted for rotation when said bottom domed section rotates,whereby said products of combustion ejected from said outlet of said engine provide a propulsive thrust to said aircraft and rotation of said bottom domed section controls directional movement of the aircraft. 2. The aircraft of claim 1, further comprising at least one pivotal flap member attached with each said wing, wherein each said pivotal flap member is in communication with said rotating bottom domed section to further control the directional movement of said aircraft. 3. The aircraft of claim 1, wherein said top domed section is adapted for rotation. 4. The aircraft of claim 1, wherein said top domed section comprises a radar device adapted for rotation. 5. The aircraft of claim 3, wherein said top domed section comprises a missile bay and at least one missile. 6. The aircraft of claim 1, wherein said bottom domed section further comprises retractable landing gear. 7. The aircraft of claim 1, wherein said gas turbine engine further comprises: a compressor, said compressor capable of pressurizing air;a combustion chamber in communication with said compressor, said combustion chamber having a means for igniting pressurized air from said compressor to create ignited gas;a first turbine connected to a first side of said combustion chamber, wherein said ignited gas from said combustion chamber motivates said first turbine to generate force in a first direction; anda second turbine connected to a second side of said combustion chamber that is diametrical to said first side of said combustion chamber, wherein said ignited gas from said combustion chamber motivates said second turbine to generate force in a second direction that is opposite to said first direction. 8. The aircraft of claim 7, wherein said gas turbine engine further comprises: a rotator shaft, said rotator shaft extending centrically through said compressor;a rotator, said rotator mounted to said rotator shaft and connected to said combustion chamber;whereby said rotator separates said combustion chamber from said compressor, and said combustion chamber is capable of rotation by movement of said rotator. 9. The aircraft of claim 8, wherein said compressor has an inlet and an outlet, said outlet connecting with said rotator and communicating with said combustion chamber. 10. The aircraft of claim 9, wherein said compressor is located above said combustion chamber such that air received in said inlet flows downwardly to said outlet. 11. The aircraft of claim 7, wherein said first turbine has a movable nozzle for expelling said ignited gas in variable directions. 12. The aircraft of claim 7, said second turbine further comprising: a turbine housing, said turbine housing connected to said combustion chamber;a first duct connected to said turbine housing, said first duct having a first section extending from said turbine housing in said second direction anda second section continuing from said first section that is bent reversely to extend in said first direction;a second duct connected to said turbine housing, said second duct having a first section extending from said turbine housing in said second direction anda second section continuing from said first section that is bent reversely to extend in said first direction;wherein said ignited gas flowing through said second turbine is separated by said first duct and said second duct. 13. The aircraft of claim 12, wherein said second turbine has a movable left nozzle and a movable right nozzle; said movable left nozzle fixed to said first duct for expelling said ignited gas in variable directions; and,said movable right nozzle fixed to sad second duct for expelling said ignited gas in variable directions. 14. The aircraft of claim 8, said gas turbine engine further comprising: a gear shaft regulator, said gear shaft regulator mounted to said rotator shaft;a first turbine shaft, said first turbine shaft mounted to said gear shaft regulator in said combustion chamber;a second turbine shaft, said second turbine shaft mounted to said gear shaft regulator in said combustion chamber;wherein said first turbine is mounted on said first turbine shaft, and said second turbine is mounted on said second turbine shaft, said first turbine shaft and said second turbine shaft being capable of independent rotation. 15. The aircraft of claim 7, wherein said gas turbine engine further comprises: a compressor, said compressor capable of pressurizing air;a combustion chamber in communication with said compressor, said combustion chamber having a means for igniting pressurized air from said compressor to create ignited gas;at least two turbines connected to opposite sides of said combustion chamber, wherein said ignited gas from said combustion chamber motivates said turbines to generate force in multiple directions.
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