IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0190516
(2008-08-12)
|
등록번호 |
US-8104707
(2012-01-31)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- Honeywell International Inc.
|
대리인 / 주소 |
Shumaker & Sieffert, P.A.
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인용정보 |
피인용 횟수 :
5 인용 특허 :
11 |
초록
▼
Disclosed herein is a propulsion system, which may be implemented in an air-vehicle, such as a ducted-fan organic air-vehicle. The propulsion system comprises (a) a power source, (b) a fan located within a duct and powered by the power source, (c) a plurality of vanes arranged in an x-clocked config
Disclosed herein is a propulsion system, which may be implemented in an air-vehicle, such as a ducted-fan organic air-vehicle. The propulsion system comprises (a) a power source, (b) a fan located within a duct and powered by the power source, (c) a plurality of vanes arranged in an x-clocked configuration and configured to produce control moments from the flow generated by the fan. The maximum control moments, which can be created by the vanes in the x-clocked configuration, are substantially oriented along the flight axes of the air-vehicle or the principle axis of the maximum moment of inertia.
대표청구항
▼
1. A propulsion system for an air-vehicle, the propulsion system comprising: a power source;a ducted-fan that is powered by the power source and configured to create an air flow through a duct; anda plurality of vanes configured to produce control moments by deflecting the air flow created by the du
1. A propulsion system for an air-vehicle, the propulsion system comprising: a power source;a ducted-fan that is powered by the power source and configured to create an air flow through a duct; anda plurality of vanes configured to produce control moments by deflecting the air flow created by the ducted-fan, each vane of the plurality of vanes defining a vane axis that is aligned with a moment created by the respective vane, wherein the vanes of the plurality of vanes are arranged in an x-clocked configuration in which the vane axes of at least two of the vanes are oriented at approximately 45 degrees relative to a flight axis of the air vehicle. 2. The propulsion system of claim 1 wherein the power source is a gas engine or an electric motor. 3. The propulsion system of claim 1, wherein the air-vehicle is a ducted-fan organic air-vehicle. 4. The propulsion system of claim 1, wherein the air flow provides thrust and lift for the air-vehicle. 5. The propulsion system of claim 1, wherein each vane is independently moveable. 6. The propulsion system of claim 1, wherein the air-vehicle has an associated direction of flight, wherein the direction of flight defines a set of flight axes including the flight axis, and wherein the vane axes of the vanes of the plurality of vanes are oriented at approximately forty-five degrees to the flight axes. 7. The propulsion system of claim 1, wherein each vane comprises a set of sub-vanes, wherein the sub-vanes in each set are arranged substantially parallel to each other. 8. The propulsion system of claim 1, wherein the plurality of vanes arranged in an x-clocked configuration comprises four vanes arranged perpendicular to each other. 9. The propulsion system of claim 8, wherein each of the vanes creates a control moment, wherein the effect of control moments created by all the vanes is a combined control moment, and wherein the vanes are configurable so that the combined moment is a maximum moment of the x-clocked configuration. 10. The propulsion system of claim 9, wherein the maximum moment created by the vanes of the plurality of vanes of the x-clocked configuration is aligned with at least one flight axis of the air vehicle. 11. The propulsion system of claim 9, wherein the air-vehicle has a maximum moment of inertia, and wherein the maximum moment created by the vanes of the plurality of vanes of the x-clocked configuration is aligned with a principle axis of the maximum moment of inertia. 12. The propulsion system of claim 1, wherein the plurality of vanes comprises a plurality of flapped vanes, wherein each flapped vane is moveable to control deflection of the air flow through the ducted-fan. 13. A ducted-fan air-vehicle comprising: a power source;a duct;a fan located within the duct and powered by the power source, wherein the fan is configured to create air flow through the duct; anda plurality of vanes arranged in an x-clocked configuration in which a maximum control moment created by vanes of the plurality of vanes is aligned with a flight axis of the air-vehicle, wherein the vanes of the plurality of vanes are configured to produce control moments by deflecting the air flow through the duct. 14. The ducted-fan air-vehicle of claim 13, wherein the ducted-fan air-vehicle further comprises an avionics system to control the flight of the ducted-fan air-vehicle. 15. The ducted-fan air-vehicle of claim 14, wherein the avionics system is configured to orient the vehicle around a forward direction of flight, wherein the forward direction of flight defines a set of flight axes comprising the flight axis, the flight axis being one of a forward flight axis, a roll-axis, a pitch-axis, and a yaw-axis, wherein the roll-axis is oriented substantially parallel to the forward flight axis and the pitch-axis is oriented substantially perpendicular to the forward flight axis. 16. The ducted-fan air-vehicle of claim 13, wherein the plurality of vanes arranged in the x-clocked configuration comprises four vanes arranged perpendicular to each other such that each vane is aligned with a vane axis, wherein each vane axis is oriented at substantially forty-five degrees to at least one flight axis of the air vehicle. 17. The ducted-fan air-vehicle of claim 13, wherein the plurality of vanes comprises a plurality of flapped vanes, wherein each flapped vane is independently moveable to control deflection of the air flow through the ducted-fan. 18. The propulsion system of claim 1, wherein a maximum control moment created by the vanes of the plurality of vanes is aligned with a flight axis of the air-vehicle. 19. The ducted-fan air-vehicle of claim 13, wherein the vanes of the plurality of vanes each define a vane axis that is aligned with a moment created by the respective vane, and wherein the vane axes of at least two of the vanes are oriented approximately 45 degrees relative to a flight axis of the air vehicle.
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