Directional control system and method of providing directional control
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/82
B64C-021/04
B64C-027/12
B64D-033/04
B64D-033/02
출원번호
US-0074454
(2016-03-18)
등록번호
US-10118695
(2018-11-06)
발명자
/ 주소
Thomassin, Jean
Dussault, Serge
Julien, Andre
Saby, Gordon
Ullyott, Richard
출원인 / 주소
PRATT & WHITNEY CANADA CORP.
대리인 / 주소
Norton Rose Fulbright Canada LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A directional control system for a rotorcraft having a tail boom including a no-tail-rotor apparatus configured to control rotorcraft yaw using forced air ejected from the tail boom and a duct configured to deliver the forced air to the no-tail-rotor apparatus. The directional control system compris
A directional control system for a rotorcraft having a tail boom including a no-tail-rotor apparatus configured to control rotorcraft yaw using forced air ejected from the tail boom and a duct configured to deliver the forced air to the no-tail-rotor apparatus. The directional control system comprises a heat exchanger having air passages and fluid passages, the air passages in fluid communication with the duct, the fluid passages in heat exchange relationship with the air passages and configured for receiving a cooling fluid, and a forced air driver in fluid communication with the duct for driving the forced air through the duct to the no-tail-rotor apparatus. Methods of providing directional control in a rotorcraft are also discussed.
대표청구항▼
1. A directional control system for a rotorcraft having an internal combustion engine, a main rotor and a tail boom, the directional control system comprising: a no-tail-rotor apparatus configured to control rotorcraft yaw using forced air ejected from the tail boom;a duct configured to deliver the
1. A directional control system for a rotorcraft having an internal combustion engine, a main rotor and a tail boom, the directional control system comprising: a no-tail-rotor apparatus configured to control rotorcraft yaw using forced air ejected from the tail boom;a duct configured to deliver the forced air to the no-tail-rotor apparatus; a heat exchanger in heat exchange relationship with an internal combustion engine, the heat exchanger having air passages and fluid passages, the air passages in fluid communication with the duct, the fluid passages in heat exchange relationship with the air passages and configured for receiving a cooling fluid of the internal combustion engine; anda forced air driver in fluid communication with the duct and the air passages of the heat exchanger for driving the forced air, including engine cooler exhaust air from the air passages, through the duct to the no-tail-rotor apparatus. 2. The system of claim 1, wherein the no-tail-rotor apparatus includes: at least one nozzle in fluid communication with the duct, having a linear configuration and extending longitudinally along an outer surface of the tail boom; anda thruster on the tail boom and in fluid communication with the duct, the thruster positionable to be directed laterally with respect to the tail boom in a selected one of a plurality of different orientations. 3. The system as defined in claim 1, further comprising an exhaust conduit communicating with the duct downstream of the heat exchanger and upstream of the no-tail-rotor apparatus, and a valve modulating the communication between the exhaust conduit and the duct. 4. The system as defined in claim 2, wherein a distal end of the tail boom includes an end portion with a slot defined therein, and an inner element having a shape complementary to that of the end portion is received within the end portion, the inner element being pivotable within the end portion and having a hole defined therethrough cooperating with the slot of the end portion to define the thruster. 5. The system as defined in claim 1, wherein the heat exchanger is received within the duct. 6. The system as defined in claim 1, further comprising a bypass passage having one end communicating with the duct upstream of the heat exchanger and an opposed end communicating with the duct downstream of the heat exchanger. 7. The system as defined in claim 1, wherein the fluid passages of the heat exchanger are configured to receive a liquid coolant. 8. An assembly comprising an engine core, the internal combustion engine forming part of the engine core and including at least one rotary internal combustion engine and the system as defined in claim 1, each rotary internal combustion engine having a housing including cooling passages in fluid communication with the fluid passages of the heat exchanger. 9. The assembly as defined in claim 8, wherein the forced air driver is a fan in driving engagement with the at least one rotary internal combustion engine. 10. A method of providing directional control in a rotorcraft having a main rotor and a tail boom, the method comprising: cooling a component of the rotorcraft with a liquid coolant;cooling the liquid coolant from the component in a heat exchanger by circulating a cooling airflow through the heat exchanger in heat exchange relationship with the liquid coolant; andcirculating the cooling airflow from the heat exchanger through the tail boom and out of the tail boom, including creating a boundary layer flow along an outer surface of the tail boom with the cooling airflow, and directing a downwash from the main rotor around the tail boom with the boundary layer flow to produce a thrust opposite a torque from the main rotor. 11. The method as defined in claim 10, wherein cooling the component of the rotorcraft with the liquid coolant includes circulating the liquid coolant through a housing of an internal combustion engine of an engine assembly of the rotorcraft. 12. The method as defined in claim 11, wherein circulating the cooling airflow is performed by driving rotation of a fan with the engine assembly. 13. The method as defined in claim 10, wherein circulating the cooling airflow out of the tail boom includes circulating the cooling airflow through two elongated slots extending along a length of the tail boom. 14. The method as defined in claim 10, wherein the boundary layer is created from a first part of the cooling airflow, the method further comprising expelling a second part of the cooling airflow out of the tail boom through a thruster, including orientating the thruster to create a yaw moment on the rotorcraft. 15. The method as defined in claim 14, further comprising modulating a flow of the cooling air out of the thruster. 16. A method of providing directional control in a rotorcraft having a main rotor and a tail boom, the method comprising: creating a flow of air from an environment of the rotorcraft into the tail boom, at least part of the air circulating in heat exchange relationship with a cooling fluid of the rotorcraft before reaching the tail boom, the air picking up heat from the cooling fluid; andcirculating air out of the tail boom through a thruster positionable to discharge the air along a selected one of opposed sides of the tail boom, including orienting the thruster to create a predetermined yaw moment on the rotorcraft with the air discharged therefrom. 17. The method as defined in claim 16, further comprising circulating the cooling fluid through a housing of an internal combustion engine of an engine assembly of the rotorcraft. 18. The method as defined in claim 17, wherein creating the flow is performed by driving rotation of a fan with the engine assembly. 19. The method as defined in claim 16, wherein circulating the cooling airflow out of the tail boom includes circulating the cooling airflow through at least one nozzle extending longitudinally along the tail boom to direct a downwash from the main rotor around the tail boom to create a thrust opposite a torque effect of the main rotor. 20. The method as defined in claim 16, further comprising modulating a flow of the air out of the thruster.
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이 특허에 인용된 특허 (4)
Daggett, David L., Aircraft wing heat exchanger apparatus and method.
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