Long-range aircraft with high forward speed in cruising flight
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/22
B64C-027/26
출원번호
US-0946932
(2010-11-16)
등록번호
US-8540184
(2013-09-24)
우선권정보
FR-09 05521 (2009-11-17)
발명자
/ 주소
Gemmati, Bernard
출원인 / 주소
Eurocopter
대리인 / 주소
Brooks Kushman P.C.
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
The present invention relates to an aircraft (1) comprising an airframe (2) provided with a fuselage (10) and fixed wings (20), a rotary wing (30), at least two propellers (41, 42), and a power plant suitable for driving said rotary wing (30) and said propellers (41, 42) into rotation. The fixed win
The present invention relates to an aircraft (1) comprising an airframe (2) provided with a fuselage (10) and fixed wings (20), a rotary wing (30), at least two propellers (41, 42), and a power plant suitable for driving said rotary wing (30) and said propellers (41, 42) into rotation. The fixed wings (20) comprise a front wing (21) arranged in the high portion (15) of the front portion (11) of the fuselage (10), and a rear wing (22) arranged in the rear portion (13) of said fuselage (10), said front and rear wings (21 and 22) each extending transversely on either side of the fuselage (10), said front wing (21) having a first front half-wing (21′) and a second front half-wing (21″), at least one of said propellers (41) being mounted on said first front half-wing (21′) and at least one of said propellers (42) being mounted on said second front half-wing (21″), said rotary wing (30) being arranged in the central portion (12) so that an axis of rotation (AX) of the rotor (31) of said rotary wing (30) is located between said front and rear wings (21 and 22).
대표청구항▼
1. An aircraft with a long-range and with high forward speed, the aircraft comprising: an airframe provided with a fuselage extending along a longitudinal direction (X) from a front portion towards a rear portion and passing via a central portion, and in a vertical direction (Z) from a low portion t
1. An aircraft with a long-range and with high forward speed, the aircraft comprising: an airframe provided with a fuselage extending along a longitudinal direction (X) from a front portion towards a rear portion and passing via a central portion, and in a vertical direction (Z) from a low portion to a high portion;fixed wings secured to the fuselage;a rotary wing above the the fuselage;at least two propellers for enhancing advance of the aircraft; anda power plant suitable for driving the rotary wing and the propellers into rotation;wherein the fixed wings comprise a front wing arranged in the high portion of the front portion of the fuselage and a rear wing arranged in the rear portion of the fuselage, the front and rear wings each extending transversely on either side of the fuselage, the front wing having a first front half-wing extending transversely from the fuselage in a first front traverse direction (Y1) and a second front half-wing extending transversely from the fuselage in a second front transverse direction (Y2), at least one of the propellers being mounted on the first front half-wing and at least one of the propellers being mounted on the second front half-wing, the rotary wing being arranged in the central portion so that the axis of rotation (AX) of a rotor of the rotary wing lies between the front and rear wings, wherein the rear wing is located in the low portion of the rear portion of the fuselage. 2. An aircraft according to claim 1, wherein the rear wing has a first rear half-wing extending transversely from the fuselage in a first rear transverse direction (Y3) and a second rear half-wing extending transversely from the fuselage in a second rear transverse direction (Y4), the aircraft including landing gear provided with a first wheel set fastened to the front portion of the fuselage, a second wheel set fastened to the first rear half-wing, and a third wheel set fastened to the second rear half-wing. 3. An aircraft according to claim 1, wherein each propeller forms part of a propulsion engine unit provided with a streamlined nacelle fairing an engine of the power plant, the nacelle being mounted on the top of a front half-wing. 4. An aircraft according to claim 1, wherein the power plant has a plurality of propulsion engine units, the aircraft including a mechanical interconnection system between the propulsion engine units and the rotary wing. 5. An aircraft according to claim 1, including declutching means for declutching the rotary wing so that the power plant no longer drives the rotary wing in rotation during certain stages of flight. 6. An aircraft according to claim 1, wherein a front wing area of the front wing is equal to a rear wing area of the rear wing. 7. An aircraft according to claim 1, wherein the fixed wings present a total wing area equal to the sum of a front wing area of the front wing and a rear wing area of the rear wing, the aircraft being suitable for flying at a speed going from zero speed to a maximum speed and passing via a mean speed equal to half the maximum speed, the total wing area generating lift equal to the weight of the aircraft: under a load factor equal to the acceleration due to gravity, and at a forward speed equal to the mean speed; andunder a load factor equal to four times the acceleration due to gravity, and at a forward speed equal to the maximum speed. 8. An aircraft according to claim 1, including stabilization and control surfaces, namely: first flaps for controlling pitching and roll arranged at the trailing edge of each wing of the fixed wings; anda fin provided with at least one second flap for yaw control. 9. An aircraft according to claim 1, wherein the rotary wing is provided with a rotor having a plurality of blades rotating about an axis of rotation (AX), and the center of gravity of the aircraft moves within a centering range as a function of the loading of the aircraft, a mean center of gravity (Cgmoy) being placed at the center of the centering range, and the axis of rotation (AX) being located in a transverse plane (P2) of the aircraft containing the center of gravity of the aircraft. 10. An aircraft according to claim 1, wherein a first aspect ratio (λ1) of the front wing is greater than a second aspect ratio (λ2) of the rear wing. 11. An aircraft with a long-range and with high forward speed, the aircraft comprising: an airframe provided with a fuselage extending along a longitudinal direction (X) from a front portion towards a rear portion, and in a vertical direction (Z) from a low portion to a high portion, the high portion being disposed above the low portion;fixed wings secured to the fuselage;a rotary wing above the fuselage;at least two propellers for enhancing advance of the aircraft; anda power plant suitable for driving the rotary wing and the propellers into rotation;wherein the fixed wings comprise a front wing extending transversely from the high portion of the front portion of the fuselage and a rear wing extending transversely from the low portion of the rear portion of the fuselage, the front wing having a first front half-wing extending transversely from the fuselage in a first front traverse direction (Y1) and a second front half-wing extending transversely from the fuselage in a second front transverse direction (Y2) opposite the first front transverse direction, at least one of the propellers being mounted on the first front half-wing and at least one of the propellers being mounted on the second front half-wing, the rotary wing being arranged above a central portion of the fuselage so that the axis of rotation (AX) of a rotor of the rotary wing lies between the front and rear wings. 12. An aircraft according to claim 11, wherein the rear wing has a first rear half-wing extending transversely from the fuselage in a first rear transverse direction (Y3) and a second rear half-wing extending transversely from the fuselage in a second rear transverse direction (Y4) opposite the first rear transverse direction, the aircraft including landing gear provided with a first wheel set fastened to the front portion of the fuselage, a second wheel set fastened to the first rear half-wing, and a third wheel set fastened to the second rear half-wing. 13. An aircraft according to claim 11, wherein the rear wing is disposed entirely behind the front wing. 14. An aircraft according to claim 11, wherein the power plant has a plurality of propulsion engine units, the aircraft including a mechanical interconnection system between the propulsion engine units and the rotary wing. 15. The aircraft of claim 14, wherein the rear wing has a first rear half-wing extending transversely from the fuselage in a first rear transverse direction (Y3) and a second rear half-wing extending transversely from the fuselage in a second rear transverse direction (Y4). 16. An aircraft according to claim 11, wherein the rotary wing is provided with a rotor having a plurality of blades rotating about an axis of rotation (AX), and the center of gravity of the aircraft moves within a centering range as a function of the loading of the aircraft, a mean center of gravity (Cgmoy) being placed at the center of the centering range, and the axis of rotation (AX) being located in a transverse plane (P2) of the aircraft containing the center of gravity of the aircraft. 17. An aircraft with a long-range and with high forward speed, the aircraft comprising: an airframe provided with a fuselage extending along a longitudinal direction (X) from a front portion towards a rear portion, and in a vertical direction (Z) from a low portion to a high portion, the front portion being disposed in front of the rear portion and the high portion being disposed above the low portion;a front wing secured to the front portion and the high portion of the fuselage;a rear wing secured to the rear portion and the low portion of the fuselage;a rotary wing supported above the fuselage;at least two propellers for enhancing advance of the aircraft; anda power plant suitable for driving the rotary wing and the propellers into rotation;the front wing extending transversely from the high and front portions of the fuselage and the rear wing extending transversely from the low and rear portions of the fuselage,the at least two propellers being mounted on the front wing, andthe rotary wing being arranged above a central portion of the fuselage so that the axis of rotation (AX) of a rotor of the rotary wing lies between the front and rear wings. 18. The aircraft of claim 17, wherein the front wing has a first front half-wing extending transversely from the fuselage in a first front traverse direction (Y1) and a second front half-wing extending transversely from the fuselage in a second front transverse direction (Y2), at least one of the propellers being mounted on the first front half-wing and at least one of the propellers being mounted on the second front half-wing. 19. The aircraft of claim 17, wherein the wings present a total wing area equal to the sum of a front wing area of the front wing and a rear wing area of the rear wing, the aircraft being suitable for flying at a speed going from zero speed to a maximum speed and passing via a mean speed equal to half the maximum speed, the total wing area generating lift equal to the weight of the aircraft: under a load factor equal to the acceleration due to gravity, and at a forward speed equal to the mean speed; andunder a load factor equal to four times the acceleration due to gravity, and at a forward speed equal to the maximum speed. 20. The aircraft of claim 17, wherein the rotary wing is provided with a rotor having a plurality of blades rotating about an axis of rotation (AX), and the center of gravity of the aircraft moves within a centering range as a function of the loading of the aircraft, a mean center of gravity (Cgmoy) being placed at the center of the centering range, and the axis of rotation (AX) being located in a transverse plane (P2) of the aircraft containing the center of gravity of the aircraft.
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