IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0791216
(2010-06-01)
|
등록번호 |
US-8196857
(2012-06-12)
|
우선권정보 |
FR-09 02685 (2009-06-04) |
발명자
/ 주소 |
- Gemmati, Bernard
- Biest, Romuald
- Mirman, Carine
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
8 |
초록
▼
The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of said aircraft (1)
The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of said aircraft (1) suitable for causing a change in flight attitude. Said bellcrank (40) includes first and second sliders (50, 52). Said first slider (50) is connected to a movable portion (57, 61) of a setpoint flight-attitude-changing linkage (24) that delivers a setpoint, with movements of said linkage causing the gain of said variable-gain linkage (27, 25A, 28A) to be adjusted, which gain is proportional to the position of said movable portion (57, 61).
대표청구항
▼
1. A bellcrank for a manual flight control device dedicated to making a selected flight attitude change in a rotary wing aircraft receiving it, said bellcrank comprising at least a main body mounted to pivot about a pivot axis, said main body defining perpendicularly to said axis both a first radius
1. A bellcrank for a manual flight control device dedicated to making a selected flight attitude change in a rotary wing aircraft receiving it, said bellcrank comprising at least a main body mounted to pivot about a pivot axis, said main body defining perpendicularly to said axis both a first radius and a second radius that diverge from each other at a crank angle; said first radius having a first hinge at its outside end and said second radius having a second hinge at its outside end, the hinges being suitable for connecting the first and second radii respectively to first and second portions of a flight-attitude-changing linkage that actuates at least one airfoil of the aircraft receiving the crank, wherein said flight-attitude-changing linkage is of gain that is variable, and wherein, for this purpose, said bellcrank includes a first slider suitable for being moved relative to the pivot axis in a first direction for adjusting the length of the first radius, while a second slider is suitable for being moved relative to the pivot axis in a second direction for adjusting the length of the second radius, said first slider including a connection finger close to the inlet movement hinge, the finger being for connection to a setpoint flight-attitude-changing linkage that is distinct from the variable-gain linkage, said finger) being movable between two extreme positions for minimum gain and for maximum gain. 2. A bellcrank according to claim 1, wherein the first and second portions of the flight-attitude-changing linkage are also connected respectively to the manual flight control device and to at least one airfoil. 3. A bellcrank according to claim 1, wherein the first and second portions of the flight-attitude-changing linkage are also connected respectively to at least one airfoil and to the manual flight control device. 4. A bellcrank according to claim 1, wherein an interlink of fixed length connects the first slider to the second slider so that the variation in the gain of said flight-attitude-changing linkage is linear. 5. A bellcrank according to claim 1, wherein each of said first and second hinges includes a pivot axis substantially parallel to said pivot axis of the crank, whereas close to the first hinge, for said connection of the setpoint linkage to the variable-gain linkage, said connection finger is rigidly fastened to said first slider and to a movable element of the setpoint linkage, such that the movements of said finger are parallel to said first radius between two extreme positions of minimum gain and of maximum gain. 6. A bellcrank according to claim 4, wherein the movements of said connection finger between the two extreme positions act via the interlink respectively to adjust the lengths of the first radius and of the second radius, said setpoint linkage being connected to a manual control member for controlling the thrust of the aircraft. 7. A bellcrank according to claim 4, wherein the interlink is arranged within the bellcrank so that the length adjustment RP of the first radius and the length adjustment RD of the second radius are such that the ratio RD/RP lies in the range 1 to 3 respectively for a minimum relative gain in the extreme position and for a maximum relative gain in the extreme position. 8. A bellcrank according to claim 1, wherein the first radius forms a crank angle relative to the second radius lying in the range 30° to 180°, and particularly in the range 45° to 90°, with the second slider being connected to the variable-gain linkage via a pull rod extending substantially parallel to the first slider. 9. A bellcrank according to claim 1, wherein the first and second sliders are of circular cross-section relative to their respective radii, the sliders being guided in rectilinear movement in translation, each in a respective complementary housing in the main body. 10. A bellcrank according to claim 4, wherein the first and second hinges and the hinges of the interlink are ball joints and/or bearings. 11. A bellcrank according to claim 1, wherein the first and second hinges serve to connect said crank to a yaw flight-attitude-changing linkage that is of variable gain, and the manual control device is a rudder bar. 12. A bellcrank according to claim 1, wherein the first and second hinges enable said crank to be connected to a pitch flight-attitude-changing linkage of the variable gain type, and the manual control device is a cyclic pitch stick. 13. A bellcrank according to claim 1, wherein the first and second hinges enable said crank to be connected to a roll flight-attitude-changing linkage of the variable gain type, and the manual control device is a cyclic pitch stick. 14. A bellcrank according to claim 1, wherein the first and second hinges enable said crank to be connected to an altitude flight-attitude-changing linkage of the variable gain type, and the manual control device is a collective pitch lever. 15. A bellcrank according to claim 1, wherein the connection finger is secured to a movable element in the form of an element for unidirectional transmission of the setpoint that is suitable for transmitting forces solely from the control member towards the control device. 16. A bellcrank according to claim 1, wherein the connection finger is rigidly secured to a moving portion in the form of a transmission cable that extends locally between two guide pulleys substantially parallel to the first radius, the transmission cable forming part of the setpoint linkage and being connected to a manual thrust control member. 17. A bellcrank according to claim 16, wherein said guide pulleys are held between two holding walls extending substantially parallel to the pivot axis of the crank and to the first radius, these two holding walls also supporting two grooved wheels that are placed facing each other to guide the movable portion for transmitting the setpoint, and against which the movable portion bears. 18. A bellcrank according to claim 16, wherein the transmission cable follows a loop between the two holding walls running from two inlet strands located upstream and extending substantially parallel and close together, and passing on the inside between two upper grooved wheels and then on the outside around two guide pulleys, between which it is secured to said connection finger. 19. A rotary wing aircraft fitted with at least one bellcrank according to claim 1, wherein the aircraft is a hybrid helicopter, the connection finger being connected to a setpoint flight-attitude-changing linkage that controls a differential advance thrust by adjusting the pitches of the blades of the propellers of at least two propulsion arrangements, one on the left and the other on the right of the aircraft.
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