Auxiliary nose undercarriage, a force-transmission structure, and a rotary wing aircraft
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-025/10
B64C-025/00
B64C-025/14
B64C-025/20
B64C-001/00
B64C-030/00
출원번호
US-0408171
(2006-04-21)
등록번호
US-7407134
(2008-08-05)
우선권정보
FR-05 04030(2005-04-22)
발명자
/ 주소
Bietenhader,Claude
출원인 / 주소
Eurocopter
대리인 / 주소
Young & Thompson
인용정보
피인용 횟수 :
8인용 특허 :
19
초록▼
A steerable auxiliary nose undercarriage (2) for a rotary wing aircraft (1); the undercarriage (2) being retractable substantially rearwards. In the undercarriage (2), an oscillating system (13) presents a elevation stroke (58) about its hinged front end (52) that is greater than a shock absorbing s
A steerable auxiliary nose undercarriage (2) for a rotary wing aircraft (1); the undercarriage (2) being retractable substantially rearwards. In the undercarriage (2), an oscillating system (13) presents a elevation stroke (58) about its hinged front end (52) that is greater than a shock absorbing stroke (59), and a shock-absorbing actuator (9) possesses retraction elements for going beyond a high abutment position of the oscillating system (13) so that the oscillating system (13) and the shock-absorbing actuator (9) provide both a shock-absorption function and an undercarriage retraction function.
대표청구항▼
What is claimed is: 1. A steerable auxiliary nose undercarriage for a rotary wing aircraft, the undercarriage being retractable substantially rearwards and comprising at least: a wheel set having a wheel axle about which at least one wheel rotates; a generally longitudinally-extending oscillating s
What is claimed is: 1. A steerable auxiliary nose undercarriage for a rotary wing aircraft, the undercarriage being retractable substantially rearwards and comprising at least: a wheel set having a wheel axle about which at least one wheel rotates; a generally longitudinally-extending oscillating system having a first end adjacent to the wheel axle, and a hinged front end that is longitudinally opposite from said first end, the oscillating system being pivotally mounted via at least one transverse hinge for anchoring to a force-transmission structure for being rigidly secured to the aircraft, and the wheel axle being arranged on the oscillating system via a steering pivot; and a shock-absorbing actuator having a connection end hinged to the oscillating system between the hinged front end and the first end, the shock-absorbing actuator having a coupling end axially opposite from the connection end, the coupling end being hinged to the structure, the oscillating system being vertically swingable about the hinged front end over a distance that is greater than a shock-absorbing stroke; wherein: said steering pivot comprises a steering axis substantially intersecting the wheel axle, said steering pivot enabling the wheel to be steered on either side of a position corresponding to the aircraft running in a straight line by means of a steering actuator connected to a portion of the steering pivot that is constrained to pivot with the wheel axle, said steering pivot and said steering actuator both being substantially integrated around the steering axis, so that said steering axis extends through both said steering pivot and said steering actuator; and the shock-absorbing actuator possesses means for retracting the oscillating system beyond an abutment position marking the end of the shock-absorbing stroke, so that the oscillating system and the shock-absorbing actuator perform both a function of absorbing shocks and a function of retracting the undercarriage. 2. An undercarriage (2) according to claim 1, wherein the connection end (56) and the coupling end (57) of the shock-absorbing actuator (9) are hinged by ball joints respectively to the oscillating system (13) and to the structure (5), in such a manner that the shock-absorbing actuator (9) is stressed mainly along its sliding axis. 3. An undercarriage (2) according to claim 1, wherein the shock-absorbing actuator (9) extends substantially in an elevation direction (Z), with its coupling end then being a top for being hinged to a portion of the structure (5) which likewise extends substantially in the elevation direction (Z). 4. An undercarriage according to claim 3, wherein the shock-absorbing actuator extends substantially in an elevation direction, the connection end of the shock-absorbing actuator being close to the first end of the oscillating system. 5. An undercarriage according to claim 1, wherein the oscillating system is a trailed single-arm rocker that rocks in elevation. 6. An undercarriage according to claim 1, wherein the wheel set possesses at least one wheel and its tread coming in elevation substantially up to the level of the first end of the oscillating system. 7. A force-transmission structure for a rotary wing aircraft, with at least one undercarriage, said under carriage comprising a steerable auxiliary nose undercarriage for a rotary wing aircraft, the undercarriage being retractable substantially rearwards and comprising at least a wheel set having a wheel axle about which at least one wheel rotates; a generally longitudinally-extending oscillating system having a first end adjacent to the wheel axle, and a hinged front end that is longitudinally opposite from said first end, the oscillating system being pivotally mounted via at least one transverse hinge for anchoring to a force-transmission structure for being rigidly secured to the aircraft, and the wheel axle being arranged on the oscillating system via a steering pivot; and a shock-absorbing actuator having a connection end hinged to the oscillating system between the hinged front end and the first end, the shock-absorbing actuator having a coupling end axially opposite from the connection end, the coupling end being hinged to the structure, the oscillating system being vertically swingable about the hinged front end over a distance that is greater than a shock-absorbing stroke, wherein said steering pivot comprises a steering axis substantially intersecting the wheel axle, said steering pivot enabling the wheel to be steered on either side of a position corresponding to the aircraft running in a straight line by means of a steering actuator connected to a portion of the steering pivot that is constrained to pivot with the wheel axle, and wherein the shock-absorbing actuator possesses means for retracting the oscillating system beyond an abutment position marking the end of the shock-absorbing stroke, so that the oscillating system and the shock-absorbing actuator perform both a function of absorbing shocks and a function of retracting the undercarriage, said under carriage being mounted on said structure said structure comprising at least: a rigid arrangement extending substantially in an elevation direction; a structural bottom floor rigidly connected to the arrangement and defining at least part of a well for retracting the undercarriage; and within the structural bottom floor at least an anchor point for receiving said transverse hinge of the oscillating system of the undercarriage; wherein, in longitudinal elevation view, the structure presents an L-shape in which the arrangement forms a transversely centered box and at least two lateral arms which extend substantially in the elevation direction and form with the box a transverse passage on either side of the box, the structural bottom floor extends from the box and the lateral arms substantially longitudinally in a forward direction. 8. A structure according to claim 7, wherein a transverse hinge for anchoring the shock-absorbing actuator is disposed substantially vertically above the box. 9. A structure according to claim 7, wherein the connection end of the shock-absorbing actuator connecting it to the oscillating system is disposed substantially vertically above in the box.
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이 특허에 인용된 특허 (19)
Abramovitsh Dan (Rehovot ILX), Aircraft landing gear shortening apparatus.
Lucienne Philippe (Aumont FRX) De Pindray Albert (Magny-les-Hameaux FRX), Force-limiting device for an aircraft landing gear shock absorber, and a shock absorber including such a device.
Aubry Jacques A. (Cabries FRX) Mauduit Daniel A. (Marignane FRX), Shock absorbing jack, a stay comprising it and landing gear equipped with such a stay.
Mairou, Joseph; Bertin, Didier; Lassus, Vincent; Nicola, Jean, Energy absorber system for an undercarriage, and an aircraft provided with said energy absorber system.
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