子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Control system and method for a semi-levered landing gear for an aircraft | US10126226 | 2002-04-19 | US06575405B2 | 2003-06-10 | Malcom S. Bryant; Thomas R. Hasenoehrl; Jerome R. Kilner; Gary M. Lindahl; Taiboo Song |
| A control system for controlling a tiltable wheel truck of a main landing gear includes an auxiliary strut, a ground mode system operably connected with the aircraft for detecting and providing signals indicative of when the aircraft is on the ground; a takeoff mode system operably connected with the aircraft for detecting and providing signals indicative of when the aircraft is operating in a throttled-up mode; and an auxiliary strut control unit operably connected with the ground mode system, takeoff mode system, and auxiliary strut. The auxiliary strut control unit is operable to issue a lock-up command signal to the auxiliary strut upon detecting signals from the systems indicating that the aircraft is on the ground and that the aircraft is operating in a throttled-up mode, whereby the auxiliary strut is caused to lock up during a takeoff roll but is unlocked during other operating modes of the aircraft. | ||||||
| 122 | Control system and method for a semi-levered landing gear for an aircraft | US10126226 | 2002-04-19 | US20030033927A1 | 2003-02-20 | Malcom S. Bryant; Thomas R. Hasenoehrl; Jerome R. Kilner; Gary M. Lindahl; Taiboo Song |
| A control system for controlling a tiltable wheel truck of a main landing gear includes an auxiliary strut, a ground mode system operably connected with the aircraft for detecting and providing signals indicative of when the aircraft is on the ground; a takeoff mode system operably connected with the aircraft for detecting and providing signals indicative of when the aircraft is operating in a throttled-up mode; and an auxiliary strut control unit operably connected with the ground mode sensor, takeoff mode sensor, and auxiliary strut. The auxiliary strut control unit is operable to issue a lock-up command signal to the auxiliary strut upon detecting signals from the sensors indicating that the aircraft is on the ground and that the aircraft is operating in a throttled-up mode, whereby the auxiliary strut is caused to lock up during a takeoff roll but is unlocked during other operating modes of the aircraft. | ||||||
| 123 | Semi-levered landing gear and auxiliary strut thereof | US09716760 | 2000-11-20 | US06345564B1 | 2002-02-12 | Jerome Kilner; Gary Lindahl |
| A semi-levered landing gear includes a main strut, a wheel truck pivotally attached at a main pivot to a lower end of the main strut and supporting forward and aft wheels, and an auxiliary strut attached at its upper end to the main strut and at its lower end to the wheel truck forward of the main pivot. The auxiliary strut includes a main piston that slides within a cylinder barrel and is attached at its lower end to the auxiliary pivot, and a floating piston that slides relative to the cylinder barrel and the main piston and divides the cylinder barrel into a pair of fluid chambers. The main piston includes snubbing holes or orifices through which fluid can flow between the two fluid chambers. The auxiliary strut also includes a lock-up valve that slides relative to the floating and main pistons and is configured to close the fluid path through the snubbing holes or orifices when the main and floating pistons are in predetermined positions relative to the lock-up valve, thereby locking the strut at a predetermined fixed length. The lock-up valve is configured such that the strut locks up at an intermediate length between a minimum and a maximum length of the strut, so that on takeoff, as the main strut extends, the auxiliary strut locks up to cause the wheel truck to tilt into a nose-up attitude. In one embodiment, the lock-up valve is actuatable to move into either a retracted position providing a short extension before locking up, or an extended position enabling the auxiliary strut to extend a greater amount before locking up. The auxiliary strut is also actuatable to extend the main piston for stowing the landing gear and to retract the main piston for tilting the wheel truck on landing approach. | ||||||
| 124 | Shock absorber for aircraft landing gear | US000720 | 1993-01-05 | US5310139A | 1994-05-10 | Michel Derrien; Bernard Guyot |
| The invention relates to a shock absorber of the type comprising a cylinder and a sliding rod, together with a moving disk that defines a bottom hydraulic chamber that communicates via a diaphragm with a top hydraulic fluid chamber that is adjacent to a pressurized gas chamber formed in the top of the cylinder. According to the invention, a self-contained linear actuator is disposed coaxially inside the sliding rod, being interposed between the moving disk and a lower abutment secured to said sliding rod, independent control means being also provided to control the linear actuator, such that when said means are engaged they enable the landing gear to be extended when the aircraft is stationary on the ground. | ||||||
| 125 | Ground handling apparatus for a helicopter | US568885 | 1984-01-06 | US4600168A | 1986-07-15 | Charles E. Selecman |
| An apparatus with wheels which may be removably attached to either of the skid type landing rails of a helicopter. A generally U-shaped attaching member is adapted to be removably attached to either of the rails. A support member has its bottom end pivotally coupled to the top of said attaching member. Structure connected to said support member has an engaging end adapted to engage the top portion of said rail when said attaching member is attached to said rail. The central portion of a generally U-shaped axle member is pivotally coupled to the upper end of the support member. The axle member has two outwardly extending arms with wheels attached thereto such that the wheels will be located on opposite sides of the rail. One end of a cylinder is pivotally coupled to said structure. Said cylinder has a piston which is pivotally coupled to the central portion of said axle member offset from the axis of said central portion. When the piston is retracted, the wheels are at a position such that the rail engages and is supported by the ground. When the piston is extended, the wheels are moved to a position to lift and support the rail above the ground. | ||||||
| 126 | Shock absorber cartridge | US28452663 | 1963-05-31 | US3252548A | 1966-05-24 | PETER PAJAK THEODORE; WESLEY BARSAM EDWARD; MOLL BISHOP J |
| 127 | Nose-wheel under-carriage apparatus for aircraft | US25949163 | 1963-02-19 | US3150849A | 1964-09-29 | GRAHAM CONWAY HUGH; KEITH BOWDEN MALCOLM |
| 128 | Torque arm quick disconnect assembly | US73633447 | 1947-03-21 | US2487329A | 1949-11-08 | GERRY JULIAN E |
| 129 | Automatically operable safety landing switch for airplanes | US38065841 | 1941-02-26 | US2352692A | 1944-07-04 | DANN JOSEPH A |
| 130 | Aircraft structure | US17121537 | 1937-10-27 | US2230614A | 1941-02-04 | DE SEVERSKY ALEXANDER P |
| 131 | Safety device for airplanes | US11415936 | 1936-12-04 | US2161520A | 1939-06-06 | JAMES MARTIN |
| 132 | Safety frame for airplanes | US57609331 | 1931-11-19 | US1885881A | 1932-11-01 | GABRIEL WOLF |
| 133 | Safety device for aircraft | US30952828 | 1928-10-01 | US1787294A | 1930-12-30 | WARD WILLIS C |
| 134 | Aeroplane landing-gear arm | US35387529 | 1929-04-09 | US1741964A | 1929-12-31 | VARKAS SPIROS S |
| 135 | Landing gear | US14312226 | 1926-10-21 | US1633174A | 1927-06-21 | JULES FRITSCH |
| 136 | Airplane safety cage | US45824821 | 1921-04-04 | US1509962A | 1924-09-30 | LORENZ WILLIAM A |
| 137 | Wireless sensor architecture | US15606349 | 2017-05-26 | US10135624B2 | 2018-11-20 | Andrew Bill; Kurt Bruggemann; Timo Warns |
| A Wireless Access Point (WAP) for enabling remote access to data generated by systems of an aircraft including a wireless interface having a transmitter and a receiver; and a processor. The WAP is configured to: wirelessly receive sensor data generated by a plurality of sensors on an aircraft; receive aircraft data from an avionics system of the aircraft; wirelessly receive a data request signal from a remote computing device; and, responsive to the data request signal, wirelessly transmit to the remote computing device data based on received sensor data and/or received aircraft data. | ||||||
| 138 | AIRCRAFT DOOR CONTROL | US15980004 | 2018-05-15 | US20180327073A1 | 2018-11-15 | Mark GRUFFERTY; Nicholas ELLIOTT; Martin Griffith ROWLANDS; Christopher James PERKINS |
| An aircraft door controller 100 including a receiver 110 configured to receive a command 14 to move an aircraft door between an open position and a closed position relative to a door frame. The aircraft door controller 100 is configured to not store the command 14 when power to move the aircraft door between the open position and the closed position relative to the door frame is unavailable. | ||||||
| 139 | TAIL SKID SHOCK ABSORBER AND INDICATOR | US15493379 | 2017-04-21 | US20180304998A1 | 2018-10-25 | James E. CUSWORTH; Michael P. HUESTED; Justin D. COTTET |
| A tail skid shock absorber including an outer shock absorber canister, a crushable indicator cartridge disposed within the outer shock absorber canister, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit. | ||||||
| 140 | Aircraft landing gear assembly stop member | US14993437 | 2016-01-12 | US09994306B2 | 2018-06-12 | Lee Williams; Peter Millington; Anthony Foy; Richard Tutton |
| An aircraft landing gear assembly stop member is arranged to be coupled to a first part of an aircraft landing gear assembly and includes a pair of projections which control movement of a second part of the landing gear assembly. | ||||||
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