起落板相关的专利数据

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	Operation panel in car for elevator, and operation panel of evacuation floor for elevator	JP2011190428	2011-09-01	JP2013052935A	2013-03-21	OSAWA TAKUYA; TABUCHI HIKARI; IWASE SHIGEKI; NAGAO AKIRA
PROBLEM TO BE SOLVED: To provide an elevator system that allows a rescuer to understand a location where a person having difficulty in evacuating by himself/herself in the event of disaster, and enables the person to be rapidly evacuated.SOLUTION: When an elevator is aggressively used in the event of the disaster, an existing fixed operation panel is difficult to properly cope with the disaster. The elevator system employs a touch panel in an operation panel at a landing space and in an operation panel in a car, and therefore can flexibly cope even with a situation required for a completely different function, without increasing the number of buttons and switches.
122	Aircraft landing gear having axle to brake plate integration	US09644931	2000-08-23	US06354537B1	2002-03-12	Harry C. Ralph
An aircraft landing gear brake arrangement wherein a landing gear stub axle and brake pressure plate are integrated. Each of the integrated assemblies is attached to a support fitting which pivots on the truck axle thereby causing the torque links to be unaffected by steering operations.
123	Common cast draft sill for type E and F draft gear	US10766930	2004-01-30	US20040245202A1	2004-12-09	Paul A. Limbach; Andrew G. Kurtyak; John F. Deppen; John F. Oesch
A common E/F type draft sill is provided that accommodates either Type E or Type F draft gear components, including rotary coupler applications. The draft sill is preferably cast, but may also be fabricated. The common E/F draft sill is provided with a fixed, integral spring basket of a Type F draft sill to accommodate and house standard spring-biased spring basket support systems and accommodate standard Type F draft gear. Standard vertical connection of Type F draft gear is provided. The common draft sill is also provided with the horizontal keyslot of a Type E draft sill to also accommodate attachment of Type E draft gear. A drop-in E coupler support is also available that replaces the nullspring basketnull support system used with Type F draft gear so as to allow proper support of Type E draft gear. Additional standardization and reduction of specialized castings can be achieved by incorporating both body bolster pads and body bolster wings on the common draft sill. Further standardization can be realized by providing a standardized machined end sill pad that accommodates a plurality of different design specifications for application with a plurality of different railcar specifications. Even further standardization can be realized by having flange hole patterns that accept multiple types of draft gear applications. Additional standardization can be achieved by having a standardized center sill facing end and a series of nullplug-n-receivernull combinations in which an application-specific nullplugnull is provided that may be welded on the center sill facing end of the common draft sill to adapt it to a particular configuration.
124	Common cast draft sill for type E and F draft gear	US10766930	2004-01-30	US06986432B2	2006-01-17	Paul A. Limbach; Andrew G. Kurtyak; John F. Deppen; John F. Oesch
A common E/F type draft sill is provided that accommodates either Type E or Type F draft gear components, including rotary coupler applications. The draft sill is preferably cast, but may also be fabricated. The common E/F draft sill is provided with a fixed, integral spring basket of a Type F draft sill to accommodate and house standard spring-biased spring basket support systems and accommodate standard Type F draft gear. Standard vertical connection of Type F draft gear is provided. The common draft sill is also provided with the horizontal keyslot of a Type E draft sill to also accommodate attachment of Type E draft gear. A drop-in E coupler support is also available that replaces the “spring basket” support system used with Type F draft gear so as to allow proper support of Type E draft gear. Additional standardization and reduction of specialized castings can be achieved by incorporating both body bolster pads and body bolster wings on the common draft sill. Further standardization can be realized by providing a standardized machined end sill pad that accommodates a plurality of different design specifications for application with a plurality of different railcar specifications. Even further standardization can be realized by having flange hole patterns that accept multiple types of draft gear applications. Additional standardization can be achieved by having a standardized center sill facing end and a series of “plug-n-receiver” combinations in which an application-specific “plug” is provided that may be welded on the center sill facing end of the common draft sill to adapt it to a particular configuration.
125	Landing gear for aircraft constructed with extruded fluted plastic sheet	US339586	1994-11-14	US5573204A	1996-11-12	George S. Barker; Lawrence H. Ragan
Aircraft components utilize flexible fluted extruded twin wall plastic sheet to form aileron hinges, horizontal staibilizers and elevators, vertical stabilizers and rudders, compound landing gear, struts, and control systems which are lighter in weight and lower in cost than previously available structures. The landing gear has damping characteristics superior to previous gear. The invention is particularly well suited to remotely controlled flying model aircraft.
126	Independent suspension undercarriage module for a low floor vehicle	US10021128	2001-12-12	US06893046B2	2005-05-17	Ragnar Ledesma; Lawrence Brill; Steven E. Hunter; Malcolm Green; Duy Lam; Mike Schuster; Tomaz Dopico Varela
An independent suspension undercarriage module includes a first subframe segment and a second subframe segment. The subframe is manufactured of a composite material to provide a truss-like structural unibody which is mounted as a unit to the underside of a low floor vehicle through a plurality of resilient dampers. Passengers are thereby provided with a secondary vibration isolation structure separate from the suspension systems which filter out high frequency content generated by the suspension systems.
127	Gripping and locking arrangement for aircraft flap doors or undercarriages	US484498	1990-02-23	US5040747A	1991-08-20	Brian Kane; Jurgen Laude
A gripping and locking arrangement for an aircraft movable component such as a flap door or undercarriage comprises a piston and a piston rod operative as a means for sensing a closing movement of the flap door or undercarriage, and also operative automatically actively to pull same by means of a closing hook into a position in which it is to be locked. The arrangement includes a locking member displaceable within the piston to move lock elements into a locking position and to hold them in the locking position until the arrangement receives a hydraulic pressure signal for causing lowering of the flap door or undercarriage, and the locking member is then displaced whereby the lock elements move into a release position. The hydraulic oil pressure can then act on the piston to produce displacement thereof into a position in which the closing hook releases the flap door or undercarriage component.
128	Independent suspension undercarriage module for a low floor vehicle	US10021128	2001-12-12	US20030111834A1	2003-06-19	Ragnar Ledesma; Lawrence Brill; Steven E. Hunter; Malcolm Green; Duy Lam; Michael Edward Schuster; Tomaz Dopico Varela
An independent suspension undercarriage module includes a first subframe segment and a second subframe segment. The subframe is manufactured of a composite material to provide a truss-like structural unibody which is mounted as a unit to the underside of a low floor vehicle through a plurality of resilient dampers. Passengers are thereby provided with a secondary vibration isolation structure separate from the suspension systems which filter out high frequency content generated by the suspension systems.
129	Sweeping track shoe for undercarriage system in a track-type machine	US12967608	2010-12-14	US08833871B2	2014-09-16	Kenneth Nebergall; Stephen Garnett; Britta A. Jost; Eric J. Johannsen
A ground engaging track for a track-type machine includes a set of identical standard track shoes each having a relatively narrow shoe footprint, and a sweeping track shoe having a relatively wide shoe footprint. The sweeping track shoe is connectable via track links with the standard track shoes in an endless chain configuration such that the sweeping track shoe juts outwardly of the standard track shoes, for sweeping debris from a clearance between the track and a main frame of the track-type machine. The sweeping track shoe includes bolting apertures formed therein and communicating between an upper shoe surface and a ground contacting shoe surface, the bolting apertures being arranged in a directional link bolting pattern. The directional link bolting pattern defines a minor shoe axis and a major shoe axis, and the sweeping shoe body may be configured such that an inboard sweeping edge is spaced further than an outboard edge from the minor shoe axis.
130	Cover panel for an aircraft, more particularly a landing gear cover panel for a cargo plane	US12457076	2009-06-01	US20090308976A1	2009-12-17	Hermann Benthien; Bjorn Bertram; Sandra Kuckuck; Frank Gustavel
The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap 6, 7. According to the invention the at least one flap 6, 7 is attached for swivel movement to the fuselage cell 2 of the aircraft by means of at least one multi-articulated joint 8, 9, 13 wherein the multi-articulated joint 8, 9, 13 is constructed with a number of individual joints seated on a shaft 17, similar to a piano hinge, and a mechanical play increases preferably uniformly starting from a middle individual joint 14 towards the outer individual joints 15, 16. As a result of the mechanical play which increases within the multi-articulated joint 8, 9, 13 from the middle individual joint 14 to the two outer individual joints 15, 16 in the direction of the x-axis or aircraft longitudinal axis, a substantial mechanical isolation of the cover panel from any possible fuselage cell movements is provided. The flap 7 has at least in the area of one side edge an anti-lift security mechanism 26 in order to prevent aerodynamically conditioned flapping and lifting movements of the flap 7 in the direction of the aircraft vertical axis or z-axis.
131	Cover panel for an aircraft, more particularly a landing gear cover panel for a cargo plane	US12457076	2009-06-01	US08740146B2	2014-06-03	Hermann Benthien; Björn Bertram; Sandra Kuckuck; Frank Gustävel
The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap 6, 7. According to the invention the at least one flap 6, 7 is attached for swivel movement to the fuselage cell 2 of the aircraft by means of at least one multi-articulated joint 8, 9, 13 wherein the multi-articulated joint 8, 9, 13 is constructed with a number of individual joints seated on a shaft 17, similar to a piano hinge, and a mechanical play increases preferably uniformly starting from a middle individual joint 14 towards the outer individual joints 15, 16. As a result of the mechanical play which increases within the multi-articulated joint 8, 9, 13 from the middle individual joint 14 to the two outer individual joints 15, 16 in the direction of the x-axis or aircraft longitudinal axis, a substantial mechanical isolation of the cover panel from any possible fuselage cell movements is provided. The flap 7 has at least in the area of one side edge an anti-lift security mechanism 26 in order to prevent aerodynamically conditioned flapping and lifting movements of the flap 7 in the direction of the aircraft vertical axis or z-axis.
132	Low load angle step deck trailer having shiftable undercarriage	US354637	1989-05-19	US5013056A	1991-05-07	Donald R. Landoll; Kelly Williams; Ted Peck
A trailer having a tiltable main deck and a shiftable undercarriage includes an undercarriage assembly having a deck support structure mounted thereon for supporting the deck. The deck support structure includes lifting arms for lifting the elongated deck assembly relative to the undercarriage independently of the undercarriage shifting mechanism so that the deck may be lifted relative to the undercarriage without simultaneouly shifting the undercarriage along the deck. The trailer may include a hitch assembly that permits the trailer to be pivotally connected to a towing vehicle to permit the forward deck to be tilted away from the main deck to increase the angle between the main deck and the forward deck when the trailer is in the unloading position. Further, a deck angle adjustment assembly is disclosed for adjusting the relative positions of the decks.
133	Track-type machine having undercarriage system with sweeping track shoe	US12967674	2010-12-14	US08764128B2	2014-07-01	Kenneth Nebergall; Stephen Garnett; Britta A. Jost
A ground engaging track for a track-type machine includes a set of identical standard track shoes each having a relatively narrow shoe footprint, and a sweeping track shoe having a relatively wide shoe footprint. The sweeping track shoe is connectable via track links with the standard track shoes in an endless chain configuration such that the sweeping track shoe juts outwardly of the standard track shoes, for sweeping debris from a clearance between the track and a main frame of the track-type machine. The sweeping track shoe includes bolting apertures formed therein and communicating between an upper shoe surface and a ground contacting shoe surface, the bolting apertures being arranged in a directional link bolting pattern. The directional link bolting pattern defines a minor shoe axis and a major shoe axis, and the sweeping shoe body may be configured such that an inboard sweeping edge is spaced further than an outboard edge from the minor shoe axis.
134	Track-Type Machine Having Undercarriage System With Sweeping Track Shoe	US12967674	2010-12-14	US20120146399A1	2012-06-14	Kenneth Nebergall; Stephen Garnett; Britta A. Jost
A ground engaging track for a track-type machine includes a set of identical standard track shoes each having a relatively narrow shoe footprint, and a sweeping track shoe having a relatively wide shoe footprint. The sweeping track shoe is connectable via track links with the standard track shoes in an endless chain configuration such that the sweeping track shoe juts outwardly of the standard track shoes, for sweeping debris from a clearance between the track and a main frame of the track-type machine. The sweeping track shoe includes bolting apertures formed therein and communicating between an upper shoe surface and a ground contacting shoe surface, the bolting apertures being arranged in a directional link bolting pattern. The directional link bolting pattern defines a minor shoe axis and a major shoe axis, and the sweeping shoe body may be configured such that an inboard sweeping edge is spaced further than an outboard edge from the minor shoe axis.
135	Method and device for an optimal management of the slats, the flaps and the landing gear of an aircraft	US13557381	2012-07-25	US08864081B2	2014-10-21	Florian Constans; Mickaël Lefebvre
A method is described for optimized energy management of an aircraft upon a flight along a trajectory. The method allows the aircraft to join a given point of the trajectory in a given energy state, with a given position of the slats and flaps, and with a given position of the landing gear. The method includes determining current parameter values of the aircraft. The method also includes determining optimized command orders based on the current parameter values by performing a sequence of operations in an iterative way. The method further includes applying the optimized command orders to an automatic slats and flaps command device and an automatic landing gear command device for automatic control of the slats and flaps and the landing gear, respectively.
136	Method And Device For An Optimal Management Of The Slats, The Flaps And The Landing Gear Of An Aircraft	US13557381	2012-07-25	US20130026299A1	2013-01-31	Florian Constans; Mickaël Lefebvre
Method and device for an optimal management of the slats, the flaps and the landing gear of an aircraft.The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state, optimal commands of means (10, 11) for controlling the slats, the flaps and the landing gear of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given energy state with a given aerodynamic configuration and a given position of the landing gear.
137	METHOD FOR INFLIGHT DEICING OF LANDING GEAR AND WHEEL BAYS IN AIRCRAFT WITH ONBOARD DRIVE MEANS	US13779724	2013-02-27	US20150210399A1	2015-07-30	Isaiah W. Cox
A method is provided for removing ice, snow, slush, and frozen contaminants from landing gear, wheel wells, and associated structures while an aircraft is in flight and preventing the accumulation of frozen contaminants during flight in an aircraft equipped with onboard drive means powered to drive at least one landing gear wheel and selectively controllable to move the aircraft on the ground during taxi in winter and other weather conditions.
138	Dispositif d'augmentation de la stabilité des hélicoptères embarqués et posés, à train d'atterrissage tricycle, et hélicoptère équipé d'un tel dispositif	EP89400076.9	1989-01-10	EP0324683A1	1989-07-19	Bernard, Louis Arthur; Thomassin, René
L'invention concerne un dispositif d'augmentation de la stabilité, en particulier latérale, d'un hélicoptère embarqué (1) à train d'atterrissage tricycle (2, 6), lorsqu'il est posé sur une plate-forme mouvante. Le dispositif comprend deux stabilisateurs latéraux (13) munis chacun d'une roue (16) d'appui sur la plate-forme et relié à la structure de l'hélicoptère par un support essentiellement rigide comprenant une jambe (17), autour de l'axe de laquelle la roue (16) peut tourillonner, la jambe (17) étant elle-même reliée à la structure par un organe rigide et transversale pouvant être un axe de pivot si la jambe est relevable, ou un bras d'emmanchement si le stabilisateur (13) est additionnel. Les stabilisateurs peuvent aussi être intégrés à un chariot de remorquage. Application à l'équipement des hélicoptères embarqués à train d'atterrissage tricycle.
139	仿真飞机起落架模拟装置	CN201510632393.2	2015-09-29	CN105160961B	2017-12-26	陈笑慰
一种仿真飞机起落架模拟装置，包括：左固定板及右固定板，设有起落架三档位位置槽及起落架限位装置槽；起落架操纵杆，通过支撑轴固定在左固定板与右固定板之间；多个起落架档位感应开关，靠近起落架三档位位置槽及起落架三档位位置槽的档位设置于左固定板或右固定板上；起落架收放限位杆，固定在设置起落架操纵杆上，与起落架三档位位置槽及起落架三档位位置槽相配合；电磁铁，固定在左固定板与右固定板之间；限位装置，在电磁铁的作用下撑起或者落下；限位轴，固定在起落架操纵杆的末端，可沿起落架限位装置槽及起落架限位装置槽滑动；服务器，接收起落架档位感应开关传输的位置数据，根据位置数据控制限位装置的撑起或者落下。
140	仿真飞机起落架模拟装置	CN201510632393.2	2015-09-29	CN105160961A	2015-12-16	陈笑慰
一种仿真飞机起落架模拟装置，包括：左固定板及右固定板，设有起落架三档位位置槽及起落架限位装置槽；起落架操纵杆，通过支撑轴固定在左固定板与右固定板之间；多个起落架档位感应开关，靠近起落架三档位位置槽及起落架三档位位置槽的档位设置于左固定板或右固定板上；起落架收放限位杆，固定在设置起落架操纵杆上，与起落架三档位位置槽及起落架三档位位置槽相配合；电磁铁，固定在左固定板与右固定板之间；限位装置，在电磁铁的作用下撑起或者落下；限位轴，固定在起落架操纵杆的末端，可沿起落架限位装置槽及起落架限位装置槽滑动；服务器，接收起落架档位感应开关传输的位置数据，根据位置数据控制限位装置的撑起或者落下。

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