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Patent Searching and Data


Matches 601 - 650 out of 2,533

Document Document Title
WO/2007/106070A3
An airplane gear leg that is strong, stiff, and capable of storing large amounts of energy and formed of two composite materials. The first fiber material is very strong and flexible, allowing it to store a great deal of energy in a hard...  
WO/2007/005040A3
An adaptive landing gear system for use in an aircraft includes a plurality of leveling struts. Each leveling strut includes an adaptive portion and landing pad. Each adaptive portion includes a fluid reservoir. A change in the volume of...  
WO/2009/045788A2
Aircraft skid shoes (20) are provided with wear-resistant cladding layers (30). Powders of hard particles and braze material are impregnated into at least one cloth which is applied to the wear surface of a skid shoe (20) of a helicopter...  
WO/2009/037687A1
A Separate and mobile landing gear which substitutes the existing fixed landing gear in aircrafts. This innovated landing gear locks on the landing aircraft in the manner described in the detailed description.  
WO/2008/127468A3
Addressed are systems and methods for providing to pilots of landing aircraft real-time (or near real-time) information concerning runway conditions and aircraft-stopping performance to be encountered upon landing. The systems and method...  
WO/2009/037465A1
An overload detecting assembly comprises a first load bearing member (10) adapted to flex laterally in response to a load to be monitored, a second load bearing member (11) spaced from the first under normal load conditions and which is ...  
WO/2009/037475A1
A load indicator comprises a load bearing assembly of first and second load bearing members (23, 22) connected together to bear a lateral load applied to the first member (23), the first load bearing member defining a cavity (25) with th...  
WO/2009/034264A2
The invention relates to a method for making a mechanical part (10, 110) including at least one insert (3) made of a composite material with a metal matrix in which extend ceramic fibres, the composite material insert (3) being obtained ...  
WO/2009/010643A3
The invention relates to a shock absorber for the landing gear of an aircraft, including two members (1, 2) mounted so as to be capable of telescopically sliding one in the other and defining an inner volume filled with a hydraulic fluid...  
WO/2009/034263A2
The invention relates to a method for making a mechanical part (10) that comprises at least one insert (3) made of a composite material with a metal matrix in which extend ceramic fibres, the composite material insert (3) being obtained ...  
WO/2009/030200A1
The invention relates to a wheel bearing for aircraft, that has an increased service life and is more reliable having a small number of individual parts and consists of components that are simple to handle, to mount or to dismount. The i...  
WO/2009/031022A1
Flotation systems including separately packed floats (1) and life rafts (6) are disclosed. Such systems, advantageously used for helicopters or other vessels, attach rafts to exterior covers (3,4) of the floats. Thus, if not needed, or i...  
WO/2005/070761A3
An aircraft vehicular front wheel landing gear assembly is provided that includes a nonelastomeric outer upper strut tubular member (12) having an inner axial center bore (22) with a tubular cylindrical frictional interface inner surface...  
WO/2009/010643A2
The invention relates to a shock absorber for the landing gear of an aircraft, including two members (1, 2) mounted so as to be capable of telescopically sliding one in the other and defining an inner volume filled with a hydraulic fluid...  
WO/2009/007562A1
Steel characterized in that its composition is, in percentages by weight: - C = 0.20 - 0.30%; - Co = traces - 1%; - Cr = 2 - 5%; - Al = 1 - 2%; - Mo + W/2 = 1 - 4%; - V = traces - 0.3%; - Nb = traces - 0.1%; - B = traces - 30 ppm; - Ni =...  
WO/2009/004200A1
The invention relates to a landing gear casing that comprises a longitudinal box with walls defining an inner housing (24) open at the bottom and enabling the stowage of the landing gear (20) inside the housing and the deployment thereof...  
WO/2008/121530A4
Methods and apparatus are provided for optimizing runway exiting. Prior to landing, the pilot may choose to input one or more new landing parameters. Then, based on current landing parameters (e.g., any new landing parameter(s) and remai...  
WO/2006/094145A9
A landing gear (10) is equipped with a mechanism (66) that isolates a hydraulic pitch trimmer (72) outside of the landing loop thereby eliminating the need for complex hydraulics normally associated with articulated landing gear designs ...  
WO/2008/060338A4
Electrically controlled and/or actuated landing gear mechanisms are presented that allow for adjustment of aircraft attitude on the ground as well as for retraction and extension of the landing gear in a single unit. Most preferably, the...  
WO/2008/139072A3
The device of the invention includes a loading and non-compression position locking mechanism for a master cylinder (1) hydraulically connected to the tank and the braking members, wherein said mechanism is connected to a control member ...  
WO/2008/153547A1
A power management architecture as disclosed herein is suitable for use in connection with an electric brake system of an aircraft. During ground towing operations when the aircraft engines are off, the power management architecture prov...  
WO/2008/060338A3
Electrically controlled and/or actuated landing gear mechanisms are presented that allow for adjustment of aircraft attitude on the ground as well as for retraction and extension of the landing gear in a single unit. Most preferably, the...  
WO/2008/139072A2
The device of the invention includes a loading and non-compression position locking mechanism for a master cylinder (1) hydraulically connected to the tank and the braking members, wherein said mechanism is connected to a control member ...  
WO/2008/121530A3
Methods and apparatus are provided for optimizing runway exiting. Prior to landing, the pilot may choose to input one or more new landing parameters. Then, based on current landing parameters (e.g., any new landing parameter(s) and remai...  
WO/2008/135647A1
The invention relates to a landing gear including a noise reducing means (2) comprising at least one individual net (5) which is disposed close to a component (4) of the landing gear.  
WO/2008/100335A3
For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, wh...  
WO/2008/132375A1
According to the invention, in order to generate an efficient aerodynamic braking force independently from the speed of a vehicle such as an aircraft moving in the air, the method comprises a step of generating energy using the vehicle, ...  
WO/2008/131161A1
According to the present invention, an electromechanical braking system (10) is provided. The braking system (10) includes at least one brake system control unit (BSCU (20)) for converting an input brake command signal into a brake clamp...  
WO2007104862A8
The invention concerns a method for brake proportioning among an aircraft brakes, including the following steps: estimating a target brake load and a target yawing torque to be achieved by the aircraft brakes; defining at least two brake...  
WO/2008/105813A3
A system and procedures for adjusting a parking brake for an aircraft having an electric brake system are disclosed. Adjustment of a parking brake as described herein can compensate for thermal expansion or contraction of components of, ...  
WO/2008/121530A2
Methods and apparatus are provided for optimizing runway exiting. Prior to landing, the pilot may choose to input one or more new landing parameters. Then, based on current landing parameters (e.g., any new landing parameter(s) and remai...  
WO/2008/118229A2
A hybrid composite-metal component is provided. The component includes an elongate inner metal piece, an outer metal piece disposed about at least a portion of the inner metal piece, and composite material disposed between the inner meta...  
WO/2007/106863A3
A plasma fairing for reducing noise generated by, for example, an aircraft landing gear is disclosed. The plasma fairing includes at least one plasma generating device, such as a single dielectric barrier discharge plasma actuator, coupl...  
WO/2008/108933A1
An auxiliary on board power system (10, 110, 21) for an aircraft provides the capability of taxiing the aircraft (60) on the ground without using the main aircraft engine (s) (66). The power system includes a small driver (12) mounted on...  
WO/2008/105813A2
A system and procedures for adjusting a parking brake for an aircraft having an electric brake system are disclosed. Adjustment of a parking brake as described herein can compensate for thermal expansion or contraction of components of, ...  
WO/2008/102791A1
A wheel support device for an aircraft, having a suspension mechanism (2) for rotatably supporting a wheel (3) by the lower end of a support member (1) connected to an aircraft body. The suspension mechanism is provided with a crank elem...  
WO/2008/100335A2
For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, wh...  
WO2008060338A9
Electrically controlled and/or actuated landing gear mechanisms are presented that allow for adjustment of aircraft attitude on the ground as well as for retraction and extension of the landing gear in a single unit. Most preferably, the...  
WO/2008/076792A3
An electric brake system for an aircraft (100) includes a power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The interlock removes operating power from the brake mechanisms (124,126,128,130) whenever...  
WO/2008/048335A3
An aircraft shock strut (12) includes a titanium cylinder (32) and a piston (30) telescopically movable within the titanium cylinder (32). A first bearing (40) is mounted to the piston (30), and includes a non-metallic bearing surface (5...  
WO/2008/092270A1
This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be use...  
WO/2008/089511A1
A method of retrofitting retractable floats to an aircraft such as a floatplane. The aircraft considered have existing landing gear such as wheeled landing gear to equip said aircraft to optionally takeoff or land on a solid surface such...  
WO/2008/060996A3
A method and system for detecting a hard landing or other high load event of an aircraft are disclosed. A heuristic algorithm may be used to estimate loads experienced by the aircraft during landing. The heuristic algorithm may use fligh...  
WO/2008/086578A1
A suspension apparatus for providing a progressively dampened motion, said apparatus comprising a housing (14) defining a first chamber (12) having a first end (26) with said first chamber (12) containing a volume of liquid (52). The app...  
WO/2008/076792A2
An electric brake system for an aircraft (100) includes a power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The interlock removes operating power from the brake mechanisms (124,126,128,130) whenever...  
WO/2008/048701A3
A method and a brake assembly retention device are disclosed. The method discloses the automatic operation of the brake assembly retention device to retain releasably the brake assembly upon a stationary member. The retention device (300...  
WO/2008/054515A3
A method to detect if an aircraft is airborne or on the ground may include detecting at least one of a truck tilt of each main landing gear and a strut compression of each main landing gear. The method may also include detecting the airc...  
WO/2008/052051A3
A compact aircraft brake actuation measurement unit (5) mountable between left and right brake pedals for measuring the position of each pedal. The unit (5) can generate a signal indicative of a position of a pedal that can be used to co...  
WO/2008/065335A1
A braking system (1) for an aircraft which includes a by-pass control system (9) for activation when undemanded braking or loss of braking is detected. The braking system (1) comprises: a brake pedal transducer (2) for generating a brake...  
WO/2008/063685A2
A mechanism for increasing the ride height of aircraft by selectively increasing the hydraulic fluid content within landing gear struts. By increasing the hydraulic fluid volume within a strut, the strut is lengthened without adversely a...  

Matches 601 - 650 out of 2,533