70results about "Energy efficient operational measures" patented technology

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

A kind of wheel holding device of aircraft tractor, it includes: car body, pedestal turntable, load floor, hydraulic cylinder group, clamping push plate, rotating motor and front pressing plate;Pedestal turntable, load floor, hydraulic cylinder group, clamping push plate, rotating motor and front pressing plate are all installed on car body.The wheel holding device of aircraft tractor provided by the present application has the advantages that: the wheel holding device does not need engine power, and moves by external ground power from the exit of the aircraft to the end of the runway waiting for takeoff, and the pilot controls the tractor to carry out departure operation, with the advantages of simple operation, safety, stable work, long service life, high lifting height, wide application range, etc.

An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

A method for extending a landing gear system for a vehicle is disclosed. The landing gear system includes a first landing gear assembly and a second landing gear assembly. The method includes the steps of sensing a first load on the first landing gear assembly after the first landing gear assembly has reached a wheels-on-ground state and comparing the first load to a first target value. The method further includes the step of controlling an extension speed of the first landing gear assembly according to a difference between the first load and the first target value.

The invention relates to an aircraft wheel electric motor (1) (1000) comprising a through bore and concentric rings of poles (P) enabling the generation of torque sufficient to operate the aircraft while maintaining a similar overall size to conventional solutions. The invention also relates to an aircraft wheel comprising such a motor (1), an aircraft wheel control assembly, and an aircraft (1000). Advantageously, it is thus possible to use an aircraft electric wheel in place of a conventional wheel, without substantial modification to the aircraft landing gear.

Processes and systems for operating an aircraft having a first engine and a second engine, a non-transitory computer readable media comprising computer executable instructions that when executed cause a processor to execute the steps of the present processes. A plurality of taxiways are determined and zones for changing to or from single engine taxing operations are also determined and displayed. Additionally, countdown timers for takeoff or engine shutdown may be displayed.

The invention relates to a towed aircraft refueling system which comprises a refueling control device, an interlocking device, a hydraulic device and an electric control device. The refueling control device is installed on a pipeline refueling trailer and comprises a ground well hose connector, a ground well hose, a coarse oil filter assembly, an electromagnetic pressure control valve, a rotary connector, a flow control electromagnetic valve, a filter, a flow meter, a safety relief valve, a reel ball valve, a venturi tube, an oil conveying hose and a pressure refueling connecting nozzle which are sequentially connected. The ground well hose connector is used for being connected with a ground well valve on an airport apron so as to introduce aviation oil. The pressure refueling nozzle is used for being connected with an aircraft fuel tank inlet to complete refueling. The interlocking device is used for performing brake interlocking and refueling oil path interlocking control on the refueling control device; the hydraulic device is used for providing hydraulic driving force for a hydraulic execution component on the refueling trailer; the electric control device is used for providing a control circuit for the refueling control device. Compared with the prior art, the invention has the advantages of maneuverability, flexibility, easy operation, energy conservation, economy, safety, environmental protection and the like.

A multi-disk brake system comprises an electrical generator (105) disposed therein. The electrical generator is configured to convert mechanical energy to electrical energy. The mechanical energy may be generated during a braking event of the multi-disk brake system. The electric generator may power various electrical components on the aircraft or store the electrical energy in a capacitor bank. The electric generator may also act as a motor and / or power a landing gear in a motor configuration.

The invention relates to a modular vertical take-off and landing aircraft (1) for transporting persons and / or loads, having: — a flight module (2) with multiple drive units (4) arranged on a wing assembly (3), each drive unit (4) having an electric motor (5) and a propeller (6) that is operatively connected to the electric motor (5), — a transport module (7) having a conveying pod (8) and a connection device (9) for connecting the conveying pod (8) to the flight module (2), the connection device (9) having an elongate shaft (10), one end of which is attached to the conveying pod (8), and — a coupling device (11) for connecting the flight module (2) to another end of the elongate shaft (10) of the transport module (7).

The invention discloses a general aircraft electric drive system and a control method, the electric drive system comprises electric drive aircraft wheels and a flight motor, and under the control of a control module, the electric drive aircraft wheels can drive an aircraft to move on the ground at a low speed and can assist propellers driven by the flight motor to take off. When the aircraft lands, the propellers and the aircraft landing gear rollers can charge the energy storage device through the corresponding motors respectively. The control method comprises the following steps: realizing low-speed movement on the ground by utilizing the electrically-driven airplane wheels; the electrically-driven airplane wheels assist the propellers to realize takeoff of the airplane; the flying motor drives the propellers to rotate to drive the aircraft to fly; in the landing process of the aircraft, the propellers are charged through the flight motors; after landing, the tires charge the energy storage device through the airplane wheel motors. The ground scheduling is linked with the take-off stage, the take-off efficiency is improved, and the effective flight time is prolonged; energy recovery is achieved in the airplane deceleration landing process.

The invention relates to an aircraft wheel electric motor (1) (1000) comprising a through bore and concentric rings of poles (P) enabling the generation of torque sufficient to operate the aircraft while maintaining a similar overall size to conventional solutions. The invention also relates to an aircraft wheel comprising such a motor (1), an aircraft wheel control assembly, and an aircraft (1000). Advantageously, it is thus possible to use an aircraft electric wheel in place of a conventional wheel, without substantial modification to the aircraft landing gear. Fig. 2

A passive lateral stability system maintains the position of a vehicle relative to a guideway. The system includes first and second guide assemblies that urge the vehicle away from first and second electrically conductive guide walls, respectively. The first guide assembly includes a wheel configured to reciprocate toward and away from the first guide wall. A biasing element bias biases the wheel toward the first guide wall. The system further includes a magnetic element associated with the wheel, wherein movement of the magnetic element relative to the first guide wall produces a magnetic force that biases the wheel away from the first guide wall. A second guide assembly is mounted to the vehicle and urges the vehicle away from the second guide wall.

A biwheel has large left and right main wheels (1, 2) supported by suspension assemblies (7) acting between rims of each main wheel and a payload carrying cockpit (3) suspended above the ground between the wheels. The arrangement facilitates access to the cockpit payload space through the wheels. Each wheel is cambered to deter pitching motion of the cockpit within the wheel. A rear jockey wheel (61) is provided to further deter pitching. Propulsion to the wheels is via electric motors built into drive wheels (16) which are mounted onto a suspension assembly (7). The torque applied to the electric motors can be controlled by a digital control system responsive to sensors such as a cockpit attitude sensor, to further deter pitching motion of the cockpit. Propulsion may additionally be delivered by a manual propulsion system supplemented by the electric motors.

A landing gear system includes a wheel rotatably coupled to the axle about an axis. A motor is fixedly positioned relative to the axle with a clutch assembly operably coupled to an output shaft of the motor. The landing gear includes an actuator and a drive assembly. The actuator applies a braking force to the wheel. The drive assembly includes a pinion gear and a drive gear rotatably associated with the pinion gear. The drive gear is configured to transfer a rotational force to the wheel in order to provide autonomous taxiing capability. Both the brake assembly and the drive assembly are operably coupled to the clutch assembly so that the output shaft of the motor drives both the brake assembly and the drive assembly.

The invention relates to an aircraft wheel (1) comprising a ring (3a, 3b) that is secured to a central hub (5a, 5b) defining an axis (X) of rotation of the wheel. The wheel comprises at least one driving lug (15) that extends from the hub, projecting in a direction substantially parallel to the axis of rotation of the wheel so as to cooperate with a drive member (17) for rotating the wheel. Landing gear and aircraft comprising such a wheel. Method for driving such a wheel.

The invention relates to a landing gear (1) of an aircraft (2) having an upper portion (1a) intended to be joined to a structure (2a) of the aircraft (2) and a lower portion (1b) provided with a first and second axle (3, 4), the first axle (3) being provided with a braked wheel (3a) and the second axle (4) being provided with a motorised wheel (4a). A first actuator (5) moves one of said axles between remote and close positions with respect to the upper portion (la) while the other axle (3) is kept stationary with respect to said upper portion (1a) in one of said remote and close positions, and the wheels (3a, 4a) on the axles (3, 4) are simultaneously in contact with a running surface (P) while, in the other of said remote and close positions, each wheel (4a) on the second axle (4) is at a distance from said running surface (P).

Disclosed is landing gear (100) of an aircraft (1000) comprising a pair of wheels (5) between which an electric actuator (10) at least partially covered with a lightning arrester cowl (20, 40) is placed, the lightning protection cowl (20, 40) comprising an insulating matrix (25) onto which at least one electrical conductor is attached, the electrical conductor (26, 60) comprising electrical connection means (27, 28) for connecting the electrical conductor to a ground conductor (90) of the aircraft (1000).

A method of parking an aircraft is disclosed including flight crew pedal braking to cause a brake force to be applied to the aircraft wheel brakes to slow the aircraft to a stationary state in which it is ready to be parked. Flight crew then activate a parking brake device and then release the pedal braking. An electronic control device, forming part of the aircraft's braking system for example, automatically intervenes, following the manual release of the pedal braking, to cause a brake force to continue to be applied to the wheels. This may be until sufficient brake force is applied, as a result of the activation of the parking brake device, to hold the aircraft in its parked state or may be for a predetermined period of time, say, ten seconds.

The invention relates to an aircraft comprising a drive system having a power unit, at least one drive battery, and at least one electric motor drawing electrical energy from the at least one drive battery, wherein the power unit comprises a two-cylinder reciprocating-piston engine having two cylinder-piston units in tandem arrangement and comprises at least one generator for generating electrical energy, wherein each cylinder-piston unit has a crankshaft, and wherein the crankshafts are mechanically coupled to each other, and wherein at least one crankshaft is mechanically connected to the at least one generator. The invention also relates to additional improvements of the aircraft and to an operating method.

A device (10) for driving at least one wheel (12) of an aircraft landing gear (14), this device (10) comprising: - at least one landing gear wheel (12), this wheel (12) having a rim (16) having an axis of rotation (X), - an electric motor (20) having a shaft (30), - a mechanical transmission system (22) between the motor shaft (20) and the rim (16), this mechanical transmission system (22) comprising a mechanical reduction gear (28) which includes: - a movable ring gear (38) fixed for rotation to the motor shaft (20), - a movable sun gear (32) fixed for rotation to the rim (16), - a fixed sun gear (56) attached to a stator of the device (10), and - planet gears (34) which are meshed with the ring gear and the sun gears. Figure for the abbreviation: Figure 7

A landing gear system includes an axle having an internal cavity and a wheel rotatably coupled to the axle. A drive shaft is mounted in the cavity to be rotatable about an axis. The landing gear system further includes a rod and a clutch, the rod being slidably mounted within the drive shaft. The clutch has a first portion coupled to the rod and rotates with the drive shaft. A second portion of the clutch is fixedly coupled to the wheel. The rod is selectively reciprocated along the axis between a first position and a second position to engage and disengage the clutch.

The invention relates to a motor sub-assembly of an electromechanical actuator for braking the wheels of an aircraft, comprising a housing, a shaft mounted in the housing to pivot about a longitudinal axis of the shaft, a shuttle comprising a second set of teeth mounted to slide with respect to the housing and arranged to engage the first set of teeth, the actuator further comprising a selection mechanism for selectively moving the shuttle in a first position in which the first set of teeth engages the second set of teeth and in a second position in which the first set of teeth is disengaged from the second set of teeth, the actuator comprising means for retaining the shuttle in its first position and means for permanently preventing the rotation of the shuttle with respect to the housing.

The invention relates to an aircraft wheel (1) comprising a rim (2) which is provided with rotor discs (11b) which are rotated with the rim by means of first studs (7) which are fixedly joined to the rim and which are engaged in notches of the rotor discs, stator discs (11a) being inserted between the rotor discs and being provided with notches which are engaged with second studs fixedly joined to a torsion brake tube (13) which is arranged to be attached to an axle (4) which supports the wheel. According to the invention, the wheel comprises at least one sintered heat pipe (20) which extends into at least one of the first and second studs parallel with a plane which extends through the rotation axis of the wheel, the heat pipe having an end (20.1) projecting outside the wheel, and at least one heat sink (21) which is fixedly joined to the end of the heat pipe.

The invention relates to the technical field of mechanical driving, in particular to an aircraft autonomous taxiing system with a high-speed separation function, which comprises an airborne oil tank, an airborne hydraulic pump, a servo valve and a hydraulic motor, an inlet of the onboard hydraulic pump is communicated with the onboard oil tank; an inlet and an outlet of the onboard hydraulic pump are communicated with an inlet and an outlet of the hydraulic motor through the servo valve; the servo valve has a driving state and a separation state; the hydraulic motor has a working state and an idling state, and the hydraulic motor is a radial inner curve plunger motor; and in the separation state, an inlet and an outlet of the hydraulic motor are both communicated with the onboard oil tank, and the hydraulic motor is in an idling state. According to the invention, the safety and reliability of the aircraft taxiing system can be greatly improved.

The invention relates to the technical field of mechanical driving, in particular to a wide-speed-range aircraft autonomous taxiing system based on a variable displacement motor, which comprises an aircraft wheel rotationally connected with an undercarriage, a variable displacement hydraulic motor mounted on the undercarriage and in transmission connection with the aircraft wheel, and a servo valve, the servo valve can form a first loop and a second loop with an onboard oil supply path, an onboard oil return path and the variable hydraulic motor; the first loop is used for controlling the machine wheel to rotate along a first direction; the second loop is used for controlling the machine wheel to rotate along a second direction; the first direction is opposite to the second direction; the variable hydraulic motor has a small-displacement working condition and a large-displacement working condition, when the aircraft needs to move quickly, the variable hydraulic motor is in the small-displacement working condition, and when the aircraft needs to move at a low speed, the variable hydraulic motor is in the large-displacement working condition. According to the invention, wide-speed-range aircraft autonomous taxiing can be realized.

A method of taxiing an aircraft may comprise: determining, via a brake controller, whether the aircraft is taxiing with a first thrust provided from a first side of the aircraft, a second thrust from a second side of the aircraft, or both the first thrust and the second thrust; and modifying, via the brake controller, a first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal deflection in response to the taxiing with the first thrust only.

The application discloses a wheel-holding device of an airplane towing vehicle, which comprises a vehicle body, a base turntable, a load-bearing bottom plate, a mechanical arm and a clamping push plate. The base turntable is transversely arranged in an opening and is in sliding connection with the inner side of the opening, so that the base turntable can rotate around its center along the circumference of the opening. When the wheel is held and fixed with the base turntable as a whole, the airplane and the towing vehicle can be followed, and the operation is simple. The load-bearing bottom plate, the mechanical arm and the clamping push plate are cooperated with each other, so that the load-bearing surface of the load-bearing bottom plate is inclined in the initial state, and the rear end can be in contact with the lower part of the wheel. In the in-place state, the load-bearing surface is horizontal to support the wheel. The wheel is smoothly transferred to the load-bearing bottom plate and is lifted. The working process is stable. In addition, the lifting height of the wheel is determined by the height of the rotating shaft around which the load-bearing bottom plate is turned. Compared with the prior art, the lifting height of the wheel can be higher, and the application range is wider.

Methods for reducing brake wear during aircraft taxiing are disclosed. As one example, a method comprises determining a sequence to apply brakes of a given set of landing gear during a brake event, wherein the determining includes selecting a warmer brake of the brakes to initially apply at a start of the brake event, and selecting a cooler brake of the brakes to subsequently apply when the warmer brake is released during the brake event. The method further comprises applying the warmer brake and the cooler brake in the determined sequence during the brake event. In another example, an aircraft brake system comprises brakes and a controller that is programmed to, during taxiing, apply a warmer subset of the brakes before applying a cooler subset of the brakes during a brake event.

Disclosed is a vehicle wheel (1) rotatably mounted on an axle (E) and comprising:-an annular rim (2), a web (3) and a hub (4) delimiting a closed annular space,-an electric motor (10) comprising a first stator (11) and a first rotor (12) arranged coaxially with the wheel, and-a magnetic brake (20). Inside the annular space, the motor and the brake extend one within the other. Or the first rotor is used as a rotor of the brake (22), or the first stator (11) is used as a stator of the brake (21), in order to generate a second magnetic flux capable of inducing an eddy current generating a braking torque. Or the first stator or the first rotor is provided with a Halbach array which is at least partially formed by electromagnets.

The invention relates to a flight module (1) for a vertical take-off and landing aircraft comprising multiple drive units (3) arranged on a wing assembly (2), the wing assembly (2) having wing assembly struts (5) interconnected at node points (4) and each drive unit (3) having an electric motor (6) and a propeller (7) that is operatively connected to the electric motor (6). each drive unit (4) having an electric motor (5) and a propeller (6) that is operatively connected to the electric motor (5)A number of the drive units (3) are arranged outside the node points (4).