| Document |
Document Title |
|
JP4044991B2 |
The system consists of a hydraulic subsystem (12) and an electrical subsystem (13), between which a bi-directional energy transfer occurs. Each subsystem contains a machine (20) whose rotary elements are mechanically coupled. The hydraul...
|
|
JP2007531855A |
A gearbox for rotating a propeller in a selected one of a first and second direction is provided. The gearbox includes a many common components, selected irrespective of desired propeller direction, and a few unique components selected b...
|
|
JP3930413B2 |
To provide a system capable of supplying power and selectively supplying thrust as required to an aircraft system. This variable cycle boost propulsor system 10 has a core engine 14, a free turbine 30, a fan 34 connected to the free turb...
|
|
JP2007510591A |
Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one po...
|
|
JP2007015423A |
To provide a power supply system for an airplane 1 of lightweight construction and with a high efficiency.The power supply system S is equipped with main generators GEN1 and GEN2 driven by a propulsive engine 4 of the air plane 1, an aux...
|
|
JP2006518683A |
A system and method for an engine bleed flow-sharing control system is disclosed. For a multi-engine bleed system, one (10) of the engines is selected as the master channel (15) such that the bleed air supply pressure of the control syst...
|
|
JP2006518297A |
A fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oil cooler in the eve...
|
|
JP3803326B2 |
To provide an auxiliary power device integrally formed with an engine. In the auxiliary power device integrally formed with an engine, the engine 10 has: a high pressure spool including a high pressure compressor 20 connected to a high p...
|
|
JP3793529B2 |
To integrate environmental control, secondary power and emergency power. An apparatus comprises of a cooling turbine that is coupled to a first rotor of an electromechanical machine and has an input for receiving compressed air or ram ai...
|
|
JP2006062439A |
To continuously supply power to apparatuses loaded on a hot-air balloon during flight with a simple structure.The power supply of hot-air balloon for supplying power to apparatuses equipped in the hot-air balloon comprises a thermoelectr...
|
|
JP2005507044A |
A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separa...
|
|
JP2004340148A |
To provide a device and a method for decomposition of propellant.The propellant 24 includes ionic salt and additional fuel. A means 42 to decompose most parts of the ionic salt is provided. A means 48 to burn the additional fuel and deco...
|
|
JP2004524474A |
A swirl generator for creating bulk swirl in a compressor plenum in the opposite direction to the direction of rotation of the compressor rotor. The generator includes a continuous flow passageway formed by an inlet duct and a compressor...
|
|
JP2004211706A |
To provide a device for improving the efficiency and energy output of an electric power device, and its method.The electric power device uses a fuel cell which is constructed to chemically convert combustible fuel into electrical energy....
|
|
JP2003304699A |
To provide a small-sized light-weight power-generating apparatus which can generate a predetermined power, irrespective of the operating state of a connected prime mover.The power generating apparatus comprises a generator having a rotor...
|
|
JP3440287B2 |
To provide a method and device for driving at constant rate a generator mounted in an aircraft, whereby the generator can be formed into a compact structure having high efficiency and reliability and long life. The AC generator 2 is driv...
|
|
JP2003523298A |
A thermoelectric power generator for an aircraft including a heat source or hot air exhaust air flow (30), characterized as providing thermal energy, at least one thermoelectric module (32), including a plurality of thermoelectric elemen...
|
|
JP3270845B2 |
To provide a boundary layer control mechanism for a short takeoff/ landing distance plane without apprehension generating hot circulation while forming a protruded part behind a pilot seat aerodynamically approximated to an optimum shape...
|
|
JP2001234999A |
To provide a highly reliable axial force generating device by a simple constitution and to provide a traction transmission using it.This axial force generating mechanism 10 comprises a centrifugal force generating mechanism, a converting...
|
|
JP2001130498A |
To prevent a hazard by belly landing and a crash accident due to engine trouble. The conventional equipment is exchanged basically with new ones. This operation is performed positively.
|
|
JP2001116499A |
To secure initial power by generating electric power in its launching tube in a flying object which gyratingly flies. A self-gyration type initial generator incorporated in an object which gyratingly flies generates electric power by usi...
|
|
JP2001086723A |
To provide an oscillation-absorbing type generator for reducing oscillations by absorbing the oscillation of the body generated at a helicopter, and generating electricity by using the oscillatory energy of an oscillator that reduces the...
|
|
JP2000516553A |
There is described an integrated muffler and exhaust cone 20, for use in a tailcone assembly 10 having a gas turbine engine 12 mounted therein. The integrated muffler and exhaust cone 20 includes a casing defining a conduit for porting t...
|
|
JP2000344200A |
To restrain the increase in the weight of an airframe.This auxiliary power unit 1 is provided with an air intake 2, a nozzle unit 3, an exhaust nozzle 4, a turbine 5, a bevel gear 6 and a gearbox 7. The air intake 2 is used to intake hig...
|
|
JP3108098B2 |
An electrical generator (1) comprising first and second relatively rotatable winding assemblies (5,8), the first winding assembly (5) having a first electrical output for connection to a first electrical load (4) and the second winding a...
|
|
JP3060382B2 |
The fuel cell (1) generates direct current electricity which is converted for the aircraft network, air for the air conditioning system, warm water for the aircraft supply and hydrogen. A converter (9) converts the supplied direct curren...
|
|
JP2000177697A |
To restrain a gear box from being adversely affected to the minimum even when a rotor is turned out to be in a very unstable condition.This mounting part 60 includes a cross member 62 both the ends of which are mounted on an engine case,...
|
|
JP2972688B2 |
To provide a constant speed drive gear unit for an aircraft generator and a generating set for an aircraft having small size, light weight and high efficiency. This constant speed drive unit 10 for an aircraft generator is composed of an...
|
|
JP2964063B2 |
PURPOSE: To obtain a highly reliable, compact and lightweight combustor which can produce emergency power through harmless and clean combustion while facilitating maintenance. CONSTITUTION: Air from a high pressure air tank is mixed with...
|
|
JPH11240495A |
To eliminate the need for a special person to control charging by simplifying the charging of the radio transmitter for unmanned helicopter control. A battery charger composed of a charger 1, a charging current voltage detection circuit ...
|
|
JP2897622B2 |
|
|
JP2768290B2 |
PURPOSE: To realize an aerial moving body, such as a compact unmanned machine, which is relatively light, and can add to appliances requiring power and lengthen their operating time largely. CONSTITUTION: In a compact unmanned machine 11...
|
|
JP2683685B2 |
To provide an auxiliary power system for short distance landing machine which can supply air for controlling a boundary layer stably. A compressor 21 for controlling boundary layer is driven by a first engine 11 through a first gear row ...
|
|
JPH09511714A |
An environmental control system has an air cycle machine that includes a compressor, a cooling turbine, a motor/generator, and a power turbine all mounted on a single shaft. The power turbine receives bleed air from the aircraft's engine...
|
|
JPH09272496A |
To solve such a problem that the mounting of a tunnel cable transmitting a control signal and a power from a guidance part to a drive source is difficult because a space in which the internal space of a tunnel cover for protecting a tunn...
|
|
JP2616841B2 |
The invention relates to secondary power system apparatus and method for use aboard aircraft in place of conventional auxiliary power units (APU's) and emergency power units (EPU's). The invention integrated power unit (IPU) performs the...
|
|
JP2590318B2 |
A ram air turbine and deployment mechanism has commonly had power-generating means in the form of either one, or both, of a hydraulic pump and electrical generator mounted at the end of a pivotal strut adjacent the ram air turbine. Reloc...
|
|
JPH08313199A |
PURPOSE: To enable a long-time flight by a method wherein one end part of a bypass piping is linked to a shunting point on the side of a fuel gas generator of a fuel gas piping while a converging point on the side of a jetting port to th...
|
|
JP2519620B2 |
The invention relates to secondary power system apparatus and method for use aboard aircraft in place of conventional auxiliary power units (APU's) and emergency power units (EPU's). The invention integrated power unit (IPU) performs the...
|
|
JPH07315297A |
PURPOSE: To provide a kinetic energy storing device, which stores and utilizes flying energy to be lost in deceleration of an airplane, for an airplane. CONSTITUTION: A kinetic energy storing device for an airplane is constructed in such...
|
|
JPH07505107A |
The invention concerns the field of aircraft engine construction, and more specifically the development of new aircraft. The aim of the invention is to develop new aircraft for non-stop long-haul flights with the same cargo carrying capa...
|
|
JPH05338593A |
PURPOSE: To provide a windmill type generating device of an aircraft, which is rotated at a constant rotating speed regardless of the speed of the aircraft by simple constitution, and can generate electric power of constant frequency and...
|
|
JPH052559B2 |
|
|
JPH0215596U |
|
|
JPH01269700A |
PURPOSE: To stably maintain control of an aircraft by providing a high speed spool for driving auxiliary driving machines and a low speed spool for driving an emergency power unit at losing propulsion power on a turbofan engine. CONSTITU...
|
|
JPH01237327A |
PURPOSE: To raise reliability in emergency by inputting the power generated by two gas turbines to a common gear box, distributing the power to each power device, and supplying compressed oxidant in a storage container to a combustion ch...
|
|
JPH01501809A |
Duplication of engine and secondary power system components in individual auxiliary and emergency power units is avoided in an integrated power unit including a gas turbine engine 10 having a centrifugal compressor 28 and a turbine 40, a...
|
|
JPS6469721A |
PURPOSE: To use a gas turbine multipurposely by communicating a turbine impeller at a boss of a centrifugal compressor through a clutch and connecting a source of a load and pressure on halfway of a duct connecting a gas inlet to the tur...
|
|
JPS645183B2 |
An integrated drive-generator system having a drive input shaft with a mechanical differential positioned in coaxial relation with the drive input shaft, a generator positioned alongside said differential and drive input shaft, and a hyd...
|
|
JPS6342094B2 |
|
