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JPH10131805A |
To provide the subject device having an excellent characteristic at the time of direct propulsion and thrust inversion. Each movable member 6, 7 is supported by turning shaft 12 secured to a fixed structure, and composed of an outer pann...
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JPH10122046A |
To provide a thrust inverter for a double flow turbojet engine, capable of controlling a leakage flow at the inversion of thrust. A thrust inverter comprises a swing gate 2 adapted to be retracted inside the outer wall of a flow conduit ...
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JPH10115254A |
To reduce or remove a torsional moment generated by lining up (arranging on one straight line) the connection point of a control jack with an upperstream side fixed structure and the connection point of the control jack with the door of ...
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JPH1081300A |
To make improvements in performance at the time of a reverse jet, by supporting an upstream side panel with at least one connecting rod so as to maintain a parallelism between a surface of the upstream side panel and a flowing layer comi...
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JPH1071998A |
To provide a thrust reversing device for a turbofan engine that can increase safety, reduce mass or improve performance at the time of reverse jet. A turning door has internal space 37 forming a jet nozzle between a first opening part 36...
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JPH1067397A |
To establish stream-shaped continuity of a nacelle at the time of direct injection drive operation even at a surface which limits the range of a blower duct as well as an external surface by smoothing a passage of the second flux without...
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JPH1059297A |
To provide an air intake shielding device which can shield an air intake electromagnetically by a plasma, and can reduce the danger caught by a threat radar. This shielding device is composed of a laser transmitter 2 loaded on an aircraf...
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JPH1054299A |
To provide a thrust reversing device which can attain safety improvement and/or mass reduction, or performance improvement at the time of reverse jetting. This thrust reversing device for double-current turbojet engine is constituted so ...
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JPH1030497A |
To enable restarting of engine in the air without deceleration to subsonic speed by providing a restart by-pass duct which by-passes whole engine or fan. A supersonic aircraft engine 10 provides a re-start by-pass duct 20 for by-passing ...
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JPH1016893A |
To provide an airplane posture control device for controlling the postures of the tow or more shafts of a machine body by the one-shaft propelling force deflecting device of the machine body. An airplane posture control device includes, ...
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JP2695658B2 |
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JP2695659B2 |
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JP2691051B2 |
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JP2686149B2 |
The bidimensional supersonic air intake for the combustion air of an aircraft engine comprises on the one hand a front flap (3) forming a visor and on the other hand a hull (4). The front flap (3) is movable about a pivot axis (5) situat...
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JP2686150B2 |
The bidimensional supersonic and hypersonic air intake for the combustion air of an aircraft engine comprises two forward flaps (3) forming a visor, which are disposed symmetrically on either side of a longitudinal plane (P), each forwar...
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JPH09250394A |
To provide a thrust reversing device for a double flow turbo-jet engine which prevents a danger of an unexpected development and a weakening of a panel structure and ensures gas-tightness and avoids the sound processing area from being d...
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JP2645447B2 |
A propfan turbine engine having a reduction gearing for the propfan rotors is provided with a lubricating system of its own for the reduction gearing, the system being arranged axially between the gas turbine and the reduction gearing an...
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JP2634651B2 |
A ventilation system for a nacelle 14 is disclosed. The ventilation system includes pressure relief doors 50 and 52, and a holdback device 68 which blocks each open door from moving from the open position to the closed position.
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JPH09507449A |
Nozzles for discharging high velocity air are positioned on either side of an aircraft engine exhaust duct exit. High velocity air is discharged tangential to an outer surface of each nozzle and follows the contour thereof. The nozzles a...
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JP2631497B2 |
In a pipe line for an engine, in particular a cooling line in aircraft construction, the walls of the pipe line are composed of a load-bearing inner layer (2) of fibre reinforced, curable synthetic resin and of a heat insulating outer la...
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JP2620114B2 |
A divergent flap actuation system for a two-dimensional exhaust nozzle for a gas turbine engine powered aircraft includes stationary sidewalls (2) with oppositely disposed movable divergent flaps (10) and (39) located therebetween, and f...
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JPH09151797A |
To take-in air having uniformity regardless of change of air current direction by arranging a member having a parallel center shaft on the center shaft of a cowl for taking-in air in the cowl freely to rotate it, and freely to move it in...
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JPH0966899A |
To realize the improvement of engine output in a radio controlled helicopter in a simple, light-weighted and low-priced mechanism without adopting complicated mechanism and method. An introduction pipe 11 for supercharging air is connect...
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JPH0932638A |
To enlarge the deflection angle of thrust and deflect the thrust in any direction in three dimensions in a flying object such as an aircraft, a spacecraft and the like. A thrust deflection nozzle of a flying object comprises plural engin...
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JPH08282596A |
PURPOSE: To maintain the threat detecting accuracy, and to reduce the operation of an active sensor, by inputting an integrated threat detecting data from a data fusion system to a rule base system, and carrying out the trade-off of the ...
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JPH08268391A |
PURPOSE: To measure pressure highly accurately via the application of electrical signals without any mutual effect, regarding a pitot tube rake for measuring pressure distribution at the air intake port of an aircraft. CONSTITUTION: A pl...
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JP2540615B2 |
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JPH0818597B2 |
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JPH0820396A |
PURPOSE: To dispense with the power for operating a cooling medium and make a helicopter lightweight at a low cost by using the surface of an airframe at the portion hit by much downwash as a cooling surface, and providing a cooling devi...
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JPH07329889A |
PURPOSE: To generate deflecting thrust in the 360° direction by arranging two-dimensional deflecting nozzles having pairs of convergent flaps and divergent flaps so that extended surfaces of sidewalls cross with each other on each of re...
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JPH07323898A |
PURPOSE: To reduce radiation of infrared rays due to engine exhaust of an airplane. CONSTITUTION: When a pilot switch 1 is operated, coolant from a pressure accumulator 3 is injected to engine exhaust of an airplane from an injection noz...
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JPH07277292A |
PURPOSE: To effectively cool the engine exhaust of a helicopter. CONSTITUTION: A cooling air intake 7 is provided through the top surface of the body of a helicopter 1 where a downwash 6 from a rotor 5 is strong, so that a large amount o...
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JPH07277291A |
PURPOSE: To improve the performance of a helicopter during advancing and hovering by providing a deflector device by which a rotor downwash roughly perpendicular to the body axis of the helicopter is deflected in the direction of the axi...
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JPH07257492A |
PURPOSE: To provide a duct for an aircraft of light weight by reducing a reflected radio wave without obstructing a flow of inflow air. CONSTITUTION: In this constitution, an intake duct for an aircraft comprises a radio wave transmissib...
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JPH07232700A |
PURPOSE: To cause the automatic passage of a desired flow of cooling air matching with an engine output through a radiator. CONSTITUTION: A cooling device for an internal combustion engine for an aircraft comprises a cooling air passage ...
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JPH07217449A |
PURPOSE: To recover a normal starting condition immediately even in a stall condition due to a change of a flying condition or the like by arranging a throat wall, a sealed type cylinder, a piston, and a rod connecting the piston and the...
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JPH0762466B2 |
An aircraft speedbrake is integrated into a jet engine exhaust nozzle. A first set of nozzle flaps which are normally out of the airstream, are extended into the airstream to create drag on the airframe and thereby act as speedbrakes. A ...
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JPH07160273A |
PURPOSE: To efficiently eliminate noise sent from a helicopter to ground at near an airframe by arranging a microphone so as to correspond to pointed directions of each noise of a rotor, and generating sound having the effect of eliminat...
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JPH0737240B2 |
A hybrid laminar flow nacelle for housing an engine of an aircraft includes an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at the leading ...
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JPH0736719B2 |
A generator (13) is driven by an aircraft engine (11) through a continuously variable ratio drive device (20) responsive to error signals from a circuit (24) indicating a difference between desired and actual speeds of an output shaft (2...
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JPH0711260B2 |
An exhaust flap for use in the exhaust section of an aircraft gas turbine engine is built with increased service life and ease of replacement. The exhaust flap includes convergent nozzle flaps, divergent nozzle flaps, convergent seal fla...
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JPH079216B2 |
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JPH06105051B2 |
A thermal protection liner is composed of rings formed from tiles (1) arranged side by side, each tile comprising a panel (13) having external additional thicknesses (11, 12) on its upstream and downstream edges forming an annular stiffe...
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JPH06105064B2 |
A thrust vectoring axisymmetric convergent divergent variable exhaust nozzle is provided with a universally pivoting joint between the divergent and convergent flaps and actuating the linkage mechanisms for changing the divergent nozzle ...
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JPH0696985B2 |
A nacelle cooling and ventilation system for an aircraft gas turbine engine which includes a chin scoop (20) and duct assembly for directing air through the engine bay (24) where it is exhausted into the engine exhaust through an exhaust...
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JPH0678735B2 |
A nacelle structure (14) for a gas turbine engine (4) extends upstream from the engine air inlet (10) and includes an external surface (18) and an internal surface (16). The external surface (18) is concentric about a linear centerline (...
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JPH06257512A |
PURPOSE: To provide an exhaust gas nozzle for aircraft and aerospace engines capable of altering its form in the flow direction of exhaust gas. CONSTITUTION: A variable exhaust nozzle comprises a convergent flap 1, a divergent flap 3 con...
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JPH06191493A |
PURPOSE: To provide a tandem two-seat type twin-engined aircraft whose fuselage frontal projected area can be made small while excellent forward field of view is secured for a rear seat. CONSTITUTION: Two engines 2 and 3 are mounted onto...
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JPH0649480B2 |
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JPH06173713A |
PURPOSE: To prevent generation of bending moment on all casings without changing the outer casing of an engine by providing an aircraft structure with a thrust transmission member and a thrust transmission ball joint. CONSTITUTION: A dev...
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