摘要:
There are described methods and systems for providing an autothrottle mode in a propeller-driven aircraft. A thrust change is obtained corresponding to a difference between an actual thrust and a desired thrust for an engine. When greater than a pre-determined threshold, a setting change to one or more control input(s) of the engine is determined. One or more commands is output to cause the setting change of the control input(s).
摘要:
An aircraft includes a fuselage having a tapered rear shape, a landing gear for moving the aircraft on a runway, a wing attached to the fuselage, at least a main engine for providing a main thrust and a rear fan, wherein the rear fan is attached to a tail section of the fuselage, wherein the aircraft is designed for conducting a take-off rotation around the landing gear during take-off from the runway, such that the tail section of the fuselage approaches the runway, wherein the rear fan is an open fan having fan blades extending in a radial direction to a longitudinal axis of the fuselage, wherein the fan blades are dimensioned to equal at least a boundary layer thickness of the flow along the fuselage and to be smaller than the gap between the runway and the tail section of the fuselage during the take-off rotation.
摘要:
A propulsion system is described that includes an AC generator configured to produce AC current, and a plurality of propulsors configured to receive the AC current from the AC generator and provide thrust based on the AC current from the AC generator. The propulsion system further includes an AC distribution system configured to deliver a first portion of the AC current to a first group of propulsors from the plurality of propulsors, and a second subsystem configured to deliver a second portion of the AC current to a second group of propulsors from the plurality of propulsors.
摘要:
A control horn arrangement includes a control horn body with an inboard end and an opposed outboard end. The control horn body defines a torque tube axis which extends between the inboard and outboard end of the control horn body. An inner flange and an outer flange are disposed on the outboard end of the control horn body. The inner flange and the outer flange extend about the torque tube axis and define between one another a receptacle to fix a torque tube to the outboard end of the control horn body.
摘要:
A system is configured to change the pitch of blades of at least one turbine engine propeller provided with multiple blades. The system includes a control means acting on a connecting mechanism connected to the blades of the propeller. The control means includes a stationary body and a movable body translatable along a longitudinal axis (X) relative to the stationary body and defining two chambers. A fluid supply means is configured to be connected to a fluid supply source and to supply the chambers. The fluid supply means includes at least one channel. The channel is arranged and extends along an axis (Q) parallel to the longitudinal axis in an overthickness of a wall of the stationary body, the overthickness extending radially inside relative to the longitudinal axis.
摘要:
The invention relates to turbine engine module (1) including a case (9) rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case (15) comprising a cylindrical wall (16) extending between an inner wall (17) and an outer wall (18) of the rotating case (9), and a system (26) for changing the pitch of the blades (14) of the propeller. The wall (16) is connected downstream to a first substantially frustoconical wall (42) and upstream to a second substantially frustoconical wall (41), a first rolling bearing (19) being inserted respectively downstream directly between a radially outer face (21) of the inner wall (17) and a radially inner face (23) of the first frustoconical wall, and a second rolling bearing (19′) inserted downstream directly between the radially outer face (21) of the inner wall (17) and an inner face (43) of the second frustoconical wall (41).
摘要:
A tail-sitter aircraft is provided and includes a fuselage having first and second axisymmetric sides, first collectively controllable prop-rotors, which are formed to define a first pair of rotor disks and which are respectively supported at the first axisymmetric side of the fuselage, and second collectively controllable prop-rotors, which are formed to define a second pair of rotor disks and which are respectively supported at the second axisymmetric side of the fuselage.
摘要:
A solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network. A telecommunications network incorporating such aircraft is also discussed.
摘要:
A solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network. A telecommunications network incorporating such aircraft is also discussed.
摘要:
A propeller assembly has a main hub and a propeller hub circumferentially movable relative to the main hub about a main axis of the assembly. Circumferentially spaced propeller blades on the propeller hub are i) circumferentially movable together with the propeller hub relative to the main hub between a first position and a second position against a biasing force, and ii) pivotal about respective radial axes. A pitch linkage mechanism is operatively connected between each propeller blade and the main hub such that each propeller blade is pivotal about the respective radial axis from a first pitch orientation to a second pitch orientation together with movement of the propeller hub relative to the main hub from the first position to the second position responsive to air resistance in the second direction exceeding the biasing force.