A method converts an aircraft takeoff trim setting that would be a function of several parameters to a value that is a function of CG position only. In this way, it is possible to create a direct simple equivalence between Stabilizer angle and CG. The equivalent CG can be presented in real time to the pilot.

A method converts an aircraft takeoff trim setting that would be a function of several parameters to a value that is a function of CG position only. In this way, it is possible to create a direct simple equivalence between Stabilizer angle and CG. The equivalent CG can be presented in real time to the pilot.

A control grip for an aircraft control stick or yoke has within it electrically controlled actuators. Each actuator extends a thrust pin that corresponds with the fingertips of the pilot's hand that is holding the control grip. Additional thrust pins are positioned at the base of the thumb and base of the index finger. The actuators, upon receiving their electrical input, extend their thrust pin a small distance and press on the pilot's fingertips. This movement signals the pilot information that is currently conveyed to the pilot's eyes or ears through conventional instruments. Angle of attack for best rate of climb would be indicated to the pilot by an extension of the thrust pin that corresponds to the third finger. Angle of attack for best angle of climb would be indicated by the extension of the thrust pin that corresponds to the pilot's second finger. Angle of attack at which the wing reaches aerodynamic stall would be indicated by the button that corresponds to the index finger. Thrust pins positioned at the base of the index finger and thumb will be used to indicate slip/skid attitude. The thrust pins will be made to pulse as this is more effective for tactile feedback. Roll attitude can also be included in the thrust pins. Although the pin assignments listed are the primary functions, the thrust pins would not be limited to these functions. Additional actuators can be added to include other aircraft information.

A control grip for an aircraft control stick or yoke has within it electrically controlled actuators. Each actuator extends a thrust pin that corresponds with the fingertips of the pilot's hand that is holding the control grip. Additional thrust pins are positioned at the base of the thumb and base of the index finger. The actuators, upon receiving their electrical input, extend their thrust pin a small distance and press on the pilot's fingertips. This movement signals the pilot information that is currently conveyed to the pilot's eyes or ears through conventional instruments. Angle of attack for best rate of climb would be indicated to the pilot by an extension of the thrust pin that corresponds to the third finger. Angle of attack for best angle of climb would be indicated by the extension of the thrust pin that corresponds to the pilot's second finger. Angle of attack at which the wing reaches aerodynamic stall would be indicated by the button that corresponds to the index finger. Thrust pins positioned at the base of the index finger and thumb will be used to indicate slip/skid attitude. The thrust pins will be made to pulse as this is more effective for tactile feedback. Roll attitude can also be included in the thrust pins. Although the pin assignments listed are the primary functions, the thrust pins would not be limited to these functions. Additional actuators can be added to include other aircraft information.

A flight control device of an aircraft including a support, an action member attached to the support rotating freely around a primary axis, a rotary device including a stator, rotatably connected to the support around a secondary axis, and a rotor rotating freely relative to the stator around the secondary axis, the rotary device applying a force sensing torque on the rotor relative to the stator around the secondary axis, and a mechanical reducing gear, which connects, with a reduction ratio, rotation of the action member with rotation of the rotor, the mechanical reducing gear including a screw-nut system with rolling elements, including a screw, attached to the rotor, connected in rotation to the rotor around the secondary axis, and a nut fixed in rotation around the secondary axis relative to the stator and helically connected with the screw around and along the secondary axis via the rolling elements.

A flight control device of an aircraft including a support, an action member attached to the support rotating freely around a primary axis, a rotary device including a stator, rotatably connected to the support around a secondary axis, and a rotor rotating freely relative to the stator around the secondary axis, the rotary device applying a force sensing torque on the rotor relative to the stator around the secondary axis, and a mechanical reducing gear, which connects, with a reduction ratio, rotation of the action member with rotation of the rotor, the mechanical reducing gear including a screw-nut system with rolling elements, including a screw, attached to the rotor, connected in rotation to the rotor around the secondary axis, and a nut fixed in rotation around the secondary axis relative to the stator and helically connected with the screw around and along the secondary axis via the rolling elements.

A control system for electronically linked pilot and co-pilot inceptors (103) permits an asymmetric roll axis feel depending on whether an inceptor is moved inboard or outboard. A circuit (401) receives a signal representative of a force applied to the pilot's inceptor resulting from a side-to-side movement and detects if the force applied is in an inward or an outward direction. A gain factor is applied to the received force signal to produce a factored force signal. The gain applied to a signal representative of force applied in an outward direction is greater than the gain factor applied to a signal representative of force applied in an inward direction. A summer (212, 213) sums the factored force signal with a corresponding factored force signal derived from force signals from the co-pilot's inceptor to produce a modified force signal for use in a force feedback control system associated with each inceptor.

A control system for electronically linked pilot and co-pilot inceptors (103) permits an asymmetric roll axis feel depending on whether an inceptor is moved inboard or outboard. A circuit (401) receives a signal representative of a force applied to the pilot's inceptor resulting from a side-to-side movement and detects if the force applied is in an inward or an outward direction. A gain factor is applied to the received force signal to produce a factored force signal. The gain applied to a signal representative of force applied in an outward direction is greater than the gain factor applied to a signal representative of force applied in an inward direction. A summer (212, 213) sums the factored force signal with a corresponding factored force signal derived from force signals from the co-pilot's inceptor to produce a modified force signal for use in a force feedback control system associated with each inceptor.

A control system (400) for an active inceptor (103) for a fly by wire aircraft permits a zero force null point to settle to a non-zero displacement trim position. An internal position state of a second order mass spring damper model is moved in conjunction with force-displacement characteristic coordinates. This results in no second order dynamics being superimposed on the feel of the inceptor (103) when dynamically adjusting the trim position, thereby eliminating the possibility of any unpleasant buzzing been felt by the operator of the inceptor during a trimming operation.

The present invention achieves technical advantages as a pilot and passenger seating. An aircraft employs a pilot seat, comprising a contoured structure having ergonomically formed and padded surfaces, with left and right arm supports that include an articulated control knob, movable in three rectangular axes and rotatable about a vertical axis to provide one or more aircraft steering functions for an aircraft, and a touch-sensitive control surface for controlling one or more power system components. A passenger seat, having a contoured structure, having ergonomically formed and padded surfaces, a headrest, a seat, a left support member, and a right support member are adapted to cradle a portion of a passenger's body to support the passenger during travel.