초록 ▼

A method of providing speed protection to a neutrally-stable aircraft including the calculation of at least one of a stall protection signal and an overspeed protection signal. The aircraft includes a pitch control system having a command pitch signal received from pilot input to a control column. T

A method of providing speed protection to a neutrally-stable aircraft including the calculation of at least one of a stall protection signal and an overspeed protection signal. The aircraft includes a pitch control system having a command pitch signal received from pilot input to a control column. The protection signal is provided to the pitch control system to limit the commanded pitch signal during flight. The calculation of a stall protection signal includes differencing the aircraft's current airspeed with a reference speed and multiplying the difference by a scaling factor that corresponds to the force required by the pilot to move the control column. The calculation of an overspeed protection signal includes calculating a first signal based on airspeed, calculating a second signal based on Mach, selecting the large of the two signal and passing it through a limiter. The limiter is a function of roll attitude and corresponds to the force required by the pilot to move the control column. Also provided is a method of calculating a flare compensation signal to emulate ground effects encountered by an aircraft while executing a landing. The flare compensation signal is determined using a table of gear heights versus flare compensation amounts. The flare compensation signal is limited to a value between zero and a positive upper limit.

대표청구항 ▼

[ What is claimed is:] [1.] A method of providing speed protection to a neutrally-stable aircraft, the aircraft including a pitch control system having a commanded pitch signal received from pilot input to a control column, the method comprising:(a) calculating at least one of a stall protection sig

[ What is claimed is:] [1.] A method of providing speed protection to a neutrally-stable aircraft, the aircraft including a pitch control system having a commanded pitch signal received from pilot input to a control column, the method comprising:(a) calculating at least one of a stall protection signal and an overspeed protection signal;wherein calculating the stall protection signal includes calculating the difference between the aircraft's current filtered airspeed and a stick shaker reference speed and multiplying the difference by a scaling factor that corresponds to the force required by the pilot to move the control column, the scaling factor causing more force to be exerted by the pilot on the control column when attempting to increase pitch at low speeds; the stick shaker reference speed being set to an amount based on the aircraft's amber band speed value; andwherein calculating the overspeed protection signal includes calculating a first overspeed protection signal based on airspeed, calculating a second overspeed protection signal based on Mach, selecting the larger of the two overspeed protection signals, passing the larger amount through a limiter that is a function of roll attitude and that corresponds to the force required by the pilot to move the control column, the passing through the limiter thereby causing more force to be exerted by the pilot on the control column when attempting to decrease pitch at high speeds; and(b) providing the at least one stall protection signal and overspeed protection signal to the pitch control system for use in limiting the commanded pitch signal during flight; the inclusion of a stall protection signal to the pitch control system resulting in a pilot-overridable nose-down movement of the aircraft; the inclusion of an overspeed protection signal to the pitch control system resulting in a pilot-overridable nose-up movement of the aircraft.