초록 ▼

A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protecti

A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings.

대표청구항 ▼

1. An aircraft control method for commanding at least one control surface based on a pilot command and an augmentation command, the method comprising: computing, with at least one processor, a control law reference command δlaw, wherein the control law reference command δlaw is a function of a posit

1. An aircraft control method for commanding at least one control surface based on a pilot command and an augmentation command, the method comprising: computing, with at least one processor, a control law reference command δlaw, wherein the control law reference command δlaw is a function of a position of a pilot inceptor, wherein δi is a measurement of a pilot inceptor position sensor that senses the position of the pilot inceptor;computing, with the at least one processor, a feed-forward command ΔFF, wherein the feed-forward command ΔFF is proportional to the control law reference command δlaw, such that the feed-forward command comprises ΔFF=GFFδlaw, wherein GFF is a gain;computing, with the at least one processor, an integral feedback command ΔI, wherein the integral feedback command ΔI is a gain GI multiplied by an integral of an error e , wherein under at least a first condition error e=δlaw−α, wherein α is an angle of attack measured by an angle of attack sensor, and δlaw is the control law reference command, such that, ΔI⁡(t)=GI⁢∫0t⁢e⁡(τ)⁢ⅆτ, wherein t is time, and wherein under at least a second condition the error is e=δlaw−θ, where θ is a pitch angle measured by an inertial sensor, and δlaw is the control law reference command; andcommanding the at least one control surface based on the pilot command and the augmentation command Δ, wherein the augmentation command Δ is a summation which comprises the feed-forward command (ΔFF), the integral feedback command (ΔI) and a state feedback command (ΔSF). 2. The method of claim 1, wherein said at least one first condition includes engagement of a stall protection, buffeting protection and/or low speed protection; and wherein said at least one second condition includes engagement of a high attitude protection. 3. The method of claim 1, further including: changing said error during a flight, from e=δlaw−α to e=δlaw−θ, and vice versa; as a function that depends on flight parameters comprising height above ground level (hAGL), the pitch angle (θ), the angle-of-attack (α), a flight path angle (γ), and a ground speed (uG). 4. The method of claim 3, further including: computing the state feedback ΔSF command, wherein ΔSF is a summation of a set of flight parameters, measured from a plurality of sensors, and wherein the set of flight parameters are multiplied by a set of gains. 5. The method of claim 4, wherein the set of flight parameters comprise the angle of attack (α), a pitch rate (q), the pitch angle (θ) and an airspeed (u), and the set of gains comprise Gα, Gq, Gθ and Gu, such that ΔSF=Gαα+Gqq+Gθθ+Guu. 6. The method of claim 4, wherein the parameters comprise the angle of attack (α), an angle of attack rate ({dot over (α)}), the pitch angle (θ) and an airspeed (u), and the set of gains comprise Gα, G{dot over (α)}, Gθ and Gu, such that ΔSF=Gαα+G{dot over (α)}{dot over (α)}+Gθθ+Guu. 7. The method of claim 1, further including: determining if a sensed angle-of-attack α plus a bias b is larger than an angle-of-attack reference value (αR), wherein said augmentation command (Δ) is enabled if the sensed angle-of-attack plus the bias is larger than the angle-of-attack reference value. 8. The method of claim 7, wherein said bias b is at least dependent on an angle-of-attack rate {dot over (α)}. 9. The method of claim 7, wherein said angle-of-attack reference value αR is a function that includes a Mach number (M), a landing gear position (δGEAR), a flap position (δFLAP) and an ice detection condition (bICE). 10. The method of claim 1, further including: determining if a sensed airspeed u minus a bias b is lower than an airspeed reference value (uR), i.e., u−b