Flight control system with tactile feedback

• US 5,062,594 A
• Filed: 11/29/1990
• Issued: 11/05/1991
• Est. Priority Date: 11/29/1990
• Status: Expired due to Fees

• Current Assignee: The United States of America As Represented By The Secretary of Agriculture
• Original Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Inventors: Repperger, Daniel W.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US07/624,096
• Time in Patent Office: 341 Days
• Field of Search: 364/433, 364/434, 244/223, 244/175, 244/177, 244/178, 244/181, 244/191, 244/194, 244/195, 340/705, 350/172, 358/103, 352/132
• US Class Current: 244/175
• CPC Class Codes: B64C 13/507 with artificial feel
• CPC Class Codes: G05D 1/0808 specially adapted for aircraft

Abstract

A control system for an aircraft or other man-machine system wherein the usual visual feedback system is characterized and is optimally supplemented by a secondary feel oriented feedback arrangement in which input signals are derived from either of two supplementary feedback signal sources and the resulting algorithms characterized mathematically. The disclosure includes several exemplary arrangements of the feedback systems in which some of the input parameters are of selected value. Mathematical characterization of the feedback paths is used.

Claims

1. An aircraft flight controller system providing a human operator with visual primary flight control information and tactile secondary flight control information supplementary to the visual primary flight control comprising the combination of:

a primary information human operator vision based and noise input forcing function f_D (t) signal inclusive closed feedback loop aircraft dynamics plant controlling apparatus, said apparatus including,

an aircraft dynamics plant means output, θ

(t) signal, to target input forcing function, F_T (t) signal, difference error based visual display having plant position display e(t) signal, output to said human operator,

a human operator force and secondary information tactile feedback force operated control stick including a predetermined stick mechanical impedance characteristic and integration means for converting stick velocity signals to stick position signals, and

aircraft dynamics plant for generating said output θ

(t) signal, said aircraft dynamics plant means including said F_D (t) noise forcing signal as an input thereto;

a secondary information tactile signal feedback path having said aircraft dynamics plant means output θ

(t) signal and said control stick position output signal as inputs thereto, and

a secondary information force signal output connected with said control stick, and

a transfer function defined by the mathematical relationship

space="preserve" listing-type="equation">1/P.sup.N (1/P-s.S SIMP)

wherein

P represents the aircraft dynamics plant transfer function

N represents a feedback determination variable having possible values of zero and one,

s represents the Laplace transform operator, and S IMP represents the impedance of said control stick.

2. The aircraft flight controller system, of claim 1 wherein said F_D (t) noise disturbance input forcing function is of zero magnitude and said variable N has a value of one;

whereby said secondary information tactile signal feedback path transfer function is defined by the mathematical relationship 1/P² -(s SIMP)/P.

3. The aircraft flight controller system, of claim 1 wherein said target input forcing function F_T (t) signal is of zero magnitude and said variable N has a value of zero;

whereby said secondary information tactile signal feedback path transfer function is defined by the mathematical relationship (1/P-s.S IMP).

4. The aircraft flight controller system of claim 1 wherein said F_D (t) noise disturbance input forcing function is of zero magnitude and said variable N has a value of zero;

whereby said secondary information tactile signal feedback path transfer function is defined by the mathematical relationship (1/P-s.S IMP).

5. The aircraft flight controller system of claim 1 wherein said F_D (t) noise disturbance input forcing signal is comprised of aircraft wind buffeting determined signal components.

6. The aircraft flight controller system of claim 5 wherein said F_D (t) noise disturbance input forcing signal is comprised of white noise determined signal components.

7. The aircraft flight controller system of claim 1 wherein said aircraft dynamics plant means output θ

(t) signal is representative of a position output signal from said flight controller system.

8. The aircraft flight controller system, of claim 1 wherein said control stick has a voltage output signal that is proportional to stick position.

9. The aircraft flight controller system of claim 1 wherein said target input forcing function F_T (t) signal is representative of the target input trajectory of a second aircraft, an aircraft being chased by said flight controller system aircraft.