Control augmentation system for flight vehicles

• US 4,198,017 A
• Filed: 10/13/1978
• Issued: 04/15/1980
• Est. Priority Date: 10/13/1978
• Status: Expired due to Term

• Current Assignee: The United States Of America As Represented By The Secretary Of The Army
• Original Assignee: The United States Of America As Represented By The Secretary Of The Army
• Inventors: Murray, James B.
• Primary Examiner(s): Blix, Trygve M.
• Assistant Examiner(s): Eisenzopf, Reinhard J.
• Application Number:
  US05/951,201
• Time in Patent Office: 550 Days
• Field of Search: 244/17.13, 244/178, 244/83 G, 244/83 H, 318/628, 318/610, 364/434, 364/116
• US Class Current: 244/221
• CPC Class Codes: G05D 1/0816 to ensure stability

Abstract

A control augmentation system for stabilization and control of flight vehes, wherein control of vehicle angular velocities in proportion to control input is effected, and where stabilization of the corresponding vehicle attitude is also effected. The system consists of both feedforward and feedback signal paths. The feedback paths provide augmentation of the vehicle'"'"'s inherent stability. The feedforward paths augment the controllability factors available to the pilot. The control augmentation system is a solution to hingeless rotor control problems.

Claims

1. In a flight control system including a control stick, a mechanical gain means, a hydraulic boost actuator, and a control augmentation system including a rate gyroscope having an output, a first feedback path having a gain K_ql driven by said rate gyroscope output, a second feedback path having a gain K_qs driven by said rate gyroscope output, a control stick position transducer having an output, a first feedforward path having a gain K.sub.δ

l driven by said control stick position transducer output, a second feedforward path having a gain K.sub.δ

s driven by said control stick position transducer output, a first summing means for summing the outputs of said first feedback path and said first feedforward path, a pseudo-integrator means including an output driven by the output of said first summing means, a second summing means for summing the output of said psuedo-integrator, said second feedback path and said second feedforward path, and a servo actuator means for receiving the output of said second summing means for augmenting the mechanical gain of said flight vehicle whereby control of flight vehicle angular velocities in proportion to control input and stabilization of flight vehicle attitude is effected, an automatic series trim system comprising;

(a) a hydraulic servo actuator displacement sensor;

(b) a bi-directional switch;

(c) a trim motor, and

(d) a stability compensation path with gain K;

wherein said system measures said hydraulic actuator displacement, and through said bi-directional switch operates said trim motor, whereby said trim motor adds to the output of said servo actuator causing control surface and vehicle motion.

2. The flight control system of claim 1 including a ground handling system comprising:

(a) a ground contact sensing switch;

(b) a ground handling feedback path including a dual valued lag filter;

(c) a split secondary feedforward path K.sub.δ

S, including paths K.sub.δ

S1, and K.sub.δ

S2 ;

(d) a ground feedback pickoff point;

(e) a summing means downstream of said ground feedback pickoff which cancels some or all of said mechanical system gain and wherein said ground handling feedback path desensitizes the vehicle rate to surface deflection paths thereby preventing said feedback paths from commanding excessive control surface deflections during landing transients.