CONTROL SURFACE DUAL REDUNDANT SERVOMECHANISM
Assignee
UNITED STATES OF AMERICA AS REPRESENTED BY THE SECRETARY OF THE UNITED STATES AIR FORCE.
Filed
Dec 11, 1984
Granted
Jan 31, 1989
Location
RENTON WA US
Abstract
A dual redundant servomechanism for moving aircraft control surfaces is disclosed. The servomechanism is of the type whose input commands, from the pilot of the aircraft, are transmitted electrically. Force fight, which is associated with such dual servomechanisms when they are connected to a common aircraft control surface, is minimized. This is accomplished by providing the control system for each servomechanism with input signals which are electrically summed. Each control system includes electrical transducers which provide a signal indicative of actuator position and the pressure associated with the hydraulic motor used in each servomechanism.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Aug 5, 1985
Rescinded
Jul 15, 1988
Duration
2 years, 11 months
Inventor
- 1CLETE M. BOLDRIN
Record Details
- Patent number
- US 4800798
- Application
- 06680674
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
UNITED STATES OF AMERICA AS REPRESENTED BY THE SECRETARY OF THE UNITED STATES AIR FORCE.Related by domain
V/STOL AIRCRAFT
BRITISH AEROSPACE PUBLIC LIMITED COMPANY
CRYOGENIC TANKS FOR LAUNCH VEHICLES
KISTLER AEROSPACE CORPORATION, A WASHINGTON CORPORATION
PROCESS FOR PREVENTING TURNING OVER DURING THE LANDING OF AN AIRCRAFT OR SPACECRAFT
DAIMLER-BENZ AEROSPACE AG
NEURAL NETWORK CONTROLLER FOR A PULSED ROCKET MOTOR TACTICAL MISSILE SYSTEM
Raytheon
VTOL AIRCRAFT NOZZLE
ROLLS-ROYCE PLC
MISSILE JET VANE CONTROL SYSTEM AND METHOD
HUGHES MISSILE SYSTEMS COMPANY