Automatic control system for directional control of an aircraft during landing rollout
US4482961A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 18, 1981 |
| Grant date | Nov 13, 1984 |
| Priority date | — |
| Expiry date | Sep 18, 2001 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0083
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
A control system for maintaining an aircraft within the lateral boundaries of a runway during landing rollout under conditions of combined crosswind and low runway friction is disclosed. An automatic mode of operation is provided wherein the system utilizes an input signal representative of the heading of the runway being utilized and signals provided by (or derivable from ) an inertial navigation system to exercise coordinated control of the aircraft rudder, steering and differential braking system. In a semiautomatic mode of operation, signals supplied by the inertial navigation system (or its equipment) are utilized in conjunction with a continuous command signal that is provided by the pilot to indicate the desired aircraft trajectory. An optional provision is included for limiting the aircraft ground velocity slip angle to a range wherein an increase in ground velocity slip angle results in increased lateral corrective force on the aircraft. An additional optional provision modifies operation of the brake-antiskid system employed by the aircraft so as to reduce braking pressure by an amount that substantially optimizes lateral corrective force on the aircraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.