Two-axis rudder trim for aircraft
US4373689A · kind A · utility
Inventor
Key dates
| Filing date | Jul 16, 1980 |
| Grant date | Feb 15, 1983 |
| Priority date | — |
| Expiry date | Jul 16, 2000 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C5/10
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A swivel-mounted trim element of a predetermined configuration for use with aircraft for the purpose of providing additional control in flight. The trim element is mounted immediately to the rear of a channel-shaped stabilizer mounted externally or molded into the fuselage of an aircraft and is especially suited for small aircraft, particularly those having V-surface tail assemblies. The trim element configuration is generally right-angled with the base portion being additionally formed to have a downwardly-canted portion at the leading edge and an inwardly-canted portion at the trailing edge. In operation, the trim element provides two-axis rudder trim about both the pitch and yaw axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.