Tested, dissimilar helicopter stability augmentation
US4313201A · kind A · utility
12Cited by
7References
2Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 5, 1980 |
| Grant date | Jan 26, 1982 |
| Priority date | — |
| Expiry date | Mar 5, 2000 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0077
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
The main roll and yaw axes of a helicopter having a main rotor operative in response to cyclic and collective pitch commands and a tail rotor operative in response to pitch commands, include stability inputs to actuators which are selectively provided by an analog channel, a digital channel, or one half by each, the digital channels being manifested in a digital computer system which includes programs of self-test, in-flight comparison between the inputs and outputs of corresponding analog and digital channels, and ground tests of testable rate gyro inputs to the various digital and analog channels and the outputs thereof.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.