Helicopter, high rotor load speed enhancement
US4998202A · kind A · utility
8Cited by
7References
3Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 19, 1989 |
| Grant date | Mar 5, 1991 |
| Priority date | — |
| Expiry date | May 19, 2009 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0858
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down (120, 103-105).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.