Helicopter autopilot providing airspeed control
US5738300A · kind A · utility
Inventor
Key dates
| Filing date | Jul 1, 1996 |
| Grant date | Apr 14, 1998 |
| Priority date | — |
| Expiry date | Jul 1, 2016 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0858
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
The invention relates to novel basic architecture for helicopter autopilots, transforming the conventional objective of maintaining fuselage trim to an objective of maintaining airspeed, and without making use of coupler techniques. On each of the pitch and roll control systems, a known fraction of the output signal (24S) from the flight control is injected by being summed with the standard fuselage trim input (1S). The signal (4S) formed in this way possesses the novel static and dynamic properties required for the control loop to make the helicopter statically stable in speed throughout its flight envelope. The novel architecture makes it possible to replace the conventional fuselage trim signal (1S) with an accelerometer signal. The signal (4S) is displayed in particular on a standard "artificial horizon" type instrument (33), thereby making it possible simultaneously to monitor rapid variations of fuselage trim and to control airspeeds.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.