Aircraft pitch stabilization apparatus
US4442490A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Feb 28, 1983 |
| Grant date | Apr 10, 1984 |
| Priority date | — |
| Expiry date | Feb 28, 2003 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0607
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
An automatic aircraft pitch axis flight stabilization system which does not require the use of a gyroscope is described. Stability signals are derived from an altitude signal responsive to atmospheric pressure. Means responsive to rate of change of altitude produces a vertical rate signal and means responsive to rate of change of vertical rate produces a vertical acceleration signal. The vertical speed signal is combined with a command signal which causes the aircraft to fly at constant altitude, at constant vertical speed, or to descend along a glide slope, and the vertical acceleration signal to produce a control signal which operates a means, such as a servomechanism for positioning the vertical control surfaces of the aircraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.