{
  "$type": "site.standard.document",
  "description": "The method involves estimating a turn rate of an aircraft (1) by estimating an angular speed measurement on a vertical geometrical axis. North and east horizontal components (34-36) of corrections of linear acceleration, angular speed and angular acceleration of the aircraft, are obtained by a…",
  "path": "/patents/1010452",
  "publishedAt": "2011-08-03T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "G01C21/185",
    "EUROCOPTER FRANCE [FR]"
  ],
  "textContent": "The method involves estimating a turn rate of an aircraft (1) by estimating an angular speed measurement on a vertical geometrical axis. North and east horizontal components (34-36) of corrections of linear acceleration, angular speed and angular acceleration of the aircraft, are obtained by a linear combination of north and east airspeed error inputs (32, 33) to obtain cross coefficients between horizontal axes. Each coefficient is a continuous function of time and is dependent on estimation of the turn rate such that estimation of trim angles is stable during turning of the aircraft. Independent claims are also included for the following: (1) a device for estimating a trim angle of an aircraft, comprising a virtual platform (2) an aircraft comprising an inertial measurement unit.",
  "title": "Stabilised estimation of the pitch angles of an aircraft during turns"
}