The Boeing Company

David S Yotsuuye

Ethmer W King

Robert C Kircher, Jr

Syed Tahir Shafaat

Minh-Tri Le

Tan Nhat Che

Siamak H Ghaffari

Mohammed R Radfar

A method for achieving and maintaining spacing between aircraft may include receiving by a following aircraft information related to a lead aircraft. The information is useable for achieving and maintaining spacing by the following aircraft from the lead aircraft. The method may also include determining spacing of the following aircraft from the lead aircraft. The method may additionally include receiving by the following aircraft a vertical profile for the traffic management environment. The method may further include automatically controlling throttle settings to achieve and maintain spacing by the following aircraft from the lead aircraft while maintaining the vertical profile of the following aircraft in response to an automatic spacing mode being enabled.

On-board aircraft system and method for achieving and maintaining spacing

An aircraft navigational system which provides flight data information for an aircraft to travel along a first airway to a point of intersection with a second airway and then along said second airway. The system determines whether the point of intersection is at a named waypoint common to both said first and second airways, or if the point of intersection is unnamed. If unnamed, the system computes the location of the unnamed point of intersection and provides flight path data to said unnamed point of intersection and then along said second airway.

Aircraft navigational system and method for guiding an aircraft along

An aircraft navigational system includes a digital computer, a first visual output for displaying to an aircrew a geometrical representation of an optimum descent guideslope relative to a symbol representing the location of the aircraft, and a second visual output for displaying optimum descent guideslope information, such as altitude and distance, alphanumerically. The visual display provides guidance information to the aircrew to control the descent of the aircraft along an optimum descent guideslope which is referenced to a selected end of descent waypoint such as a destination airport or to an instrument approach marker. The guideslope is calculated in accordance with predetermined airspeed and altitude requirements with define a descent profile which is fuel efficient and which complies with aviation regulations regarding maximum airspeed limitations. The navigational system includes a keypad interfaced with the computer to allow the aircrew to enter data inflight to generate the visual and alphanumerical display of the optimum descent guideslope.

Aircraft descent guide system and method for creating descent guidance

An aircraft navigational system for providing a geometic display to the pilot of the vertical position of the aircraft relative to a selected vertical flight path profile as the aircraft progresses between its departure and destination. The vertical profile, which has a climb portion, a cruise portion and a descent portion, is formed by a number of navigational points, each of which is defined by an altitude component and a geographical position component. The profile points which form the climb and descent profiles are calculated from controller assigned altitude and waypoint constraints as well as from airspeed and altitude operating limitations which define various selected aircraft performance climb and descent modes.

Navigational apparatus and methods for displaying aircraft position with

Aircraft navigational system and methods are disclosed for creating aircraft navigational guidepoints during in-flight operations. A digital computer and computer control displays provide dynamic and static display of the aircraft relative to the flight path and earth referenced data. In one embodiment, a new guidepoint is located and displayed at the intersection of a pilot selected radial and a track line, such as the aircraft projected flight path, defined by a series of guidepoints which are stored in the computer. The selected radial emanates from a selected geographical location defined by a known latitude/longitude, such as for example, preprogrammed NAVAIDS, geographical reference points and pilot entered geographical locations. The latitude/longitude and place-bearing-distance of the new guidepoint is calculated by first determining the great circle distance and true bearing from the NAVAID to each of the guidepoints using spherical geometry, and then comparing the true bearing of the selected radial to each set of adjacent guidepoints to determine between which set of adjacent guidepoints the selected radial lies. Then using geometric relationships and spherical geometry, the place-bearing-distance of the new guidepoint is determined.

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Renton, WA, United States of America

David S Yotsuuye