发明名称 |
TCAS II pitch guidance control law and display symbol. |
摘要 |
<p>An airplane pitch guidance control law and display symbol for a Traffic alert and Collision Avoidance System (TCAS) is disclosed. The control law converts a TCAS computer-generated vertical air speed command into a pitch guidance command. The pitch guidance command controls the location of a symbol (51) on the pitch axis of an electronic attitude display (21) that guides a pilot toward a pitch attitude that will result in a vertical speed that eliminates a collision threat. The preferred symbol is a pitch axis leg (53) and a pair of outwardly diverging legs (55a, 55b). The pitch axis leg (53) defines the minimum climb or descent attitude required to achieve a safe climb or descent angle. The pitch axis leg (53) and the diverging legs (55a, 55b) combine to define a climb or descent attitude range to avoid. The distance between the pitch axis leg 53 and the boresight 39 of the airplane symbol of the display is controlled by a RACMD signal produced by: subtractively combining the vertical speed command (VSTCAS) produced by a TCAS II computer and the vertical speed of the airplane (VSIND); multiplying the result by a sensitivity factor K whose value is related to the true air speed of the airplane and 57.3 to approximate the arc tangent of the quotient; and subtracting a factor that compensates for the fact that flight path angle changes lag pitch attitude changes. <IMAGE></p> |
申请公布号 |
EP0545473(A2) |
申请公布日期 |
1993.06.09 |
申请号 |
EP19920203644 |
申请日期 |
1992.11.25 |
申请人 |
THE BOEING COMPANY |
发明人 |
KELLY, BRIAN D.;STEMER, PAUL NMI;WIEDEMANN, JOHN NMI;BERNSTEIN, ARTHUR D.;MYERS, ROBERT J. |
分类号 |
G01C23/00;G01S13/93;G05D1/06;G08G5/04;(IPC1-7):G01S13/93 |
主分类号 |
G01C23/00 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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