Maneuver-force gradient system
First Claim
1. A maneuver-force gradient system for causing the nose of an aircraft to pitch nose down in a turn involving roll, comprising:
- actuator means for positioning the pitch axis aerodynamic surfaces of the aricraft in response to a command signal;
roll angle sensor means for providing a roll angle signal indicative of the aircraft roll angle as measured from wings-level flight; and
control means for causing the aircraft to pitch nose down in the turn as a function of the aircraft roll angle by providing the command signal to the actuator in response to the roll angle signal.
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Accused Products
Abstract
A maneuver force gradient system causes a helicopter, that otherwise tends to pitch up in a banked turn, to pitch nose-down. A command signal (25) is provided as a function of the roll angle to operate the longitudinal trim actuator (27) which automatically moves the cyclic control (50) resiliently (28) forward to push the nose down. The pilot must consequently pull back on the cyclic control (50) to achieve a desired pitch attitude, thereby establishing a longitudinal positive maneuver-force gradient. The system is operable only when the pilot initiates a roll (33, 38, 50, 51) and the roll angle equals or exceeds 30° (30, 33, 36, 37). Both analog (FIG. 1) and digital (FIG. 2) embodiments are disclosed, and the invention may be practiced in association with an AFCS (101) having the longitudinal trim actuator (27) and resilient linkage (28).
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Citations
8 Claims
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1. A maneuver-force gradient system for causing the nose of an aircraft to pitch nose down in a turn involving roll, comprising:
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actuator means for positioning the pitch axis aerodynamic surfaces of the aricraft in response to a command signal; roll angle sensor means for providing a roll angle signal indicative of the aircraft roll angle as measured from wings-level flight; and control means for causing the aircraft to pitch nose down in the turn as a function of the aircraft roll angle by providing the command signal to the actuator in response to the roll angle signal. - View Dependent Claims (2, 3, 4, 5, 6)
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7. In a method of controlling an aircraft that pitches up in a maneuver involving roll, for establishing a positive maneuver-force gradient on the pitch control indicative of the magnitude of the roll angle of the maneuver, the steps of:
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automatically moving the pitch control forward as a function of the roll angle to cause the aircraft to pitch nose-down; and moving the pitch control aft to oppose the automatic forward movement, thereby arresting the downward pitching of the aircraft and controlling the pitch of the aircraft, whereby the automatic forward movement of the pitch control provides to the pilot an indication of the magnitude of the roll angle.
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8. In a method of controlling an aircraft that pitches up in a maneuver involving roll and that has actuator means for positioning the pitch axis aerodynamic surfaces of the aircraft, for establishing a positive maneuver-force gradient on the pilot'"'"'s pitch control indicative of the magnitude of the roll angle of the maneuver, the steps of:
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automatically causing the actuator means to control the pitch attitude of the aircraft nose-down as a function of the roll angle; and moving the pitch control aft to oppose the nose-down pitching of the aircraft and controlling the pitch of the aircraft, whereby the amount of aft movement of the pitch control required to control the aircraft attitude from the nose-down attitude to a desired pitch attitude provides to the pilot an indication of the magnitude of the roll angle.
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Specification