Abstract: An aircraft automatic throttle system is responsive to a throttle command signal to drive the aircraft throttle through a clutch and detent mechanism which allows for pilot override. Full throttle is achieved only if the throttle is driven against the stop position at the engine with a controlled, limited force. The instant invention is an improved servoamplifier system and method including a position sensor for sensing the position of the throttle, a summing circuit for summing the throttle command signal with the position sensor signal to produce an error signal and an amplifier for amplifying the error signal and producing an output signal to drive the servo driver. Unique signal processing is provided which monitors the amplifier output signal and detects a predetermined condition thereof representative of the throttle being driven against the forward stop at the engine.

Abstract: A controller for automatically controlling aircraft thrust during a noise abatement climb operates so as to smoothly reduce aircraft thrust during a reduction in aircraft climb angle at the noise abatement altitude so as to maintain a selected noise abatement climb gradient dependent upon the pilot maintaining a recommended climb airspeed. The selected noise abatement climb gradient is compared with a measured climb gradient to generate an error term. The measured climb gradient is adjusted by a acceleration correction term in order to make the resulting measured climb gradient term independent of airspeed changes. The climb gradient error term is added to the selected climb gradient to generate a commanded climb gradient which is converted to an equivalent thrust (noise abatement thrust). The resulting noise abatement thrust is compared with measured engine thrust to generate an error term for controlling engine thrust so that the aircraft follows the noise abatement climb gradient.

Abstract: An automatic throttle (A/T) controller (23) for controlling the thrust produced by the engines of an aircraft having a mixture of different types of engines (11a, 11b, . . . 11n) is disclosed. A code that denotes the type and rating is produced for each aircraft engine. If desired other codes, such as a common rating code, a maximum thrust limit code, etc. can be produced. The codes are read by the A/T controller (23) and used to look up engine type and rating data for a controller channel (25a, 25b, . . . 25n) associated with each engine (11a, 11b . . . 11n). In a conventional manner, each channel (25a, 25b, . . . 25n) uses the type and rating data, and common data, if any, to calculate rating limits, throttle control position and throttle limits, plus allocate gains for dynamic control. The calculated parameters control the production of A/T controller signals that, in turn, control the operation of servo motors (19a, 19b, . . .

Abstract: A system for displaying to the pilot an indication to enable him to fly to a desired air speed and angle of attack, especially on takeoff. An artificial angle of attack error signal is generated from actual and desired air speeds and corrected by adding to it a differentiated pitch signal. The resultant calculated angle of attack error is displayed to the pilot unless flying to that indication would result in exceeding the actual maximum or minimum angle of attack limits, in which case an indication based on the actual exceeded limit is displayed.

Abstract: A system for compensating for certain speed overshoot problems encountered in large instrument-controlled aircraft during long-term deceleration from high speeds, such as may be encountered in preparation for descent to landing approach from cruise conditions. During such long-term deceleration, the aircraft vertical gyro miss-erects due to an effect of the deceleration upon the gyro positioning control circuitry. The present system compensates for the gyro signal error, used for developing the aircraft speed command following deceleration, by the use of a threshold detector and filter to develop a compensation signal having a delay and amplitude related to the input control signals involved.