Autopilot pitch attitude control

Claim 2

In an automatic pilot system for aircraft, the combination comprising an integrator output signal level adjustment subsystem comprising integrator means, manually rotatable rate generator means for providing an output signal proportional to the rate of rotation thereof, means for operably connecting said rate generator means output signal with said integrator means, means for detecting said output from said rate generator means, and means responsive to said detecting means for enabling said integrator means whereby its output signal level is adjusted in accordance with said rate generator means output signal, wherein said rate generator means comprises a manually rotatable rate generator, a noncentering manually operated wheel and a step-up gear train operably connecting said wheel with said rate generator, wherein said detecting means comprises a threshold detector having a pre-established minimum level, wherein said integrator means comprises clampable integrator means, wherein said detecting means comprises switching means responsive to said threshold detector for operably connecting said integrator with said rate generator whereby the rate generator output signal will adjust the integrator output signal level.

Claim 3

In an aircraft automatic flight control system having a pitch attitude command mode including a source of pitch attitude command input signals, a clampable pitch integrator for integrating when unclamped the pitch attitude command input signals and when clamped for maintaining a fixed pitch attitude, a source of pitch attitude input signals, a first summing junction for combining the pitch attitude command input signals and pitch attitude signals, and a servomechanism system for positioning the aircraft pitch surfaces in accordance with the output signal of the first summing junction, wherein the improvement comprises manually operable rate generator means for providing a signal in response to the speed of rotation thereof, and means for unclamping the pitch integrator in response to an output of said rate generator means, whereby an output from said rate generator means will modify the original level stored within the pitch integrator and thereby affect the output of the first summing junction.

Claim 4

In an aircraft automatic flight control system having a pitch attitude command mode including a source of pitch attitude command input signals, a clampable pitch integrator for integrating when unclamped the pitch attitude command input signals and when clamped for maintaining a fixed pitch attitude, a source of pitch attitude input signals, a first summing junction for combining the pitch attitude command input signals and pitch attitude signals, and a servomechanism system for positioning the aircraft pitch surfaces in accordance with the output signal of the first summing junction, wherein the improvement comprises manually operable rate generator means for providing a signal in response to the speed of rotation thereof, and means for unclamping the pitch integrator in response to an output of said rate generator means, whereby an output from said rate generator means will modify the original level stored within the pitch integrator and thereby affect the output of the first summing junction.

Claim 5

The system as claimed in claim 2 wherein said unclamping means comprises a level detector for inhibiting an output of said rate generator means less than a predetermined value.

Claim 6

In an aircraft automatic flight control system having a pitch attitude command mode including a source of pitch attitude command input signals, a clampable pitch integrator for integrating when unclamped the pitch attitude command input signals and when clamped for maintaining a fixed pitch attitude, a source of pitch attitude input signals, a first summing junction for combining the pitch attitude command input signals and pitch attitude sIgnals, and a servomechanism system for positioning the aircraft pitch surfaces in accordance with the output signal of the first summing junction, wherein the improvement comprises manually operable rate generator means for proving a signal in response to the speed of rotation thereof, and means for unclamping the pitch integrator in response to an output of said generator means, whereby an output from said rate generator means will modify the original level stored within the pitch integrator and thereby affect the output of the first summing junction, wherein said unclamping means comprises a level detector for inhibiting an output of said generator means less than a predetermined value and an AND gate responsive to an output from said level detector and an output from a pitch attitude mode selector switch for providing an input to the pitch integrator, whereby said input to the pitch integrator unclamps the pitch integrator.

Claim 7

In an aircraft automatic flight control system having a pitch attitude command mode including a source of pitch attitude command input signals, a clampable pitch integrator for integrating when unclamped the pitch attitude command input signals and when clamped for maintaining a fixed pitch attitude, a source of pitch attitude input signals, a first summing junction for combining the pitch attitude command input signals and pitch attitude sIgnals, and a servomechanism system for positioning the aircraft pitch surfaces in accordance with the output signal of the first summing junction, wherein the improvement comprises manually operable rate generator means for proving a signal in response to the speed of rotation thereof, and means for unclamping the pitch integrator in response to an output of said generator means, whereby an output from said rate generator means will modify the original level stored within the pitch integrator and thereby affect the output of the first summing junction, wherein said unclamping means comprises a level detector for inhibiting an output of said generator means less than a predetermined value and an AND gate responsive to an output from said level detector and an output from a pitch attitude mode selector switch for providing an input to the pitch integrator, whereby said input to the pitch integrator unclamps the pitch integrator.

Claim 8

The system as claimed in claim 4 wherein said signal rate generator comprises a manually operated wheel, and a gear train for operably connecting said wheel with said rate generator.

Claim 9

The system as claimed in claim 5 comprising a filter for filtering the output of said rate generator.

Claim 10

In an aircraft automatic flight control system having a vertical speed command mode, the combination comprising a source for the vertical speed command signal, a vertical speed integrator, a clampable pitch integrator, a pitch attitude input signal source, a summing junction for combining the vertical speed command signal, the vertical speed integrator output, the pitch integrator output and the pitch attitude input signal, a servomechanism system for positioning the pitch control surfaces in response to the output signal of the summing junction, wherein the improvement comprises manually operated signal rate generator, means for adjusting the vertical speed integrator output signal level in accordance with the output of said rate generator, means for clamping the pitch integrator in response to an output from said rate generator means, whereby movement of said rate generator means will change the output signal level of the summing junction and energize the servomechanism system until the output signal level change is compensated by the pitch attitude input signal.

Claim 11

In an aircraft automatic flight control system having a vertical speed command mode, the combination comprising a source for the vertical speed command signal, a vertical speed integrator, a clampable pitch integrator, a pitch attitude input signal source, a summing junction for combining the vertical speed command signal, the vertical speed integrator output, the pitch integrator output and the pitch attitude input signal, a servomechanism system for positioning the pitch control surfaces in response to the output signal of the summing junction, wherein the improvement comprises manually operated signal rate generator, means for adjusting the vertical speed integrator output signal level in accordance with the output of said rate generator, means for clamping the pitch integrator in response to an output from said rate generator means, whereby movement of said rate generator means will change the output signal level of the summing junction and energize the servomechanism system until the output signal level change is compensated by the pitch attitude input signal.

Claim 12

The combination as claimed in claim 7 wherein said adjusting means comprises a level detector for inhibiting a signal output of said rate generator means of less than a predetermined value, and means for operably connecting said rate generator means to said vertical speed integrator.

Claim 13

In an aircraft automatic flight control system having a vertical speed command mode, the combination comprising a source for the vertical speed command signal, a vertical speed integrator, a clampable pitch integrator, a pitch attitude input signal source, a summing junction for combining the vertical speed command signal, the vertical speed integrator output, the pitch integrator output and the pitch attitude input signal, a servomechanism system for positioning the pitch control surfaces in response to the output signal of the summing junction, wherein the improvement comprises manually operated signal rate generator means, means for adjusting the vertical speed integrator output signal level in accordance with the output of said rate generator means, means for clamping the pitch integrator in response to an output from said rate generator means, whereby movement of said rate generator means will change the output signal level of the summing junction and energize the servomechanism system until the output signal level change is compensated by the pitch attitude input signal, wherein said adjusting means comprises a level detector for inhibiting a signal output of said rate generator means of less than a predetermined value, and means for operably connecting said rate generator means to said vertical speed integrator, wherein said clamping means comprises an output signal from said level detector, an AND gate having one input responsive to said rate generator means, said AND gate having a second input responsive to a vertical speed mode switch, means associated with the pitch integrator responsive to an output from said AND gate output for clamping the pitch integrator.

Claim 14

In an aircraft automatic flight control system having a vertical speed command mode, the combination comprising a source for the vertical speed command signal, a vertical speed integrator, a clampable pitch integrator, a pitch attitude input signal source, a summing junction for combining the vertical speed command signal, the vertical speed integrator output, the pitch integrator output and the pitch attitude input signal, a servomechanism system for positioning the pitch control surfaces in response to the output signal of the summing junction, wherein the improvement comprises manually operated signal rate generator means, means for adjusting the vertical speed integrator output signal level in accordance with the output of said rate generator means, means for clamping the pitch integrator in response to an output from said rate generator means, whereby movement of said rate generator means will change the output signal level of the summing junction and energize the servomechanism system until the output signal level change is compensated by the pitch attitude input signal, wherein said adjusting means comprises a level detector for inhibiting a signal output of said rate generator means of less than a predetermined value, and means for operably connecting said rate generator means to said vertical speed integrator, wherein said clamping means comprises an output signal from said level detector, an AND gate having one input responsive to said rate generator means, said AND gate having a second input responsive to a vertical speed mode switch, means associated with the pitch integrator responsive to an output from said AND gate output for clamping the pitch integrator.

Claim 15

The combination as claimed in claim 9 including an automatically actuatable switch responsive to an output from said level detector whereby the signal level stored within said vertical speed integrator is modified by the output of said level detector.