The Boeing Company

Theboeing Company

Christopher J Heiberg

Robert J Atmur

Patrick Joseph McCormick

Thomas Edward Yochum

Kelly Schofield

Patrick J Mccormick

Apparatus and methods for controlling an aircraft are described. A computing device can receive a flight plan from an origin to a destination via waypoint(s) and can calculate a flight trajectory for the flight plan. While controlling the aircraft to fly along the flight trajectory, the computing device can receive inputs that change the flight plan resulting in trajectory recalculation. After determining that the inputs include the inputs to change the flight plan resulting in trajectory recalculation, the computing device can calculate a new flight trajectory for the new flight plan. After calculating the new flight trajectory, the computing device can switch from the flight trajectory to the new flight trajectory, where the aircraft maintains continuous flight along the flight trajectory during the switch.

Methods and apparatus for providing continuous flight trajectories for aircraft

A method includes generating a flight plan of an aircraft. The flight plan is based on at least one waypoint and a set of operational rules associated with the aircraft. The method also includes generating an initial trajectory profile based on the at least one waypoint and the set of operational rules. The method further includes identifying an impermissible flight condition associated with the initial trajectory profile. The impermissible flight condition violates at least one operational rule of the set of operational rules. The method further includes generating a modified trajectory profile by modifying at least one aspect of the initial trajectory profile to remove the impermissible flight condition. The modified trajectory profile can be used by a pilot to fly the aircraft, the modified trajectory profile can be used by an autopilot system, or the modified trajectory profile can be displayed.

System and method to modify an aircraft flight trajectory

Actuators for high lift devices on aircraft are disclosed herein. An example apparatus includes an actuator for a high lift device of an aircraft including a motor and a transmission, where the transmission includes a first gear stage and a second gear stage, the first gear stage including a first worm gear and the second gear stage including a second worm gear, the first worm gear, the second worm gear and the motor operative to prevent backdrive of the actuator.

Actuators for high lift devices on aircraft

Techniques for providing singularity escape and avoidance are disclosed. In one embodiment, a method for providing control moment gyroscope (CMG) attitude control singularity escape includes calculating a Jacobian A of a set of control equations, calculating a measure of closeness to a singularity, and comparing the calculated closeness to a threshold value, when the calculated closeness is less than or equal to the threshold value, recalculating the Jacobian A. Recalculating may include determining a new direction of virtual misalignment of &#x3b2; and &#x3b3;, recalculating the Jacobian inputting the new direction of the virtual misalignment, recalculating the measure of closeness to a singularity, and comparing the measure of closeness to the threshold value. Further, the method may include calculating a gimbal rate command if the of closeness is greater than the threshold value and generating a torque from the gimbal rate command to control the attitude of a satellite.

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Sunset Beach, CA, United States of America

Christopher J Heiberg