The present application provides methods and systems for launching an unmanned aerial vehicle (UAV). An exemplary system for launching a UAV includes a detector configured to detect acceleration of the UAV in a launch mode. The exemplary system may also include a memory storing instructions and a processor configured to execute the instructions to cause the system to: obtain a signal configured to notify the UAV to enter the launch mode, determine whether the acceleration of the UAV satisfies a condition corresponding to threshold acceleration in the launch mode, and responsive to the determination that the acceleration of the UAV satisfies the condition, turn on a motor of the UAV.

A no/low visibility automatic takeoff system for an aircraft obtains a runway reference centerline and aircraft pointing direction (via the aircraft's sensors) and automatically controls the aircraft pointing direction to track the runway reference centerline. An initial vector is obtained based on the initial position of the aircraft the first piloted initiation of the takeoff roll. After the system obtains a centerline, it automatically tracks the centerline and corrects aircraft trajectory so the aircraft heading closely matches the runway centerline as the aircraft proceeds down the runway.

An aircraft includes at least one line replaceable unit (LRU) configured to determine, based on initial data collected prior to a takeoff roll of the aircraft, a takeoff rotation speed of the aircraft and a rotation time associated with the takeoff rotation speed. The LRU is configured to determine, during the takeoff roll and prior to the rotation time, a predicted speed of the aircraft at the rotation time. The predicted speed is at least partially based on data collected during the takeoff roll. The LRU is also configured to determine whether an alert condition is satisfied at least partially based on whether a disparity between the takeoff rotation speed and the predicted speed exceeds a rotation speed disparity threshold and to generate a takeoff performance alert in response to the alert condition being satisfied.

An unmanned aerial vehicle, UAV, is operable in an autonomous mode. The UAV comprises an upwards-configurable sensor an actuator and a controller. The upwards-configurable sensor is configurable in an upwards-facing configuration during an autonomous procedure such that a field of view of the upwards-configurable sensor includes airspace directly above the UAV during the autonomous procedure. The controller is operable to control the actuator during the autonomous procedure based on data captured by the upwards-configurable sensor to cause the UAV to make physical contact with an object in the airspace directly above the UAV during the autonomous procedure.

An unmanned aerial vehicle (UAV) includes one or more motors configured to drive one or more propellers of the UAV, a motion sensor configured to determine a motion parameter of the UAV, a memory storing instructions, and a processor coupled to the one or more motors, the motion sensor, and the memory. The processor is configured to execute the instructions to cause the UAV to determine whether a hand thrown mode is selected for the UAV and whether the one or more motors are turned off; responsive to a determination that the hand thrown mode is selected, receive a motion parameter from the motion sensor; and activate the one or more motors when the motion parameter is greater than a threshold value.

Provided are airplane trim systems and methods of controlling such systems. These systems utilize smaller portions of the stabilizer total travel range for takeoff trims, in comparison to other trim systems. A trim system described includes stabilizer and elevator, and these components are used together to achieved a takeoff total tail pitching moment. The elevator or, at least a portion of the elevator operating range, is available for flight control. As such, takeoff trim settings include stabilizer and elevator orientation settings. Addition of the elevator to control the takeoff tail pitching moment allows reducing the stabilizer total travel. The elevator orientation can be changed much faster than that of the stabilizer providing pilot more control.

An example method includes: receiving information indicative of a desired aircraft cruise insertion point comprising achieving a desired cruise altitude for an aircraft within a predetermined period of time from departure, or within a predetermined distance from departure; determining a desired airspeed for the aircraft; prior to a flight of the aircraft, determining, based on the desired airspeed and the desired aircraft cruise insertion point, a climb trajectory for the aircraft; and during a climb flight phase of the aircraft, varying climb thrust of an engine of the aircraft to follow the climb trajectory and achieve the desired aircraft cruise insertion point.

An apparatus and method for establishing air data. An aircraft progresses while a processing module receives speed data from at least one sensor. The processing module can determine an actual airspeed of the aircraft based on the speed data. The processing model can also receive sensed real-time airspeed data for comparison to the actual airspeed. The comparison can automatically initiate a countermeasure.

A no/low visibility automatic takeoff system for an aircraft obtains a runway reference centerline and aircraft pointing direction (via the aircraft's sensors) and automatically controls the aircraft pointing direction to track the runway reference centerline. An initial vector is obtained based on the initial position of the aircraft the first piloted initiation of the takeoff roll. After the system obtains a centerline, it automatically tracks the centerline and corrects aircraft trajectory so the aircraft heading closely matches the runway centerline as the aircraft proceeds down the runway,

An example method includes: receiving information indicative of a desired aircraft cruise insertion point comprising achieving a desired cruise altitude for an aircraft within: a predetermined period of time from departure, or within a predetermined distance from departure; receiving information indicative of an estimated weight of the aircraft upon the aircraft reaching the desired cruise altitude; determining a desired airspeed for the aircraft based on the information indicative of the estimated weight of the aircraft; prior to a flight of the aircraft, determining, based on the desired airspeed and the desired aircraft cruise insertion point, a climb trajectory for the aircraft; and during a climb flight phase of the aircraft, varying climb thrust of an engine of the aircraft to follow the climb trajectory and achieve the desired aircraft cruise insertion point.