A test flight system includes a test aircraft, and an atmospheric conditions-detecting vehicle that is separate and distinct from the test aircraft. The atmospheric conditions-detecting vehicle is configured to be deployed during a test flight of the test aircraft to detect atmospheric conditions of an environment in which the test aircraft operates during the test flight.

A test flight system includes a test aircraft, and an atmospheric conditions-detecting vehicle that is separate and distinct from the test aircraft. The atmospheric conditions-detecting vehicle is configured to be deployed during a test flight of the test aircraft to detect atmospheric conditions of an environment in which the test aircraft operates during the test flight.

A mounting rail system for a console of an aircraft includes a pair of mounting rails. The first mounting rail is secured to the console and includes a first track with a pair of threaded faces that are configured to receive a first fastener. The second mounting rail is secured to the console opposite the first mounting rail and includes a second track with a pair of threaded faces that are configured to receive a second fastener. The mounting rail system includes a first mounting bracket configured to be secured to the first mounting rail via the first fastener and a second mounting bracket configured to be secured to the second mounting rail via the second fastener.

A mounting rail system for a console of an aircraft includes a pair of mounting rails. The first mounting rail is secured to the console and includes a first track with a pair of threaded faces that are configured to receive a first fastener. The second mounting rail is secured to the console opposite the first mounting rail and includes a second track with a pair of threaded faces that are configured to receive a second fastener. The mounting rail system includes a first mounting bracket configured to be secured to the first mounting rail via the first fastener and a second mounting bracket configured to be secured to the second mounting rail via the second fastener.

Boundary information associated with a three-dimensional (3D) flying space is obtained, including a boundary of the 3D flying space. Location information associated with an aircraft is obtained, including a location of the aircraft. Information is presented based at least in part on the boundary information associated with the 3D flying space and the location information associated with the aircraft, including by presenting, in a display, the boundary of the 3D flying space and an avatar representing the aircraft at the location of the aircraft.

A computer implemented method for estimating angles of attack and/or an angle of sideslip of a flying body includes the steps of: providing data or measurements representative of a time derivative of a module of a speed of the flying body with respect to an air; providing data or measurements representative of corresponding projections of coordinate accelerations on a Cartesian reference frame fixed to the flying body; and calculating the angles of attack and/or the sideslip on a basis of an mathematical relationship of the angles of attack and the sideslip with the coordinate accelerations and the time derivative of the module of the speed of the flying body with respect to the air.

A computer implemented method for estimating angles of attack and/or an angle of sideslip of a flying body includes the steps of: providing data or measurements representative of a time derivative of a module of a speed of the flying body with respect to an air; providing data or measurements representative of corresponding projections of coordinate accelerations on a Cartesian reference frame fixed to the flying body; and calculating the angles of attack and/or the sideslip on a basis of an mathematical relationship of the angles of attack and the sideslip with the coordinate accelerations and the time derivative of the module of the speed of the flying body with respect to the air.

An autothrottle for an aircraft that includes a power-control input (PCL) manually movable by a pilot along a travel path to effect a throttle setting that controls engine power of the aircraft. The autothrottle determines a control-target setting for a throttle of the aircraft and dynamically adjusts the throttle according to the control-target setting, including moving the PCL to achieve the control-target setting. A virtual detent is set and dynamically adjusted at positions along a travel path of the PCL corresponding to the control-target setting. The virtual detent is operative, at least when the autothrottle is in a disengaged state for autothrottle control, to indicate the control-target setting to the pilot via a haptic effect that applies a detent force opposing motion of the PCL in response to the PCL achieving the position of the virtual detent.

An autothrottle for an aircraft that includes a power-control input (PCL) manually movable by a pilot along a travel path to effect a throttle setting that controls engine power of the aircraft. The autothrottle determines a control-target setting for a throttle of the aircraft and dynamically adjusts the throttle according to the control-target setting, including moving the PCL to achieve the control-target setting. A virtual detent is set and dynamically adjusted at positions along a travel path of the PCL corresponding to the control-target setting. The virtual detent is operative, at least when the autothrottle is in a disengaged state for autothrottle control, to indicate the control-target setting to the pilot via a haptic effect that applies a detent force opposing motion of the PCL in response to the PCL achieving the position of the virtual detent.

A torque measurement system determines torque on a shaft by monitoring angular deflection of the shaft under load using phase shift measurements. Calibration of the system uses a defined offset that is determined using a reference operating condition. The offset calibration value is determined for a rotorcraft using the following steps: defining a reference operational condition in which the shaft is rotating, estimating the torque at the reference condition based on aerodynamic knowledge of the rotors coupled to the shaft, operating the shaft at the reference operational condition, capturing sensor data to determine the phase difference at the operational condition, and associating the phase difference and an estimated torque as a calibration value to enable calculation of torque in the torque measurement system.