Abstract: Sensor data that includes or more of the following: (1) aircraft state information associated with an aircraft or (2) parachute canopy state information associated with a parachute canopy is received. The parachute canopy is coupled to the aircraft at a point aft of a center of mass of the aircraft. It is determined, based at least in part on the sensor data, whether to generate a control signal associated with maneuvering the aircraft into a nose-up position. A recovery action is performed, including by deploying the parachute canopy; wherein a load on the parachute canopy is reduced in the event the aircraft is in the nose-up position compared to the aircraft being in a nose-down position.

Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

Abstract: An automated aircraft recovery system is disclosed. In various embodiments, the system includes an interface configured to receive sensor data; and a control mechanism configured to: perform automatically a recovery action that is determined based at least in part on the sensor data. In various embodiments, the control mechanism may determine an expected state of an aircraft, determine whether a state of the aircraft matches the expected state, and in the event the state of the aircraft does not match the expected state, perform the recovery action.

Abstract: A first hand control controls an altitude of a vertical takeoff and landing (VTOL) aircraft; the movement of the VTOL aircraft within a plane defined by a roll axis and a pitch axis is independent of the first hand control. The first hand control is provided on a first hand side of a pilot's seat included in the VTOL aircraft. A second hand control controls the movement of the VTOL aircraft within the plane defined by the roll axis and the pitch axis; the altitude of the VTOL aircraft is independent of the second hand control. The second hand control is provided on a second hand side of the pilot's seat that is opposite from the first hand side.

Abstract: Hand controls for an aircraft, including a single axis hand control which is configured to control movement of an aircraft along a vertical axis where the aircraft includes a plurality of rotors that are attached to the aircraft at a fixed position and the plurality of rotors rotate independently of one another. The hand controls further include a three axis hand control which is configured to control movement of the aircraft within a plane defined by a roll axis and a pitch axis, as well as about a yaw axis.

Abstract: A hinged propeller comprising a hub and one or more blades is disclosed. In various embodiments, a blade is connected to the hub via a hinge, wherein at least a substantial part of the blade has a longitudinal axis that is substantially parallel to a line extending radially from a center of the hub, and wherein the hinge has an axis of hinge rotation that is oriented at a non-zero acute angle to a line that is perpendicular, in a plane of rotation of the hub, to said longitudinal axis.

Abstract: A first sensitivity level is used to interpret an input signal received from an input device in a vehicle while the vehicle is in a first region. A second sensitivity level is used to interpret the input signal received from the input device in the vehicle while the vehicle is in a second region, wherein the second sensitivity level is greater than the first sensitivity level.

Abstract: A set of commands for each of a plurality of actuators to alter an aircraft's state responsive to one or more inputs is produced. The set of commands is provided to fewer than all actuators comprising the plurality of actuators.

Abstract: A hinged propeller comprising a hub and one or more blades is disclosed. In various embodiments, a blade is connected to the hub via a hinge, wherein at least a substantial part of the blade has a longitudinal axis that is substantially parallel to a line extending radially from a center of the hub, and wherein the hinge has an axis of hinge rotation that is oriented at a non-zero acute angle to a line that is perpendicular, in a plane of rotation of the hub, to said longitudinal axis.

Abstract: Techniques to deploy a parachute are disclosed. In various embodiments, a first projectile is configured to be propelled in a first direction, causing the parachute to be deployed. A second projectile configured to be propelled in a second direction is coupled to a line tethered to the parachute in such a way that a force in a direction opposite the first direction is applied to the line of the parachute when the second projectile is propelled in the second direction.

Abstract: A first sensitivity level is used to interpret an input signal received from an input device in a vehicle while the vehicle is in a first region. A second sensitivity level is used to interpret the input signal received from the input device in the vehicle while the vehicle is in a second region, wherein the second sensitivity level is greater than the first sensitivity level.

Abstract: A float has a front-to-back length, a width, and a height where the front-to-back length of the float is strictly greater than the height of the float which in turn is strictly greater than the width of the float. At least a bottom portion of the float is watertight. The float includes an access panel to access the inside of the float. A battery is inside the float and is accessible via the access panel.

Abstract: A propeller includes a blade free to rotate about a longitudinal axis of the blade. The propeller also includes a mechanical stop positioned to engage mechanically a first portion of the blade and/or a first structure coupled mechanically to the blade when the blade is in a first position. The propeller also includes a magnetic stop positioned to engage magnetically a second portion of the blade and/or a second structure coupled mechanically to the blade when the blade is in a second position. The blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position.

Abstract: A set of commands for each of a plurality of actuators to alter an aircraft's state responsive to one or more inputs is produced. The set of commands is provided to fewer than all actuators comprising the plurality of actuators.

Abstract: A multicopter aircraft with a wide span rotor configuration is disclosed. In various embodiments, a multicopter as disclosed herein includes a fuselage and a plurality of rotors. The plurality of rotors includes inner rotors and outer rotors, with the inner rotors being substantially surrounded by the outer rotors or the fuselage. The inner rotors and the outer rotors may be tilted based at least in part on their arrangement in relation to the fuselage.

Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

Abstract: A first sensitivity level is used to interpret an input signal received from an input device in a vehicle while the vehicle is in a first region. A second sensitivity level is used to interpret the input signal received from the input device in the vehicle while the vehicle is in a second region, wherein the second sensitivity level is greater than the first sensitivity level.

Abstract: A self-adjusting flight control system is disclosed. In various embodiments, an input interface receives an input signal generated by an inceptor based at least in part on a position of an input device comprising the inceptor. A processor coupled to the input interface determines dynamically a mapping to be used to map input signals received from the inceptor to corresponding output signals associated with flight control and uses the determined mapping to map the input signal to a corresponding output signal. The processor determines the mapping at least in part by computing a running average of the output signal over an averaging period and adjusting the mapping at least in part to associate a neutral position of the input device comprising the inceptor with a corresponding output level that is determined at least in part by the computed running average.

Abstract: A multicopter with boom mounted rotors is disclosed. In various embodiments, a multicopter includes multiple rotors, each mounted substantially horizontally on a distal end of a boom. The multicopter further includes a plurality of boom extensions, each boom extension being associated with a corresponding boom and each boom extension being configured to extend an associated distal end of said corresponding boom by an amount determined based at least in part on a swept area associated with a rotor mounted at or near said associated distal end. The multicopter includes a material, such as netting, secured to the aircraft and of a size sufficient to reach a far end of one or more of said boom extensions.