A robot including a hybrid fan-based and fluid-based propulsion system to provide thrust, such as deceleration during fall to create a smooth landing or to provide a quick reduction in velocity, and to provide actuation/controlled motion, such as to hover after quick deceleration and to control orientation or pose. The hybrid propulsion system uses discharging of pressurized fluid and exhausted gas (or fluid in some cases) from ducted fans (or propellers, impellers, and the like) to provide controlled thrust and/or lift forces. The hybrid propulsion system uses of pressurized fluid for generating larger or primary thrust and quick changes in velocity. The hybrid propulsion system includes a fan-based propulsion assembly with ducted fans that use environmental air (or fluids) to provide lower or secondary thrust. Both types of propulsion can be integrated into a robot or robotic figure to move the robot during flight (e.g., during falling or hovering).

Methods, systems, and assemblies for operating an aircraft having a turboprop engine are described. The method comprises obtaining a measured torque of the turboprop engine from a mechanical torque piston measurement system and displaying the measured torque in a cockpit of the aircraft. During operation of the turboprop engine, a torque measurement saturation condition of the torque piston measurement system is monitored to detect when the torque piston measurement system is outside of an operating range. A synthesized torque of the turboprop engine is determined based on one or more actual engine operating parameters of the turboprop engine. In response to detecting that the torque piston measurement system is outside of the operating range, the synthesized torque is displayed in the cockpit of the aircraft.

Methods, systems, and assemblies for operating an aircraft having a turboprop engine are described. The method comprises obtaining a measured torque of the turboprop engine from a mechanical torque piston measurement system and displaying the measured torque in a cockpit of the aircraft. During operation of the turboprop engine, a torque measurement saturation condition of the torque piston measurement system is monitored to detect when the torque piston measurement system is outside of an operating range. A synthesized torque of the turboprop engine is determined based on one or more actual engine operating parameters of the turboprop engine. In response to detecting that the torque piston measurement system is outside of the operating range, the synthesized torque is displayed in the cockpit of the aircraft.

In an aspect, a system includes a plurality of propulsors connected to an aircraft. Each propulsor of the plurality of propulsors is configured to operate independently from one another. A system includes a fuselage of an aircraft. A fuselage is configured to include a protective barrier and a height greater than the plurality of propulsors. A system includes a plurality of electric motors configured to adjust a torque of each propulsor of the plurality of propulsors. A system includes a computing device configured to detect a torque of each propulsor of the plurality of propulsors. A computing device is configured to determine a flight maneuver. A computing device is configured to adjust a property of each propulsor of the plurality of propulsors using the plurality of electric motors as a function of the detected torque.

In an aspect, a system includes a plurality of propulsors connected to an aircraft. Each propulsor of the plurality of propulsors is configured to operate independently from one another. A system includes a fuselage of an aircraft. A fuselage is configured to include a protective barrier and a height greater than the plurality of propulsors. A system includes a plurality of electric motors configured to adjust a torque of each propulsor of the plurality of propulsors. A system includes a computing device configured to detect a torque of each propulsor of the plurality of propulsors. A computing device is configured to determine a flight maneuver. A computing device is configured to adjust a property of each propulsor of the plurality of propulsors using the plurality of electric motors as a function of the detected torque.

Systems and methods according to embodiments of the present technology vary engine throttle and flight control surfaces (such as high-lift devices, which can include flaps and/or slats) during takeoff, climb, approach, and/or landing of a supersonic aircraft to reduce noise. A representative computing device automatically controls thrust output of the propulsion system according to a schedule of thrust output, such that the thrust output remains below levels at which the jet exhaust becomes supersonic, and such that noise is reduced to comply with noise regulations or other limitations. The computing device also automatically controls the position and configuration of flight control surfaces to compensate for the reduced thrust and to maintain an appropriate climb and/or descent rate.

Systems and methods according to embodiments of the present technology vary engine throttle and flight control surfaces (such as high-lift devices, which can include flaps and/or slats) during takeoff, climb, approach, and/or landing of a supersonic aircraft to reduce noise. A representative computing device automatically controls thrust output of the propulsion system according to a schedule of thrust output, such that the thrust output remains below levels at which the jet exhaust becomes supersonic, and such that noise is reduced to comply with noise regulations or other limitations. The computing device also automatically controls the position and configuration of flight control surfaces to compensate for the reduced thrust and to maintain an appropriate climb and/or descent rate.

An electric aircraft having fixed pitch lift includes a plurality of flight components, wherein the plurality of flight components further comprises at least a lift propulsor component, wherein the lift propulsor component comprises a plurality of blades configured at an angle of attack, and a flight controller, wherein the flight controller is configured to calculate a flight element using an intermediate representation, and transmit the flight element to the plurality of flight components.

This disclosure describes an unmanned aerial vehicle that may be configured during flight to optimize for agility or efficiency.

This disclosure describes an unmanned aerial vehicle that may be configured during flight to optimize for agility or efficiency.