Abstract:
An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle.
Abstract:
An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle.
Abstract:
A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.
Abstract:
A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.
Abstract:
An unmanned air vehicle (“UAV”) apparatus is configured to have a body and a body-conformal wing. The body-conformal wing is configured to variably sweep from a closed position to a fully deployed position. In the closed position, the body-conformal wing span is aligned with the body axis and in the fully deployed position the body-conformal wing span is perpendicular to the axial direction of the body. Delivery of the UAV comprises the steps of: positioning the span of a body conformal wing in alignment with the axis of the body of the UAV; initiating the flight of the UAV; and adjusting the sweep angle of the body-conformal wing as a function of the current speed, altitude, or attack angle of the UAV, with the adjustment starting at a 0 degree position and varying between a closed position and a fully deployed position. The UAV also has a control mechanism configured to variably adjust the sweep of the body-conformal wing to achieve a high lift over drag ratio through out the flight path of the UAV.
Abstract:
A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.
Abstract:
A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.
Abstract:
A law enforcement drone system is provided. The system features an unmanned aerial vehicle, having a wireless transceiver, an airframe, a propulsion system, a navigation mechanism, a processor, a memory, a power source, and at least one fuel tank. The system also features a control system having a wireless transceiver, an input device, capable of receiving a user's input and converting the user's input to electrical signals, a processor, and a memory. The control system is in wireless communication with the vehicle such that the control system is capable of utilizing the propulsion system in substantially real-time.
Abstract:
The present invention provides an Unmanned Aircraft System, including an integrated unmanned aerial vehicle and all related components and subsystems that can be packaged and transported as a kit, and customized to fit desired mission profiles, and easily repaired by replacement of damaged components or subsystems. The present invention further provides unmanned aircraft system components and subsystems that facilitate low power and low noise operation, and extended flight times.