Abstract: Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.

Abstract: Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.

Abstract: An apparatus for controlling the formation flight of a trailing aircraft relative to a vortex generated by a leading aircraft includes a position module, peak-seeking module, limiter module, and control module. The position module is configured to determine a position of the vortex relative to the trailing aircraft. The peak-seeking module is configured to determine a desired position of the trailing aircraft for providing desired vortex-induced aerodynamic benefits based on the position of the vortex relative to the trailing aircraft and a mapping function of an individual performance metric. The limiter module is configured to modify the desired position of the trailing aircraft to avoid unintended crossings of the trailing aircraft into the vortex. Finally, the control module is configured to control flight of the trailing aircraft based on one of the desired position of the trailing aircraft and modified desired position of the trailing aircraft.

Abstract: An aircraft system may include an airfoil and a deployable device coupled to the airfoil. The system may further include a shape memory alloy actuator coupled between the airfoil and the deployable device. The actuator may be movable between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. The system may additionally include an activatable link positioned between the actuator and the deployable device. The link may have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device.

Abstract: A transponder module for vehicles. The module has a substantially universal vehicle sensor input interface capable of receiving sensor input from different types of vehicle sensors and from different types of vehicles. One or more processors and memory, in real time, receive vehicle sensor input data via the input interface. Based on a vehicle type stored in the memory, the processor(s) use the sensor input data to determine conditions of subsystems the vehicle. Based on the determined conditions, the processor(s) determine performance capabilities of the vehicle. The transponder module outputs information as to the stored vehicle type, determined conditions, and vehicle performance capabilities.

Abstract: Representing vehicles in a customizable virtual environment is disclosed. One embodiment includes a controlled environment including prototype vehicles and a virtual environment including virtual representations of the prototype vehicles. The virtual environment is a display that includes an environment scenario, a number of virtual objects, and the various represented vehicles. The represented vehicles are linked to the prototype vehicles by communicating kinematic data from the prototype vehicles to the virtual vehicles real-time. The positions of the represented vehicles are updated based on the communicated kinematic data such that the virtual environment is a realistic visualization of the prototype vehicles. In addition, the virtual environment is highly customizable.

Abstract: An aircraft system may include an airfoil and a deployable device coupled to the airfoil. The system may further include a shape memory alloy actuator coupled between the airfoil and the deployable device. The actuator may be movable between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. The system may additionally include an activatable link positioned between the actuator and the deployable device. The link may have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device.

Abstract: Aircraft systems with shape memory alloy (SMA) actuators, and associated methods are disclosed. A system in accordance with one embodiment includes an airfoil, a deployable device coupled to the airfoil, and a shape memory alloy actuator coupled between the airfoil and the deployable device. In one embodiment, the deployable device can be coupled to the airfoil with a hinge having a hinge load path supporting the deployable device relative to the airfoil, and the actuator can be movable along a motion path different than the hinge load path between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil.

Abstract: Systems and methods for development testing of vehicles and components are disclosed. In one embodiment, a system includes a position reference system and a command and control architecture. The position reference system is configured to repetitively measure one or more position and motion characteristics of one or more vehicles operating within a control volume. The command and control architecture is configured to receive the repetitively measured characteristics from the position reference system, and to determine corresponding control signals based thereon. The control signals are then transmitted to the one or more vehicles to control at least one of position, movement, and stabilization of the one or more vehicles in a closed-loop feedback manner. The system may further include a health monitoring component configured to monitor health conditions of the one or more vehicles, the control signals being determined at least in part on the health conditions.

Abstract: A transponder module for vehicles. The module has a substantially universal vehicle sensor input interface capable of receiving sensor input from different types of vehicle sensors and from different types of vehicles. One or more processors and memory, in real time, receive vehicle sensor input data via the input interface. Based on a vehicle type stored in the memory, the processor(s) use the sensor input data to determine conditions of subsystems the vehicle. Based on the determined conditions, the processor(s) determine performance capabilities of the vehicle. The transponder module outputs information as to the stored vehicle type, determined conditions, and vehicle performance capabilities.

Abstract: This disclosure is directed to methods, computer-readable media, and systems for controlling one or more uninhabited heterogeneous autonomous transport devices. Embodiments of the present invention advantageously reduce costs and improve efficiencies by providing capabilities for a computing device to be able to control and to monitor one or more heterogeneous autonomous transport devices. This occurs by generating a command signal from a computing device and transmitting the command signal to control on-board computing devices of one or more heterogeneous transport devices to execute requirements of a mission. Also, embodiments of the present invention provide ways to start-up, to send commands, and to shut down real or simulated heterogeneous autonomous transport devices.

Abstract: Representing vehicles in a customizable virtual environment is disclosed. One embodiment includes a controlled environment including prototype vehicles and a virtual environment including virtual representations of the prototype vehicles. The virtual environment is a display that includes an environment scenario, a number of virtual objects, and the various represented vehicles. The represented vehicles are linked to the prototype vehicles by communicating kinematic data from the prototype vehicles to the virtual vehicles real-time. The positions of the represented vehicles are updated based on the communicated kinematic data such that the virtual environment is a realistic visualization of the prototype vehicles. In addition, the virtual environment is highly customizable.

Abstract: Aircraft systems with shape memory alloy (SMA) actuators, and associated methods are disclosed. A system in accordance with one embodiment includes an airfoil, a deployable device coupled to the airfoil, and a shape memory alloy actuator coupled between the airfoil and the deployable device. In one embodiment, the deployable device can be coupled to the airfoil with a hinge having a hinge load path supporting the deployable device relative to the airfoil, and the actuator can be movable along a motion path different than the hinge load path between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil.

Abstract: Improved miniature trailing edge effectors for aerodynamic control are provided. Three types of devices having aerodynamic housings integrated to the trailing edge of an aerodynamic shape are presented, which vary in details of how the control surface can move. A bucket type device has a control surface which is the back part of a C-shaped member having two arms connected by the back section. The C-shaped section is attached to a housing at the ends of the arms, and is rotatable about an axis parallel to the wing trailing edge to provide up, down and neutral states. A flip-up type device has a control surface which rotates about an axis parallel to the wing trailing edge to provide up, down, neutral and brake states. A rotating type device has a control surface which rotates about an axis parallel to the chord line to provide up, down and neutral states.

Abstract: Systems and methods for development testing of vehicles and components are disclosed. In one embodiment, a system includes a position reference system and a command and control architecture. The position reference system is configured to repetitively measure one or more position and motion characteristics of one or more vehicles operating within a control volume. The command and control architecture is configured to receive the repetitively measured characteristics from the position reference system, and to determine corresponding control signals based thereon. The control signals are then transmitted to the one or more vehicles to control at least one of position, movement, and stabilization of the one or more vehicles in a closed-loop feedback manner. The system may further include a health monitoring component configured to monitor health conditions of the one or more vehicles, the control signals being determined at least in part on the health conditions.