The present disclosure relates to systems, methods, and computer readable media implemented in connection with an unmanned aerial vehicle (UAV) to navigate a UAV along a desired path. For example, systems disclosed herein identify an anticipatory flight path and identify a plurality of reference points on the flight path relative to a current position of the UAV. The systems described herein may further determine reference angles between a current trajectory of the UAV and the reference points to determine an updated trajectory that the UAV should take to stay close to the identified flight path. The systems described herein may further cause the UAV to accelerate in a lateral direction based on the updated trajectory. The features and functionality of systems disclosed herein enable the UAV to accurately follow a complex path having sharp turns with little or no advanced knowledge of the flight path prior to departure.

Systems, devices, and methods for determining, by a processor, an unmanned aerial system position relative to at least one flight boundary; and effecting, by the processor, at least one flight limitation of a flight limiting device if the determined unmanned aerial system position crosses the at least one flight boundary.

Systems and methods of aircraft modal suppression informed by an underlying non-uniform vertical turbulence model and uniform lateral turbulence model. The systems and methods include receiving a plurality of signals from on-board inertial sensors of an aircraft, utilizing the plurality of signals to generate a plurality of observers, utilizing the observers to determine a control law command for controlling one or more control surfaces of the aircraft, and moving the one or more control surfaces of the aircraft in accordance with the determined control law command such that lateral mode vibrations of the aircraft are diminished.

A method for optimizing a climb phase of an aircraft, implemented repeatedly during the climb phase, includes an acquiring step for acquiring current values of input parameters, a determining step for determining a current optimized DT.sub.flex value from the current values of the input parameters and from optimized DT.sub.flex values recorded in a database and a transmitting step for transmitting the determined current optimized DT.sub.flex value to a user system with a view to controlling the thrust of the aircraft, the method making it possible to continuously adapt, during the climb phase, the optimized DT.sub.flex value so it corresponds to current conditions of the aircraft to maximize its performance particular for fuel consumption.

A re-usable intercept drone (104) comprises an elongate fuselage (200), a first wing (202) and a second wing (206) operably coupled to the elongate fuselage (200) and extending substantially away from the elongate fuselage (200). A first propulsion unit (210) and a second propulsion unit (212) are operably coupled to the first wing (202) and the second wing (206), respectively. A third propulsion unit (214) and a fourth propulsion unit (218) are operably coupled to the fuselage (200). The first, second, third and fourth propulsion units (210, 212, 214, 218) are circumferentially spaced about the elongate fuselage (200).

Autonomous systems increase the robustness and safety of current aircraft and to support simplified vehicle, reduced crew, and single pilot operations. The autonomous systems aid air crews in their handling of non-normal, high workload, aircraft upset scenarios. The upset scenarios include the recovery from attitudes outside of the normal operating envelope that even the most robust automatic flight control systems currently in service today do not support.

An electromechanically steered passive directional arrays and ESA antenna with the rectangular apertures' mathematically separable radiation pattern array lattice rotated to rotate the higher cardinal plane side lobes to 45 relative to the vertical plane. Rotation minimizes clutter returns that mask weaker power returns and generates larger mean side lobe path loss. The higher sidelobe power levels are directed away from the critical area along the runway during approach. Individual array elements may be counter rotated to maintain desired antenna polarization state.

A method for guiding an autonomous aircraft, the aircraft includes an automatic pilot, a plurality of sensors and an imaging unit, the aircraft being configured to fly over a geographic zone comprising overflight prohibited zones, the guidance method can advantageously comprise a phase of real flight of the autonomous aircraft by using a given guidance law, comprising the following steps: determining a current state of the autonomous aircraft; determining an optimum action to be executed by using a neural network receiving the current state; determining a plurality of control instructions compatible with the guidance law based on the optimum action to be executed; transmitting to the automatic pilot the plurality of control instructions, which provides a new state of the autonomous aircraft.

A distributed sensor network includes a first plurality of cooperatively acting unmanned autonomous vehicles, UAVs, spatially distributed to create a domain exclusion zone, DEZ. Each of the UAVs includes one or more first sensors configured to gather detection signals from any object entering the DEZ, a signal processor connected to the one or more first sensors and configured to process the detection signals gathered by the one or more first sensors, to perform object classification, discrimination, and identification, CDI, algorithms on the detection signals, and to output a CDI signal related to the object, and one or more communication modules coupled to the signal processor and configured to transmit the CDI signal to other UAVs in the first plurality of cooperatively acting UAVs.

Systems and methods are provided for promoting stable aircraft approach conditions. The system comprises a display device that is onboard an aircraft and a controller in communication with the display device. The controller is configured to, by a processor: receive data that includes information relating to an action configured to stabilize an approach of the aircraft during landing thereof and a recommended timing of performing the action relative to a predetermined flight plan of the aircraft, and render a first visual element on the display device that is configured to display the action relative to the flight plan and dynamically indicate the recommended timing of performing the action relative to a geographic position of the aircraft along the flight plan.