Abstract: An aircraft control unit has modules for interfacing with various systems of an aircraft to integrate control of the systems. The modules include a communication module configured to be coupled to a communication system of the aircraft and a surveillance module configured to be coupled to a surveillance system of the aircraft. The aircraft control unit also includes a display screen for displaying information and a user interface usable to interact with the modules. Each of the modules is configured to display information on the display screen and to receive user input from the user interface.

Abstract: A vehicle control system and related sub-components together provide an operator with a plurality of specific modes of operation. The various modes of operation incorporate different levels of autonomous control. Through a control user interface, an operator can move between certain modes of control even after vehicle deployment. Specialized autopilot system components and methods are employed to ensure smooth transitions between control modes. Empowered by the multi-modal control system, an operator can manage multiple vehicles simultaneously.

Abstract: A method of determining variations in operating characteristics of a mechanical system having a rotatory mode of operation and bearing balls entrained within a bearing balls recirculation system. There are provided the steps of first monitoring operating impulses generated by the mechanical system during a first interval of operation; first analyzing the operating impulses obtained during the first interval to determine the intensity and frequency of the operating impulses; first correlating the operating impulses obtained during the first interval to corresponding angular positions of the rotatory mode of operation; and first producing a first record of the intensity and frequency of the operating impulses obtained during the first interval correlated to the corresponding angular positions of the mechanical system.

Abstract: The invention relates to a method for assisting the piloting of an aircraft in the vicinity of a landing or takeoff point, by: determining the locus of entry and/or exit points for a given approach and/or departure altitude that are not safe for reaching the landing and/or takeoff point; and presenting a diagram including said locus on a display device.

Abstract: The difference between a first position of a first pylon of a tiltrotor aircraft and a second position of a second pylon of the aircraft is prevented from becoming too large. An actuator position error for the first pylon is calculated from a difference between the first position and a commanded first position of the first pylon. An actuator position error for the second pylon is calculated from a difference between the second position and a commanded second position of the second pylon. An absolute value of the actuator position error for the first pylon is compared to the preset limit. If the absolute value of the actuator position error for the first pylon is greater than or equal to a preset limit, the actuator position error for the second pylon is calculated from the difference between the first position and the second position.

Abstract: This disclosure involves aerial robots that dispenses conductive filament or systems, methods, and software for support such aerial robots. One remotely powered aerial robot system includes an aerial robot and a power source. The aerial robot comprises a body, a first propeller coupled to the body and operable to provide thrust to the aerial robot, a rotatable spool coupled to the body, and a conductive filament that is dispensed from the spool by rotation of the spool is one direction and retrieved by rotation of the spool in another direction. The power source is coupled with, and remote from, the aerial robot via the conductive filament, where the conductive filament is operable to power the first propeller using power from the power source.

Abstract: The invention relates generally to the control and landing of unmanned aerial vehicles. More specifically, the invention relates to systems, methods, devices, and computer readable media for landing unmanned aerial vehicles using sensor input and image processing techniques.

Abstract: An airborne processor is linked to a ground-based, vehicle based, or satellite-based supplier of approaching aircraft data and/or terrain data, including airfield structures. The processor also has access to the aircraft's state, e.g. position, speed, intended route, aircraft dimensional data, or the like. Algorithms within the processor calculate a zone of protection about the aircraft in light of aircraft type, turning radius, and other identifying data. The processor combines the present and estimated future positions of the aircraft with the approaching aircraft and/or airfield structure data, and creates an alert to the crew if a threat of a ground incursion is detected. The display provides a visual of the zone of protection about the aircraft, and approaching aircraft and/or airfield structure to draw the attention of the crew to the threat.

Abstract: Systems and methods for controlling activation of a look-ahead function of a terrain alert and warning system. The system receives rate of climb and aircraft speed information, compares the rate of climb and aircraft speed information to a predefined threshold, and deactivates a look-ahead function based on the comparison.

Abstract: An Auxiliary Power System includes an APU controller and an aircraft load controller which include an APU load capacity algorithm which provides an uncomplicated and robust method of APU load control. The APU load capacity algorithm defines three load zones: a continuous APU load capacity zone (zone A); a time controlled zone (zone B); and a fault zone (zone C). Each zone is related to altitude to the service ceiling of the APU to provides consistent APU load capacity that addresses APU performance variation and deterioration effects to an end of the APU useful life.

Abstract: An airborne mobile platform may have a wing having a length and a chord wise dimension, and a plurality of elongated structural components extending span-wise along the length of the wing. The elongated structural components may each have a localized hinge area. A device may be used for manipulating the elongated structural component to position the localized hinge area to selectively change a hinge line of the wing in response to an airflow over the wing.

Abstract: A fluid dynamically effective surface of a device moving in a fluid, especially a lifting surface of a flying machine, has an elastic axis extending in the span direction of the surface, and an adjustable control surface. The lifting surface is elastically deformable in a bending direction and/or in a torsion direction about the elastic axis, due to and dependent on the adjustment of the control surface, while changing the induced fluid dynamic drag. A control and/or regulating arrangement is provided for adjusting the control surface in the sense of minimizing the induced fluid dynamic drag of the lifting surface.

Abstract: An aircraft structure comprising: a rear spar; and a composite cover attached to the rear spar and having an overhanging portion extending to its rear. The overhanging portion of the cover comprises one or more ramps along which the thickness of the cover reduces. A second cover is attached to the rear spar and overhangs to its rear. A hinge rib is attached to one or both of the covers, and an aerodynamic control element such as an aileron, rudder or elevator is pivotally mounted to the hinge rib.

Abstract: An embodiment of an aircraft wing includes a main wing section and a variable incidence wing tip. The main wing section is adapted to connect to an aircraft fuselage at a first angle of incidence. The variable incidence wing tip is connected to the main wing section so that the variable incidence wing tip is rotatable to angles of incidence that are different from the first angle of incidence. An embodiment of a method for operating an aircraft includes generating a control signal based on an indication of a desired angle of incidence of a variable incidence wing tip, conveying the control signal to a wing tip rotation mechanism, and rotating the variable incidence wing tip in accordance with the control signal, so that the angle of incidence of the variable incidence wing tip is different from an angle of incidence of the main wing section.

Abstract: A system and a method for adjusting and locking a control surface that is movably arranged on a wind-tunnel aircraft model and comprises a drive arrangement for driving the control surface, and a locking arrangement. The drive arrangement comprises a first drive motor, arranged in a fixed manner relative to the control surface, at least one first connecting rod eccentrically connectable to the first drive motor, and at least one lever, whose one end can be held on the first connecting rod and whose other end can be held on a fixed point of the aircraft model. The locking arrangement can be attached in a fixed manner relative to the control surface and is further designed to block a relative movement between the control surface and the aircraft model.

Abstract: The present invention relates to an autopilot system for a rotary wing aircraft operating relative to at least two pilot axes, which system comprises, for each of the two axes, at least one servo-control relationship providing a respective initial control instruction, with the two relationships having a common target; the system includes combination means (36) for providing a series of control instructions by combining the two initial control instructions (UCV, UTV).

Abstract: An aircraft flight control surface actuation system includes a plurality of electric motors-driven flap actuators, and a plurality of electric motor-driven slat actuators. The motor-driven actuators receive activation signals from flap and slat actuator controllers and is, in response to the activation signals, move the flaps and slats between stowed and a deployed positions. The flap and slat actuator controllers each include a plurality of independent actuator control channels that independently supply the activation signals to the motor-driven actuators.

Abstract: Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.

Abstract: A rotary-wing aircraft with an electric motor mounted along an axis of rotation to drive a rotor system about the axis of rotation.

Abstract: A small, reusable interceptor unmanned air vehicle (UAV), an avionics control system for the UAV, a design method for the UAV and a method for controlling the UAV, for interdiction of small scale air, water and ground threats. The UAV includes a high performance airframe with integrated weapon and avionics platforms. Design of the UAV first involves the selection of a suitable weapon, then the design of the interceptor airframe to achieve weapon aiming via airframe maneuvering. The UAV utilizes an avionics control system that is vehicle-centric and, as such, provides for a high degree of autonomous control of the UAV. A situational awareness processor has access to a suite of disparate sensors that provide data for intelligently (autonomously) carrying out various mission scenarios. A flight control processor operationally integrated with the situational awareness processor includes a pilot controller and an autopilot controller for flying and maneuvering the UAV.

Abstract: An objective of the invention, focusing on these issues involved in the use of a small, hobby-type, unmanned helicopter, is to develop an autonomous control system comprising autonomous control systems for a small unmanned helicopter, to be mounted on said small unmanned helicopter; a servo pulse mixing/switching unit; a radio-controlled pulse generator; and autonomous control algorithms that are appropriate for the autonomous control of the aforementioned small unmanned helicopter, thereby providing an autonomous control system that provides autonomous control on the helicopter toward target values.

Abstract: Methods and apparatus for deploying control surfaces generally comprise a fin deployment system for projectiles. The fin deployment system is used to control the timing of the control surface deployment. In one embodiment, the deployment system comprises a clip that is configured to react the biasing force of one control surface against another in order to maintain the control surfaces in a non-deployed state until at least one control surface is able to overcome the retention force of the clip, thus beginning a chain reaction in which all of the control surfaces deploy sequentially.

Abstract: A system and method to provide extensibility to an existing vehicular control network. To provide such extensibility, an information layer network incorporating a protocol such as an Ethernet protocol in which additional peripheral devices may be easily coupled thereto or additional software applications providing enhanced functionality. Interfacing of the information layer to the vehicular control network is accomplished via an Information layer interface mechanism that translates signals from those compliant to the vehicular control network to those compliant with the information layer. Additionally, means are disclosed to provide for momentary control over one or more peripheral devices that are coupled to the vehicular control network via peripheral devices that are coupled to the information layer.

Abstract: An aerial robot is disclosed. The aerial robot may include at least one pair of counter-rotating blades or propellers, which may be contained within a circumferential shroud or a duct. In one embodiment, the aerial robot may have the ability to hover and move indefinitely. Electric power to the robot may be provided by a tether or an on-board power supply. In tethered embodiments, a solid-state, electronic voltage transformer may be used to reduce a high voltage, low current source to lower voltage, higher current source. In one embodiment, secure data communication between a ground unit and the aerial robot is facilitated by impressing high bandwidth serial data onto the high voltage tether wires or a thin optical fiber which is co-aligned with the tether wires. In one embodiment, precise navigational and position controls, even under extreme wind loads, are facilitated by an on-board GPS unit and optical digital signal processors.

Abstract: This onboard flight management system displays on the navigation screen the plots of the flight plan parts corresponding to the navigation procedures whose names are displayed on the MCD console during the introduction by the crew of the aircraft, by means of the MCD console, of the elements allowing the FMS flight management computer to plot a flight plan. This facilitates the task of the crew when choosing navigation procedure since the plot of the flight plan part corresponding to a navigation procedure is much more expressive than the name of the procedure.

Abstract: Methods and systems for linking input control signals, such as control signals used to control aspects of aircraft operation. In one embodiment, the method includes receiving first and second force signals corresponding to first and second forces applied to first and second controllers. The method can further include directing first and second position signals to the first and second controllers to move the first and second controllers to approximately the same positions. Each force signal is transmitted along a signal path, and the signal paths can be linked at a point where the signals on each path correspond to a quantity other that a position of a controller. The signal paths can be linked such that only one of the forces must exceed a threshold value for both controllers to be moved, and if one of the forces is outside a selected limit range, that force can be at least partially discounted.

Abstract: There is described a rotary wing aircraft comprising a fuselage (5), a main rotor (3) rotatable e in a main rotor plane relative to the fuselage for supporting the aircraft in flight, and a plurality of control thrusters (7) each operable to provide a thrust force acting in a tangential direction relative to the main rotor and in a plane parallel to and spaced from the main rotor plane. The plurality of control thrusters may comprise a pair of oppositely directed thrusters, the pair being mounted for selective rotation relative to the fuselage about the main rotor axis. Alternatively and preferably, the plurality of thrusters may comprise three or more thrusters spaced in the circumferential direction of the main rotor. There is also described a tilt-rotor aircraft in which such an array of thrusters is provided for lateral control in hovering flight, and directional control in forward flight.

Abstract: A method for operating an aircraft includes the steps of receiving guidance instructions and guidance parameters at a navigation computer, and transmitting automatic pilot instructions from the navigation computer to a flight control computer. The method also includes the steps of receiving control instructions and the automatic pilot instructions at the flight control computer, and generating operating commands at the flight control computer. In an automatic pilot mode, the operating commands are generated at the flight control computer based on the automatic pilot instructions.

Abstract: A method of braked pivot turning an aircraft, the aircraft comprising a fuselage and a landing gear assembly located to one side thereof. The landing gear comprises a bogie with wheels mounted thereon, at least one wheel being located on a first side of the bogie and at least one wheel being located on a second side of the bogie. The method includes the steps of applying thrust (7?) for moving or turning the aircraft, and via the braking of at least one wheel, applying a greater braking force to the first side of the bogie than to the second side. The first side is located closer to the centre of turning of the aircraft than the second side. The method thereby generates relatively low torque loads in the landing gear leg, reducing fatigue damage. A brake control system is also provided for selectively braking wheels during a turn.

Abstract: This invention relates to the concept of managing the rate of change of energy in a helicopter or other aeronautical vehicle. The invention uses energy management calculations to determine the maximum longitudinal and lateral inputs that can be made while still enabling the vehicle to maintain a desired vertical state. The results of the calculations can be cued to the pilot either tactilely, aurally, or visually, or used for internal software limiting.

Abstract: The present invention provides a practical method for UAVs to take advantage of thermals in a manner similar to piloted aircrafts and soaring birds. In general, the invention is a method for a UAV to autonomously locate a thermal and be guided to the thermal to greatly improve range and endurance of the aircraft.

Abstract: A method and system for providing a bearing from a vehicle to a transmitting station are described. The method includes accessing a database to obtain transmitter position information for the transmitter, obtaining vehicle position information based on a GPS signal, and generating the bearing from the vehicle to the station utilizing the transmitter position information and the vehicle position information. The system includes a database storing transmitter position information identifying a position of the transmitter, a GPS receiver obtaining vehicle position information identifying a current position of the vehicle based on a GPS signal, and a controller generating a bearing from the vehicle to the transmitter utilizing the transmitter position information and the vehicle position information.

Abstract: This invention provide systems and methods for cockpit flight crew preflight planning and subsequent, systematic recall and execution of procedures, ground/inflight navigation, and communications using portable electronic data storage and display devices. A capability is provided within a portable electronic data storage and display device to replace and replicate the typical preflight planning methodology of the individual flight crew member to facilitate execution of a procedures, navigation and communications plan from preflight to postflight. A user may create a usable subset of the potentially thousands of available pages of data or data reference pages stored in the portable electronic data storage and display device, organizing the perhaps 100 or less individual pages of data, static or interactive, desired for a specific leg of the flight in order that required information is immediately available in an expected order of need.

Abstract: A yaw control system and a method of controlling yaw for an aircraft are provided. The yaw control system includes a first wing set and a second wing set which are rotatable in opposite directions. Each of the wing sets includes at least two wings each including a pivotable flap forming a trailing edge of its respective wing. A flap control assembly controls the pivotable flaps of the first wing set and of the second wing set such that when the pivotable flaps of the first wing set are pivoted in a first direction by a first set angle, the pivotable flaps of the second wing set are simultaneously pivoted by a second set angle in an opposite direction, thereby providing yaw control for the aircraft.

Abstract: The device (1) comprises a set (3) of information sources, an information processing unit (4), a display means (6) comprising a display screen (8), and a configuration means (9) allowing an operator to configure said device (1), according to one of the three configuration states, a first configuration state, for which the display means (6) presents aircraft piloting information, a second configuration state, for which the display means (6) presents aircraft navigation information, and a third configuration state, for which the display means (6) presents both piloting information and navigation information.

Abstract: An aircraft performance degradation detection system may include information sources, a central unit connected to the information sources, and a warning device that is connected to the central unit. Using information received from the information sources, the central unit computes the current weight and drag of the aircraft and computes a theoretical drag based on the current weight. The current and theoretical drags are compared, and a determination is made regarding performance degradation based on the comparison.

Abstract: A flight control system for use in flight apparatus wherein the motors are capable of movement in more than one plane with respect to the support member in response to movement of the control member is disclosed herein. Further, a flight apparatus, aircraft, spacecraft, and personal flight means, having motors that are moveably attached to the flight apparatus such that the motors are capable of movement in more than one plane with respect to the body of the flight apparatus is disclosed.

Abstract: A control system for an aircraft includes an actuation section that moves lift-enhancing devices as a function of received control orders, a control member operable by a pilot of the aircraft, and a control unit that includes a control section that produces control orders, as a function of actuation of the control member, so as to control the actuation section to bring the lift-enhancing devices into a predetermined position. The control unit further includes a device that produces automatically auxiliary control orders which are transmitted to the actuation section to automatically retract the lift-enhancing devices when the aircraft is in a first flight condition and another device that automatically disables control orders produced by the control section following actuation of the control member to deploy the lift-enhancing devices when the aircraft is in a second flight condition.

Abstract: A method of determining variations in operating characteristics of a mechanical system having a rotatory mode of operation. There are provided the steps of first monitoring operating impulses generated by the mechanical system during a first interval of operation; first analyzing the operating impulses obtained during the first interval to determine the intensity and frequency of the operating impulses; first correlating the operating impulses obtained during the first interval to corresponding angular positions of the rotatory mode of operation; and first producing a first record of the intensity and frequency of the operating impulses obtained during the first interval correlated to the corresponding angular positions of the mechanical system.

Abstract: A system includes a computer server for receiving an aircraft dataset; a database operably coupled to the computer server for storing the aircraft dataset into data fields; a web portal operably coupled to the computer server and the database for providing real-time access to consumers; and a maintenance analysis engine coupled to the computer server, the database, and the web portal to process the aircraft dataset into informational reports for an automatic delivery to the consumers, and optionally issuing a notification for retrieval thereof.

Abstract: A safe interactive navigation apparatus and method allows the crew of an aircraft to prepare and follow a safe flight plan without relying on instrument flying infrastructure. An aircraft navigation assistance method calculates a continuous, three-dimensional projected path on board the aircraft as a function of data related to the route and characteristics of the aircraft.

Abstract: Embodiments are disclosed for a vehicle control system and related sub-components that together provide an operator with a plurality of specific modes of operation, wherein various modes of operation incorporate different levels of autonomous control. Through a control user interface, an operator can move between certain modes of control even after vehicle deployment. Specialized autopilot system components and methods are employed to ensure smooth transitions between control modes. Empowered by the multi-modal control system, an operator can even manage multiple vehicles simultaneously.

Abstract: A system and method for providing autonomous control of unmanned aerial vehicles (UAVs) is disclosed. The system includes a ground station in communication with an unmanned aerial vehicle. The method for providing autonomous control of a UAV includes methods for processing communications between the ground station and UAV. The method also includes procedures for processing commands from the ground station. Also included in the method is a process for estimating the attitude of the UAV and autonomously maintaining its altitude within a desired threshold. The method also includes a process for autonomously orbiting about a specified point in space. Combined with these processes, the method also includes a process for an autonomous takeoff and landing of the UAV.

Abstract: An aircraft takeoff process may include applying a pitch command deflecting an adjustable horizontal tailplane of the aircraft by a predetermined angle. Thereafter, the pitch command is corrected in accordance with the deviation between a takeoff rotation speed and a stall reference speed VRref of the aircraft.

Abstract: Process for reducing the aerodynamic loads applied to the elevators of an aircraft during takeoff wherein, prior to the rotation, the adjustable horizontal tailplane (2) is nose-up overdeflected and the elevators (4) are nose-down deflected.

Abstract: A method and device for controlling the attitude of an aircraft may employ spoilers that are arranged on the wings of the aircraft and whose respective angular positions can be adjusted by controllable actuators. A command attitude determining section determines a command attitude of the aircraft corresponding to an attitude that the aircraft must achieve. A command position calculator calculates command positions of the spoilers, corresponding to particular angular positions of the spoilers, making it possible to bring the aircraft to the command attitude. A control instruction calculator calculates control instructions for the controllable actuators, making it possible to bring the spoilers into the command positions, and applies the control instructions to the spoiler actuators.

Abstract: A method and device for detecting pilot induced oscillations in an aircraft may detect signals having frequencies of between 0.3 Hz and 0.6 Hz within commands signals generated by a pilot for controlling an aerodynamic surface of the aircraft. The energy of the detected signals is analyzed to determine whether significant pilot induced oscillations are present within the command signals, and an indication of the degree of the oscillations is generated for use by the pilot.

Abstract: Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced signals are processed through control logic which, in response thereto, and in response to aircraft inertial, velocity and altitude related signals produces output control signals. The control signals effect control surface deployment creating forces to suppress the natural mode induced vibrations on multiple geometric axis's. More particularly, a symmetric and anti-symmetric control surface deployments are used on one or more geometric axis'to damp lateral, longitudinal, vertical and most importantly torsional vibrational modes.

Abstract: Methods and apparatuses for displaying and receiving tactical and strategic flight guidance information. A method in accordance with one aspect of the invention includes displaying at least one first indicator to an operator of the aircraft, with a first indicator corresponding to a first instruction input by the operator for directing a first aircraft behavior and implemented upon receiving an activation instruction from the operator. At least one second indicator corresponding to a second instruction for directing a second aircraft behavior at least proximately the same as the first aircraft behavior is displayed, with the at least one second instruction to be automatically implemented at a future time. The at least one second indicator is at least approximately the same as the at least one first indicator. Indicators can be hierarchically organized to simplify presentation and reduce pilot training time.

Abstract: Side-slip of an aircraft during flight is detected through a pair of pressure sensors fixedly mounted on opposite lateral sides of the aircraft fuselage. Pressure measurement signals at said sensors are fed to electronic circuitry within the aircraft for generating magnitude and frequency signals reflective of the side-slip that are applied to a pair of vibrators respectively mounted on the undersides of a pair of pilot foot pedals located within the cockpit. The foot pedals are connected by linkage to the tail rudder on the aircraft fuselage. The varying magnitude and frequency of vibrations applied to the rudder foot pedals by the vibrators enables the pilot to immediately sense side-slip through the feet on the pedals. In response to such side-slip sensing, one of the pedals may be timely depressed for side-slip corrective angular displacement of the rudder.