| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244203000 | Condition responsive | 16 |
| 20080265102 | DEPLOYABLE FLAP EDGE FENCE - A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions. | 10-30-2008 |
| 20080296438 | Control surface actuation system - Systems for controlling flow effector control surfaces. The system comprises a flow effector control coupled to an elongated bar at one end of the bar. The elongated bar is coupled at the other end to the middle of a T-shaped member. A compliant link is coupled to the bar between the control surface and the T-shaped member. At each end of the T-shaped member is coupled a shape memory alloy wire which acts as an actuating means. When one of the shape memory alloy wire contracts, the elongated bar pivots about the compliant link and activates or retracts the flow effector control surface. | 12-04-2008 |
| 20090261205 | APPARATUS AND METHOD FOR CONTROLLING TWIST OF A WING OF AN AIRBORNE MOBILE PLATFORM - 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. | 10-22-2009 |
| 20110042524 | PASSIVE ADAPTIVE STRUCTURES - Morphing an aerodynamic body's geometry in situ can optimize its aerodynamic properties, increasing range, reducing fuel consumption, and improving many performance parameters. The aerodynamic load exerted on the body by the flow is one such parameter, typically characterized as lift or drag. It is the aim of the present disclosure to teach the use of passive adaptive morphing structures to manage these aerodynamic loads. | 02-24-2011 |
| 20110127384 | Flying vehicle - An aircraft includes a fuselage and takeoff and landing wings that are extended at takeoff and landing and serve as the main aerodynamic elements producing the lift. The takeoff and landing wings are in a retracted position in cruising flight to attain a minimum possible drag coefficient of the aircraft and, as a result, reduce fuel requirements in the cruising configuration significantly. When retracted, the takeoff and landing wings are integrated compactly into the fuselage surface. The retracted takeoff and landing wings are fixed in position by retracted position locks of the fuselage. A takeoff and landing wing has a turbine blade profile in cross-section. A takeoff and landing wing has longitudinal rows of slots simulating the operation of a slat and a two-slot flap. The slots are closed with shutters on the outer side of the wing. | 06-02-2011 |
| 20120261517 | Multi-Element Airfoil System - A multi-element airfoil system includes an airfoil element having a leading edge region and a skin element coupled to the airfoil element. A slat deployment system is coupled to the slat and the skin element, and is capable of deploying and retracting the slat and the skin element. The skin element substantially fills the lateral gap formed between the slat and the airfoil element when the slat is deployed. The system further includes an uncoupling device and a sensor to remove the skin element from the gap based on a critical angle-of-attack of the airfoil element. The system can alternatively comprise a trailing edge flap, where a skin element substantially fills the lateral gap between the flap and the trailing edge region of the airfoil element. In each case, the skin element fills a gap between the airfoil element and the deployed flap or slat to reduce airframe noise. | 10-18-2012 |
| 20120292452 | AIRCRAFT WING ASSEMBLY - An aircraft wing assembly, comprising: a fixed wing portion; a first and second flight control surfaces; a first and second actuators operatively coupled to the first and second flight control surfaces for moving respective first and second flight control surfaces with respect to the fixed wing portion; a control system operatively coupled to the first and second actuators for controlling movement of the first and second flight control surfaces; and a third actuator selectively engaged with the second flight control surface for engaging and moving the second flight control surface out of a path of movement of the first flight control surface only in the event of a failure in the second actuator or its control, so as to avoid direct contact between the first and second flight control surfaces. | 11-22-2012 |
| 20120312931 | FLAP ADJUSTING SYSTEM OF AN AIRCRAFT WITH A REGULATING FLAP - Embodiments pertain to a flap adjusting system including a regulating flap mounted on an airfoil using at least two bearing devices and movable relative to the airfoil, and an adjusting device. The adjusting device includes an actuator and adjusting kinematics with a drive rod that couples the actuator to the regulating flap using a first and a second joint, as well as a load sensor. The adjusting kinematics are configured such that, at a maximum adjustment travel of the regulating flap, the second joint between the drive rod and the regulating flap is adjusted by an angle less than 50% of the angle by which the first joint is adjusted. The load sensor is arranged in at least one adjusting device and in the second joint, which couples the drive rod to the regulating flap. The load sensor is configured to measure the forces in this load path. | 12-13-2012 |
| 20120318929 | AIRCRAFT WITH A REFUELING DEVICE AND METHOD FOR CONTROLLING THE FLIGHT PATH OF AN AIRCRAFT DURING ITS REFUELING - An aircraft with a refueling device for receiving fuel from a tanker aircraft in-flight is described, including an arrangement of flow influencing devices, an arrangement of flow condition sensor devices measuring flow conditions on respective surface segments, a flight data transmission device receiving flight data of a tanker aircraft, a flight path specification module that determines a nominal flight path or a nominal flight path corridor from the flight data of the flight data transmission device, and a flight control device configured to generate nominal commands for the flow influencing devices based on the measured flow condition and the nominal flight path or the nominal flight path corridor. These nominal commands control or maintain the movement of the aircraft along the nominal flight path or in the nominal flight path corridor. A method for controlling the flight path of an aircraft during the refueling thereof is also provided. | 12-20-2012 |
| 20120325976 | SLAT MONITORING SYSTEM - A system for determining whether the relative rate of deployment of all the slats ( | 12-27-2012 |
| 20130009015 | HIGH-LIFT SYSTEM FOR AN AIRCRAFT - A high-lift system with a main wing and adjustable flaps as well as guiding devices for holding the adjustable flaps and adjustment devices for adjusting the adjustable flaps, wherein the respective guiding device and/or adjustment device at least in part include/includes a fairing, including a flow influencing device for influencing the flow around the high-lift system, with at least one inlet line with at least one inlet that is situated on or below the bottom of the high-lift system, wherein, furthermore, at least one outlet line for air is provided that includes a fluid-communicating connection to the inlet line and includes at least one outlet situated at the top in the region of at least one adjustable flap of the high-lift system. | 01-10-2013 |
| 20130026300 | HIGH LIFT SYSTEM FOR AN AIRCRAFT - A high lift system with a main wing and regulating flaps, also bearing devices for the mounting of the regulating flaps, and positioning devices for the positioning of the regulating flaps, wherein the respective bearing device and/or positioning device is at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least one inlet duct with at least one inlet, which device is located on or underneath the lower face of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet duct in a fluid-communicating manner, and has at least one outlet, which is located on the upper face in the region of at least one regulating flap of the high lift system. | 01-31-2013 |
| 20130187009 | AIRCRAFT WITH WINGS AND A SYSTEM FOR MINIMIZING THE INFLUENCE OF UNSTEADY FLOW STATES - An aircraft (F) with wings ( | 07-25-2013 |
| 20130206916 | SYSTEM AND METHOD FOR MINIMISING BUFFETING - A system and method for minimizing buffeting in the case of an aircraft. Buffeting load control elements are provided in airfoils of the aircraft are arranged to be at least partly moved out of the airfoils by a control to reduce buffeting loads acting on the aircraft. | 08-15-2013 |
| 20140239126 | DRIVE SYSTEM FOR GROUND SPOILER, AND AIRCRAFT - The present invention provides a drive system which can automatically deploy a ground spoiler even when a wheel is locked. A drive system for a ground spoiler deploys closed ground spoilers | 08-28-2014 |
| 20150122951 | MORPHING AEROFOIL - A morphing aerofoil comprising: a leading edge; a trailing edge; and upper and lower surfaces extending between the leading and trailing edges. An upper thermal actuation member is provided proximate the upper surface; and a lower thermal actuation member is provided proximate the lower surface opposite the upper thermal actuator. The upper and lower thermal actuation members have different thermal expansion coefficients and are positioned such that they cause the trailing edge to deflect when they expand or contract by different amounts in response to a change in ambient temperature, thereby changing a camber of the aerofoil. | 05-07-2015 |
