987 results about "High lift" patented technology

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.

A method is provided for control of transition between combustion modes of a direct-injection engine operable in a homogeneous charge compression ignition (HCCI) mode at lower loads and a spark ignition flame propagation (SI) mode at higher loads. The engine includes a variable valve actuation system including two-step high and low lift valve actuation and separate cam phasing for both intake and exhaust valves. The method includes operating the engine at steady state, with fuel-air-exhaust gas mixtures at predetermined conditions, for each speed and load, and controlling the engine during mode changes between the HCCI mode and the SI mode by switching the exhaust and intake valves between low lift for HCCI operation and high lift for SI operation. High load may be an SI throttled mode with an intermediate unthrottled mode (SI/NTLC} in which transition between HCCI and SI/NTLC modes requires switching only the exhaust valve lift and transition between SI/NTLC and SI throttled modes requires switching only the intake valve lift, with predetermined phase adjustments in the valve timing phasing.

Golf ball with a novel combination of spin rate, lift coefficient, drag coefficients, and optionally moment of intertia: a golf ball with a low spin rate, a high lift coefficient, a low drag coefficient, and optionally a high moment of inertia; and a golf ball with a high spin rate, a low lift coefficient, a low drag coefficient, and optionally a low moment of inertia.

Deltoid Main Wing idea provides for several innovative aerodynamic configurations for large subsonic and supersonic civil and military aircraft including “T-tailed Deltoid Main Wing” configuration that allows for design of high-subsonic jumbo jet passenger aircraft with a capacity between 200 and 700 passengers whose outer dimensions fit within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with the same passenger capacity, while further allowing for design of all-size and all-purpose, high-lift-capacity, and long-range unmanned aircraft.

A navigation system for an aircraft, including a calculator of an estimated flight path for the aircraft; a device for determining an estimated value of a flight parameter that corresponds to an estimated speed for the extension of at least a portion of the high-lift devices of the aircraft; and a display of an indication for such estimated value. A command process for such a system and an aircraft equipped with such a system are also disclosed.

A high-lift airfoil embodying a combination of loading conventions in a single design specifically to reduce and control total pressure losses that occur in the flow channels between airfoils employed in turbomachinery applications is disclosed herein. The mixed-loading high-lift airfoil designs embody and exhibit the best total profile and secondary loss characteristics possessed by both aft-loaded airfoil and front-loaded airfoil conventions through controlling the development and interaction of boundary layers forming along the surfaces of the airfoils and the endwalls in such applications. The mixed-loading high-lift airfoil may be utilized in both rotating and non-rotating turbomachinery applications.

The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, computer component cooling, propulsors for unmanned and manned air vehicles, propulsors for airboats, air-cushion vehicles, airships and model aircraft. Additionally, the invention provides higher performance such as higher lift and higher lift efficiency to small air vehicles. These advantages are achieved by using plasma actuators to provide active flow control effectors into thin fan blades and wing.

Aerial dispersion systems that may be employed to allow rapid and temporary conversion of aircraft for aerial dispersion purposes, such as aerial fire-fighting. The aerial dispersion systems may be implemented using modular components that may be configured for compatibility with conventional cargo loading and unloading systems of modern aircraft, including side-loading cargo systems of wide body passenger and cargo aircraft having high lift capacities. The aerial dispersion systems may be rapidly installed in a large fleet of high capacity aircraft in response to a wildfire or other rapidly-developing emergency such as an oil spill, chemical or biological contamination incident, building or refinery fire, etc. After use, the aircraft of the fleet may be rapidly de-modified and returned to original condition. The aerial dispersion systems may be operated with a fleet of aircraft in a coordinated manner, for example, as part of an aerial firefighting formation having multiple aircraft sharing information and/or common control.

An airfoil family for a helicopter rotor blade, designated SC362XX. SC362XX essentially removes the large lower surface suction peak associated with ‘drag creep’ at moderate lift coefficients while reducing the peak Mach number and shock strength at high lift/Mach number conditions. Another optional airfoil family for use at inboard regions of the helicopter rotor, which is designated SC3252XX airfoil family, is a relatively thicker airfoil section that includes a significant increase in thickness forward of the 30% x/c location to provide a relatively thick and rigid inboard section. The lift coefficient at which the drag divergence Mach number was optimized is the same in both families thereby readily providing application to a single rotor blade.

The invention provides a rotor blade airplane with a variable flight mode, comprising an airplane body, a plurality of canards, a rotor blade, an empennage and a power system. The rotor blade airplane is characterized in that the canards are symmetrically arranged at two sides of the head of the airplane body; the empennage comprises a perpendicular empennage and a horizontal empennage, the perpendicular empennage is arranged at the back of the airplane body, and the horizontal empennage is arranged at the top end of the perpendicular empennage to form into the 'T'-shaped empennage; the canards, the rotor blade and the horizontal empennage are distributed with one another in the manner of a step from low to high along with the Z direction of the airplane; and a plurality of high lift devices are arranged on the canards and the horizontal empennage, and the lift force requirement for the controllable flight of the airplane can be met by a lift force generated on the canards and the horizontal empennage during transition flight. The rotor blade airplane can prevent the empennage from being directly impacted by the downwash of the rotor blade under a rotor blade flight mode, the distraction to a horizontal tail caused by the downwash of the rotor blade can be reduced, and the airplane can be controlled under the rotor blade flight mode during the transition flight.

Micro-electro-mechanical (MEM) translational tabs are introduced for enhancing and controlling aerodynamic loading of lifting surfaces. These microtabs are mounted at or near the trailing edge of lifting surfaces, deploy approximately normal to the surface, and have a maximum deployment height on the order of the boundary layer thickness. Deployment of this type of device effectively changes the camber, thereby affecting the lift generated by the surface. The effect of these microtabs on lift is as powerful as conventional control surfaces such as ailerons. Application of this simple yet innovative lift enhancement and control device will permit the elimination of some of the bulky conventional high-lift and control systems and result in an overall reduction in system weight, complexity and cost.

An apparatus advantageously influences the wing root airflow along the wing root of an aircraft having a high lift system including leading edge slats provided on the main wings. The apparatus includes a respective vortex generator arranged on the inboard end of each leading edge slat in the area of the wing root, and further includes a respective transition fairing arranged on a separation edge that is let into the leading edge of the wing root and that borders along the inboard edge of the respective slat. The vortex generator is a rigid member fixed to the leading edge slat and may be in the shape of a horn, a disk, or a winglet. The transition fairing may be a rigid member fixed to the wing root along the separation edge, or may be a flexible elastic member that can be inflated to have a variable outer contour. The present system avoids the need of additional independently movable auxiliary flaps, and thus achieves a reduced weight, complexity, and maintenance requirement.

The invention relates to a wing tip support device for wind tunnel test. The upper connecting surface and the lower connecting surface of a force measuring balance are respectively connected with a support beam top plate and a force platform, two variable attack angle mechanisms are respectively arranged at the top end of a support upright post positioned at the outer sides of two side walls of the middle part of the wind tunnel test section, passing holes of a flange spline shaft are symmetrically arranged on the wind tunnel side wall of the equal height part of the center line of the flangespline shaft of the variable attack angle mechanism, one end of the flange spline shaft passes through the passing hole arranged on the wind tunnel side wall and is positioned in a wind tunnel, the other end of the flange spline shaft is connected with the variable attack angle mechanism arranged outside the wind tunnel, two variable side slide angle mechanisms are positioned in the wind tunnel and are fixed on a flange plate arranged at the end surface of the flange spline shaft positioned in the wind tunnel through a slide plate, and slide flanges of the two variable side slide angle mechanisms are connected with the wing tip of an airplane model through a model connecting element. The wing tip support device is applicable to airplane airdrop and airborne wind tunnel test, and airplane fuselages, high lift devices and afterbody drag wind tunnel tests, and has the characteristics that the structure is simple, the use is convenient, and the test data is reliable.

Vortex generators are arranged on the edges of aircraft wing control surfaces to generate smaller vortices that weaken the main vortex that would otherwise be generated at these areas, and thereby reduce the aerodynamic generation of noise. Each vortex generator includes plural elongated elements in the form of rigid rods or flexible bristles protruding laterally outwardly from the respective edge of the control surface. The vortex generators are preferably arranged on the inboard and outboard edges of high lift flaps and slats.

Systems and methods for rotor/wing aircraft are disclosed. In one embodiment, an aircraft includes an airframe, a high-lift canard and tail, a rotor/wing, a propulsion system, and a drive assembly. The drive assembly, which may include a radial inflow turbine, is configured to extract work from the propulsion system to selectively rotate the rotor/wing assembly thus enabling the aircraft to conduct rotary-wing flight, fixed wing flight as well as smoothly transition between the two modes of flight.

The invention relates to a high-lift-to-drag-ratio hypersonic stable gliding reentry guidance method based on a drag profile. The method comprises the following steps that the first step, modeling ofa hypersonic flight vehicle is conducted; the second step, gliding distance analytic solution derivation is conducted; the third step, reentry track planning and tracking guidance are conducted; and the fourth step, a stable gliding trajectory tilt angle based on an earth rotation model is derived. The high-lift-to-drag-ratio hypersonic stable gliding reentry guidance method based on the drag profile has the advantages that a gliding distance analytic solution which is higher in accuracy and is based on energy is obtained, the form is simple, and application is convenient; the drag profile isplanned by using the energy as an independent variable, the drag profile is converted into the longitudinal lift-to-drag ratio under the rotating earth background, then a heeling angle is adjusted, tracking is conducted under the condition of the maximum lift-to-drag ratio, and transverse movement is controlled by a course error threshold; and in order to solve the reentry trajectory oscillation problem, the stable gliding trajectory tilt angle based on the earth rotation model is derived, and a trajectory damping technology using the stable gliding trajectory tilt angle as the feedback item is adopted to restrain oscillation.