Aeronautics Patents for Sale or License

Safety For Aircraft pilot handler instrumentation Design for cockpits

on behalf of the crashes in the twin tower in u.s.a. i think there needs a design for save the people of airplane and pilot as well as against terrorist attacks.when any attemps made by the terrorist they no way take position in the cockpits.so arises a design by me: 1.) A signal device designd for a particular shape of frequency level to communicate on cockpits to ground level tower first by using VHF level. Two frequency uses here. 2.) One frequency for route connection. 3.)
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Antithermal Shield for Rockets

At high speed, the friction of air mass with the rocket surface produce local heating more than 1000 0C. For heat protection of rocket, on their outside surface are install antithermal shields. Studing Coanda effect, respectively, the fluid flow on solids surface, the author Ioan Rusu discover by simply researches that the Coanda effect could be expanded also for the fluid flow on discontinuous solids, respectively, on solids with orifices. This phenomenon was named by the author, the expande
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Free Compression Tube for Rockets

The flight optimization by increasing speed and reducing fuel consumption has directed research in the aerodynamics field. The flying vehicles shapes obtained through studies in the wind tunnel provide the optimization of the impact with the air masses and the airflow along the vehicle. By energy balance studies for vehicles in flight, the author Ioan Rusu directed his research in reducing the energy lost at vehicle impact with air masses. In this respect as compared to classical solutions for b
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Airplane Leading Edge De-Icing Apparatus

Retrofit-able aircraft de-icing system which utilizes exhaust gases to heat up an oil which is circulated to the leading edges to heat them and prevent ice formation.
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Foil journal bearing having straight foils to support for high speed rotors

Title: Foil journal bearing having straight foils useful for providing support for high speed rotors and a process for fabricating said bearing Abstract:A foil journal bearing having straight foil useful for providing support for a high speed rotor and a process for manufacturing the foil journal bearing, said foil journal bearing comprising an outer holder enclosing an inner holder, the inner holder being provided with a plurality of slots for straight flexible foils one end of which being fi
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Lighting solution for pilots, navigators, truck drivers, ...

Here is a lighting solution that is truly unique. Designed from the ground up to fulfill the lighting requirements for a highly reliable easy to use light source for both general high intensity white lighting and low intensity red lighting for night adaptation. For example, airplane cockpits use red lights so pilots can read their instruments and maps while maintaining night vision to see outside the aircraft. The same can be said for navigators on ships, truck drivers, train engineer, control
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Aerodynamic Body and Carrier Wing Comprising an Aerodynamic Body, Actuating Drive Control Module, Computer, Computer Program, and Method for Influencing Post-turbulences

The invention relates to an aerodynamic body for applying to a carrier wing on which at least two flow flaps adjacently arranged in the longitudinal direction of the aerodynamic body are mounted, to a carrier wing comprising a main carrier wing and the at least one additional aerodynamic body, and to a computer comprising an actuating drive control module which generates time-variable command signals for actuating drives. The actuating drive control module has a function which, when activated, g
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Device for Generating Aerodynamic Resistance on an Aircraft

An aircraft (1) has a brake flap (6) arranged upstream of a vertical tail (4), which brake flap (6) can be pivoted out into the air flow approaching the vertical tail (4). To reduce dynamic structural loading of the vertical tail (4), through openings (7, 8) are formed in the brake flap (6).
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Controllable Miniature Mono-wing Aircraft

Micro/nano mono-wing aircraft with the wing configured as a winged seed (Samara) is uniquely suited for autonomous or remotely controlled operation in confined environments for surrounding images acquisition. The aircraft is capable of effective autorotation and steady hovering. The wing is flexibly connected to a fuselage via a servo-mechanism which is controlled to change the wing's orientation to control the flight trajectory and characteristics. A propeller on the fuselage rotates about the
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Adjustable Single-channel Inertial Navigation System with Side Channel

The invention applies to aircraft's navigation industry. It gives possibility to decrease mistakes of the inertial navigation system and to accomplish inertial system technically more simple than its classical analog. The developed inertial navigation system which functional block diagram is shown in Fig.2 consists of only one channel - side channel. The developed single-channel inertial system contains specific correction chains that substantially decrease system's failures. The correction chai
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Flying Device with Flapping Wings

The invention relates to a flying device with flapping wings, the device comprising a chassis on which two pivots are pivotally mounted about two parallel articulation axes (X), each of the pivots bearing a wing, the device comprising a first oscillation generator in order to oscillate the pivots so as to cause the wings to flap, said first oscillation generator comprising: two arms (6) each secured to one of the pivots (2); two cranks (9) each articulated to the end of one of the arms about axe
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Aerostatic device damper

A damping device for an aerostatic device, comprises a male part 14 having a projecting portion 16, a female part 10 having a channel 12 in which the projecting portion 16 of the male part 14 is slidably receivable, means 22 for providing a magnetic field at or adjacent to the projecting portion 16 of the male part 14 and/or the channel 12 of the female part 10, and magnetic oil 26 interposed between the projecting portion 16 of the male part 14 and the channel 12 of the female part 10. The in u
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Low-Power Control and Signal Processing Asic for Vibrtory Rate Gyroscopes

Tech ID: 10260 / UC Case 2002-493-0 BACKGROUND Current gyroscope feedback control and signal processing elements take the form of a discrete analog implementation and/or a general purpose digital signal processing (DSP) chip. However, both of these methods present drawbacks. The discrete analog option is inflexible with regard to modifying component values for the purpose of "tuning" or customizing the control loops for a given sensor. The chip's disadvantage is that general purpose DSPs do
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Easily Replicatable Liquid Micro Pulsed Plasma Thruster

Micropropulsion devices are enabling technologies for a number of critical space missions involving all manner of spacecraft. Microthrusters can provide primary propulsion or attitude control on miniscule pico-satellites flying in tight-knit constellations. They can offer precision pointing or positioning as part of a bimodal propulsion system on conventionally scaled spacecraft. Even large space structures could be effectively manipulated via distributed systems of microthrusters. Most current
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Light Detection and Ranging (LIDAR) Mapping System

A mechanical computer used in tandem with a GPS to approach, enter and fly the traffic pattern of any uncontrolled airport. Pilots must navigate to a relatively small area or approach point before entering the traffic pattern of an uncontrolled airport. While airports are programmed into GPS units, the approach points are not. The computer works in tandem with an onboard GPS unit programmed for navigation direct to the airport of intended landing and employs triangulation to navigate to an appro
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Autonomous Micro-Pulse Lidar System (MPL) (GSC-13493)

Abstract: MPL is an eye safe lidar system for detecting cloud-base height and profiling atmospheric cloud and aerosol scattering up to altitudes of 30 kilometers. Developed at the Goddard Space Flight Center in answer to the challenge of creating an efficient lidar system for space-borne applications, it has been proven reliable for full-time autonomous operation in ground-based applications over a two year period.
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Passive Venting for Alleviating Helicopter Tail-Boom Loads (DRC98-96)

Abstract: The tail boom of a single-rotor helicopter is subjected to a complex flow field that includes the wakes of the main and tail rotors, the freestream, and the wake from the forward fuselage. Hovering and sideward flight present the operational regimes that are most critical with respect to adverse sideward and downward loads on the tail boom. These adverse loads necessitate additional engine power, thereby reducing payload, performance, and available yaw-control margins. In addition, no
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Fuel Cell System for Aircraft Propulsion

Background: Aircraft thrust is traditionally come from a combustion engine (internal combustion or gas turbine) coupled to either a propeller or a nozzle to produce thrust. These systems deliver high performance but also have high emissions and low fuel efficiency. Some proposals have used fuel cells as propulsion devices by using the electricity a fuel cell produces to power an electric motor linked to a propeller. This system lowers emissions and increases fuel efficiencies, but increases wei
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Suppression of Jet Noise from Aircraft

University researchers have developed a method to achieve significant noise reduction with simple modifications of the engine exhaust. These modifications have a very small effect on engine thrust. Moreover, the nature of the modification allows for on-demand activation of the noise suppression mechanism when quiet operation is desired; e.g, during takeoff and landing. At other flight stages such as cruise, the mechanism could be deactivated. This results in a very efficient noise suppression sy
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