| Patent Number |
Title Of Patent |
Date Issued |
| 6543719 |
Oscillating air jets for implementing blade variable twist, enhancing engine and blade efficienc |
April 8, 2003 |
| A porous surface on an aircraft structure driven with oscillating positive and negative pressures is used as an active control device for attenuating negative aerodynamic interactions. The porous surfaces can be driven with positive and negative pressures either continuously or when pred |
| 6406783 |
Bulk absorber and process for manufacturing same |
June 18, 2002 |
| A bulk absorber has a continuous concentration gradient of particles with dielectric or magnetic altered properties. The bulk absorber may be made from foam or, ceramic. The particles may be carbon fibers, carbon black, carbon whiskers, coated hollow microspheres, or a combination thereo |
| 6291071 |
Bonded composite structure and its fabrication |
September 18, 2001 |
| A composite structure is made by first furnishing a skin layer made of a composite material of quartz fibers embedded in an uncured cyanate ester-resin matrix. A transition layer of a first epoxy resin is applied to the skin layer. The skin structure including the skin layer and tran |
| 6234751 |
Oscillating air jets for reducing HSI noise |
May 22, 2001 |
| Porous surfaces on an aerodynamic structure driven with positive and negative pressures are used in an active control system for attenuating shock waves responsible for high-speed impulsive (HSI) noise. The control system includes an array of apertures in the outer skin of the structure |
| 6056846 |
Bonded composite structure and its fabrication |
May 2, 2000 |
| A composite structure is made by first furnishing a skin layer made of a composite material of quartz fibers embedded in an uncured cyanate ester-resin matrix. A transition layer of a first epoxy resin is applied to the skin layer. The skin structure including the skin layer and tran |
| 5922987 |
Hydraulic traverse and elevation mechanism |
July 13, 1999 |
| A locking mechanism for locking an orientation of a weapon is disclosed. The locking mechanism includes a first movable arm adapted to contact and apply pressure onto a control surface associated with the weapon, and a second movable arm adapted to contact and apply pressure onto the con |
| 5897077 |
Quick-change skid landing gear |
April 27, 1999 |
| A low-profile transportation and storage assembly is readily substitutable with a conventional pair of skid landing gear. The low-profile transportation and storage assembly includes a front auxiliary crosstube having low-profile wheels attached to opposing ends of the front auxiliary |
| 5850615 |
Rotor blade swashplate-axis rotation and gyroscopic moments componsator |
December 15, 1998 |
| An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is disclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are d |
| 5823470 |
Split torque proprotor transmission |
October 20, 1998 |
| A conversion access gearset includes a first bevel gear, which is connected to a wing cross shaft leading from the proprotor drive train path to the second turbine engine. A second bevel gear is connected to a main transmission input shaft, which is adapted for driving the proprotor. A |
| 5802918 |
Concentric face gear transmission assembly |
September 8, 1998 |
| A concentric face gear assembly includes a first face gear having first face gear teeth and second face gear having second face gear teeth. At least one input pinion contacts both the first face gear teeth and the second face gear teeth, and at least one idler pinion contacts both the |
| 5799901 |
Rotor blade swashplate-axis rotation and gyroscopic moments compensator |
September 1, 1998 |
| An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is disclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are d |
| 5791875 |
Tip vortex reduction system |
August 11, 1998 |
| An active control device is disclosed for modifying a tip vortex on a lifting body. The lifting body includes a positive-pressure generating structure and a negative-pressure generating structure, and is adapted for providing lift when a first fluid pressure adjacent to the positive- |
| 5788181 |
Thermostatic metal actuator for nozzle actuation |
August 4, 1998 |
| A nozzle for use on opposing ends of the rotor of a jet powered tri-mode aircraft is disclosed. The nozzle includes two thermally-controlled doors, which are moveable between an open configuration where hot jet engine exhaust is vented therethrough to propel the rotor in a helicopter mod |
| 5727757 |
Slotted cam control system |
March 17, 1998 |
| The present invention provides a slotted cam control system for controlling pitch angles of fan blades of a relatively low-pressure-ratio fan within a fuselage of a helicopter. The stream of air generated by the fan is directed into the tailboom of the helicopter, and is selectively |
| 5678786 |
Reconfigurable helicopter flight control system |
October 21, 1997 |
| A failure of any one of three swashplate actuators of a helicopter rotor blade is detected. Once such a detection is made, the position of this nonfunctional swashplate is locked and measured. The inputted commanded swashplate collective position, commanded swashplate x-axis rotational |
| 5641133 |
Rotorcraft fuselage modal frequency placement using resilient mounting connections |
June 24, 1997 |
| The present invention provides a desired design approach for retuning a rotorcraft airframe by utilizing resilient connections between major airframe components. In the preferred embodiment, the design employs resilient material, preferably elastomeric material, in the mounting syste |
| 5621967 |
Method of making a leading edge weight retention assembly for a helicopter rotor |
April 22, 1997 |
| A method for making helicopter rotor blades includes wrapping a prepreg strap around the conical or cylindrical outboard end of each weight segment. The weight segment is then placed in the rotor blade spar and goes through the spar cure cycle with it. Primary retention is provided by |
| 5588800 |
Blade vortex interaction noise reduction techniques for a rotorcraft |
December 31, 1996 |
| An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The flap may be actuated in any conventional way, and is scheduled to |
| 5571992 |
Lightweight shielded cable assembly |
November 5, 1996 |
| A cable assembly is described, which includes a bundle of wires (14, FIG. 1) and a shield structure (24) around them which is of light weight for aircraft applications, and which provides effective shielding especially against electromagnetic interference. The shield structure includes a |
| 5462409 |
Leading edge weight retention assembly for a helicopter rotor |
October 31, 1995 |
| Leading edge weights for helicopter rotor blades are required to provide blade chordwise balance and maintain rotor inertia. Provision for retention of the leading edge weights in a high centrifugal force field, after failure of the primary adhesive bond, is necessary. The invention |
| 5381985 |
Wingtip mounted, counter-rotating proprotor for tiltwing aircraft |
January 17, 1995 |
| A tiltwing aircraft, capable of in-flight conversion between a hover and forward cruise mode, employs a counter-rotating proprotor arrangement which permits a significantly increased cruise efficiency without sacrificing either the size of the conversion envelope or the wing efficien |
| 5364705 |
Hybrid resistance cards and methods for manufacturing same |
November 15, 1994 |
| A hybrid resistance card (R-Card) is manufactured using a two-step process wherein an electrically conductive ink layer and an electrically resistive ink layer are printed onto a surface, which may be either a substrate or the part on which the R-Card is to be used. The conductive ink la |
| 4715263 |
Roll turret for a gun mount |
December 29, 1987 |
| A retractable gun for mounting within the fuselage of an aircraft, typically a helicopter, is disposed in a firing position and aimed by rotation of a turret which is coupled to and parallel to the longitudinal axis of the aircraft. The gun is aimed by simultaneous and independent ro |
