Richard W Henry

US Patent:

7312871, Dec 25, 2007

Filed:

Apr 22, 2003

Appl. No.:

10/491988

Inventors:

Richard W. Henry - West Chester OH, US

Assignee:

A.P. Fixturlaser AB - Mölndal

International Classification:

G01B 11/26
G01B 11/00
G01C 1/00

US Classification:

356400, 356138, 356399

Abstract:

A method and apparatus for measuring the relative positions of first and second components, comprising: mounting first and second measurement units on respective housings forming part of each component and which are rotatably arranged and infinitely adjustable thereon in respective brackets for defining first and second adjustably selected rotational axes, respectively; measuring the relative positions of the components in first and second states of operation by detecting the relative positions of those selected axes in each state of operation and producing measurement values determinative of those relative positions.

US Patent:

45985820, Jul 8, 1986

Filed:

Jul 11, 1984

Appl. No.:

6/629850

Inventors:

Richard D. Henry - Clinton PA

International Classification:

G01C 2100

US Classification:

73178R

Abstract:

A gyro flight instrument utilizing variable rate inputs, such variable being proportional to the speed of the craft, the result of which will be a lateral display nearly corresponding to the true lateral reference. Such lateral display will be in combination with a pitch display, such display will be variable in proportion to the angle of attack of the craft in relation to the relative airstream. The resultant display will nearly match the display of a gyro horizon with the exception of extreme excursions of pitch and bank. This will result in a highly trustworthy instrument the indication of which is totally derived from basic, non-tumbling reference, totally immune of earth reference requirement.

US Patent:

46693033, Jun 2, 1987

Filed:

May 20, 1985

Appl. No.:

6/735613

Inventors:

Richard D. Henry - Clinton PA

International Classification:

G01C 2100

US Classification:

73178R

Abstract:

An evolutionary development of my prior inventions into an improved display form, more compatible to the desires of the overwhelming majority of pilots. This new invention is a natural derivative of my (co-pending application for patent, Ser. No. 629,850, file date July 11, 1984 for Bank and Pitch Indicator) and (co-pending application for patent, file number pending, file date Mar. 25, 1985 for Improved Pitch Indicator for Bank And Pitch Indicator). This new display will be composed of a display face disc, such disc will rotate in unison with the gimbal cage of a rate gyro, gyro deflective sensitivity being airspeed compensated if desired, wherein the display face disc will possess a rectangular window, whereby, a rotating drum display will show thru the window, such display will provide the pilot with a horizon reference demarcation line, painted blue sky above the line, painted black earth below the line and also short definition lines, above and below, showing five, ten, fifteen and twenty degree angle of attack deviation above or below the demarcation line, wherein by comparative reference to an aircraft tail view silhouette etched into the face plate glass, the pilot may easily determine his pitch reference with relation to the relative airstream. The aircraft will be provided with an angle of attack vane, wherein, the rotating drum of the instrument display will rotate in unison with and proportionally to the angular deflection of the angle of attack vane, such deflection being responsive to the relative airstream. The drum centerline axis will also rotate in unison with the gimbal cage, whereby, the horizon reference demarcation line will display to the pilot both bank and pitch by comparative reference to the etched silhouette and will show on or deviation therefrom.

US Patent:

42109302, Jul 1, 1980

Filed:

Nov 18, 1977

Appl. No.:

5/852961

Inventors:

Richard D. Henry - Clinton PA

International Classification:

H04N 718

US Classification:

358103

Abstract:

An airborne image camera, its respective image scan plate and image Cathode Ray Tube (CRT) forms a display which simulates runway lights and Visual Approach Slope Indicator (VASI) for the pilot so that the display portrays what the pilot would see, were it not for limited visibility conditions. The on-board CRT continuously enacts and displays, according to position of the aircraft, what would otherwise be visible to him as the runway lights of an illuminated runway, were it not for obscured vision. This is obtainable by RF microwave signals from a plurality of emitters and reflectors which substitute RF energy for visible spectrum light, with the RF energy received and processed by instruments in the aircraft to create a continuous display on the CRT.

US Patent:

46386602, Jan 27, 1987

Filed:

Jan 6, 1986

Appl. No.:

6/816453

Inventors:

Richard D. Henry - Clinton PA

International Classification:

G01C 2100

US Classification:

73178R

Abstract:

A basic flight instrument to provide the pilot the means, by which, he can easily remain upright during instrument conditions. This flight instrument will be highly trustworthy, in that it will be absolutely tumble free due to its basic input derivatives. The instrument will be provided with two separate erection systems, whereby, the roll erection system will consist of a gimbal cage, spring tension erected and the pitch erection system will consist of a drum, the rotation of which will be properly erected by means of a gravitational weight and rotational reversing system. The pilot will be provided with simultaneous display of roll and pitch of reliable derivative. The roll rate of the gyro may be speed and altitude compensated if desired.

US Patent:

47052333, Nov 10, 1987

Filed:

Feb 5, 1986

Appl. No.:

6/826330

Inventors:

Richard D. Henry - Clinton PA

International Classification:

B64D 4100

US Classification:

244 1R

Abstract:

Vacuum systems deriving their trustworthiness by means of simplified apparatus, wherein, the vacuum source will be derived from simple venturis common to the state of the art, whereby, ice prevention will be achieved by use of bleed air from the turbine section of the jet engine used to power the aircraft. Venturi ice prevention will be selectable by the pilot and will fail safe to the on position should the aircraft encounter a complete electrical failure. The remaining units comprising of the vacuum system and connective tubing will all be common to the state of the art. One of the vacuum systems will supply regulated vacuum pressure to the earth reference gyros by means of a venturi being located within the inlet mouth of a jet engine, said pressure then routed to a pressure regulator and then routed to the gyros, therefore, regulated pressure will be available immediately following engine start and will remain available in flight even should its respective engine fail. Another vacuum system will supply variable vacuum pressure to the rate gyros, said variable being responsive to and proportional with the speed of the aircraft, thereby, the deflective sensitivity of the rate gyros will increase should the speed of the craft increase, conversely, the deflective sensitivity will decrease should the speed of the craft decrease, thus, speed compensated rate gyros.

US Patent:

48178896, Apr 4, 1989

Filed:

Mar 10, 1988

Appl. No.:

7/169142

Inventors:

Richard D. Henry - Clinton PA

International Classification:

B60T 1300

US Classification:

244 1R

Abstract:

Vacuum systems for use aboard aircraft and other vehicles, wherein, by simplified design, the systems of this new invention are virtually foolproof. This new invention utilizes the age old venturi due to its simplicity and lack of moving parts, but due to innovation, the limitations of the venturi have been overcome. This new invention installs the venturi within the exhaust tailpipe of engines and puts the extreme high velocity of exhaust gas movement to good use. These systems are compatible with just about any engine, and obviously venturi ice problems are eliminated. These systems may be used to provide redundant power for gyro systems and windshield wiper systems. By the addition of a suction relief valve and connective tubing the system will provide regulated suction pressure for the operation of a Gyro Horizon and or a Directional Gyro. By further addition of a restrictor needle valve and additional connective tubing, one can power either a Turn and Bank indicator or A Turn Co-ordinator. By the simple addition of a speed control needle valve, one may power a set of vacuum motor driven windshield wipers.