Joshua M Horwitz

Author:

Joshua Horwitz

ISBN #:

0060225998

Author:

Joshua Horwitz

ISBN #:

0064460460

Author:

Joshua Horwitz

ISBN #:

0394851552

Author:

Joshua Horwitz

ISBN #:

0394853326

Author:

Joshua Horwitz

ISBN #:

0394951557

Author:

Joshua Horwitz

ISBN #:

0394953320

Author:

Joshua Horwitz

ISBN #:

0397314981

Author:

Joshua Horwitz

ISBN #:

0397316267

US Patent:

6578291, Jun 17, 2003

Filed:

Jun 6, 2001

Appl. No.:

09/875693

Inventors:

John Hirsch - Marblehead MA 01945
Joshua Horwitz - Magnolia MA 01930
Ron Zolla - Topsfield MA 01983

International Classification:

A43B 500

US Classification:

36132, 36137, 36136

Abstract:

The invention provides a shoe having a built-in, electronic wear indicator device capable of signaling (a) extent of shoe sole wear, (b) loss of ability to cushion and absorb shock, and (c) a need to replace the shoe. The wear indicator device comprises (a) a sensor and microprocessor which can measure and report the use history of the shoe, (b) a wear indicator display which shows the consumer the current point in the shoes life cycle and (c) a power source. The wear indicator device is installed between the midsole and outsole during the manufacturing process and is therefore, built-in and unobtrusive to the user.

US Patent:

42506360, Feb 17, 1981

Filed:

Jun 1, 1979

Appl. No.:

6/044497

Inventors:

Joshua Horwitz - Magnolia MA

Assignee:

Aviation Simulation Technology - Bedford MA

International Classification:

G09B 908

US Classification:

434 55

Abstract:

A yoke assembly for an aviation flight simulator capable of generating the appropriate control signals and mechanical responses for realistic flight simulation, including trim adjustment. In a preferred embodiment, the assembly comprises a rotatable and axially movable yoke shaft extending in an axial direction; a pair of sliding blocks mounted to be movable in the axial direction; a first spring rotationally coupling the yoke shaft with a first sliding block for simulating the rotational restoration force on an aircraft yoke; a second spring axially coupling the yoke shaft to the second sliding block for simulating the axial restoration force on an aircraft yoke; and adjustment means for adjusting the axial position of the second sliding block for simulating the effect of trim adjustment of an aircraft.

US Patent:

51011611, Mar 31, 1992

Filed:

Oct 12, 1990

Appl. No.:

7/598859

Inventors:

Thomas D. Walsh - Braintree MA
Nicholas Reinhardt - Lexington MA
James M. Feldman - Newton Highlands MA
George R. Vrablik - Wayland MA
Joshua Horwitz - Magnolia MA
Kathleen M. Morris - Wakefield MA
John O. Rudy - Newton MA

Assignee:

Boston Edison Company - Boston MA

International Classification:

G01R 3100

US Classification:

324543

Abstract:

Method and apparatus for identifying and determining the energization status of a cable having a conductive neutral member and an internal resistive screen layer involving probes radially movable relative to the cable to contact the neutral member and the internal resistive screen. Narrow-band AC signals and resistance measurements are utilized for self-testing and for cable testing. A microprocessor controls probe-heating in the advancing of probes through plastic sheath to reach the neutral wire and resistive screen layer. Resistance measurements made under control of the microprocessor are monitored with probe advance. Oscillators provide two signals of different frequencies, one of which is that of the power being transmitted through the cable, to provide distinctive signals indicative of cable energization status.

US Patent:

42767024, Jul 7, 1981

Filed:

Apr 25, 1979

Appl. No.:

6/033073

Inventors:

Joshua Horwitz - Magnolia MA

Assignee:

Pacer Systems, Inc. - Burlington MA

International Classification:

G09B 908

US Classification:

434 47

Abstract:

A flight simulator instrument trainer has operational controls and instruments similar to a conventional aircraft. An AC driven position simulator moves a simulated station position according to simulated power, attitude, flap condition direction and distance traveled to control simulated ADF, ILS and VOR instruments. Angularly offset phases are generated and are provided to potentiometers on directional instruments. Wipers on the potentiometers move with simulated direction indicators. Signals from the wipers are fed to other devices, and phases are compared with one of two ninety degree offset reference phases. The latter are shifted according to simulated flight characteristics, and the thus-varied output of the phase comparators are used to drive instruments and to shift angle position accumulators and distance position accumulators. Logic arrays control initiating signals which prevent attitude and altitude instrument changes until flight conditions are reached and indicate stalls and prevent stall indications during touchdown. An astable vibrator applies minor amplitude perturbations to motor drives for simulated altimeters and directional and attitude instruments.

US Patent:

42337569, Nov 18, 1980

Filed:

Dec 6, 1976

Appl. No.:

5/748116

Inventors:

Joshua Horwitz - Magnolia MA

Assignee:

Pacer Systems, Inc. - Burlington MA

International Classification:

G09B 908

US Classification:

35 12F

Abstract:

A flight simulator instrument trainer has operational controls and instruments similar to a conventional aircraft. An AC driven position simulator moves a simulated station position according to simulated power, attitude, flap condition direction and distance traveled to control simulated ADF, ILS and VOR instruments. Angularly offset phases are generated and are provided to potentiometers on directional instruments. Wipers on the potentiometers move with simulated direction indicators. Signals from the wipers are fed to other devices, and phases are compared with one of two ninety degree offset reference phases. The latter are shifted according to simulated flight characteristics, and the thus-varied output of the phase comparators are used to drive instruments and to shift angle position accumulators and distance position accumulators. Logic arrays control initiating signals which prevent attitude and altitude instrument changes until flight conditions are reached and indicate stalls and prevent stall indications during touchdown. An astable vibrator applies minor amplitude perturbations to motor drives for simulated altimeters and directional and attitude instruments.