Louis C Simons, 38680 W Boston Post Rd APT 2H, Mamaroneck, NY 10543

2013012, May 16, 2013

Nov 14, 2011

13/296029

Randall A. GREENE - Greenwich CT, US
Paul LEVINE - Valhalla NY, US
Louis SIMONS - Mamaroneck NY, US
Robert D. TETER - Hopewell Junction NY, US

Safe Flight instrument Corporation - White Plains NY

G08B 21/00

340946

A power line warning system for a helicopter, comprising a positioning system operable to determine the coordinates of the helicopter, an obstacle coordinate database comprising the coordinates of at least a portion of a first power line, a sensor operable to detect electromagnetic radiation from the first power line, and a visual display operable to represent a position of the first power line relative to the helicopter is described. When the coordinates of the first power line are within a predetermined distance of the coordinates of the helicopter, wherein the representation of the position of the first power line is modified when the sensor detects electromagnetic radiation from the first power line.

2021037, Dec 2, 2021

Oct 15, 2019

17/285860

- White Plains NY, US
Louis SIMONS - White Plains NY, US
Randall A. GREENE - White Plains NY, US

Safe Flight lnstrument Corporation - White Plains NY

B64C 13/04
B64C 13/50
B64D 31/14
B64D 31/04

An aircraft control system includes: a motor with a rotating shaft; a pilot control input; a linear actuator connecting the pilot control input to the rotating shaft; a sensor identifying a position of the pilot control input; and a transmitter transmitting the pilot control input position to a controller, the controller adjusting an aircraft performance device based on the received pilot control input position.

2019017, Jun 13, 2019

Dec 13, 2018

16/219775

- White Plains NY, US
Louis C. SIMONS - Mamaroneck NY, US
Randall A. GREENE - White Plains NY, US

Safe Flight Instrument Corporation - White Plains NY

B64D 31/04
B64D 31/06
B64D 31/14

An electronic aircraft control system and an electronic aircraft control method are provided. In some embodiments, the aircraft control system includes a motor including a rotating shaft, a lever including an axis of rotation, the lever connected to the rotating shaft, wherein the position of the lever is not maintained by a mechanical clutch during normal operations. In some embodiments, the aircraft control system includes a fail-safe system for maintaining mechanical friction of the lever in an event of a failure, a sensor identifying a position of the lever, and a transmitter transmitting the lever position to a controller, the controller adjusting an aircraft performance device based on the received lever position. In some embodiments, the motor provides a torque on the lever. In some embodiments, the fail-safe system includes shear pins configured to break when a sufficient amount of manual torque is applied to the lever.

2016003, Feb 4, 2016

Aug 1, 2014

14/450165

- White Plains NY, US
Robert D. TETER - Hopewell Junction NY, US
Louis SIMONS - Mamaroneck NY, US

G01C 23/00
B64D 43/00

In one embodiment, an aircraft display system includes a first module that identifies a label in an ARINC 429 communication between a flight director and a display, a second module that removes flight director data from the ARINC 429 communication, the flight director data associated with the label, and a third module that inserts substitute data in the ARINC 429 communication. The display receives the substitute data before an error is detected.

2015008, Mar 26, 2015

Sep 20, 2013

14/032840

- White Plains NY, US
Randall A. GREENE - Greenwich CT, US
Louis SIMONS - Mamaroneck NY, US
Darren TAILLIE - White Plains NY, US

SAFE FLIGHT INSTRUMENT CORPORATION - White Plains NY

B64D 43/02

340966

An aircraft safety system includes a Stall/Spin Warning & Recovery Computer, an angle of attack sensor, a side slip sensor and an angle of attack display. The Stall/Spin Warning and Recovery Computer detects whether the aircraft is in a safe condition or an unsafe condition. The angle of attack display includes a first configuration that displays information indicative of safe aircraft condition when the orientation detector detects a safe condition and a second configuration that displays information indicative of unsafe aircraft condition when the computer detects an unsafe condition. The display may transition from the first configuration to the second configuration when the orientation detector detects an unsafe condition and then to a third configuration, which may include visual control-input instructions that enable recovery to a safe condition.