Jun 17, 2025

US12332011 - Inert launch control simulator

An electronic device ( 210 ) is provided for simulating launch activation of a missile. The missile has a rocket motor and a payload. The device connects to a launch controller ( 380 ) for the motor and an ordnance controller ( 390 ). The device includes a direct current (DC) power supply ( 220 ); a circuit board ( 440 ); a payload jack ( 340 ); and data jacks ( 350, 360 ). The circuit board ( 440 ) includes a voltage regulator ( 570, 580 ), a thrust vector control (TVC) circuit ( 510 ), input, output and power plugs ( 550, 560, 590 ). The power plug ( 590 ) connects to the power supply ( 220 ). The payload jack ( 340 ) connects the output plug ( 560 ) to the ordnance controller ( 390 ) and to the TVC circuit ( 510 ). The output data jack ( 350 ) connects the circuit board ( 440 ) to the ordnance controller ( 390 ). The input data jack ( 360 ) connects the circuit board ( 440 ) to the launch controller ( 380 ). The circuit board ( 440 ) receives a signal from the launch controller ( 380 ) to which said ordnance controller ( 390 ) responds.

Assignee: United States of America, as represented by the Secretary of the Navy
Inventors: Christopher D. King, Taylor Richard Courtney, Amanda Nolan Dearhart, Robert William Love, III, Timothy Roy Collins, Douglas Gerald Gross, Jeremiah W. Mosse
Filing date: 2024-01-22

The patent describes an electronic device designed to simulate the launch activation of a missile, incorporating various components such as a DC power supply, circuit board, and multiple jacks for connectivity with launch and ordnance controllers. This device facilitates the interaction between the launch controller and ordnance controller by processing signals to mimic missile launch conditions.

Claim 1

An electronic device ( 210 ) for simulating launch activation of a missile having a rocket motor and a payload, said device connecting to a launch controller ( 380 ), and an ordnance controller ( 390 ), and comprising: a direct current (DC) power supply ( 220 ); a circuit board ( 440 ) having a voltage regulator ( 570 , 580 ), a thrust vector control (TVC) circuit ( 510 ), an input plug ( 550 ), an output plug ( 560 ) and a power plug ( 590 ) that connects ( 710 ) to said power supply ( 220 ); a payload jack ( 340 ) that connects ( 720 ) said output plug ( 550 ) to the ordnance controller ( 390 ) and to said TVC circuit ( 510 ); an output data jack ( 350 ) that connects said circuit board ( 440 ) to the ordnance controller ( 390 ); and an input data jack ( 360 ) that connects said circuit board ( 440 ) to the launch controller ( 380 ), whereby said circuit board ( 440 ) receives a signal from the launch controller ( 380 ) to which said ordnance controller ( 390 ) responds. a direct current (DC) power supply ( 220 ); a circuit board ( 440 ) having a voltage regulator ( 570 , 580 ), a thrust vector control (TVC) circuit ( 510 ), an input plug ( 550 ), an output plug ( 560 ) and a power plug ( 590 ) that connects ( 710 ) to said power supply ( 220 ); a payload jack ( 340 ) that connects ( 720 ) said output plug ( 550 ) to the ordnance controller ( 390 ) and to said TVC circuit ( 510 ); an output data jack ( 350 ) that connects said circuit board ( 440 ) to the ordnance controller ( 390 ); and an input data jack ( 360 ) that connects said circuit board ( 440 ) to the launch controller ( 380 ), whereby said circuit board ( 440 ) receives a signal from the launch controller ( 380 ) to which said ordnance controller ( 390 ) responds.

Google Patents

https://patents.google.com/patent/US12332011

USPTO PDF

https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/12332011