All attitude aircraft fuel measuring system

Claim 1

A FUEL MEASURING AND INDICATING SYSTEM COMPRISING TWO MEASURING SYSTEMS AND AN INDICATING SYSTEM, ONE OF SAID MEASURING SYSTEMS BEING AN INTEGRATING TYPE MASS FLOWMETER AND THE SECOND MEASURING SYSTEM BEING A TRUE WEIGHT CAPACITANCE PROBE GAGING SYSTEM WHICH INCLUDES A FUEL TANK AND MEANS FOR MEASURING THE CAPACITANCE OF THE FUEL IN SAID TANK AND SAID INDICATING SYSTEM HAVING LIQUID INERTIAL SENSORS ADAPTED TO GENERATE A VOLTAGE WHEN THE SENSORS ARE SUBJECTED TO INERTIAL FORCES IN EXCESS OF A PRESELECTED VALUE, EACH OF SAID SENSORS INCLUDING AN IMPEDANCE BRIDGE HAVING AN ELECTROLYTIC POTENTIOMETER IN AT LEAST ONE LEG THEREOF, A RELAY CIRCUIT RESPONSIVE TO THE OUTPUT OF SAID LIQUID INERTIAL SENSORS, AN INDICATOR, SAID RELAY CIRCUIT BEING CONNECTED TO EACH OF SAID FUEL MEASURING SYSTEMS AND ADAPTED TO INTRODUCE SELECTIVELY THE OUTPUT OF ONE OF SAID SYSTEMS TO SAID INDICATOR IN ACCORDANCE WITH THE STATE OF SAID LIQUID INERTIAL SENSORS, SAID RELAY SYSTEM BEING ARRANGED TO INTRODUCE THE OUTPUT OF SAID CAPACITANCE PROBE GAGING SYSTEM INTO SAID INDICATOR WHEN THE INERTIAL FORCES ON THE SENSORS ARE BELOW THE PRESELECTED VALUE AND SELECTIVELY TO INTRODUCE THE OUTPUT OF THE MASS FLOWMETER INTO THE INDICATOR WHEN THE INERTIAL FORCES ON THE SENSORS ARE ABOVE THE PRESELECTED VALUE.