Pitot static pressure compensator

Claim 1

A STATIC PRESSURE COMPENSATING SYSTEM FOR AIRCRAFT, COMPRISING: MEANS FOR SENSING AN APPARENT ANGLE OF ATTACK OF SAID AIRCRAFT AND GENERATING A FIRST ELECTRICAL OUTPUT REPRESENTATIVE OF SAID APPARENT ANGLE OF ATTACK; PRESSURE RATIO MEASURING MEANS FOR SENSING THE RATIO BETWEEN AN APPARENT STATIC PRESSURE AND IMPACT PRESSURE, AND GENERATING A SECOND ELECTRICAL OUTPUT REPRESENTING A FUNCTION OF THE FLIGHT MACH NUMBER OF SAID AIRCRAFT; A BRIDGE CIRCUIT; MEANS FOR ADDING SAID FIRST AND SECOND OUTPUTS IN SAID BRIDGE CIRCUIT; PRESSURE SUPPLY MEANS OPERABLE TO PROVIDE A CONTROLLED VARIABLE SOURCE OF PRESSURE; AND MECHANISM RESPONSIVE TO UNBALANCE OF THE BRIDGE CIRCUIT TO ADJUST THE PRESSURE PROVIDED AT THE CONTROLLED PRESSURE SOURCE IN A DIRECTION DETERMINED BY THE CONDITION OF BRIDGE UNBALANCE COMPRISING: MEANS FOR SENSING RELATIVE VARIATION BETWEEN SAID APPARENT STATIC PRESSURE AND THE PRESSURE PROVIDED BY THE CONTROLLED VARIABLE SOURCE, AND MEANS OPERABLE IN RESPONSE TO THE LAST MENTIONED MEANS TO RESTORE BRIDGE BALANCE WHEN THE PRESSURE PROVIDED AT