Abstract: The security system provides an aircraft security system capable of protecting both single and multiple engine aircraft. Variations of the present system prevent unauthorized starting of protected aircraft and activate an alarm when engine starting it is attempted. Embodiments of the system draw no power from the aircraft when the security system is armed and in no way interferes with the normal starting or operation of the aircraft when the system is disarmed. Embodiments of the present system can activate an alarm when an aircraft's doors or panels are opened. Embodiments of the present invention can activate an alarm when installed equipment or other devices are tampered with or removed from their housings.

Abstract: The security system provides an aircraft security system capable of protecting both single and multiple engine aircraft. Variations of the present system prevent unauthorized starting of protected aircraft and activate an alarm when engine starting it is attempted. Embodiments of the system draw no power from the aircraft when the security system is armed and in no way interferes with the normal starting or operation of the aircraft when the system is disarmed. Embodiments of the present system can activate an alarm when an aircraft's doors or panels are opened. Embodiments of the present invention can activate an alarm when installed equipment or other devices are tampered with or removed from their housings.

Abstract: The security system provides an aircraft security system capable of protecting both single and multiple engine aircraft. Variations of the present system prevent unauthorized starting of protected aircraft and activate an alarm when engine starting it is attempted. Embodiments of the system draw no power from the aircraft when the security system is armed and in no way interferes with the normal starting or operation of the aircraft when the system is disarmed. Embodiments of the present system can activate an alarm when an aircraft's doors or panels are opened. Embodiments of the present invention can activate an alarm when installed equipment or other devices are tampered with or removed from their housings.

Abstract: The security system provides an aircraft security system capable of protecting both single and multiple engine aircraft. Variations of the present system prevent unauthorized starting of protected aircraft and activate an alarm when engine starting it is attempted. Embodiments of the system draw no power from the aircraft when the security system is armed and in no way interferes with the normal starting or operation of the aircraft when the system is disarmed. Embodiments of the present system can activate an alarm when an aircraft's doors or panels are opened. Embodiments of the present invention can activate an alarm when installed equipment or other devices are tampered with or removed from their housings.

Abstract: An Air/Fuel mixture control system for an internal combustion engine which uses a closed loop controller for varying an air/fuel mixture in response to the voltage output of the engine's exhaust gas oxygen sensor. The oxygen sensor will produce a voltage output which is classified in a range extending from very rich, net rich, net lean or very lean depending upon the sensed voltage output in milli-volts. The controller responds to an onset of a lean or rich exhaust signal, representative of either too much or too little oxygen, by instructing the fuel injectors to either increase or decrease the fuel delivery rate to a predetermined rich step value or lean step value. The delivery rate at the rich or lean step value is maintained until the onset of either a rich or lean exhaust indication or until a predetermined rich or lean step duration expires.

Abstract: A true closed-loop air/fuel ratio control system for an internal combustion engine which uses a cylinder air charge percentage value also known as a cylinder or engine load value, is used to control the air/fuel ratio of said engine in response to the difference of said measured load value and a predetermined optimum load value. This process allows true closed-loop fuel control immediately following a cold or warm engine start without need of a traditional exhaust gas sensor. As this process automatically compensates for all fuel utilized by the engine, even during cold starting and idles, the problems associated with fuel vapor purge systems are eliminated. This process can reduce government regulated emissions from said engine considerably and improve fuel economy a significant percentage particularly when operated net lean of stoichiometric. Elimination of currently required engine hardware for traditional systems can allow for a considerable cost savings.

Abstract: An electronic engine controller (EEC) is utilized to perform an onboard diagnostic test of a catalytic converter. An upstream oxygen sensor detects the exhaust gas entering the catalytic converter and an downstream oxygen sensor detects the exhaust gas exiting the catalytic converter. An air/fuel mixture is maintained at a first bias level until the exhaust gas produced by combustion of the air/fuel mixture is detected by the downstream oxygen sensor at which point the air/fuel mixture is altered to a second bias level and maintained at the second bias level until the exhaust gas produced by combustion of the air/fuel mixture is detected by the downstream oxygen sensor. An amount of time required for the upstream oxygen sensor to detect the exhaust products of the first bias value and for the second bias value is calculated, and similar values are calculated for the downstream oxygen sensor.

Abstract: An air/fuel mixture control system for an internal combustion engine uses a closed-loop controller which varies the air/fuel mixture in response to the oxygen level in the engine's exhaust emissions to achieve stoichiometry. The oxygen sensor produces a binary signal indicating either a rich or a lean mixture. The controller responds changes in binary sensor signal by delivering fuel at a fixed rate until either (1) the sensor responds by indication an oxygen level change or (2) a predicted transport delay interval expires. In the event the predicted interval expires before the sensor responds, the fixed rate is adjusted in an effort to obtain the desired level change within the allotted interval. In the event the level change is delayed beyond a limit, the predicted transport delay interval is enlarged.