Abstract: Space vehicles such as space stations are often constructed as segmented inflatable structures which are susceptible to being punctured by small meteoric materials, resulting in small insidious leaks which are difficult to locate and repair. A method and apparatus are described in which a differential pressure transducer is positioned between segments of the space vehicle. Atmospheric gas pressure of all segments is continuously monitored. Analysis is performed on any pressure differentials which are determined to exist between adjacent segments. Detection of small leaks initiates an automatic isolation of the leaking segment. Detection of catastrophic leaks initiates an emergency evacuation of personnel from the affected segment.