Abstract: Vacuum systems for use aboard aircraft and other vehicles, wherein, by simplified design, the systems of this new invention are virtually foolproof. This new invention utilizes the age old venturi due to its simplicity and lack of moving parts, but due to innovation, the limitations of the venturi have been overcome. This new invention installs the venturi within the exhaust tailpipe of engines and puts the extreme high velocity of exhaust gas movement to good use. These systems are compatible with just about any engine, and obviously venturi ice problems are eliminated. These systems may be used to provide redundant power for gyro systems and windshield wiper systems. By the addition of a suction relief valve and connective tubing the system will provide regulated suction pressure for the operation of a Gyro Horizon and or a Directional Gyro. By further addition of a restrictor needle valve and additional connective tubing, one can power either a Turn and Bank indicator or A Turn Co-ordinator.

Abstract: Vacuum systems deriving their trustworthiness by means of simplified apparatus, wherein, the vacuum source will be derived from simple venturis common to the state of the art, whereby, ice prevention will be achieved by use of bleed air from the turbine section of the jet engine used to power the aircraft. Venturi ice prevention will be selectable by the pilot and will fail safe to the on position should the aircraft encounter a complete electrical failure. The remaining units comprising of the vacuum system and connective tubing will all be common to the state of the art. One of the vacuum systems will supply regulated vacuum pressure to the earth reference gyros by means of a venturi being located within the inlet mouth of a jet engine, said pressure then routed to a pressure regulator and then routed to the gyros, therefore, regulated pressure will be available immediately following engine start and will remain available in flight even should its respective engine fail.

Abstract: An evolutionary development of my prior inventions into an improved display form, more compatible to the desires of the overwhelming majority of pilots. This new invention is a natural derivative of my (co-pending application for patent, Ser. No. 629,850, file date July 11, 1984 for Bank and Pitch Indicator) and (co-pending application for patent, file number pending, file date Mar. 25, 1985 for Improved Pitch Indicator for Bank And Pitch Indicator).

Abstract: A basic flight instrument to provide the pilot the means, by which, he can easily remain upright during instrument conditions. This flight instrument will be highly trustworthy, in that it will be absolutely tumble free due to its basic input derivatives. The instrument will be provided with two separate erection systems, whereby, the roll erection system will consist of a gimbal cage, spring tension erected and the pitch erection system will consist of a drum, the rotation of which will be properly erected by means of a gravitational weight and rotational reversing system. The pilot will be provided with simultaneous display of roll and pitch of reliable derivative. The roll rate of the gyro may be speed and altitude compensated if desired.

Abstract: A gyro flight instrument utilizing variable rate inputs, such variable being proportional to the speed of the craft, the result of which will be a lateral display nearly corresponding to the true lateral reference. Such lateral display will be in combination with a pitch display, such display will be variable in proportion to the angle of attack of the craft in relation to the relative airstream. The resultant display will nearly match the display of a gyro horizon with the exception of extreme excursions of pitch and bank. This will result in a highly trustworthy instrument the indication of which is totally derived from basic, non-tumbling reference, totally immune of earth reference requirement.

Abstract: An airborne image camera, its respective image scan plate and image Cathode Ray Tube (CRT) forms a display which simulates runway lights and Visual Approach Slope Indicator (VASI) for the pilot so that the display portrays what the pilot would see, were it not for limited visibility conditions. The on-board CRT continuously enacts and displays, according to position of the aircraft, what would otherwise be visible to him as the runway lights of an illuminated runway, were it not for obscured vision. This is obtainable by RF microwave signals from a plurality of emitters and reflectors which substitute RF energy for visible spectrum light, with the RF energy received and processed by instruments in the aircraft to create a continuous display on the CRT.