Aircraft total energy sensor
OwnerOran W. Nicksinventor
Life of this patent
Estimating the term…
Abstract
An inexpensive total energy sensor utilizing the principles of laminar flow separation around a small cylinder having the desired relationship between static and dynamic pressures for use with sensitive rate of climb instruments for maximum utilization of external pressures by aircraft, in general, and sailplanes in particular.
Claims11
An energy sensor probe for providing a signal representative of changes in useful total energy for an aircraft during flight comprising:
- an elongated tubular member positioned on the exterior of the aircraft and having an open end and a closed end,
- said closed end of said tubular member being angularly inclined forward relative to the direction of flight of the aircraft and provided with a single orifice formed in the aft portion thereof and spaced from said closed end,
- said open end of said tubular member being in fluid connection with a sensitive variometer whereby, during aircraft flight the laminar air flow around said tubular member produces pressures which vary with changes in aircraft velocity and altitude that are proportional to changes in total energy pressure and these changes being detected by the energy sensor probe and indicated by the variometer.
In combination, an aircraft and a variometer provided on the instrument panel thereof to provide readings of the available total energy air pressure available during flight of the aircraft at a given instant, the improvement therewith consisting of:
- a total energy pressure probe exteriorly disposed on the aircraft,
- said total energy pressure probe being an elongated tubular member having an open end portion and a closed end portion,
- the open end portion of said tubular member being secured to the aircraft fuselage so as to be in fluid communication with the variometer and the closed end portion of said tubular member extending into the free airstream about the aircraft,
- said closed end portion of said tubular member being provided with a single orifice disposed in the aft cylindrical portion thereof and spaced from the closed end thereof,
- whereby, laminar flow around the tubular member produces pressures that vary with changes in aircraft velocity and altitude proportional to changes in total energy and these pressure changes are transmitted through the total energy pressure probe to the aircraft variometer.
Dependencies are inferred from the claim text.