U.S. Patent Specifications

Abstract

In an aircraft an engine mounting device comprising essentially an adaptor ring unitary with said engine and having only three shock absorbing engine connection fittings unitary therewith and extending outwardly therefrom in spaced relation there around, a pair of pyramidal frames composed of strut means connected respectively at their apex ends to two of said iittings and extending into rigid connexion at the other of their ends with said aircraft, and a triangular frame composed of strut means connected at its apex end to the other of said fittings and extending therefrom into rigid connexion at its base end with said aircraft.

Citation

(1942), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 14 No. 3, pp. 89-90. https://doi.org/10.1108/eb030887