Back to results
US 3,984,837 AGranted
Rotatable and tiltable radome with independent scan and tilt antenna
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorGeorge J. Tatnall
Life of this patent
Estimating the term…
Abstract
A low drag gyro stabilized radome for an aircraft. The radome is pivoted roll and pitch by a universal joint between the radome and a pylon rigidly attached to the aircraft thereby enabling the radome, under gyro control, to remain horizontal to the ground during varying flight attitudes. An enclosed antenna is driven independently of the radome for tilt and sweep motion.
Claims14
An antenna apparatus for an aircraft, comprising:
- an antenna rotatable within preselected angles about a scanning axis and a tilt axis perpendicular to said scanning axis;
- a radome formed to be pivotally connected to the aircraft, said radome enclosing said antenna with said axes fixed relative to said radome and having a minimum internal clearance for permitting scan and tilt of said antenna;
- means connected to said antenna for effecting displacement thereof in tilt and scan directions about the respective antenna axes independent of the attitude of said radome;
- and
- control means formed to be connected to the aircraft and operatively connected to said radome for effecting displacement thereof about a pitch axis and a roll axis perpendicular to said pitch axis.
2 more elements
An antenna apparatus for an aircraft, comprising:
- pivot means formed to be connected to the aircraft;
- an antenna rotatable within preselected angles about a scanning axis and a tilt axis perpendicular to said scanning axis;
- a radome rotatably connected to said pivot means, said radome enclosing said antenna with said axes fixed relative to said radome and having a minimum internal clearance for permitting scan and tilt of said antenna;
- means connected to said antenna for effecting displacement thereof in tilt and scan directions about the respective antenna axes independent of the attitude of said radome;
- and
- control means formed to be connected to the aircraft and operatively connected to said radome for effecting displacement thereof about a pitch axis and a roll axis perpendicular to said pitch axis.
3 more elements
Dependencies are inferred from the claim text.