Rotatable and tiltable radome with independent scan and tilt antenna

Claim 2

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.

Claim 3

Antenna apparatus according to claim 1 wherein said antenna displacement means further comprises: axle means positioned along the scanning axis of said antenna and rotatably secured at the ends thereof to the interior surface of said radome; first rotating means drivingly connected to said axle means for effecting the rotation of said antenna about said scanning axis; and second rotating means drivingly secured between said antenna and a point intermediate the ends of said axle means for tilting said antenna about said tilt axis.

Claim 4

Antenna apparatus according to claim 2 wherein said axle means further comprises: an axle positioned along said scanning axis; a first bearing rotatably secured between one end of said axle and a first portion of said radome interior surface; and a second bearing rotatably secured between the other end of said axle and a second portion of said radome interior surface.

Claim 5

Antenna apparatus according to claim 2 wherein said control means further comprises: gyro means for sensing changes in roll and pitch of the aircraft and for providing roll and pitch output signals indicative thereof; roll displacement means connected to receive said gyro means roll output signal and formed to be secured between the aircraft and said radome to effect roll displacement of said radome according to said roll output signal; and pitch displacement means connected to receive said gyro means pitch output signal and formed to be secured between the aircraft and said radome to effect pitch displacement of said radome according to said pitch output signal.

Claim 6

Antenna apparatus according to claim 4 wherein said roll displacement means further comprises: first motor means connected to receive said gyro means roll output signal for moving an output shaft a predetermined distance according to said output signal; and a first actuating rod assembly rotatably engaged at one end to said first motor means output shaft and rotatably engaged at the other end to said radome to effect roll displacement thereof.

Claim 7

Antenna apparatus according to claim 4 wherein said pitch displacement means further comprises: second motor means connected to receive said gyro means pitch output signal for moving an output shaft a predetermined distance according to said output signal; and a second actuating rod assembly rotatably engaged at one end to said second motor means output shaft and rotatably engaged at the other end to said radome for effecting pitch displacement thereof.

Claim 8

Antenna apparatus according to claim 4 wherein said radome is an ellipsoid.

Claim 9

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.

Claim 10

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.

Claim 11

Antenna apparatus according to claim 8 wherein said antenna displacement means further comprises: axle means positioned along the scanning axis of said antenna and rotatably secured at the ends thereof to the interior surface of said radome; first rotating means drivingly connected to said axle means for effecting the rotation of said antenna about said scanning axis; and second rotating means drivingly secured between said antenna and a point intermediate the ends of said axle means for tilting said antenna about said tilt axis.

Claim 12

Antenna apparatus according to claim 9 wherein said axle means further comprises: an axle positioned along said scanning axis; a first bearing rotatably secured between one end of said axle and a first portion of said radome interior surface; and a second bearing rotatably secured between the other end of said axle and a second portion of said radome interior surface.

Claim 13

Antenna apparatus according to claim 9 wherein said control means further comprises: gyro means for sensing changes in roll and pitch of the aircraft and for providing roll and pitch output signals indicative thereof; roll displacement means connected to receive said gyro means roll output signal and formed to be secured between the aircraft and said radome to effect roll displacement of said radome according to said roll output signal; and pitch displacement means connected to receive said gyro means pitch output signal and formed to be secured between the aircraft and said radome to effect pitch displacement of said radome according to said pitch output signal.

Claim 14

Antenna apparatus according to claim 11 wherein said roll displacement means further comprises: first motor means connected to receive said gyro means roll output signal for moving an output shaft a predetermined distance according to said output signal; and a first actuating rod assembly rotatably engaged at one end to said first motor means output shaft and rotatably engaged at the other end to said radome to effect roll displacement thereof.

Claim 15

Antenna apparatus according to claim 11 wherein said pitch displacement means further comprises: second motor means connected to receive said gyro means pitch output signal for moving an output shaft a predetermined distance according to said output signal; and a second actuating rod assembly rotatably engaged at one end to said second motor means output shaft and rotatably engaged at the other end to said radome for effecting pitch displacement thereof.

Claim 16

Antenna apparatus according to claim 11 wherein said radome is an ellipsoid.