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US3984837A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rotatable and tiltable radome with independent scan and tilt antenna
Assignee: United States Department of the Navy
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Filing: 1975-03-31
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Granted: 1976-10-05
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Expires: 1995-03-31
Abstract
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.
Inventors
- 👤 George J. Tatnall
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 12:46
CPC Classifications
H; H01; H01Q; H01Q1/00; H01Q1/12; H01Q1/18; H01Q1/42; H01Q1/428
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
122 words
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 2
Dependent Claim
122 words
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
Dependent Claim
84 words
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
Dependent Claim
61 words
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
Dependent Claim
107 words
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
Dependent Claim
71 words
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
Dependent Claim
71 words
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
Dependent Claim
12 words
Antenna apparatus according to claim 4 wherein said radome is an ellipsoid.
Claim 9
Dependent Claim
129 words
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
Dependent Claim
129 words
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
Dependent Claim
84 words
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
Dependent Claim
61 words
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
Dependent Claim
107 words
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
Dependent Claim
71 words
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
Dependent Claim
71 words
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
Dependent Claim
12 words
Antenna apparatus according to claim 11 wherein said radome is an ellipsoid.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1979-10-05 | 1980-04-05 | 1980-10-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-10-05 | 1984-04-05 | 1984-10-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-10-05 | 1988-04-05 | 1988-10-05 | $7700.00 | Window Closed / Lapsed |