US3727180A
Expired / Lapsed
US
⏱️ 0.0 years remaining
On-board aircraft weight and c. g. synchro-type self-checking attitude sensor
Assignee: BLH Electronics Inc
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Filing: 1971-03-23
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Granted: 1973-04-10
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Expires: 1991-03-23
Abstract
Abstract In an on-board aircraft weight and c. g. system, compensation for effects of pitch or slope of the craft is provided by a synchro-type attitude sensor in which a relatively light weight, immersed in a damping fluid within close confines of a container, is suspended for limited fore-aft tilting about the axis of a precision-bearing synchro-rotor; the stator windings of the synchro include a normally-disabled winding having a close coupling with the rotor winding over the limited tilting range, and selective switching causes the normally disabled winding to yield an electrical output which serves as a test of electrical operating characteristics of the sensor.
Inventors
- 👤 F Lingel
- 👤 A Filipov
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 01:00
CPC Classifications
G; G08; G08C; G08C19/00; G08C19/38; G08C19/46; G08C19/48; B; B64; B64C; B64C17/00; G01; G01C; G01C9/00; G01C9/12
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
260 words
Attitude-sensing apparatus comprising an electrical inductive device having rotor and stator portions relatively movable angularly about an axis, a support, bearings mounting said portions in relation to said support for relative angular movements about said axis, each of said rotor and stator portions including electrical winding means disposed for inductive coupling with the winding means of the other of said portions, means for electrically exciting the winding means of said rotor portion with periodically varying electrical signals, pendulous means slaving the angular orientation of said rotor portion in relation to the vertical, at least some of said winding means of said stator portion being fixed in relation to said support and disposed to develop substantially a zero net electrical output signal when in a predetermined angular relation to said rotor portion and to develop net electrical output signals of phase and magnitude characterizing the direction and extent of angular tilting movements of said support and winding means of said stator portion from said predetermined angular relation about said axis, mechanical stop means limiting to a relatively small angular range the relative angular movements between said stator and rotor portions, said range including said predetermined angular relation, and said winding means of said stator portion including a further winding disposed to have an electrical output signal induced therein by said winding means of said rotor portion when said rotor and stator portions are in any angular relation within said range about said axis, whereby said output signal from said further winding characterizes operativeness of said inductive device and electrically exciting means.
Claim 2
Dependent Claim
260 words
Attitude-sensing apparatus comprising an electrical inductive device having rotor and stator portions relatively movable angularly about an axis, a support, bearings mounting said portions in relation to said support for relative angular movements about said axis, each of said rotor and stator portions including electrical winding means disposed for inductive coupling with the winding means of the other of said portions, means for electrically exciting the winding means of said rotor portion with periodically varying electrical signals, pendulous means slaving the angular orientation of said rotor portion in relation to the vertical, at least some of said winding means of said stator portion being fixed in relation to said support and disposed to develop substantially a zero net electrical output signal when in a predetermined angular relation to said rotor portion and to develop net electrical output signals of phase and magnitude characterizing the direction and extent of angular tilting movements of said support and winding means of said stator portion from said predetermined angular relation about said axis, mechanical stop means limiting to a relatively small angular range the relative angular movements between said stator and rotor portions, said range including said predetermined angular relation, and said winding means of said stator portion including a further winding disposed to have an electrical output signal induced therein by said winding means of said rotor portion when said rotor and stator portions are in any angular relation within said range about said axis, whereby said output signal from said further winding characterizes operativeness of said inductive device and electrically exciting means.
Claim 3
Dependent Claim
44 words
Attitude-sensing apparatus as set forth in claim 1 further including means connecting said output signal from said further winding for measurement through said winding means of said stator portion, whereby said output signal further characterizes operativeness of said winding means of said stator portion.
Claim 4
Dependent Claim
62 words
Attitude-sensing apparatus as set forth in claim 2 wherein said winding means of said stator portion comprises a pair of windings connected in series and disposed to have electrical signals of opposite polarities induced simultaneously therein by said winding means of said rotor portion, and wherein said net electrical output signals are developed across the series combination of said pair of windings.
Claim 5
Dependent Claim
48 words
Attitude-sensing apparatus as set forth in claim 3 further including voltage divider means connected across said series combination, and wherein said output signal from said further winding is measured through said connecting means between an end of said further winding and a tap on said voltage divider means.
Claim 6
Dependent Claim
159 words
Attitude-sensing apparatus as set forth in claim 4 wherein said inductive device comprises a synchro, wherein said pair of windings and said further winding are Y-connected, wherein said means for electrically exciting said winding means of said rotor portion comprises means exciting the said winding means with electrical signals characterizing the gross weight of an aircraft, and means mounting said support on the aircraft in position to orient said axis of said synchro substantially transversely to the longitudinal axis of the aircraft, and means for selectively switching the output from said apparatus from across said series combination to across said end of said further winding and said tap, whereby said output from across said series combination characterizes angular pitch of the aircraft and a function of the gross weight, and said output from across said end of said further winding and said tap characterizes operativeness of said apparatus, including all of said winding means and said electrically exciting means.
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) | 1976-04-09 | 1976-10-09 | 1977-04-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-04-09 | 1980-10-09 | 1981-04-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-04-09 | 1984-10-09 | 1985-04-10 | $7700.00 | Window Closed / Lapsed |