US3593092A
Expired / Lapsed
US
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Multiple output multiplex actuator
Assignee: Ltv Electrosystems Inc
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Filing: 1970-02-02
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Granted: 1971-07-13
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Expires: 1990-02-02
Abstract
Abstract Four servomotors are coupled together in a velocity-summing arrangement to produce two output motions. These two output motions are combined in a linkage arrangement that results in a single output. Two of the four servomotors are coupled together through a differential gearset that has a single rotary output and the second servomotor pair is also coupled together through a differential gearset that produces a single rotary output. These two rotary outputs are in turn coupled through two additional gearsets that each have a single rotary output. Each of these two additional gearsets has one input connected to one of the motor pair outputs and a second input in a common coupling arrangement. The rotary output of each of the second and third gearsets may be converted into a linear motion by means of a rotary-to-linear motion transducer, or used as a rotary motion. Operation of one of the rotary-to-linear motion transducers is restrained below a preestablished force level. Each of the four servomotors is controlled individually by a separate generated control signal in a system that includes a tachometer for generating velocity feedback signals and a linear voltage differential transformer for generating position feedback signals.
Inventors
- 👤 Robert V Flippo
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 12:05
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/0055; G05D1/0077
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
118 words
A multiple output multiplex actuator for developing outputs that vary in accordance with generated control signals comprising: a plurality of servomotors with each motor responsive to a separate generated signal, means for velocity coupling the output of each of said servomotors to produce two rotary outputs each equal to the velocity sum of said plurality of servomotors, means for converting one of the rotary outputs of the velocitycoupling means into a first output that variEs in accordance with the generated signals, and means for converting the second rotary output of the velocitycoupling means into a second output that varies in accordance with the generates signal when a force developed at the second rotary output exceeds a preestablished level.
Claim 2
Dependent Claim
118 words
A multiple output multiplex actuator for developing outputs that vary in accordance with generated control signals comprising: a plurality of servomotors with each motor responsive to a separate generated signal, means for velocity coupling the output of each of said servomotors to produce two rotary outputs each equal to the velocity sum of said plurality of servomotors, means for converting one of the rotary outputs of the velocitycoupling means into a first output that variEs in accordance with the generated signals, and means for converting the second rotary output of the velocitycoupling means into a second output that varies in accordance with the generates signal when a force developed at the second rotary output exceeds a preestablished level.
Claim 3
Dependent Claim
49 words
A multiple output multiplex actuator for developing several outputs as set forth in claim 1 wherein said means for velocity coupling includes differential gearsets for combining two velocity inputs into a single velocity output, the two rotary outputs are generated by two differential gearsets having a common input connection.
Claim 4
Dependent Claim
33 words
A multiple output multiplex actuator for developing several outputs as set forth in claim 1 wherein said first and second converting means includes means for converting a rotary motion into a linear displacement.
Claim 5
Dependent Claim
217 words
A multiple output multiplex actuator for positioning aircraft controls in accordance with generated control signals comprising: a first plurality of servomotors with each motor responsive to a separate generated signal and velocity coupled in a manner to produce a single rotary output, a second plurality of servomotors with each motor responsive to one of the generated signals not connected to first plurality of servomotors and velocity coupled in a manner to produce a single rotary output, a velocity-coupling pair with the velocity couplers of said pair having one input interconnected and the second input of one coupler connected to the rotary output of said first plurality of servomotors, and the second input of the second coupler of said pair connected to the rotary output of said second plurality of servomotors, each velocity coupler of said pair developing a single rotary output from the two inputs connected to said pair, means for converting the rotary output of one of the velocity couplers of said pair into a control signal that varies in accordance with the pilot generated signals, and means for converting the rotary output of the second velocity coupler of said pair into a control signal that varies in accordance with the generated signals when the force of the second velocity coupler output exceeds a preestablished limit.
Claim 6
Dependent Claim
217 words
A multiple output multiplex actuator for positioning aircraft controls in accordance with generated control signals comprising: a first plurality of servomotors with each motor responsive to a separate generated signal and velocity coupled in a manner to produce a single rotary output, a second plurality of servomotors with each motor responsive to one of the generated signals not connected to first plurality of servomotors and velocity coupled in a manner to produce a single rotary output, a velocity-coupling pair with the velocity couplers of said pair having one input interconnected and the second input of one coupler connected to the rotary output of said first plurality of servomotors, and the second input of the second coupler of said pair connected to the rotary output of said second plurality of servomotors, each velocity coupler of said pair developing a single rotary output from the two inputs connected to said pair, means for converting the rotary output of one of the velocity couplers of said pair into a control signal that varies in accordance with the pilot generated signals, and means for converting the rotary output of the second velocity coupler of said pair into a control signal that varies in accordance with the generated signals when the force of the second velocity coupler output exceeds a preestablished limit.
Claim 7
Dependent Claim
45 words
A multiple output multiplex actuator for positioning aircraft controls as set forth in claim 4 including means for inhibiting the operation of the second converting means when the force at the output of the second velocity coupler of said pair is below a preestablished level.
Claim 8
Dependent Claim
33 words
A multiple output multiplex actuator for positioning aircraft controls as set forth in claim 5 wherein said first and second converting means includes means for converting a rotary motion into a linear displacement.
Claim 9
Dependent Claim
67 words
A multiple output multiplex actuator for positioning aircraft controls as set forth in claim 6 wherein the velocity couplers of said pair includes two differential gearsets having one input of each interconnected and the second input of one connected to the rotary output of said first plurality of servomotors and the second input of the other connected to the rotary output of said second plurality of servomotors.
Claim 10
Dependent Claim
40 words
A multiple output multiplex actuator for positioning aircraft controls as set forth in claim 4 wherein said means for converting the rotary output of each of the velocity couplers of said pair includes a lead screw and ball nut assembly.
Claim 11
Dependent Claim
261 words
A multiple output multiplex actuator for positioning aircraft controls in accordance with generated control signals, comprising: a first servomotor pair with each motor responsive to a separate generated signal, a first differential gearset having inputs individually connected to the servomotors of said first pair for coupling said servomotors together and producing a single rotary output therefrom, a second servomotor pair with each motor responsive to one of the generated signals not connected to said first servomotor pair, a second differential gearset with inputs individually coupled to the servomotoRs of said second motor pair for coupling said motors together to produce a single rotary output therefrom, a third differential gearset having one input connected to the rotary output of said first differential gearset and having a second input, said third differential gearset developing a single rotary output from two inputs connected thereto, a fourth differential gearset having one input connected to the rotary output of said second differential gearset and having a second input connected to the second input of said third differential gearset, said fourth differential gearset developing a single rotary output from two inputs connected thereto, means for converting the rotary output of the third differential gearset into a control signal that varies in accordance with the generated signals, and means for converting the rotary output of the fourth differential gearset into a control signal that varies in accordance with the generated signals when the force developed at the output of said fourth gearset exceeds a preestablished level for controlling said aircraft controls upon a failure of the first output.
Claim 12
Dependent Claim
261 words
A multiple output multiplex actuator for positioning aircraft controls in accordance with generated control signals, comprising: a first servomotor pair with each motor responsive to a separate generated signal, a first differential gearset having inputs individually connected to the servomotors of said first pair for coupling said servomotors together and producing a single rotary output therefrom, a second servomotor pair with each motor responsive to one of the generated signals not connected to said first servomotor pair, a second differential gearset with inputs individually coupled to the servomotoRs of said second motor pair for coupling said motors together to produce a single rotary output therefrom, a third differential gearset having one input connected to the rotary output of said first differential gearset and having a second input, said third differential gearset developing a single rotary output from two inputs connected thereto, a fourth differential gearset having one input connected to the rotary output of said second differential gearset and having a second input connected to the second input of said third differential gearset, said fourth differential gearset developing a single rotary output from two inputs connected thereto, means for converting the rotary output of the third differential gearset into a control signal that varies in accordance with the generated signals, and means for converting the rotary output of the fourth differential gearset into a control signal that varies in accordance with the generated signals when the force developed at the output of said fourth gearset exceeds a preestablished level for controlling said aircraft controls upon a failure of the first output.
Claim 13
Dependent Claim
41 words
A multiple output multiplex actuator for positioning aircraft controls as set forth in claim 9 wherein said converting means connected to the rotary outputs of the third and fourth differential gearsets each includes a lead screw and a ball nut assembly.
Claim 14
Dependent Claim
36 words
A multiple output multiplex actuator for positioning aircraft controls as set forth in claim 9 including means for restraining the operation of the converting means connected to said fourth differential gearset below the preestablished force level.
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) | 1974-07-12 | 1975-01-11 | 1975-07-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-07-12 | 1979-01-11 | 1979-07-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-07-12 | 1983-01-11 | 1983-07-13 | $7700.00 | Window Closed / Lapsed |