Force summing multiplex actuator

Claim 2

A multiplex actuator having an output motion that varies in accordance with generated control signals, comprising: a plurality of control channels each including a rotary-tolinear motion transducer responsive to a separate one of the generated control signals, motion transmitting means for transferring the linear motion produced by the transducer to an attachment point, said motion transmitting means having: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movement of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and switching means carried by said motion transmitting means and actuated thereby when the force applied thereto exceeds the breakout values to disconnect the transducer from the generated control signal, and a forcing bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion varying in accordance with the generated signal energizing each of the control channels.

Claim 3

A multiplex actuator having an output motion that varies in accordance with generated control signals, comprising: a plurality of control channels each including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, and motion transmitting means coupled to the output of the transducer for transferring the linear motion produced thereby to an attachment point, said motion transmitting means including: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movement of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and a force bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion varying in accordance with the generated signals energizing each of the control channels.

Claim 4

A multiplex actuator having an output motion that varies in accordance with generated control signals, comprising: a plurality of control channels each including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, and motion transmitting means coupled to the output of the transducer for transferring the linear motion produced thereby to an attachment point, said motion transmitting means including: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movement of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and a force bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion varying in accordance with the generated signals energizing each of the control channels.

Claim 5

A multiplex actuator having an output motion that varies in accordance with generated control signals as set forth in claim 2 including a position transducer in each of the control channels coupled to said rotary-to-linear motion transducer for generating a position feedback signal from the motion transducer to balance out the generated control signal applied thereto.

Claim 6

A multiplex actuator having an output motion that varies in accordance with generated control signals as set forth in Claim 2 wherein said force bar is a torque tube having a pivotal connection to each of said plurality of control channels and producing a rotary output from said actuator.

Claim 7

A multiplex actuator having an output motion that varies in accordance with generated control signals, comprising: a plurality of control channels each including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, and motion transmitting means coupled to the output of the transducer for transferring the linear motion produced thereby to an attachment point, said motion transmitting means including: a. a housing pivotally connected to the attachment point, b. a connecting rod slidably positioned in said housing and coupled to the output of said motion transducer, c. a first collet fitted over said rod and engaging a stop thereon and said housing, d. a second collet also fitted over said rod and engaging a stop thereon, e. a first spring positioned between said first and second collets in a preloaded condition, f. a third collet concentrically mounted with said second collet and movable with respect thereto and engaging said housing, and g. a second spring positioned between said first and third collets in a preloaded condition, said first and second springs establishing an asymmetrical breakout force for movement of the connecting rod with respect to the housing, and a force bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion varying in accordance with the generated signals energizing each of the control channels.

Claim 8

A multiplex actuator having an output motion that varies in accordance with generated control signals, comprising: a plurality of control channels each including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, and motion transmitting means coupled to the output of the transducer for transferring the linear motion produced thereby to an attachment point, said motion transmitting means including: a. a housing pivotally connected to the attachment point, b. a connecting rod slidably positioned in said housing and coupled to the output of said motion transducer, c. a first collet fitted over said rod and engaging a stop thereon and said housing, d. a second collet also fitted over said rod and engaging a stop thereon, e. a first spring positioned between said first and second collets in a preloaded condition, f. a third collet concentrically mounted with said second collet and movable with respect thereto and engaging said housing, and g. a second spring positioned between said first and third collets in a preloaded condition, said first and second springs establishing an asymmetrical breakout force for movement of the connecting rod with respect to the housing, and a force bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion varying in accordance with the generated signals energizing each of the control channels.

Claim 9

A multiplex actuator for positioning an aircraft control surface in accordance with pilot generated control signals, comprising: a plurality of control channels each including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, a breakaway force coupler coupled to the output of the transducer for transferring the output motion to an attachment point, said breakaway force coupler including: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movemenT of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and switching means carried by the breakaway coupler and actuated thereby when the force applied thereto exceeds by a given amount the breakout values to disconnect the transducer from the generated control signal, a position transducer in each of the control channels coupled to said rotary-to-linear motion transducer for generating a position feedback signal connected to the respective amplifier for that channel, and a force bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion for controlling a power ram connected to said aircraft surface for varying the position of said surface in accordance with the pilot generated control signals.

Claim 10

A multiplex actuator for positioning an aircraft control surface in accordance with pilot generated control signals, comprising: a plurality of control channels each including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, a breakaway force coupler coupled to the output of the transducer for transferring the output motion to an attachment point, said breakaway force coupler including: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movemenT of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and switching means carried by the breakaway coupler and actuated thereby when the force applied thereto exceeds by a given amount the breakout values to disconnect the transducer from the generated control signal, a position transducer in each of the control channels coupled to said rotary-to-linear motion transducer for generating a position feedback signal connected to the respective amplifier for that channel, and a force bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion for controlling a power ram connected to said aircraft surface for varying the position of said surface in accordance with the pilot generated control signals.

Claim 11

A multiplex actuator for positioning an aircraft control surface as set forth in claim 6 including means for monitoring the output of all of said plurality of control channels and generating an alarm signal when the switching means carried by all but two of said channels is actuated.

Claim 12

A multiplex actuator for positioning an aircraft control surface as set forth in claim 6 wherein said force bar is a torque tube having a pivotal connection to each of said plurality of control channels and producing a rotary output, and including a rotary-to-linear motion transducer for generating the control signals to said power ram.

Claim 13

A multiplex actuator for positioning an aircraft control surface as set forth in claim 6 wherein said rotary-to-linear motion transducer includes a lead screw connected to said breakaway coupler and a ball-nut assembly as part of a motor armature, said lead screw and ball-nut assembly may be back driven by a force applied to the output of said transducer.

Claim 14

A multiplex actuator for positioning an aircraft control surface in accordance with pilot generated control signals, comprising: a plurality of control channels each including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, a breakaway force coupler coupled to the output of the transducer for transferring the output motion to an attachment point, said breakaway force coupler including: a. a housing pivotally connected to the attachment point, b. a connecting rod slidably positioned in said housing and coupled to the output of said motion transducer, c. a first collet fitted over said rod and engaging a stop thereon and said housing, d. a second collet also fitted over said rod and engaging a stop thereon, e. a first spring positioned between said first and second collets in a preloaded condition, f. a third collet concentrically mounted with said second collet and movable with respect thereto and engaging said housing, and g. a second spring positioned between said first and third collets in a preloaded condition, said first and second springs establishing an asymmetrical breakout force for movement of the connecting rod with respect to the housing, and switching means carried by the breakaway coupler and actuated thereby when the force applied thereto exceeds by a given amount the breakout values to disconnect the transducer from the generated signal, a position transducer in each of the control channels coupled to said rotary-to-linear motion transducer for generating a position feedback signal connected to the respective amplifier for that channel, and a force bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion for controlling a power ram connected to said aircraft surface for varying the position of said surface in accordance with the pilot generated control signals.

Claim 15

A multiplex actuator for positioning an aircraft control surface in accordance with pilot generated control signals, comprising: a plurality of control channels each including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, a breakaway force coupler coupled to the output of the transducer for transferring the output motion to an attachment point, said breakaway force coupler including: a. a housing pivotally connected to the attachment point, b. a connecting rod slidably positioned in said housing and coupled to the output of said motion transducer, c. a first collet fitted over said rod and engaging a stop thereon and said housing, d. a second collet also fitted over said rod and engaging a stop thereon, e. a first spring positioned between said first and second collets in a preloaded condition, f. a third collet concentrically mounted with said second collet and movable with respect thereto and engaging said housing, and g. a second spring positioned between said first and third collets in a preloaded condition, said first and second springs establishing an asymmetrical breakout force for movement of the connecting rod with respect to the housing, and switching means carried by the breakaway coupler and actuated thereby when the force applied thereto exceeds by a given amount the breakout values to disconnect the transducer from the generated signal, a position transducer in each of the control channels coupled to said rotary-to-linear motion transducer for generating a position feedback signal connected to the respective amplifier for that channel, and a force bar having the attachment point of each of the plurality of control channels connected thereto and producing an output motion for controlling a power ram connected to said aircraft surface for varying the position of said surface in accordance with the pilot generated control signals.

Claim 16

A multiplex actuator for positioning an aircraft control surface by means of a power ram in accordance with pilot generated control signals, comprising: a first control channel pair coupled together in a force summing arrangement to a common attachment point, each of said control channels including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, a breakaway force coupler engaging the output of the transducer for transferring the linear motion output thereof to the common attachment point, said breakaway force coupler including: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movement of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and switching means carried by the coupler and actuated thereby when the force applied thereto exceeds by a given amount the established breakout values to disconnect the transducer from the generated control signal, a second control channel pair coupled together in a force summing arrangement to a common attachment point, each of the control channels including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, a breakaway force coupler engaging the output of the transducer for transferring the linear motion output thereof to the common attachment point, said breakaway force coupler including: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movement of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and switching means carried by the coupler and actuated thereby when the force applied thereto exceeds by a given amount the established breakout values to disconnect the transducer from the generated control signal, a position transducer in each of the control channels connected to the rotary-to-linear motion transducer for generating a position feedback signal from the motion transducer to balance out the pilot generated signal connected thereto, a torque tube having the common attachment points for the said first and second control pairs connected thereto and producing an output motion varying in accordance with the pilot generated signal, and means for converting the rotary motion at said torque tube into a linear motion for controlling the power ram connected to an aircraft control surface.

Claim 17

A multiplex actuator for positioning an aircraft control surface by means of a power ram in accordance with pilot generated control signals, comprising: a first control channel pair coupled together in a force summing arrangement to a common attachment point, each of said control channels including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, a breakaway force coupler engaging the output of the transducer for transferring the linear motion output thereof to the common attachment point, said breakaway force coupler including: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movement of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and switching means carried by the coupler and actuated thereby when the force applied thereto exceeds by a given amount the established breakout values to disconnect the transducer from the generated control signal, a second control channel pair coupled together in a force summing arrangement to a common attachment point, each of the control channels including a rotary-to-linear motion transducer responsive to a separate one of the generated control signals, a breakaway force coupler engaging the output of the transducer for transferring the linear motion output thereof to the common attachment point, said breakaway force coupler including: a. first and second members movable relative to each other, one member coupled to the output of the transducer and the second member coupled to the attachment point, b. first means for restraining the movement of the first and second members relative to each other in a first direction below a first breakout value, and c. second means for restraining the movement of the first and second members relative to each other in a second direction below a second breakout value greater than the first breakout value, and switching means carried by the coupler and actuated thereby when the force applied thereto exceeds by a given amount the established breakout values to disconnect the transducer from the generated control signal, a position transducer in each of the control channels connected to the rotary-to-linear motion transducer for generating a position feedback signal from the motion transducer to balance out the pilot generated signal connected thereto, a torque tube having the common attachment points for the said first and second control pairs connected thereto and producing an output motion varying in accordance with the pilot generated signal, and means for converting the rotary motion at said torque tube into a linear motion for controlling the power ram connected to an aircraft control surface.

Claim 18

A multiplex actuator for positioning an aircraft control surface as set forth in claim 11 wherein the rotary-to-linear motion transducer in each control channel comprises a ball-nut and lead-screw assembly which may be back driven by the other control channels coupled to said torque tube.

Claim 19

A multiplex actuator for positioning an aircraft control surface as set forth in claim 12 wherein the position transducer in each of the control channels comprises a linear voltage differential transformer.

Claim 20

A multiplex actuator for positioning an aircraft control surface as set forth in claim 11 including means for monitoring each of the breakaway couplers for generating a pilot alarm signal when the switching means of all but two of the four channels has been actuated by an excessive breakout force.

Claim 21

A multiplex actuator for positioning an aircraft control surface as set forth in claim 14 including a plurality of summing amplifiers each having an output connected to one of the rotary-to-linear motion transducers of the control channel through a switch actuaTed disconnect and a first input connected to one of the pilot generated control signals and a second input connected to the respective feedback signal from the position transducer.