Control system incorporating structural feedback
First Claim
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1. In an aircraft having flight sustaining wings, a plurality of movable control surfaces distributed along trailing portions of said wings for maneuvering the aircraft, and a separate actuator means for positioning each control surface, a structural feedback system, comprising:
- strain measuring means carried by a load carrying portion of a wing, near the aircraft center, for measuring bending moment induced strain;
AOT sensor means for measuring angle-of-attack forces acting on the aircraft;
accelerometer means for measuring acceleration forces acting on the aircraft; and
actuator control means including feedback means for each control surface responsive to a summation of signals from the strain measuring means, and AOT sensor means, and the accelerometer means, for operating the actuator means to move said control surfaces in a direction and in an amount to produce aerodynamic forces on the wings for stabilizing the wings.
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Abstract
Strain gages embedded in an upper skin structure portion of the wing, near the centerline axis, measures centerline moment and produces a feedback signal used for adjusting the control surfaces of the wing, to produce stabilizing forces. This enables the wings to be designed primarily for strength, not stiffness.
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Citations
12 Claims
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1. In an aircraft having flight sustaining wings, a plurality of movable control surfaces distributed along trailing portions of said wings for maneuvering the aircraft, and a separate actuator means for positioning each control surface, a structural feedback system, comprising:
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strain measuring means carried by a load carrying portion of a wing, near the aircraft center, for measuring bending moment induced strain; AOT sensor means for measuring angle-of-attack forces acting on the aircraft; accelerometer means for measuring acceleration forces acting on the aircraft; and actuator control means including feedback means for each control surface responsive to a summation of signals from the strain measuring means, and AOT sensor means, and the accelerometer means, for operating the actuator means to move said control surfaces in a direction and in an amount to produce aerodynamic forces on the wings for stabilizing the wings.
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2. In an aircraft, relatively limber flight sustaining wings designed for strength and not stiffness,
movable control surfaces on said wings for maneuvering the aircraft; -
actuator means for positioning the control surfaces; and a structural feedback system, comprising; strain measuring means carried by a load carrying portion of a wing, for measuring bending moment inducing strain; and actuator control means including feedback means responsive to a signal from the strain measuring means for operating the actuator means to move control surfaces in a direction and in an amount to produce aerodynamic forces on the wings for opposing bending, to in that manner compensate for a lack in wing stiffness, wherein the strain measuring means comprises at least one calibrated strain gage that is incapsulated within a beam member which is structurally integrated into an upper skin portion of a wing. - View Dependent Claims (3, 4, 5)
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6. In a distributed load aircraft,
a relatively limber flight sustaining wing designed for strength and not stiffness, having internal payload compartments, said wing being symmetrical with respect to a longitudinal center line; -
movable control surfaces on said wing for maneuvering the aircraft; actuator means for positioning the control surfaces; and a structural feedback system, comprising; strain measuring means carried by said wing adjacent said centerline, for measuring centerline bending moment induced strain; and actuator control means including feedback means responsive to a signal from the strain measuring means for operating the actuator means to move control surfaces in a direction and in an amount to produce aerodynamic forces on the wings for opposing bending, to in that manner compensate for a lack in wing stiffness, wherein the strain measuring means comprises at least one calibrated strain gage that is incapsulated within a beam member which is structurally integrated into an upper skin portion of the wing. - View Dependent Claims (7, 8, 9)
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10. In an aircraft of a type having a plurality of control surfaces distributed along the trailing edges of its wings, each of which is independently moved by its own actuator means, a method comprising:
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constructing the wings for strength and not stiffness, resulting in the wings being relatively limber; during use of the aircraft, measuring bending moment induced strain on the relatively limber wings and moving the control surfaces in rsponse to strain in a direction and in an amount to produce forces on the wing which will act to oppose beinding an stabilize the wing; measuring angle-of-attack forces acting on said wings, and generating a feedback signal for each control surface proportional to such forces, and utilizing such signal to move the control surfaces in a direction and in an amount for producing aerodynamic forces acting on such wing in opposition to the angle-or-attack forces; and measuring acceleration forces acting on the wings, producing a feedback signal for each control surface based thereon, and using such signals for further adjusting the control surfaces to counter such acceleration forces. - View Dependent Claims (11, 12)
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Specification