Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Reexamination Certificate
1999-07-20
2001-06-12
Poon, Peter M. (Department: 3643)
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
C244S225000
Reexamination Certificate
active
06244542
ABSTRACT:
FIELD OF THE INVENTION
The present invention relates generally to aircraft aerodynamic control surfaces, and more particularly to an aerodynamic control device configured to vertically translate.
BACKGROUND OF THE INVENTION
Conventional fixed winged aircraft are provided with a variety of aerodynamic control devices which include, for example, flaps, elevators, ailerons, trim tabs, and rudders. These control devices cooperatively operate to increase or decease lift over a given localized aerodynamic control surface for achieving pitch, yaw and roll control of the aircraft. Such control devices are used in both traditional winged and modern stealthy aircraft designs.
These control devices are typically rigid structures which are integrated into the edges of the wings or body (i.e., aerodynamic lifting surfaces) of the aircraft. The control devices are configured to deflect or rotate about an axis of rotation in a hinge-like fashion with respect to the attached aerodynamic lifting surfaces. Traditionally, these conventional control devices are actuated by the application of torque about an axis which is parallel to the trailing edge of the device. As such, the torque or power requirement of such devices is directly proportional to impinging air loads as the control device is rotated into an oncoming airflow. Thus, the greater the desired control device deflection, the greater the torque required to cause and maintain such deflection.
In addition, these conventional control devices are generally rigid structures which maintain their shape while being deflected or rotated about an axis which is generally parallel to the wing trailing edge. As such, gaps or abrupt contour changes occur at the lateral hinge line area of these conventional control devices. Further, as the control devices are rotated, chordwise gaps are formed between the edges of the hinged control devices and the adjacent fixed portions of the wing assembly.
It is contemplated that gaps, abrupt changes, or contour discontinuities occurring between the aerodynamic lifting surface and the attached control device are especially undesirable because they tend to increase aerodynamic drag and lessen the aerodynamic effectiveness of the control surface due to “leakage” at the end portions of the control device.
It is therefore evident that there exists a need in the art for an improved control device system which has a mitigated torque power requirement and mitigates the formation of gaps and abrupt surface contour changes occurring between an aerodynamic lifting surface and an attached control device.
SUMMARY OF THE INVENTION
In accordance with the present invention, there is provided an aerodynamic control device for use with an aerodynamic lifting member. The lifting member is defined by a horizontal reference plane disposed therethrough. The control device is provided with at least one support rotor extending from the lifting member. The support rotor is sized and configured to rotate about a rotor axis of rotation which is disposed generally parallel to the horizontal reference plane. The support rotor has an inboard segment which is disposed along the rotor axis of rotation and in rotational communication with the lifting member. The support rotor has an outboard segment disposed off-set from the rotor axis of rotation. The control device is further provided with a control device body which is engaged with the outboard segment of the support rotor. The control device body is sized and configured to translate generally orthogonal to the horizontal reference plane in response to rotation of the support rotor. Preferably, the control device body has a body trailing edge and axis of rotation of the support rotor is disposed generally perpendicular to the body trailing edge.
In the preferred embodiment of the present invention, rotational actuators are provided for rotating the support rotors. The actuators are disposable within the lifting member and in mechanical communication with the inboard segments of the support rotors. Further, the at least one support rotor comprises a pair of support rotors. The control device body has a slot formed therein. The outboard segments of the support rotors are sized and configured to slidably engage the slot. Opposing rotation of the support rotors causes the control device body to translate orthogonal to the horizontal reference plane. Further, the control device body is sized and configured to rotate about a roll axis which is generally parallel to the rotor axes of rotation in response to a differential amount of rotation of the support rotors.
Preferably, the aerodynamic lifting member has an indenture formed therein. The indenture is defined by first and second shoulder portions. The control device body has opposing first and second ends thereof. The control device further comprises first and second transition portions respectively attached to the first and second ends of the control device body. The first and second transition portions are attached to the first and second shoulder portions of the indenture. The first and second transition portions are sized and configured to deform in response to translation of the control device body.
In addition, the lifting member has upper and lower lifting member surfaces and the control device body has upper and lower body surfaces. The control device is further provided with upper and lower flexible outer skins. The upper flexible outer skin is attached to the upper lifting member surface and the upper body surface and the lower flexible outer skin is attached to the lower lifting member surface and the lower body surface. The outer skins are sized and configured to deform in response to translation of the control device body. In particular, the control device body has an upper deflected position with the control device body translated in a direction of the upper body surface. Similarly, the control device body has a lower deflected position with the control device body translated in a direction of the lower body surface. The upper and lower flexible outer skins are sized and configured to be disposed in tension while the control device body is in either the upper or lower deflected positions.
As such, based on the foregoing, the present invention mitigates the inefficiencies and limitations associated with prior art aerodynamic control devices. Significantly, actuation of the control device of the present invention is effectuated by the application of torque to the support rotor for translating the control device body generally orthogonal (i.e., vertically) to the horizontal reference plane of the lifting member. As further discussed below, such a configuration is particularly advantageous because the power or torque requirement of the control device is different than that of conventional prior art rotating control devices.
In general, as the deflection of a control device is increased, there is a corresponding increase in control surface area which is projected upon a fuselage station plane or that plane which is generally orthogonal to the direction of flight. As one of ordinary skill in the art can appreciate, as such projected control surface area is increased, there is a corresponding increase in the induced air load against the control device.
A conventional trailing edge control device, such as a flap, is configured to rotate about a spanwise or lateral axis with respect to the wing or trailing edge thereof. The torque or power requirement to actuate such a conventional control device is roughly proportional to the air load against the control device. In this respect, the torque or power requirement to actuate and maintain such a conventional control device in a slightly deflected position is minimal, because the projected surface area and therefore the air load thereon is minimal. Further, where the control device is in a maximum deflection position (i.e., flap fully up or flap fully down), the control device is at its maximum torque or power actuation requirement.
As mentioned above, actuation of the control device of the pres
Pauletti Steven Louis
Young Kendall Gardner
Anderson Terry J.
Hoch, Jr. Karl J.
Jakel Kevin
Northrop Grumman Corporation
Poon Peter M.
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