Patent Abstract:
An aircraft lift control system mounted on an aircraft is provided. The aircraft has at least one wing. The aircraft lift control system comprises an oscillating aero surface mounted to the aircraft wing. A resonant frame is connected to the oscillating aero surface. An actuator is mounted to the resonant frame wherein the sinusoidal force produced by the actuator on the resonant frame results in a resonant deformation in the resonant frame and resonant-sinusoidal displacement of the aero-surface.

Full Description:
[0001]    The present application is a continuation and claims priority of pending provisional patent application Serial No. 60/415,20, filed on Oct. 1, 2002, entitled “Aircraft Lift Control System”. 
     
    
     
       BACKGROUND OF THE INVENTION  
         [0002]    1. Field of the Invention  
           [0003]    This invention relates generally to an aircraft lift control system and, more particularly, the invention relates to an aircraft lift control system having cooperative, high frequency, and dynamic-resonant aero-effectors.  
           [0004]    2. Description of the Prior Art  
           [0005]    Conventional active vibration control and flutter suppression systems are servo-hydraulic. Conventional servo-hydraulic technology is burdened by a set of undesirable characteristics which effectively restrict their use to large aircraft. The servo-hydraulic based systems have multiple critical parts are therefore susceptible to multiple point failures. The hydraulic servo valves, pumps, and pipe networks are very heavy. The compressibility of the hydraulic fluid, viscous losses in the moving hydraulic fluid and bandwidth limitations in the servo valves themselves limit these systems to relatively low frequency applications.  
           [0006]    Accordingly, there exists a need for a high frequency bandwidth lift control for aircraft and other vehicles. In fact, a high frequency bandwidth lift control is of great practical importance for many civilian and military vehicles. For example, aircraft with stores, Uninhabited Air Vehicles (UAVs), and cruise missiles are all adversely affected by a lift driven divergent vibration response called flutter. Although lift control systems presently exist (e.g., servo-hydraulic systems and active structural components), these systems all have some limitations. The ideal lift control system, as disclosed by the present invention, would be small, lightweight, have fast response, consume little energy, and be transparent when not in use. Without such systems as described herein, some vehicles prone to flutter, such as high-altitude, long-endurance UAVs are seriously limited in their capabilities.  
         SUMMARY  
         [0007]    The present invention is an aircraft lift control system mounted on an aircraft. The aircraft has at least one wing. The aircraft lift control system comprises an oscillating aero surface mounted to the aircraft wing. A resonant frame is connected to the oscillating aero surface. An actuator is mounted to the resonant frame wherein the sinusoidal force produced by the actuator on the resonant frame results in a resonant deformation in the resonant frame and resonant-sinusoidal displacement of the aero-surface.  
           [0008]    The present invention further includes a method for controlling aircraft lift. The aircraft has at least one wing. The method comprising comprises mounting an oscillating aero surface to the aircraft wing, connecting a resonant frame to the oscillating aero surface, mounting an actuator to the resonant frame, and producing a sinusoidal force on the resonant frame resulting in a resonant deformation in the resonant frame and resonant-sinusoidal displacement of the aero-surface. 
       
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0009]    [0009]FIG. 1 a is a perspective view illustrating a high frequency, dynamic-resonant aero-effector where motive force from the voice coil actuator is applied parallel to the motion of the aero-surface, constructed in accordance with the present invention;  
         [0010]    [0010]FIG. 2 is a perspective view illustrating a high frequency, dynamic-resonant aero-effector where motive force from the voice coil actuator is applied transverse to the motion of the aero-surface, constructed in accordance with the present invention;  
         [0011]    [0011]FIG. 3 is a photograph showing the high frequency, dynamic-resonant aero-effector of FIG. 2;  
         [0012]    [0012]FIG. 4 is a perspective view illustrating the high frequency, dynamic-resonant aero-effector, constructed in accordance with the present invention, mounted in an aircraft wing; and  
         [0013]    [0013]FIG. 5 is a perspective view illustrating the high bandwidth lift control system, constructed in accordance with the present invention, with two cooperative high frequency dynamic-resonant aero-effectors mounted in a short section of a wing. 
     
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS  
       [0014]    As illustrated in FIGS. 1, 2, and  3 , the present invention is an active lift control system, indicated generally at  10 . The technology of the active lift control system  10  of the present invention is based on a set of cooperative high-frequency dynamic-resonant aero-effectors  12 . The dynamic-resonant aero-effectors  12  work together to dynamically modify the pressure distribution over an aero-surface  14  to rapidly change the time average lift and moment coefficients of the aero-surface  14 . The high frequency bandwidth of actuators  16  allow the actuators  16  to control rapid fluid-structure interactions such as flutter and to impose very rapid maneuvering loads on an airframe without causing structural overloads. The active lift control system  10  of the present invention will, therefore, result in higher safety margins and/or lower structural weights, thereby increasing aircraft payload and/or operational limits (range, altitude, etc.).  
         [0015]    [0015]FIG. 1 illustrates the active lift control system  10  of the present invention includes the high frequency, dynamic-resonant aero-effector  12 . The dynamic-resonant aero-effector  12  is composed of three main components: an actuator  16 , a resonant frame  18 , and an oscillating aero surface  20 . In an embodiment of the present invention, the actuator  16  is a linear voice coil actuator. It should be note, however, that while the active lift control system  10  of the present invention has been described as using a linear voice coil actuator, using any type of linear or rotary actuator of electromagnetic or piezoelectric origin is within the scope of the present invention. Furthermore, preferably, the oscillating aero-surface  20  has a width of approximately two (2″) inches and a length of approximately one (1″) inch, operating at a frequency of approximately 1890 Hz. While the present invention operates at approximately 72 Hz, it should be noted, however, that the oscillating aero-surface  20  can have a width of greater than or less than approximately two (2″) inches, a length greater than or less than approximately one (1″) inch, and operate at a frequency of greater than or less than approximately 1890 Hz. The small sinusoidal force developed by the voice coil effector on the middle mass results in a resonant deformation in the device columns and large resonant-sinusoidal displacement of the aero-surface  14 .  
         [0016]    [0016]FIG. 2 illustrates a high frequency, dynamic-resonant aero-effector  12  design where the motive force from the voice coil actuator is applied transverse to the motion of the aero-surface  14 . In this embodiment, the small sinusoidal force developed by the voice coil effector on the middle mass results in a resonant rocking motion of the central mass, large resonant deformation of the device columns, and consequently large resonant-sinusoidal displacement of the aero-surface  14 .  
         [0017]    [0017]FIG. 3 illustrates the transverse high frequency, dynamic-resonant aero-effector  12  of the present invention. The five small cylindrical features are pressure taps mounted in a cover for use in the wind tunnel.  
         [0018]    [0018]FIG. 4 illustrates the high frequency, dynamic-resonant aero-effector  12  installed in an aircraft wing. The top of the oscillating aero-surface  20  fits flush with the upper surface of the wing when the actuator  16  is unpowered. An acoustic frequency alternating current is transmitted through the voice coil device to produce a force which varies sinusoidally in time. The frequency of the voice coil alternating current is preferably selected to match the elastic resonance frequency of the resonant frame and oscillating aero-surface mass-spring system. This results in large amplitude oscillatory motion of the aero-surface  14  perpendicular to the wing surface. The top portion of oscillating aero-surface  20 , therefore, cyclically projects into the air flowing over the top surface of the wing. The projected aero-surface  20  disturbs the smooth flow over the wing, causing local flow separation and vortex structures. These flow structures reduce the vacuum pressure at local points on the wing resulting in a change in the coefficient of lift which can be used to maneuver the aircraft or to suppress aerodynamic flutter. Switching off power to the device returns the top of the oscillating aero-surface  20  to a position flush with the upper wing surface.  
         [0019]    Practical lift control systems of the present invention are composed of two or more aero-effectors operated cooperatively. FIG. 5 illustrates an example high bandwidth lift control system  10  composed of two cooperative high frequency dynamic-resonant aero-effectors  12  mounted in a section of a wing. The individual operation of each device  12  is the same as previously described, however, the specific displacement, phase relationship, and operation frequency of the second device is selected to amplify the lift modification effects of the first device  12 . A large number of small-scale devices  12  could be combined in this manner. A wave-like flow disturbance structure originates at the first device  12  and then very rapidly grows as subsequent effectors  12  cause flow disturbance resonance. The attenuation of the lift effects would follow a similar spatial-time pattern. The cyclic displacement of each of the aero-effector devices  12  would be actively canceled resulting in a return to smooth flow over the wing.  
         [0020]    The present invention leads to structural weight reductions on high performance unmanned air vehicles, as flutter divergence would be actively controlled. Presently, these aircraft must be over-built to protect against flutter which results in a significant weight increase. The present invention could also be used for cruise missiles and possibly high performance, light civilian jet aircraft. Since divergent flutter vibration often leads to the destruction of an aircraft, the present invention suppresses the divergent flutter vibration with minimal system weight and power demands.  
         [0021]    The foregoing exemplary descriptions and the illustrative preferred embodiments of the present invention have been explained in the drawings and described in detail, with varying modifications and alternative embodiments being taught. While the invention has been so shown, described and illustrated, it should be understood by those skilled in the art that equivalent changes in form and detail may be made therein without departing from the true spirit and scope of the invention, and that the scope of the present invention is to be limited only to the claims except as precluded by the prior art. Moreover, the

Technology Classification (CPC): 1