• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    FLUID-DYNAMIC BODY OF VARIABLE CURVATION USING OPTIMIZED INTELLIGENT MATERIALS The present invention relates to a system and methods for the configuration of a fluid-dynamic body that are disclosed. A curvature of a fluid-dynamic body is configured by activating an alloy actuator with memory coupled to the fluid-dynamic body.
    公开号:BR102012020561B1
    申请号:R102012020561-0
    申请日:2012-08-16
    公开日:2021-01-12
    发明作者:Moushumi Shome；Frederick T. Calkins；James Henry Mabe；Matthew Todd Grimshaw
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    [0001] [001] The incorporations of this disclosure generally concern the fluid dynamic project. More particularly, the embodiments of the present disclosure concern fluid-dynamic control surfaces. BACKGROUND
    [0002] [002] In the area of aeronautical engineering and aeronautics, the curvature comprises an asymmetry between an upper surface and a lower surface of an airfoil. A curvature of an airfoil can be defined by a curvature line, which is the curve that is halfway between the upper surface and the lower surface of the airfoil. Curvature is generally an important contributory factor that determines an aircraft stall speed. A change in the curvature of an airfoil can change an aircraft stall speed. SUMMARY
    [0003] [003] A system and methods for configuring a fluid-dynamic body are disclosed. A fluid-dynamic body is formatted within a first curvature configuration, and the fluid-dynamic body is formed within a second curvature configuration using an alloy actuator with shape memory.
    [0004] [004] In an embodiment, a method for configuring a fluid-dynamic body configures a curvature of a fluid-dynamic body by activating an alloy actuator with memory coupled to the fluid-dynamic body.
    [0005] [005] In another embodiment, a fluid-dynamic body system of variable curvature comprises a fluid-dynamic body and an alloy actuator with shape memory. The fluid-dynamic body is operable to assume a first curvature configuration and a second curvature configuration. The shape memory alloy actuator is operable to configure the fluid dynamic body in the first curvature configuration in response to a first temperature control. The alloy actuator with shape memory is operable, moreover, to configure the fluid dynamic body in the second curvature configuration in response to a second temperature control.
    [0006] [006] In yet another embodiment, a method for providing a fluid-dynamic body system with variable curvature provides an operable fluid-dynamic body to assume a first curvature and a second curve configuration, and couples an alloy actuator with memory to the fluid-dynamic body. The shape memory alloy actuator is operable to configure the fluid dynamic body in the first curvature configuration in response to a first temperature control, and to configure the fluid dynamic body in the second curvature configuration in response to a second temperature control.
    [0007] [007] This summary is provided to introduce a selection of concepts in a simplified way which are described in detail below in the detailed description. This summary is not intended to identify the key characteristics or essential characteristics of the claimed matter, nor is it intended to be used as an aid in determining the scope of the claimed matter. BRIEF DESCRIPTION OF THE DRAWINGS
    [0008] [008] A more complete understanding of the incorporations of the present disclosure can be obtained by consulting the detailed description and claims when considered together with the figures below, where similar reference numbers refer to similar elements throughout the figures. Numbers are provided to facilitate understanding of the disclosure without limiting the scope, scope, scale, or applicability of the disclosure. The drawings are not necessarily made to scale.
    [0009] [009] Figure 1 is an illustration of an exemplary aircraft production flow diagram and service methodology.
    [0010] [0010] Figure 2 is an illustration of an example block diagram of an aircraft.
    [0011] [0011] Figure 3 is an illustration of an exemplary variable-curvature fluid-dynamic body system according to the embodiment of the disclosure.
    [0012] [0012] Figure 4 is an illustration of an airfoil with variable curvature exemplary according to the incorporation of the disclosure.
    [0013] [0013] Figure 5 is an illustration of an exemplary variable curvature structure comprising a plurality of shape memory alloy hinge actuators showing curvature profiles according to the embodiment of the disclosure.
    [0014] [0014] Figure 6 is an illustration of an exemplary variable curvature structure comprising a plurality of shape hinge alloy actuators showing rudder control cables according to the embodiment of the disclosure.
    [0015] [0015] Figure 7 is an illustration of an alloy compound panel actuated with memory in an exemplary manner in an unactivated state according to an embodiment of the disclosure.
    [0016] [0016] Figure 8 is an illustration of a shape memory alloyed composite panel showing the shape memory alloyed composite panel of Figure 7 in a state acted upon according to an embodiment of the disclosure.
    [0017] [0017] Figure 9 is an illustration of an exemplary support surface assembly comprising an alloy frame actuator with shape memory in accordance with an embodiment of the disclosure.
    [0018] [0018] Figure 10 is an illustration of an expanded view of an alloy frame actuator of Figure 9 according to an embodiment of the disclosure.
    [0019] [0019] Figure 11 is an illustration of an exemplary flowchart showing the process of configuring a fluid-dynamic body according to an embodiment of the disclosure.
    [0020] [0020] Figure 12 is an illustration of an exemplary flowchart showing a process for providing a fluid-dynamic body system of variable curvature according to an embodiment of the disclosure. DETAILED DESCRIPTION
    [0021] [0021] The following detailed description is exemplary in nature and is not intended to limit the disclosure or the application and uses of the incorporations of the disclosure. Descriptions of specific devices, techniques and applications are provided as examples only. Modifications to the examples described herein will be readily apparent to those of ordinary skill in the art, and the general principles defined in this document may be applied to other examples and applications without departing from the spirit and scope of the disclosure. The present disclosure must be consistent with the scope agreed with the claims, and not limited to the examples described and shown in this document.
    [0022] [0022] Embodiments of the disclosure can be described here in terms of components of functional and / or logic blocks and various processing steps. It should be appreciated that such block components can be realized by any number of physical elements, software, and / or fixed program components configured to perform the specified functions. For the sake of brevity, conventional techniques and components related to aerodynamics, shape memory alloys, vehicle structures, fluid dynamics, flight control systems, and other functional aspects of the systems described in this document (and the components operating systems) may not be described in detail in this document. In addition, those skilled in the art will understand that embodiments of this disclosure may be practiced in conjunction with a variety of physical elements and software, and that the embodiments described in this document are simply exemplary embodiments of the disclosure.
    [0023] [0023] Ways of carrying out the disclosure are described here in the context of a practical non-limiting application, namely, an aircraft airfoil. Embodiments of the disclosure, however, are not limited to such applications in aircraft as airfoils, and the techniques described here can also be used in other applications. For example, but without limitation, incorporations may be applicable to hydrofoils, wind turbines, tidal power turbines, etc.
    [0024] [0024] As would be evident to a normal person skilled in the art after reading this description, the following are examples and embodiments of the disclosure and are not limited to working according to these examples. Other incorporations can be used and structural changes can be made without departing from the scope of the exemplary embodiments of the present disclosure.
    [0025] [0025] Referring more specifically to the drawings, incorporations of the disclosure can be described in the context of an exemplary aircraft manufacturing and service method 100 (method 100) as shown in Figure 1 and an aircraft 200 as shown in Figure 2. During the pre -production, method 100 may include specification and design 104 of aircraft 200, and acquisition of material 106. During production, the manufacture of component and subset 108 (process 108) and integration of system 110 of aircraft 200 takes place. aircraft 200 may undergo certification and delivery 112 in order to be placed into service 114. While in service by a customer, aircraft 200 is scheduled for routine maintenance and overhaul 116 (which may also include modification, reconfiguration, remodeling, and so on).
    [0026] [0026] Each of the method 100 processes can be performed or performed by a system builder, a third party, and / or an operator (for example, a customer). For the purposes of this description, a system builder may comprise, for example, but without limitation, any number of aircraft manufacturers and subcontractors of the main systems; a third party may comprise, for example, but without limitation, any number of sellers, subcontractors and suppliers; and an operator can understand, for example, without limitation, an airline, leasing company, military entity, service organization, etc.
    [0027] [0027] As shown in Figure 1, the aircraft 200 produced by method 100 can comprise a structure 218 with a plurality of systems 220 and an interior 222. Examples of high level systems of systems 220 comprise one or more of a system of propulsion 224, an electrical system 226, a hydraulic system 228, an environmental system 230, and a fluid-dynamic body of variable curvature using an optimized system of intelligent materials 232. Any number of other systems can also be included. Although an aerospace example is shown, the incorporations of the disclosure can be applied to other industries.
    [0028] [0028] Apparatus and methods incorporated in this document can be used in any one or more steps of method 100. For example, the components or subassemblies corresponding to the production of process 108 can be manufactured or manufactured in a similar way to the components or subassemblies produced while aircraft 200 is in service. In addition, one or more incorporations of the apparatus, incorporations of the method, or a combination thereof can be used during the production phases of process 108 and system integration 110, for example, by substantially speeding up assembly or reducing the cost of an aircraft 200. Likewise, one or more embodiments of the apparatus, incorporations of the method, or a combination thereof may be used while the aircraft 200 is in service, for example, and without limitation, for maintenance and overhaul 116.
    [0029] [0029] An alloy with shape memory (SMA) resembles its original shape after being deformed from its original shape. An SMA returns to its original shape when it is heated (shape memory effect) or when the deformation pressure is removed (super-elasticity). An SMA that returns to its original shape when heated is a unidirectional SMA. A two-way SMA resembles two different shapes: one shape, at a relatively low temperature, and another shape at a relatively high temperature. Defining the two forms by thermomechanical processing is known as SMA "training". An SMA with the two-way set is known as a "trained" SMA. The shape properties of a trained SMA result from a temperature-initiated martensitic phase transformation from a low symmetry (martensite) to a highly symmetrical crystal structure (austenite).
    [0030] [0030] The temperatures at which SMA changes its structure depends on a particular alloy, and can be adjusted by varying a chemical mixture and thermomechanical processing. Some common SMA materials may comprise, for example, but without limitation, copper-zinc-aluminum, copper-aluminum-nickel, nickel-titanium-platinum, nickel-titanium-palladium, nickel-titanium - hafnium, nickel-titanium ( NiTi or Nitinol), and the like. NiTi SMA alloys generally have higher mechanical properties than copper-based SMA's, but they are also generally more expensive. SMA actuators according to various embodiments of the disclosure can be made, for example, but without limitation, from any of these SMA materials mentioned above.
    [0031] [0031] Figure 3 is an illustration of a system 300 (system 300) of fluid-dynamic body of variable curvature exemplary according to the incorporation of the disclosure. The system 300 can comprise a fluidodynamic body 302 (airfoil 302), a shape memory alloy actuator 304 (SMA), and a controller 308. The airfoil 302 and the SMA 304 actuator can be coupled to each other via various coupling means 306. Fluid dynamic body 302, an airfoil of variable curvature 302, a fluidodynamic body with variable curvature 302, and airfoil 302 can be used interchangeably in this document.
    [0032] [0032] Airfoil 302 comprises variable curvature and, as such, is also referred to as airfoil 302 with variable curvature. The variable curvature airfoil 302 is operable to configure a shape of a curvature 414 (Figure 4) for a first curvature configuration using the SMA 304 actuator in response to a first control temperature. The variable curvature airfoil 302 is further operable to configure a curvature shape 414 (Figure 4) to reshape the first curvature configuration to a second curvature configuration using the SMA 304 actuator in response to a second control temperature. In this way, a curvature profile of the variable curvature airfoil 302 changes from a fixed curvature profile before an actuation of the SMA 304 actuator to a variable curvature profile after the actuation of the SMA 304 actuator. The curvature 414 (Figure 4 ) of the airfoil 302 of variable curvature can be defined by a medium curvature line 410 (Figure 4), which is the curve that is halfway between an upper surface 420 (Figure 4) and a lower surface 422 (Figure 4) airfoil 302 with variable curvature (airfoil 400 in Figure 4). As mentioned above, a change in the curvature of the 302/400 variable curvature wing can alter an aircraft stall speed 200.
    [0033] [0033] The airfoil 302/400 of variable curvature may comprise a cross section of a support surface and / or a cross section of a control surface of a fluid dynamic body. The control surface can comprise, for example, but without limitation, a reed, aileron, tail, rudder, lift, flap, airplane speed reducer, elevon, etc. The support surface may comprise, for example, but without limitation, a wing, a front control surface, a horizontal stabilizer, etc.
    [0034] [0034] The SMA 304 actuator is operable to vary a shape (ie, bend, deflect, change shape) of a curvature in response to heating and / or cooling. In this way, curvature 414 can change shape to alter a flow along a variable curvature 302/400 airfoil. In one embodiment, the SMA 304 actuator is controlled via a passive control mechanism to control the shape of curvature 414 based on an ambient temperature corresponding to an altitude in a flight condition. In another embodiment, controller 308 may include or be realized as a controller (connected to the aircraft systems), to facilitate control of a deformation (i.e., changing the shape) of curvature 414, as explained in more detail below.
    [0035] [0035] The SMA 304 actuator according to various embodiments of the disclosure can be made, for example, but without limitation, from any of these SMA materials mentioned above. According to the various incorporations, the SMA 304 actuator comprises an SMA 502/504/506/602/604 hinge (Figures 5-6), an SMA actuated composite panel 700 (Figure 7), an alloy panel with shape memory, an alloy support structure with shape memory, and an SMA support actuator 902 (Figure 9) as explained in more detail below. However, the SMA 304 actuator is not limited to the SMA 502/504/506/602/604 hinge, the SMA actuated composite panel 700, and the SMA 902 actuator of the frame can also comprise other SMA structures operable for vary the shape of curvature 414.
    [0036] [0036] Various coupling means 306 may comprise any coupling technology suitable for use by the system 300. The various coupling means 306 may comprise, for example, but without limitation, gluing, welding, and the like.
    [0037] [0037] Controller 308 may comprise, for example, but without limitation, a processor module 310, a memory module 312, and the like. Controller 308 can be implemented as, for example, but, without limitation, a part of an aircraft system, an aircraft centralized processor, a subsystem computing module dedicated to the variable curvature airfoil 302, and etc.
    [0038] [0038] Controller 308 is configured to thermally control the SMA 304 actuator to vary the shape of curvature 414 according to the various operating conditions. Operating conditions may comprise, for example, but without limitation, flight conditions, ground operations and etc. Flight conditions may comprise, for example, but without limitation, takeoff, navigation, approach, landing, etc. .. Ground operations can include, for example, but without limitation, air braking after landing and so on. Controller 308 can be located remotely from the SMA 304 actuator, or it can be coupled to the SMA 304 actuator. The SMA actuator 304 is controllable by adjusting a temperature between the end temperatures of martensite and austenite in such a way that the shapes between the extreme states actuated can be selected and maintained using the 308 controller.
    [0039] [0039] In operation, controller 308 can control the SMA 304 actuator by monitoring the temperature of the SMA 304 actuators and by heating and / or cooling at least a part of the SMA 304 actuator as needed. Heating / cooling of the SMA 304 actuator can be provided, for example, but without limitation, by the aircraft's heating / cooling systems, etc. For example, a heater can use an electric heating element and a controllable current source where a temperature is proportional to a current applied to the heating element. In this way, controller 308 determines a temperature based on a current flight condition, and provides heating / cooling to activate / deactivate the SMA 304 actuator. This allows controller 308 to vary the shape of curvature 414 in accordance with flight conditions. for example, whether an aircraft is approaching, landing, taking off or cruising. Controller 308 can be used to optimize a shape of curvature 414 for noise, lift, drag, etc.
    [0040] [0040] In one embodiment, the 308 controller is configured to change the temperature of the SMA 304 actuators in a non-uniform manner. Controller 308 can vary the temperatures of the respective segments of the SMA 304 actuator separately from each other, where each of the temperatures is different from each other. In this way, the different regions of the SMA 304 actuator can be heated to different temperatures, through controller 308 to effect different levels of change in the shape of curvature 414 in different regions of the variable curvature airfoil 302. For example, different SMA actuators can be heated in different amounts to maintain a desired shape.
    [0041] [0041] The processor module 310 comprises the processing logic that is configured to perform the functions, techniques, and processing tasks related to the operation of the system 300. In particular, the processing logic is configured to support the system 300 described in this document. For example, the processor module 310 can drive the SMA 304 actuator to vary the shape of curvature 414 based on the various operating conditions.
    [0042] [0042] The processor module 310 can be implemented, or realized, with a general purpose processor, an addressable content memory, a digital signal processor, an application specific integrated circuit, a programmable port arrangement in the field, any device appropriate programmable logic, discrete port or transistor logic, discrete hardware components, or any combination thereof, designed to perform the functions described in this document. In this way, a processor can be realized as a microprocessor, a controller, a micro controller, a state machine, or the like. A processor can also be implemented as a combination of computing devices, for example, a combination of a digital signal processor and a microprocessor, and a microprocessor, a plurality of microprocessors, one or more microprocessors together with a signal processor core digital, or any other configuration.
    [0043] [0043] The 312 memory module may comprise a data storage area with memory formatted to support system operation 300. The 312 memory module is configured to store, maintain and supply data as needed to support system functionality 300. For example, memory module 312 can store flight configuration data, control temperature data, etc.
    [0044] [0044] In practical embodiments, the memory module 312 may comprise, for example, but without limitation, a non-volatile storage device (non-volatile semiconductor memory, hard disk device, optical disk device, etc.). ), a random access storage device (e.g., SRAM, DRAM), or any other form of storage medium known in the art.
    [0045] [0045] The controller 312 can be coupled to the processor module 310, and configured to store, for example, however, without limitation a database, etc. In addition, the memory module 312 can represent a dynamically updated database containing a database update table, etc. The memory module 312 can also store a computer program that is executed by the processor module 310 , an operating system, an application program, the experimental data used to execute a program, and so on.
    [0046] [0046] Memory module 312 can be coupled to processor module 310 such that processor module 310 can read information and write information to memory module 312. For example, processor module 310 may have access to the memory module 312 to access an aircraft speed, flight control ground position, an angle of attack, a Mach number, an altitude, etc.
    [0047] [0047] As an example, the processor module 310 and memory module 312 can reside in the specific integrated circuits of the respective applications (ASIC's). The memory module 312 can also be integrated into the processor module 310. In one embodiment, the memory module 312 may comprise a cache memory for storing temporary variables or other intermediate information during the execution of instructions to be executed by the processor module 310.
    [0048] [0048] Figure 4 is an illustration of an exemplary variable curvature airfoil 400 (airfoil 400) according to an embodiment of the disclosure. The airfoil with variable curvature 400 can comprise a leading edge 402, the tail edge 404, the upper surface 420, the lower surface 422. The airfoil with variable curvature 400 comprises the SMA 304 actuator (Figure 3). As explained in more detail below, the SMA 304 actuator can be coupled (for example, via coupling means 306) in various ways to the variable curvature airfoil 400. The SMA 304 actuator can configure the variable curvature airfoil 400 in a first curvature configuration 406 and in a second curvature configuration 408. The first curvature configuration 406 may comprise, for example, but without limitation, a quiescent SMA state, a martensitic SMA state, an austenitic SMA state, and the like , of the SMA 304 actuator. The second curvature configuration 408 may comprise, for example, but without limitation, a quiescent SMA state, a martensitic SMA state, an austenitic SMA state, and the like, of the SMA 304 actuator.
    [0049] [0049] The airfoil with variable curvature 400 can be characterized by the medium curvature line 410 (curvature line) and a rope line 412. The curvature line 410 can comprise a curve halfway between the upper surface 420 and the surface lower upper 422 of the airfoil with variable curvature 400 featuring an asymmetry between the upper surface 420 and the lower surface 422. The curvature 414 of the airfoil with variable curvature 400 can be defined by a curvature line 410 and the chord line 412 defining a shape of curvature line 410.
    [0050] [0050] Figure 5 is an illustration of an exemplary variable curvature structure 500 comprising a plurality of SMA hinges 502/504/506 showing curvature profiles 508 and 510 (curvature lines) according to an embodiment of the disclosure. The variable curvature structure 500 is operable to couple with the dynamic fluid body 302 (Figure 3). The variable curvature structure 500 comprises a first SMA hinge 502, a second SMA 504 hinge, a third SMA 506 hinge, a first aerodynamic structure 518, a second aerodynamic structure 520, and a third aerodynamic structure 522.
    [0051] [0051] The first SMA 502 hinge is attached to the first aerodynamic structure 518, and the second SMA 504 hinge is attached to the first aerodynamic structure 518 and the second aerodynamic structure 520. The third SMA 506 hinge is attached to the second aerodynamic structure 520 and the third aerodynamic structure 522. The first SMA 502 hinge, the second SMA 504 hinge, the third SMA 506 hinge, are each operable to activate (eg, twist) in response to a first control temperature of SMA activation control, a second SMA activation control temperature, a third SMA activation control temperature, respectively. The first SMA 502 hinge, the second SMA 504 hinge, the third SMA 506 hinge can be controlled individually or in combination. The first SMA activation control temperature, the second SMA activation control temperature, the third SMA activation control temperature can be controlled individually (for example, at separate individual temperatures) or in combination (for example, two or more may have a temperature in common).
    [0052] [0052] The variable curvature structure 500 is operable to change a shape of curvature 414 (Figure 4) and thus a shape of a first line of curvature 508 by remodeling a first configuration of curvature 512 to a second configuration of curvature 516 in response to activation of the first SMA 502 hinge, the second SMA 504 hinge, and the third SMA 506 hinge. The variable curvature structure 500 comprises a first curvature line 508 in the first curvature configuration 512, and a second curvature line 510 in the second curvature configuration 516. The variable curvature structure 500 is further operable to change into various shapes such as a third curvature configuration 514 between the first curvature configuration 512 and the second curvature configuration 516.
    [0053] [0053] Figure 6 is an illustration of an exemplary variable curvature structure 600 comprising a plurality of alloy hinge actuators with 602/604 shape memory according to the embodiment of the disclosure. The variable curvature structure 600 is operable to couple with the dynamic fluid body 302 (Figure 3). The variable curvature structure 600 comprises a first SMA hinge 602, a second SMA hinge 604, a first aerodynamic structure 606, a second aerodynamic structure 608.
    [0054] [0054] The first SMA 602 hinge is attached to the first aerodynamic structure 606, and the second SMA 604 hinge is attached to the first aerodynamic structure 606 and the second aerodynamic structure 608. The first SMA 602 hinge can also be attached to the second to the fluidodynamic body 302. The first SMA 602 hinge and the second SMA 604 hinge are each operable to activate (eg, twist) in response to a first SMA activation control temperature and a second control temperature of activation of SMA, respectively. The first SMA 602 hinge and the second SMA 604 hinge can be controlled individually or in combination. The first SMA activation control temperature and the second SMA activation control temperature can be controlled individually (for example, at separate individual temperatures) or in combination (for example, two or more may have a temperature in common).
    [0055] [0055] The variable curvature structure 500 is operable to change a shape of curvature 414 (Figure 4) by remodeling a first configuration of curvature 610 to a second configuration of curvature 612 in response to the activation of the first hinge of SMA 602 and the second SMA hinge 604. The first curvature configuration 610 comprises the first aerodynamic structure 606 at a first angle 618 with respect to the second aerodynamic structure 608. The second curvature configuration 612 comprises the first aerodynamic structure 606 at a second angle 620 with respect to the second aerodynamic structure 608. The variable curvature structure 600 comprises a first rope line 614 in the first curvature configuration 610, and a second rope line 616 in the second curvature configuration 612.
    [0056] [0056] In the embodiments shown in Figures 5-6, up to three SMA hinges are used on 500 and 600 curved structures. However, any number of SMA hinges 502, 504, 506, 602, and 604 can be used. In addition, placing the SMA hinges 502, 504, 506, 602, 604 and at different hinge locations (for example, hinge locations of compound) enables efficient load transfer between variable curvature surfaces comprising variable curvature structures 500 and 600. The surfaces of variable curvature may comprise, for example, but not limited to, wing surfaces, control surfaces, the upper surface 420, the lower surface 422, and the like. The SMA hinges 502, 504, 506, 602, 604 each may need to be carefully designed between the composite panels of the variable curvature surfaces so that the performance of the composite panels is efficiently activated during a deformation process.
    [0057] [0057] Figure 7 is an illustration of an example composite memory actuated 700 (SMA 700 panel) composite panel in an unactivated state 710 according to an embodiment of the disclosure. The composite panel actuated by SMA 700 may comprise a first layer of composite laminate 712 and a second layer of composite laminate 714, and an SMA actuator 704/706/708 (alloy actuated panel with shape memory) sandwiched between the first layer of composite laminate 712 and the second layer of composite laminate 714. The SMA actuator 704/706/708 may comprise, for example, but without limitation, an SMA layer, an SMA rod, an SMA sheet, a mesh of SMA, and etc.
    [0058] [0058] Figure 8 is an illustration of the exemplary SMA composite panel 700 of Figure 7 in a state acted upon according to an embodiment of the disclosure. The composite panel actuated by SMA 700 can be actuated to form curvature 414 of the variable curvature airfoil 400 (Figure 400). In one embodiment, a composite coating of the variable curvature airfoil 400 can be filled with layers of SMA 704/706/708 material. The composite panel actuated by SMA 700 (actuator of SMA 304) can be placed, for example, without limitation, between layers of compound as a cut-out style, a style between layers, etc., to achieve an adaptive aptitude specifically where a shape-shifting ability is desired for a final variable curvature profile. For example, multiple layers of SMA film can be placed at various locations on the variable curvature airfoil 400 where greater deformation of surfaces comprising surface 420 and surface 422 is desired.
    [0059] [0059] Figure 9 is an illustration of an exemplary support surface assembly 900 comprising an SMA 902 frame actuator (alloy frame structure with shape memory) according to an embodiment of the disclosure. Figure 10 is an illustration of an expanded view 1000 of the SMA actuator 902 of the frame of Figure 9 according to an embodiment of the disclosure.
    [0060] [0060] The support surface assembly 900 comprises the upper surface 420 (removed in Figure 9 to show the SMA actuator of frame 902), and the lower surface 422 of the variable curvature airfoil 302/400. The SMA actuator of frame 902 can be located, for example, but, without limitation, near a leading edge 402 as shown in Figure 9, a trailing edge 404 (Figure 4) of the variable curvature airfoil 302/400, and etc. In the embodiment shown in Figure 9, the SMA actuator of frame 902 changes the shape, in response to a change in temperature, which bends leading edge 402 (for example, leading edge of the wing) by varying curvature 414 (Figure 4). The 902 frame SMA actuator can be made thick or thin, longer or shorter depending on the design criteria of the variable curvature, and can be placed anywhere suitable for the 300 system operation. Any number of SMA actuator of frame 902 can be used to shape curvature 414.
    [0061] [0061] Using the SMA actuator of frame 902, the 302/400 variable curvature airfoil (Figures 3-4) is operable to change a shape of curvature 414 to reshape an initial curvature configuration (for example, the first configuration of curvature curvature 406 in Figure 4) for a final variable curvature configuration (for example, the second curvature configuration 408 in Figure 4) using the SMA actuator of frame 902 in response to a first temperature control and a second control temperature , respectively. In this way, a curvature profile of the variable curvature airfoil 302 changes from an initial curvature profile (for example, a first curvature line 508 in Figure 5) before an actuation of the SMA actuator 902 of the frame to a curvature profile final variable (for example, a second curvature line 510) after actuation of the SMA 902 actuator of the frame.
    [0062] [0062] Figure 10 is an illustration of an expanded view of the SMA 902 actuator of the frame of Figure 9 according to an embodiment of the disclosure.
    [0063] [0063] Figure 11 is an illustration of an exemplary flowchart showing the process of configuring a fluid dynamic body 1100 (process 1100) according to an embodiment of the disclosure. The various tasks performed in connection with the 1100 process can be performed mechanically, by software, hardware, unalterable printed program, computer-readable software, computer-readable storage medium, or any combination of these. It should be appreciated that process 1100 can include any number of additional or alternative tasks, the tasks shown in Figure 11 do not need to be performed in the order illustrated, and process 1100 can be incorporated into a more comprehensive procedure or a process having additional functionality not described in detail in this document.
    [0064] [0064] For illustrative purposes, the following description of process 1100 may refer to elements mentioned above in relation to Figures 1-10. In practical incorporations, parts of process 1100 can be performed by various elements of system 300, such as: fluid dynamic body 302, SMA 304 actuator, controller 308, etc. It should be appreciated that process 1100 can include any number of additional or alternative tasks, the tasks shown in Figure 11 do not need to be performed in the order illustrated, and the 1100 process can be incorporated into a more comprehensive procedure or a process having additional functionality not described in detail in this document.
    [0065] [0065] Process 1100 can begin by configuring a curvature such as curvature 414 of a fluid-dynamic body such as fluid-dynamic body 302 by activating a memory shaped actuator such as the SMA 304 actuator coupled with the fluid-dynamic body 302 (task 1102).
    [0066] [0066] Process 1100 may continue through the configuration of the fluid dynamic body 302 in a first curvature configuration such as the first curvature configuration 406 (task 1104).
    [0067] [0067] Process 1100 can continue through the configuration of the fluid dynamic body 302 in a second curvature configuration such as the second curvature configuration 408 using the SMA 304 actuator (task 1106).
    [0068] [0068] Process 1100 can continue through the configuration of the fluidodynamic body 302 using a memory-shaped alloy frame structure such as the SMA actuator 902 of the frame coupled to the fluidodynamic body 302 (task 1108).
    [0069] [0069] Figure 12 is an illustration of an exemplary flowchart showing a process 1200 for providing a fluid-dynamic body system of variable curvature such as system 300 according to an embodiment of the disclosure. The various tasks performed in connection with the 1200 process can be performed mechanically, by software, hardware, unalterable printed program, computer-readable software, computer-readable storage medium, or any combination of these. It should be appreciated that process 1200 can include any number of additional or alternative tasks, the tasks shown in Figure 12 do not need to be performed in the order illustrated, and process 1200 can be incorporated into a more comprehensive procedure or a process having additional functionality not described in detail in this document.
    [0070] [0070] For illustrative purposes, the following description of process 1200 can refer to elements mentioned above in relation to Figures 110. In practical embodiments, parts of process 1200 can be performed by several elements of system 300, such as: the body fluidodynamic 302, SMA 304 actuator, controller 308, etc. It should be appreciated that process 1200 can include any number of additional or alternative tasks, the tasks shown in Figure 12 do not need to be performed in the order illustrated, and the process 1200 can be incorporated into a more comprehensive procedure or a process having additional functionality not described in detail in this document.
    [0071] [0071] Process 1200 can begin by providing a fluid dynamic body, such as fluid dynamic body 302 operable to assume a first curvature configuration 302 such as the first curvature configuration 406 and a second curvature configuration according to the second configuration curvature 408 (task 1202). The fluidodynamic body 302 can comprise, for example, but without limitation, an airfoil, a wing, an anchor, a small wing, an elevator, a rudder, an aileron, an elevon, etc.
    [0072] [0072] Process 1200 can be continued by coupling an alloy actuator with memory such as the SMA 304 actuator to the fluid dynamic body 302 (task 1204). The shape memory alloy actuator is operable to configure the fluidodynamic body 302 in the first curvature configuration 406 in response to a first temperature control, and to configure the fluidodynamic body 302 in the second curvature configuration 408 in response to a second temperature control. temperature. The SMA 304 actuator can comprise the SMA 502/504/506/602/604 hinge (Figures 5-6), the SMA-actuated composite panel 700 (Figure 7), and the SMA 902 actuator of the frame (Figure 9 ) as explained in more detail below.
    [0073] [0073] Process 1200 can continue by coupling the SMA 304 actuator to a first aerodynamic structure such as the first aerodynamic structure 606 and a second aerodynamic structure such as the second aerodynamic structure 608 (task 1206).
    [0074] [0074] Process 1200 can continue by gluing the SMA 304 actuator between a first layer of composite laminate such as the first layer of composite laminate 712 and a second layer of composite laminate such as the second layer of composite laminate 714 (task 1208 ).
    [0075] [0075] In this way, the forms of incorporation of the disclosure provide several means for configuring a curvature of a fluid-dynamic body using SMA actuators.
    [0076] [0076] In this document, the terms "computer program products", "computer-readable medium", "computer-readable storage medium" and the like can generally be used to refer to media such as, for example, memory , storage devices, or storage unit. These and other forms of computer-readable media may be involved in storing one or more instructions for use by processor module 310 to cause processor module 310 to perform specified operations. Such instructions, usually referred to as "computer program code" or "program code" (which can be grouped together in the form of computer programs or other groupings), when executed, enable system 700 power usage programming methods.
    [0077] [0077] The above description refers to the elements or nodes or resources being "linked" or "coupled" together. As used in this document, unless expressly stated otherwise, "connected" means that an element / node / resource is directly linked to (or communicates directly with) another element / node / resource, and not necessarily mechanically. Likewise, unless expressly stated otherwise, "coupled" means that an element / node / resource is directly or indirectly linked to (or communicates directly or indirectly with) another element / node / resource, and not necessarily mechanically. Thus, although Figures 2-10 describe exemplary modalities of the elements, additional intervening elements, devices, resources or components may be present in an embodiment of the disclosure.
    [0078] [0078] Terms and expressions used in this document, and variations thereof, unless expressly provided otherwise, should be interpreted as open in opposition to the limitation. As examples of the above: the term "including" should be read as meaning "including, without limitation" or the like; the term "example" is used to provide exemplary cases of the item under discussion, not an exhaustive or limiting list thereof, and adjectives such as "conventional", "traditional", "normal", "standard", "known" and terms of similar meaning should not be interpreted as limiting the item described for a given period of time or to an item available from a given time, but should be read to cover conventional, traditional, normal, or standard technologies that may be available or be known now or at any time in the future.
    [0079] [0079] Likewise, a group of items related to the conjunction "e" should not be read as requiring that each and every one of these items be present in the grouping, but should preferably be read as "and / or" unless that expressly stated otherwise. Similarly, a group of items related to the conjunction "o" should not be read as requiring mutual exclusivity between that group, but should preferably also be read as "and / or" unless expressly stated otherwise. In addition, although items, elements or components of the disclosure may be described or claimed in the singular, the plural is considered to be within the scope of the disclosure, unless the limitation to the singular is explicitly indicated. The presence of expanding words and phrases such as "one or more", "at least", "but not limited to" or other type of phrases, in some cases should not be read in the sense that the narrower case is intended or required in instances where such extension phrases may be missing.
    [0080] [0080] As used herein, unless expressly stated otherwise, "operable" means in a condition to be used, fit or ready for use or service, usable for a specific purpose, and capable of performing a function mentioned or desired described in this document. In relation to systems and devices, the term "operable" means that the system and / or the device is fully functional and calibrated, comprises elements, and meets the applicable operational requirements to perform a function mentioned when activated. In relation to systems and circuits, the term "operable" means that the system and / or the circuit is fully functional and calibrated, comprises logic, and meets the applicable operational requirements to perform a function mentioned when activated.
    权利要求:
    Claims (7)
    [0001]
    Method for configuring an aircraft dynamic fluid body (200), the method comprising: configuring a curvature of a dynamic fluid body (302) by activating an alloy actuator with shape memory (304) coupled to the dynamic fluid body (302), in which the alloy actuator with shape memory (304) comprises at least a shape memory alloy hinge (602, 604), and a controller (308) controls the shape memory alloy actuator (304); configuring (1104) the dynamic fluid body (302) in a first curvature configuration (610), wherein the dynamic fluid body (302) is coupled to a variable curvature structure (600) comprising a first memory alloy hinge shape (602), a second shape memory alloy hinge (604), a first aerodynamic structure (606) and a second aerodynamic structure (608), where the first shape memory alloy hinge (602) is coupled to the fluidodynamic body (302) and the first aerodynamic structure (606), and in which the second shape memory alloy hinge (604) is coupled to the first aerodynamic structure (606) and the second aerodynamic structure (608), in that the first shape memory alloy hinge (602) and the second shape memory alloy hinge (604) are operable each to twist in response to a first shape memory alloy activation control temperature and a second control temperature alloy activation with shape memory, respectively; and configure (1106) the fluid dynamic body (302, 400) in a second curvature configuration (612) using the shape memory alloy actuator (304), in which the first shape memory alloy hinge (602) and the second shape memory alloy hinge (604) are individually controlled, and the first shape memory alloy activation control temperature and the second shape memory alloy control control temperature are individually controlled at temperatures separate individual; characterized by the fact that the controller (308) controls the alloy actuator with shape memory (304) to vary a curvature shape (414) according to various flight conditions and ground operations by monitoring the temperature of the alloy actuator with shape memory (304) and by heating and cooling the alloy actuator with shape memory (304), where heating and cooling is provided by the aircraft's cooling and heating systems, and where the controller (308) is located remotely from the shape memory alloy actuator (304).
    [0002]
    Method, according to claim 1, characterized by the fact that the dynamic fluid body (302, 400) comprises at least one member selected from the group consisting of: an airfoil, a wing, an anchor, a small wing, an elevator, a rudder, an aileron and an elevon.
    [0003]
    Fluid dynamic body system with variable curvature for an aircraft, characterized by the fact that it comprises: a wing; a fluid dynamic body (302) operable to assume a first curvature configuration (610) and a second curvature configuration (612); an alloy hinge with shape memory (602, 604) pivotally coupled to the handle; and an alloy actuator with shape memory (304) operable for: configuring the dynamic fluid body (302) in the first curvature configuration (610) in response to a first control temperature; and configuring the dynamic fluid body (302) in the second curvature configuration (612) in response to a second control temperature; a separate aircraft control surface coupled to the aircraft wing by the shape memory alloy hinge (602, 604) disposed between the aircraft control surface and the aircraft wing, the aircraft control surface operable to rotate in relation to the aircraft wing on the shape memory alloy hinge (602, 604) in response to heating or cooling the shape memory alloy hinge (602, 604), where the shape memory alloy hinge (602 , 604) is a first shape memory alloy (SMA) hinge (602), and the aircraft control surface comprises a first aerodynamic structure (606) and a second aerodynamic structure (608) rotatable coupled along a rope direction using a second shape memory alloy hinge (SMA) (604), wherein the first aerodynamic structure (606) comprises a first fluid dynamic surface attached to the first aerodynamic structure (606), and the second structure aerodynamic (608) comprises a second fluid-dynamic surface attached to the second aerodynamic structure (608) and separated from the first fluid-dynamic surface; and a controller (308) operable for: applying a first temperature to the first SMA hinge (602) to rotate the first aerodynamic structure (606) around the first SMA hinge (602); applying a second temperature other than the first temperature to the second SMA hinge (604) to rotate the second aerodynamic structure (608) around the second SMA hinge (604); operating the first SMA hinge (602) between at least two positions of the fluid dynamic curvature line in a repeatable manner; and operating the second SMA hinge (604) between at least two positions of fluid-dynamic curvature line repeatably from the first SMA hinge (602).
    [0004]
    Fluid dynamic body system with variable curvature, according to claim 3, characterized by the fact that the aircraft control surface is selected from the group consisting of: a flap, a blade, a spoiler, an elevator, a rudder , an aileron and an elevon.
    [0005]
    Variable curvature fluid-dynamic body system according to claim 3, characterized in that it further comprises a controller (308) configured to change a temperature of the shape hinge alloy (602, 604).
    [0006]
    Fluid-dynamic body system with variable curvature according to claim 5, characterized by the fact that the aircraft control surface is coupled by separate coupling means to the alloy hinge with shape memory (602, 604).
    [0007]
    Fluid dynamic body system with variable curvature according to claim 3, characterized by the fact that the controller (308) is further configured to non-uniformly change the temperature of the first alloy hinge with shape memory (602) and the second alloy hinge with shape memory (604).
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    同族专利:
    公开号 | 公开日
    BR102012020561A2|2015-03-03|
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    ES2610394T3|2017-04-27|
    EP2562080A1|2013-02-27|
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    CN102951286A|2013-03-06|
    RU2597624C2|2016-09-10|
    CN102951286B|2016-12-21|
    EP2562080B1|2016-10-12|
    US9120554B2|2015-09-01|
    US20130043354A1|2013-02-21|
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    法律状态:
    2015-03-03| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2018-12-11| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-06-23| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-11-24| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-01-12| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 16/08/2012, OBSERVADAS AS CONDICOES LEGAIS. |
    2021-11-30| B16C| Correction of notification of the grant [chapter 16.3 patent gazette]|Free format text: REFERENTE A RPI 2610 DE 12/01/2021, QUANTO AO ITEM (30) PRIORIDADE UNIONISTA. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/210,,375|2011-08-16|
    US13/210,375|US9120554B2|2011-08-16|2011-08-16|Variable camber fluid-dynamic body utilizing optimized smart materials|
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