Multi-rod actuator configuration for airfoil control surfaces

Abstract

The disclosure relates to a multi-rod actuator configuration (1) configured to control an airfoil control surface (2) comprising; - at least two elongated guide members (10), at least one control actuator device (20) configured to control the movement of at least one of said elongated guide members (10), a control circuitry (CC) coupled to a clamping selector valve device (CS) and a servo valve device (SV) for controlling the motion of a piston device (22) of the control actuator device (20); characterized in that the multi-rod actuator configuration (1) further comprises at least two airfoil control segments (30), each of which is coupled to the respective elongated guide member (10) and forms said airfoil control surface (2). The disclosure further relates to a method for controlling an airfoil control surface (2) using the multi-rod actuator configuration (1), a data program (p) and a data medium (m).

Description

[0001] MULTI-ROD ACTUATOR CONFIGURATION FOR AIRFOIL CONTROL SURFACES

[0002] TECHNICAL FIELD

[0003] The present invention is situated within the technical field of aerospace engineering, specifically focusing on the implementation of a multi-rod actuator configuration for the precise control of airfoil surfaces. The disclosure relates to a multi-rod actuator configuration configured to control an airfoil control surface, a flight control computer, a method for controlling an airfoil control surface using the multi-rod actuator configuration and a computer-implemented software for controlling an airfoil control surface using the method. More specifically, the disclosure relates to a multi-rod actuator configuration configured to control an airfoil control surface, a flight control computer, a method for controlling an airfoil control surface using the multi-rod actuator configuration and a computer-implemented software for controlling an airfoil control surface using the method as defined in the introductory parts of the independent claims.

[0004] BACKGROUND ART

[0005] The conventional control systems traditionally used in aerospace engineering for governing the movement of airfoil surfaces and similar have primarily relied on traditional actuator mechanisms. These mechanisms are often dependent on large cylinder chamber volumes for providing long strokes and fluid leakage occurring at valve devices in energy consuming. Electromechanically actuators may also be used, but they are heavy and may generate undesirable heat. The current aircraft control surface actuators of an aircraft may also leak hydraulic fluid due to leak-age in continuous and adjustable control valves needed for prior art control systems, wherein internal leakage between the pressure side and the return side of the valve occurs for achievement of continuous motion of the piston.

[0006] While effective in basic scenarios, these configurations are heavy and bulky and take up large space. The current aircraft control surface actuators of an aircraft may also leak hydraulic fluid. There is a need for more sophisticated control systems capable of addressing the challenges mentioned above.

[0007] SUMMARY OF THE INVENTION

[0008] There is an object of the disclosure to provide an aircraft morphing wing that is applicable for the aircraft industry.

[0009] At least some of the embodiments of the disclosure have one or more of the objects listed below.

[0010] There is an object of the disclosure to provide an energy saving multi-rod actuator configuration and / or aircraft control surface multi-rod actuator arrangement.

[0011] There is an object to provide a compact and lightweight multi-rod actuator configuration of the type defined in the introduction.

[0012] There is an object of the disclosure to provide a locking mechanism capable of securely holding a surface control segment in position, addressing the challenge of maintaining stability and control over the aircraft's control system.

[0013] There is an object to provide a compact and lightweight aircraft control surface multi-rod actuator configuration.

[0014] There is an object to provide an aircraft comprising the aircraft control surface multi-rod actuator configuration, which aircraft is of low weight and which is configured to use low energy consumption.

[0015] There is an object to provide easy and cost effective maintenance of an aircraft control surface multi-rod actuator configuration after use in flight.

[0016] There is an object to provide an easy and cost effective testing of the aircraft control surface multi-rod actuator arrangement after storage or transport.

[0017] There is an object to provide an effective aircraft control surface multi-rod actuator configuration of an aircraft configured for all flight envelopes. The envelopes being lift and landing, low, medium and high speed. There is an object to provide a multi-rod actuator configuration configured to minimise the hydraulic fuel maintenance of the system.

[0018] There is an object to provide an energy saving multi-rod actuator arrangement that is configured to generate and distribute mechanical linear movement and force.

[0019] There is an object to provide an energy saving multi-rod actuator configuration that uses as few complex fluid leaking control valves as possible.

[0020] There is an object to provide an energy saving multi-rod actuator arrangement that is cost- effective to manufacture and in service maintenance.

[0021] There is an object to provide an energy saving multi-rod actuator of a control system that supplies hydraulic power for all operational phases in normal and degraded modes even in case of eventual external fluid leakage and / or fluid supply failure and / or fluid pump failure.

[0022] There is an object to provide an aircraft that exhibits low drag, low fuel consumption and that is able to fly long missions achieved by low energy consumption.

[0023] There is an object to provide an aircraft with low aerodynamic drag throughout the flight envelop.

[0024] There is an object to provide an aircraft with a thin wing with small build height for actuators in the wing box.

[0025] It is an object of the present disclosure to mitigate, alleviate or eliminate one or more of the above-identified deficiencies and disadvantages in the prior art and solve at least the above- mentioned problem.

[0026] The disclosed invention improves the field of aerospace engineering, addressing limitations observed in traditional actuator configurations. By optimizing the control of for example airfoil surfaces, the multi-rod actuator configuration introduces a novel and adaptable approach, offering significant advantages in precision, adaptability, and efficiency. Here bellow follows the advantages of the invention.

[0027] According to a first aspect there is provided a multi-rod actuator configuration configured to control an airfoil control surface comprising at least two elongated guide members, at least one control actuator device configured to control the movement of at least one of the elongated guide members, a control circuitry coupled to a clamping selector valve device and a servo valve device for controlling a clamping device and / or a holding member and the motion of a piston device of the control actuator device. The multi-rod actuator configuration is characterized in that the multi-rod actuator configuration further comprises at least two airfoil control segments, each of which is coupled to the respective elongated guide member and from the airfoil control surface.

[0028] The multi-rod actuator configuration is configured to control a control surface, such as control surfaces on an aircraft wing or turbine blades. However, it is not limited to those areas of use. The configuration could also be used in a rudder configuration of an aircraft, or a stiff sail or as a hydrofoil or other mechanisms where a fluid medium, such as air or water, is to be used for energy transfer.

[0029] The multi-rod actuator configuration includes elongated guide members that are being pushed or guided, independently or as a set, in a side-to-side motion by the control actuator device in the structure that the configuration is situated in. The motion of the guiding members is transferred to the respective control surface. This surface may be a surface that is an airfoil on an airplane or a rudder.

[0030] The control actuator device is integrated to influence the position and orientation of the guide members, with a control circuitry linked to a clamping selector valve device and a servo valve device. The clamping selector valve device regulates fluid flow of the clamping device and / or the holding member and the servo valve device regulates the fluid flow controlling the motion of a piston device within the control actuator. The piston device translates fluid pressure into mechanical motion, allowing for precise adjustments to the position of the elongated guide members when the elongated member may be transferred from side to side in the elongated member extended direction. Additionally, the multi-rod actuator configuration includes at least two airfoil control segments, each coupled to a respective guide member. These segments collectively form the airfoil control surface.

[0031] The multi-rod actuator configuration, driven by the integrated control devices and circuitry, facilitates precise adjustments to one or more of the airfoil control surface. This precision, on which control surface to manoeuvre, contributes to improved aerodynamic performance, enhancing flight efficiency and manoeuvrability of the aircraft. By enabling minute alterations to the airfoil shape and angle in real-time, the system optimizes lift, drag, and stability characteristics throughout various flight envelopes.

[0032] The precision extends the capability of the configuration away from traditional fixed-wing configurations, resembling a "morphing wing" concept. This dynamic adaptability allows for on-the-fly optimization of the airfoil geometry, tailoring it to suit prevailing flight conditions. Whether adjusting to changes in airspeed, altitude, or environmental factors, this morphing capability ensures consistently optimal aerodynamic performance, resulting in smoother flight dynamics, reduced fuel consumption, and enhanced overall aircraft handling.

[0033] The ability to finely tune the airfoil control surface via the multi-rod actuator configuration improves the aerodynamic efficiency and enables the realization of a dynamic and responsive wing morphology, where the wing is a morphing wing.

[0034] The piston used in the multi-rod actuator in the control actuator device may be of a short stroke piston which offers important advantages. A short stroke piston has a compact design to optimize space utilization. It is particularly beneficial in confined environments like in an aircraft or other hydraulic systems which has to be lightweight and use a small volume. Additionally, the quick actuation due to reduced travel distance enhances dynamic performance, increasing productivity in applications requiring speed and precision. A short stroke piston may also give an improved energy efficiency, as they displace lower fluid volumes and experience reduced frictional losses during operation. This translates to cost savings and a more sustainable operation.

[0035] The multi-rod actuator configuration ability to control at least two airfoil control segments independently enhances versatility of the segments where it assistances different flight conditions and operational requirements.

[0036] The clamping selector valve devices and servo valve devices role in regulating fluid flow enhances the efficiency of the configuration, ensuring smooth and controlled movements of the piston device and the clamping device and / or the holding member and, consequently, the airfoil control surface.

[0037] The multi-rod actuator configuration enabling the airfoil to adapt to changing aerodynamic conditions during flight and optimize performance accordingly. This configuration also allows for the integration of multiple segments along the aircraft wing, each independently controlled. The actuator can control each of the control surfaces individually, independently of all the others if required. Unlike traditional control surfaces that rely on singular, centralized mechanisms, this segmented approach offers distinct advantages. By distributing control across several segments, the invention provides greater flexibility and versatility in aerodynamic manipulation. Each segment can function autonomously, serving multiple purposes such as ailerons, flaps, or even entirely novel aerodynamic surfaces. This distributed control system enhances agility and responsiveness, allowing for finer adjustments to optimize lift, drag, and stability in real-time.

[0038] The multi-rod actuator configuration further comprises a parking module of the control actuator device coupled to the control circuitry and configured to lock said at least one elongated guide member stationary in position; the parking module comprises a holding member configured to engage or disengage the associated elongated guide member, wherein the control circuitry is adapted to lock at least one of said airfoil control segments.

[0039] In some embodiments the dependent multi-rod actuator configuration has a parking module integrated into the control actuator device. This module is coupled to the control circuitry via the clamping selector valve device and serves the purpose of immobilizing and locking at least one of the elongated guide members, thus locking it stationary in position. The parking module includes a holding member designed to engage or disengage the associated elongated guide member that needs to be locked, with the control circuitry responsible for locking at least one of the airfoil control segments. The parking module within the control actuator device contributes the function to provide a mechanism for securely locking at least one elongated guide member in a stationary position. By holding on to the guiding member the parking module may free the respective at control cylinder from clamping the guide member. This allows the control cylinder to be used less and therefore will extend the life of the cylinder and prevent continuous maintenance. The feature is advantageous during when the airfoil control surface needs to remain fixed in a specific position, enhancing operational safety.

[0040] The holding member is an integral part of the parking module and is designed to engage or disengage the associated elongated guide member. This component ensures reliable immobilization of the guide member when engaged, providing stability to the airfoil control surface. The ability to disengage allows for flexibility in adjusting and repositioning the guide member when necessary, enhancing operational efficiency.

[0041] The control circuitry, as part of the integrated system, coordinates the operation of the parking module. It receives input signals and commands from external sources, facilitating the engagement or disengagement of the holding member to lock or release the elongated guide member. This integration ensures precise control and reliable performance of the parking module.

[0042] The addition of the parking module to the multi-rod actuator configuration enhances operational flexibility. The ability to immobilize elongated guide members when required enhance the feature to lock a segment of the airfoil by choice during the envelop of a flight. In a low speed in lift-off and landing, all the segments has to work together to make the aircraft have the best possible aerodynamically conditions. When the aircraft flies in cruise speed the parking module can lock elongated guides coordinating with segments that are not necessary for that part of the flight envelope. In this way the multi-rod actuator configuration improves flight procedures and ensures stability during stationary operations.

[0043] According to some embodiments the multi-rod control actuator device comprises a cylinder device configured to move said piston device the multi-rod comprises at least two through-holes through each of which the associated elongated guide member extends, and wherein each through-hole of the piston device is associated with a respective clamping device, configured to engage or disengage the elongated guide member extending through the associated through-hole, wherein the control circuitry is adapted to control the multi-rod actuator configuration to perform a first state, wherein the clamping device is configured to engage the associated elongated guide member and the piston device is configured to move the associated elongated guide member. A second state, wherein the clamping device is configured to disengage the associated elongated guiding member, and the associated elongated guide member is permitted to freely move through the through-hole.

[0044] The control circuitry is adapted to control the multi-rod actuator configuration to perform two distinct states. The first state, where the clamping device engages the elongated guide member while the piston device moves it, and second state where the clamping device disengages, allowing free movement of the guide member through the through-hole. The cylinder device is a component of the multi-rod control actuator device and moves the piston device inside of the cylinder devices cylinder house. Its function is to generate the necessary mechanical force to actuate the piston, enabling control over the movement of the associated elongated guide member. The design enhances the efficiency and reliability of the actuation system by providing consistent and controlled motion.

[0045] The cylinder device includes at least two through-holes, each associated with an elongated guide member. These through-holes facilitate the movement of the guide members within the actuator configuration. By accommodating the guide members in through-holes, the system ensures proper alignment and stability. The guiding members may then be guided through the holes in the direction of the piston by the help of the clamping devices located inside of the cylinder device by the through-hole. Each through-hole of the piston device is hence associated with a clamping device, which is configured to engage or disengage the elongated guide member via the fluid from the clamping selector valve device. This feature allows for selective clamping of the guide members during operation. When engaged, the clamping device securely holds the guide member in place, facilitating controlled movement by the piston device in both directions of the piston extension. Conversely, disengaging the clamping device enables free movement of the guide member, offering flexibility in adjusting the airfoil control surface.

[0046] According to some embodiments the respective elongated guide member comprises a linkage arrangement coupled between the airfoil control segment and the elongated guide member.

[0047] The linkage arrangement is a features related to the structure of the elongated guide member within the multi-rod actuator configuration. It includes a linkage arrangement coupled between the airfoil control segment and the elongated guide member. The linkage arrangement serves as a connecting mechanism between the airfoil control segment and the elongated guide member. This component facilitates the transmission of motion and force between the guide member and the control segment, ensuring coordinated movement of the airfoil control surface. The design of the linkage arrangement influences the precision and range of motion of the airfoil, contributing to optimized performance of the multi-rod actuator configuration. By providing a reliable connection between the guide member and the airfoil control segment, the linkage arrangement ensures smooth and coordinated movement, resulting in precise adjustments to the airfoil.

[0048] According to some embodiments the linkage arrangement is configured to provide motion of the airfoil control segment corresponding to a gear ratio of 1 to 10 times the motion of the elongated guide member.

[0049] Gear ratios within the range of 1 to 10 times the motion of the elongated guide member offer a variety of options for adjusting the motion of the airfoil control segment relative to the guide member. The gear ratio between the elongated guide and the respective segment is driven by a gear. The gear has a ratio of 1-10, alternatively 1-8, alternatively 1-6, alternatively 1-5, alternatively 1-4, alternatively 1-3, alternatively 1-2, alternatively 1-1. A gear ratio of 1 signifies a direct 1-to-l correspondence between the motion of the guide member and the airfoil control segment. Gear ratios between 2 and 10 indicate an amplification of motion, where the airfoil control segment or other machinery moves a greater distance relative to the guide member's motion. These ratios amplify the range of motion of the airfoil, allowing for more extensive adjustments and faster control over the segments.

[0050] According to some embodiments the linkage arrangement comprises a wire mechanism and / or a push rod mechanism; and the airfoil control segment comprises a hinge mechanism configured to permit pivoting motion of the airfoil control segment relative each other and relative an airfoil body, such as a wing of an aircraft.

[0051] A wire mechanism within the linkage arrangement involves the use of flexible cables or wires to transmit motion between the elongated guide member and the airfoil control segment. A push rod mechanism utilizes rigid rods or tubes to transmit motion between the guide member and the airfoil control segment. These mechanisms delivers direct and precise control over the movement, ensuring minimal deflection and optimal responsiveness.

[0052] The airfoil control segment may be equipped with hinge mechanisms that permits pivoting motion relative to each other and relative to an airfoil body, such as the wing of an aircraft. This hinge mechanism allows for controlled movement of the airfoil control segment, enabling adjustments to the aerodynamic profile of the airfoil.

[0053] Incorporating both wire and push rod mechanisms into the linkage arrangement provides flexibility and precision in transmitting motion between the elongated guide member and the airfoil control segment. The wire mechanism offers versatility in routing and positioning, while the push rod mechanism ensures direct and precise control over the movement. Together, these mechanisms enable efficient transmission of motion, enhancing the responsiveness and adaptability of the airfoil control system. The different elongated guide member means could be used one per se or together depending on the searched feature. The inclusion of the hinge mechanism in the airfoil control segment allows for controlled pivoting motion, facilitating precise adjustments to the aerodynamic profile of the airfoil. This enhances the system's ability to optimize aerodynamic performance, responsiveness, and reliability in various flight conditions. The integration of these mechanisms enables efficient transmission of motion, precise control over airfoil adjustments, and optimized aerodynamic performance across a range of flight scenarios.

[0054] According to some embodiments the parking module comprises at least a control actuator device configured to control the movement of at least one of said elongated guide members; wherein each control actuator device comprises a cylinder device configured to move a piston device the multi-rod comprises at least two through-holes, through each of which the associated elongated guide member extends. Wherein each through-hole of the piston device is associated with a respective clamping device, configured to engage or disengage the elongated guide member extending through the associated through-hole. The multi-rod actuator configuration further comprises a control circuitry coupled to a clamping selector valve device and a servo valve device for controlling the motion of the piston device and adapted to control the multi-rod actuator configuration to perform in three states. In the first state the clamping device engages the associated elongated guide member with the use of the clamping selector valve device which engage the clamping of the clamping device with fluid, and the piston device then moves the associated elongated guide member with the fluid flow regulated from the servo valve device. In a second state the clamping device disengages the associated elongated guiding member, and the associated elongated guide member is permitted to freely move through the through hole. In a third state the clamping device engages the associated elongated guiding member, and the piston device is held stationary in the cylinder device.

[0055] The steps includes the features related to the parking module, control actuator device, cylinder device, multi-rod, through-holes, clamping devices, control circuitry, clamping selector valve device and servo valve device within the multi-rod actuator configuration. The parking module comprises at least a control actuator device responsible for controlling the movement of at least one elongated guide member. Each control actuator device includes a cylinder device designed to move a piston device. The multi-rod comprises at least two through-holes, each associated with an elongated guide member and each through-hole of the piston device is associated with a respective clamping device, configured to engage or disengage the elongated guide member extending through the associated through-hole.

[0056] The incorporation of these features into the multi-rod actuator configuration enhances its functionality and versatility in controlling the airfoil control surface. The parking module, equipped inside the control actuator devices together with at least one cylinder device allows for a climbing rope movement of the guiding member. When the parking module holds a guiding member the piston in a cylinder device may move the piston with an open clamping device to change position of the cylinder device. In the next step the cylinder device may clamp a guiding member and while the parking module un-hold the guiding member, the cylinder device moves the guiding member along the piston device length.

[0057] According to some embodiments the plurality of elongated guides comprises one of or a combination of rods and / or wires and / or pushrods and / or pulleys and / or linkage and / or arms and / or yokes.

[0058] Rods are solid cylindrical components that provide structural support and guidance within the multi-rod actuator configuration. They offer strength and stability, ensuring reliable transmission of motion and force between components.

[0059] Wires are flexible, slender components that can be used to transmit motion between different parts of the actuator system. They offer versatility in routing and positioning, allowing for efficient transmission of motion even in complex configurations.

[0060] Pushrods are rigid rods or tubes that transmit motion or force between components within the actuator system. They provide direct and precise control over the movement, ensuring minimal deflection and optimal responsiveness.

[0061] Pulleys are wheels with a grooved rim designed to guide belts, cables, or ropes to transmit motion or force within the actuator system. They offer smooth and efficient transfer of motion, enabling precise adjustments and reliable operation. Linkages are designed to transmit motion or force within the actuator system.

[0062] Arms are rigid structural components that connect moving parts within the actuator system and provide support and stability, ensuring smooth and controlled movement of the components.

[0063] Yokes are U-shaped components that provide a mounting or attachment point for other parts within the actuator system. They offer stability and support, facilitating efficient transmission of motion and force.

[0064] The inclusion of various types of elongated guides within the multi-rod actuator configuration offers versatility and adaptability in designing and implementing the system. Each type of guide has its advantages in terms of strength, flexibility, precision, and efficiency, allowing for tailored solutions to meet specific application requirements.

[0065] According to some embodiments the airfoil control surface is a portion of a wing of an aircraft and at least two airfoil control segments form a combined transformable control surface area, which is at least one of or a combination of flaps and ailerons.

[0066] The airfoil control surface is a specific part of the wing of an aircraft. It is designed to adjust the aerodynamic characteristics of the wing, influencing lift, drag, and stability during flight. The moment that is exposed to an aircraft wing when it turns or uses its control surfaces refers to the turning force generated by aerodynamic forces acting on the wing. This moment is pivotal for controlling the aircraft's attitude, stability, and manoeuvrability. This includes manoeuvers like pithing, rolling, yawing or spiralling. When two airfoil control segments, or more, form a combined transformable control surface area on the wing the wing area can undergo transformation to adjust its configuration, enhancing the aerodynamic performance of the aircraft. The wing may comprise flaps and / or ailerons. Flaps are movable surfaces attached to the trailing edge of the wing. They can be extended or retracted to increase lift or drag during take-off, landing, or other flight manoeuvres. The ailerons are movable surfaces located near the outer portion of the wing and move in opposite directions from each other to control the roll of the aircraft, facilitating wing manoeuvres. The integration of the airfoil control surface as a portion of the wing of an aircraft, along with the combined transformable control surface area comprising flaps and / or ailerons, offers several advantages. The transformable control surface area allows for precise adjustments to the aerodynamic profile of the aircraft wing, optimizing lift, drag, and stability during different phases of flight. The flaps and ailerons combined in the configuration of this invention enable the aircraft to perform a wide range of manoeuvres, including take-off, landing, banking, and turning, with increased precision and control.

[0067] By integrating flaps and ailerons into a combined control surface area, redundant components and structures can be eliminated, resulting in overall weight reduction. Traditional designs often require separate mechanisms and actuators for flaps and ailerons, increasing the weight of the aircraft. Integration allows for a more streamlined design, reducing the weight penalty associated with multiple control surfaces.

[0068] Integrating flaps and ailerons into a combined control surface area may also optimise the utilization of available wing space or fuselage space, reducing the need for additional mechanisms and actuators. Traditional designs with separate flaps and ailerons require dedicated space for each control surface, leading to increased complexity and space requirements. Integration allows for a more efficient use of wing space, freeing up valuable space for other components or fuel.

[0069] According to some embodiments the at least two airfoil control segments partly form a portion of a sail member or entirely form a sail member and could also form a portion of a rudder member or entirely form a rudder member.

[0070] The airfoil control segments may be integrated into or constitute a sail structure, which may be part of a sailing vessel for sailing. The technic in the invention could be used in sailing by the usage of a stiff sailing member. It could also apply for parts of or entirely form a rudder member. Rudder members are used in windmills.

[0071] Another alternative embodiment of the disclosure is to implement in a fin or vertical stabilizer for an aircraft. A morphing surfaces technology and a multi-rod actuator configuration as disclosed, may be implemented in the fin of an aircraft where the morphing fin dynamically adjusts its shape and surface characteristics in real-time based on various flight conditions.

[0072] According to another embodiment the airfoil control surface is an airfoil surface of a morphing wing of an aircraft with a compliant structure. A morphing wing on an aircraft is a wing design that can change its shape during flight. It adapts to different aerodynamic conditions, optimizing performance and efficiency. The adaptive features may include leadingedge, trailing edge, span wise, and twist morphing. Benefits include improved efficiency, enhanced manoeuvrability, increased range and payload capacity, and enhanced safety and stability. The multi-rod control actuator configuration moves several segments on a flying wing which creates the features of a morphing wing without the drawbacks of the morphing wing techniques traditionally used. These techniques often involve mechanical systems such as hinges, flaps, and control surfaces that adjust the wing's shape manually or semi- automatically. These systems may include movable sections for altering wing camber, twist, or span, providing limited adaptability, take up space and are often heavy in comparison to the morphing wing presented in this invention.

[0073] According to some embodiments the multi-rod actuator configuration comprises the control circuitry programmed to control the clamping device and / or the holding member.

[0074] The control circuitry serves as the central control system for the multi-rod actuator configuration and is responsible for coordinating the operation of various components. By programming the control circuitry to control the clamping device of a control cylinder and / or the holding member of a parking module a precise and automated control over the clamping and locking is achieved. The control over the clamping device and holding member ensures optimal locking and clamping of the elongated guide members, maximizing the effectiveness of the airfoil control surface and sail member configuration in adapting to changing flight conditions.

[0075] According to some embodiments each control actuator device comprises a position sensor, providing feedback to the control circuitry on real time positions of the elongated guide members.

[0076] The position sensor is integrated into each control actuator device to accurately measure and provide feedback on the real-time positions of the elongated guide members. It detects any deviations from the desired position, allowing the control circuitry to make necessary adjustments to maintain precise control over the actuator system.

[0077] The inclusion of position sensors ensures precise control over the movement of the elongated guide members, enabling accurate positioning of the airfoil control surface or other components. The position sensors provide real-time feedback to the control circuitry, allowing for immediate adjustments to maintain the desired position. It enhances the precision and responsiveness of the actuator system, ensuring optimal positioning of the airfoil control surface and sail member configuration in response to changing flight conditions. By continuous monitoring of the elongated guide member positions the reliability of the actuator system is enhance, due to minimizing the risk of errors or malfunctions and ensuring smooth and stable operation.

[0078] According to a second aspect there is provided a method for controlling an airfoil control surface using the multi-rod actuator configuration. In the first aspect, the method comprises the steps of first engaging the clamping device to the associated elongated guide member. Thereafter moving the elongated guide member by means of the piston device and disengaging the clamping device from the associated elongated guiding member. Next permitting the associated elongated guide member to freely move through the through-hole.

[0079] The method involves a sequence of steps that facilitate the movement and adjustment of the elongated guide members within the multi-rod actuator configuration. The method enables a precise control over the movement of the elongated guide members and ensures accurate positioning of the respective segments that are a part of the airfoil control surface. The method offers advantages in precision control, stability, efficiency, and adaptability contributing to improved overall performance of the aircraft.

[0080] The method further comprises the steps of locking the at least one elongated guide member stationary in position utilizing the parking module holding member. Reengaging the clamping device after the elongated guide member has been locked in place by means of the parking module holding member.

[0081] By locking the guide member stationary with the parking module, the method ensures that the guiding members and also the segments are not moving. This will also prevent the clamping devices in the cylinder devices from worn out and therefore give them a longer lifetime. The leakage of hydraulic oil will also be less due to less usage of the hydraulic systems due to the configuration feature to temporarily close the servo valve devices.

[0082] According to some embodiments the method comprises the steps of, operating the control circuitry to control the motion of the piston device and the clamping device to achieve the first state, wherein the clamping device engages the associated elongated guide member, and the piston device moves the associated elongated guide member. Operating the control circuitry to control the motion of the piston device and clamping device to achieve the second state, wherein the clamping device disengages the associated elongated guiding member allowing the associated elongated guide member to move freely through the through-hole. Coupling each airfoil control segment to a corresponding elongated guide member. Utilizing the parking module to lock at least one elongated guide member stationary in position by engaging the holding member with the associated elongated guide member and adapting the control circuitry to lock at least one of said airfoil control segments in position.

[0083] Coupling each airfoil control segment to a corresponding elongated guide member ensures synchronized movement, optimizing the performance of the airfoil control surface. Using the parking module to lock at least one elongated guide member in a stationary position enhances stability during adjustments, contributing to precise positioning of the airfoil control surface. It also has the advantage to guide away large forces from the cylinder devices. This means that the cylinder devices could be kept smaller, thinner and with less hydraulic power then traditional actuators because the large forces to lock the elongated guide members is absorbed by the parking modules. The parking module within the multi-rod actuator configuration may feature various types of holding members, distinct in strength from the clamping devices found on the cylinder device. These holding members may be designed with attributes such as a relatively increased pressure, larger area, or greater circumference. These enhancements enable the holding members to exert a sturdy locking force on the elongated guide members that require immobilization. The clamping devices of the cylinder device may then emphasis on the movement of the control surfaces. By incorporating holding members with a higher pressure or a larger contact area relative to the clamping devices, the parking module can effectively secure the elongated guide members in place, ensuring stability and precise control in various flight operations where large forces are exposed to the control surfaces.

[0084] According to a third aspect there is provided a data program that is programmed for causing the method of the multi-rod actuator configuration described in the aspects above and to execute its method. The data program comprises a program code readable on a computer of the control circuitry for providing the steps of, engaging the clamping device to the associated elongated guide member, moving the elongated guide member by means of the piston device, disengaging the clamping device from the associated elongated guiding member and permitting the associated elongated guide member to freely move through the through-hole.

[0085] The data program enables automated execution of the method steps of the multi-rod actuator method, enhancing precision and efficiency in controlling the multi-rod actuator configuration.

[0086] According to a another aspect of the disclosure there is provided a data medium, configured for storing the data program according to the aspect wherein the data medium comprises a program code which is readable on the computer for performing the method for controlling an airfoil control surface using the multi-rod actuator configuration.

[0087] Effects and features of the second through fourth aspects are to a large extent analogous to those described above in connection with the first aspect. Embodiments mentioned in relation to the first aspect are largely compatible with the second through fourth aspects.

[0088] The disclosed multi-rod actuator configuration presents a morphing wing concept with significant advancements. By integrating adaptive wing technology, this disclosure will benefits to transcend traditional aircraft structures. The morphing wing concept offers costefficiency by optimizing aerodynamic performance across a range of flight conditions due to the changeability of the wing. Through real-time adjustments to the wing's shape and surface properties, fuel consumption is minimized, resulting in energy savings. Furthermore, the compactness of the concept reduces the overall space and volume requirements within an aircraft.

[0089] The present disclosure will become apparent from the detailed description given below. The detailed description and specific examples disclose preferred embodiments of the disclosure by way of illustration only. Those skilled in the art understand from guidance in the detailed description that changes and modifications may be made within the scope of the disclosure.

[0090] Hence, it is to be understood that the herein disclosed disclosure is not limited to the particular component parts of the device described or steps of the methods described since such device and method may vary. It is also to be understood that the terminology used herein is for purpose of describing particular embodiments only, and is not intended to be limiting. It should be noted that, as used in the specification and the appended claim, the articles "a", "an", "the", and "said" are intended to mean that there are one or more of the elements unless the context explicitly dictates otherwise. Thus, for example, reference to "a unit" or "the unit" may include several devices, and the like. Furthermore, the words "comprising", "including", "containing" and similar wordings does not exclude other elements or steps.

[0091] BRIEF DESCRIPTION OF THE DRAWINGS

[0092] The above objects, as well as additional objects, features and advantages of the present disclosure will be more fully appreciated by reference to the following illustrative and non-limiting detailed description of example embodiments of the present disclosure, when taken in conjunction with the accompanying drawings.

[0093] Figure 1 Illustrates an example of a multi-rod actuator configuration;

[0094] Figure 2A-D Illustrates an aircraft wing profile of the present disclosure;

[0095] Figure 3 Illustrates an example of a multi-rod actuator configuration of the present disclosure;

[0096] Figure 4 Illustrates an example of an multi-rod actuator configuration of the present disclosure;

[0097] Figure 5A-B Illustrates aircraft wing profiles of the present disclosure;

[0098] DETAILED DESCRIPTION

[0099] The present disclosure will now be described with reference to the accompanying drawings, in which preferred example embodiments of the disclosure are shown. The disclosure may, however, be embodied in other forms and should not be construed as limited to the herein disclosed embodiments. The disclosed embodiments are provided to fully convey the scope of the disclosure to the skilled person.

[0100] Throughout the figures, same reference numerals refer to same parts, concepts, and / or elements. Consequently, what will be said regarding a reference numeral in one figure applies equally well to the same reference numeral in other figures unless not explicitly stated otherwise.

[0101] It is to be understood that the figures are schematic representations aimed at highlighting the novel features of the examples. Shown parts may not be to scale, and some parts may not be depicted for readability.

[0102] Figure 1 illustrates an overview schematic representation of an example multi-rod actuator configuration 1 designed to facilitate precise motion control in applications ranging from aircraft and windmills to various other machinery. The configuration in figure 1 comprises four elongated guide members 10', 10”, 10"', 10"" extending in the direction of the elongated guide members, along which two control actuator devices 21 and a parking module 40 positioned to control the movement and locking of the guide members.

[0103] Figure 2A illustrates an in-depth depiction of a wing profile of an aircraft design compatible for the multi-rod actuator configuration 1, featuring an airfoil segmented into three distinct segments 30', 30", 30'". Where each hinge 31', 31", 31'" in the airfoil is manoeuvred by the multi-rod actuator 1. Figure 2A further illustrates the wing profile during steady straight flight in the filled lines of the figure, as well as its behaviour when moving the hinges in an upwards and downwards direction at three pivotal hinges that divide the three segments, shown in dotted lines. The design enables the wing to generate lift during ascent and control descent as needed.

[0104] Figure 2B illustrates the wing profile similar to Figure 2A, with the first dashed illustration detailing the movement of the hinges in the airfoil as they articulate upwards and downwards to facilitate a wing profile when fully unfolded. This phase is suited for low-speed manoeuvres such as ascent and descent, where the control surfaces need to be used.

[0105] In figure 2C the inner hinge is depicted as locked, while the two outer hinges are depicted as free to move up and down. This arrangement results in a stiffer wing profile compared to the fully flexible configuration shown in Figure 2A and 2B, suitable for specific flight conditions or manoeuvres requiring increased structural integrity. This phase is suited medium-speed manoeuvres.

[0106] Lastly, figure 2D illustrates the wing profile with both the inner and middle hinges locked, leaving the outer most hinge free to move up and down. This configuration creates an even stiffer wing profile, ideal for executing precise and small manoeuvres with enhanced stability and control, particularly during intricate flight operations in a higher speed where smaller adjustments are needed. This phase is suited high-speed manoeuvres.

[0107] In the invention of the multi-rod actuator configuration 1 a precise control over the airfoil control surface segments 30', 30" is achieved through a system of elongated guide members 10', 10", control actuator devices 20, and associated mechanisms. This system enables dynamic adjustments to the wing profile, crucial for optimizing aircraft flight characteristics. By coupling the segmented airfoil control surface to the elongated guide members 10', 10" of the actuator configuration 1, each segment's movement can be precisely controlled independent from each other. For example, in Figure 2A, during steady straight flight, the multi-rod actuator 1 adjusts the segments to maintain the desired wing configuration for optimal flight and stability in high velocities. As the wing bends upwards or downwards, as depicted in Figure 2A, the actuator responds by coordinating the movement of the segmented airfoil control surface, ensuring proper aerodynamic performance for ascending or descending flight. Figures 2C and 2D demonstrate scenarios where specific segments 30', 30" of the airfoil control surface 2 are locked, resulting in a stiffer wing profile. In these configurations, the multi-rod actuator configuration 1 adjusts the remaining movable segments accordingly, providing the necessary control authority for executing precise manoeuvres while maintaining structural integrity. Overall, the integration of the segmented airfoil control surface with the multi-rod actuator configuration 1 allows for dynamic control over the wing profile, enabling the aircraft to adapt to various flight conditions and perform manoeuvres with enhanced agility and efficiency.

[0108] When all hinges and segments operates organised via a control circuitry CC, the flying capacity will be particularly effective at low speeds. Here precise control is necessary, such as during manoeuvres requiring high rudder angles. Each individual segment contributes to achieving low rudder angle speeds and minor rudder angle deflections. The combined effect of these angles and speeds is crucial for optimal performance. By utilizing all three segments simultaneously, the multi-rod actuator configuration cylinder piston 22 is required to achieve the desired rudder deflection and speeds is minimized.

[0109] In some embodiments the parking module within the multi-rod actuator configuration may feature various types of holding members, distinct in strength from the clamping devices found on the cylinder device. These holding members may be designed with attributes such as a relatively increased pressure, larger area, or greater circumference. These enhancements enable the holding members to exert a sturdy locking force on the elongated guide members that require immobilization. The clamping devices of the cylinder device may then emphasis on the movement of the control surfaces. By incorporating holding members with a higher pressure or a larger contact area relative to the clamping devices, the parking module can effectively secure the elongated guide members in place, ensuring stability and precise control in various flight operations where large forces are exposed to the control surfaces.

[0110] Figure 3 illustrates an exemplary embodiment of the multi-rod actuator configuration 1, showing features to control an airfoil control surface 2 with precision and versatility. In this configuration, the airfoil control surface is divided into three segments 30', 30", 30"', each independently controlled for enhanced manoeuvrability to simulate a morphing wing concept.

[0111] The components of the configuration includes three elongated guide members 10', 10", 10'", a control actuator devices 20, and a control circuitry CC coupled to clamping selector valve devices CS',CS" and servo valve device SV', SV”. The example shows two cylinder devices 21', 21" integrated, each equipped with a piston device 22', 22" for dynamic control.

[0112] Both cylinder devices 21', 21" features a position sensor 25', 25", configured to monitor the real-time position of the elongated guide members 10', 10", 10'" associated with the position of the cylinder devices 21', 21". The feedback mechanism ensures precise control and synchronization of the guide members movements.

[0113] The airfoil control surface segments 30', 30", 30'" are connected to the guide members 10', 10", 10'" via hinges 31', 31", 31'", allowing for pivotal motion relative to each other and the aircraft's wing structure. Each segment is connected via a set of gears 50', 50", 50'" for a possible increase of the exchange of power between the actuator and the segments.

[0114] Further, figure 3 shows a parking module 40 comprising three through-holes 42', 42", 42'" and respective three holding members 41', 41", 41'" configured to engage or disengage the associated guide members 10', 10”, 10'" to immobilize or allow movement, respectively providing additional stability and safety to the configuration.

[0115] The multi-rod actuator configuration 1 enables precise and coordinated movement of the airfoil control surface segments, enhancing the aircraft's flight control capabilities. By independently controlling each segment and monitoring their positions in real-time, the configuration achieve optimal performance and manoeuvrability in various flight conditions.

[0116] Figure 4 illustrates the core components and concept of the multi-rod actuator configuration 1. The figure is one adaptation of the invention and include the elongated guide members 10', 10”, a control actuator device 20, a control circuitry CC coupled and clamping selector valve devices CS', CS". The clamping selector valve devices receives hydraulic fluid from a fluid supply. This setup allows for the controlled movement of an airfoil control surface 2 or other manipulations in mechanisms, through the manipulation of guide members 10', 10” via the actuator device 20.

[0117] The multi-rod actuator configuration 1 features two airfoil control segments 30', 30” coupled to the respective guide members 10', 10”, forming the airfoil control surface 2. These segments facilitates the desired motion of the control surfaces in response to the actuator's commands.

[0118] Figure 4 further shows a parking module 40 integrated within the control actuator device 20 and enables the stationary locking of guide members 10', 10” when necessary. The control segments 30', 30” can be locked when an aircraft is flying in a high velocity. The parking module 40 in this example includes two holding members 41', 41” which engages or disengages the associated guide members 10', 10” to immobilize or allow movement, respectively. The parking module 40 comprises through-holes 42', 42” associated with the holding members 41', 41” and work in tandem to control the locking of the guide members 10', 10” with the control circuitry CC coordinating various states of operation.

[0119] The control actuator device 20 comprises a cylinder device 21 responsible for moving a piston device 22. The cylinder device 21 comprises through-holes 23', 23” associated with clamping devices 24', 24”. These components also work in tandem to control the movement of the guide members 10', 10” with the control circuitry CC coordinating various states of operation. When the clamping devices 24', 24” are engaged in at least one of the elongated guide members 10', 10” while the holding members 41', 41” of the parking module 40 are disengaged, the piston device 22 will move the elongated guide members 10', 10” utilizing the piston movement in the servo valve device SV in the direction of the elongated guide member extension.

[0120] A component for ensuring motion synchronization is the linkage arrangement LA', LA” coupled between the airfoil control segments 30', 30” and guide members 10', 10”. This arrangement provides motion corresponding to a specified gear ratio using at least one gear 50, achieved through mechanisms such as wire or push rod mechanisms.

[0121] The figure 4 further comprises hinge mechanisms 31', 31” within the airfoil control segments 30', 30”, enabling pivoting motion relative to each other and relative to an airfoil control surface 2, such as a wing of an aircraft.

[0122] The disclosed method for controlling the airfoil control surface 2 involves a sequence of steps facilitated by the control circuitry CC. These steps include engaging and disengaging the clamping device 24', 24” with the clamping selector valve devices CS', CS", moving the guide member 10', 10” with the movement of the piston device 22 via the servo valve device SV, and adapting the control circuitry CC to lock the airfoil control segments 30', 30” in position as required. In some examples the linkage arrangement between the airfoil control segments and guide members comprises LA', LA” comprises a wire mechanism WM', WM” and / or a push rod mechanism PM', PM”.

[0123] In some examples the plurality of elongated guides 10', 10" comprises one of or a combination of rods 11 and / or wires 12 and / or pushrods 13 and / or pulleys 14 and / or linkage 15 and / or arms 16 and / or yokes 17.

[0124] In some examples the airfoil control surface 2 is a portion of a wing of an aircraft, and wherein the at least two airfoil control segments 30', 30" form a combined transformable control surface area 2, which is at least one of or a combination of flaps and ailerons.

[0125] In some examples airfoil control segments 30', 30" partly form a portion of a sail member or entirely form a sail member. In another example airfoil control segments 30', 30" partly form a portion of a rudder member or entirely form a rudder member. The multi-rod actuator configuration may be used in other mechanical designs, such as a stiff sail for a sailboat or for the movement of the rudder in a windmill.

[0126] In some examples the disclosure is implemented in a fin or vertical stabilizer for an aircraft. The morphing surfaces technology and a multi-rod actuator configuration as disclosed, may be implemented in the fin of an aircraft where the morphing fin dynamically adjusts its shape and surface characteristics in real-time based on various flight conditions.

[0127] In some examples the multi-rod actuator configuration controls an airfoil control surface 2 that is an airfoil surface of a morphing wing of an aircraft with a compliant structure. The compliant structure in the morphing wing is designed to allows the wing shape to deform or change in response to external forces or control inputs from the multi-rod actuator configuration. The flexibility enables the wing to adapt its shape and aerodynamic properties, enhancing performance and efficiency during flight.

[0128] In some examples the multi-rod comprises the control circuitry CC programmed to control the clamping device 24', 24" and / or the holding member 41', 41" via the clamping selector valve devices CS', CS". In some examples the control actuator devices 20 comprises a position sensor 25, providing feedback to the control circuitry CC on real time positions of the elongated guide members 10', 10".

[0129] Figure 5A illustrates the trailing edge control surface 2 of a wing airfoil in a cross- sectional view. The figure features a three-segmented 30', 30", 30'" control surface with three hinges 31', 31", 31'". The control surface is divided into three segments 30', 30", 30'", each capable of independent movement for enhanced manoeuvrability. The inner hinge closest to the wing frame, in this example is a stiff rod hinge designed to provide structural support and stability. The inner hinge ensures that the innermost segment 30' maintains rigidity during flight, contributing to overall wing integrity. The rod hinge may be controlled by the multi-rod actuator configuration 1 and holds the largest forces exposed to the control surfaces on the wing. After the inner hinge 31' comes the two outer hinges 31", 31'" positioned along the outer edges of the control surface 2. These hinges are wire hinges controlled by wires connected to the multi-rod actuator configuration 1. The wires enable individual control of each segment 30', 30", 30'", allowing for precise adjustments in their positions.

[0130] Figure 5B illustrates a wing profile control surface comprising three segments, each controlled individually by a set of wires. These wires are strategically organized within the body of the control surface to facilitate precise movement and coordination of the segments. The control mechanism operates such that as much thread as is rolled out on the upper thread of the upper wheel, is rolled on the lower wheel when rotating downwards on the first segment. This arrangement ensures that the length of the threads remains constant from the first segment to the third segment, maintaining consistent tension and control throughout the entire control surface.

[0131] The multi-rod actuator configuration 1 serves the central control CC system for all three hinges. By integrating the control of the wire hinges into the same actuator system, the wing achieves synchronized movement across all segments 30', 30", 30'". The centralized control enhances coordination and responsiveness during flight manoeuvres.

[0132] The multi-rod actuator configuration 1 comprises a data program P for operating the multi-rod actuator configuration in accordance with the outlined method. The data program P contains a readable code designed for interpretation by the control circuitry's CC computer, enabling the execution of the method steps. Additionally, the invention features a dedicated data medium M designed to store the data program P. This data medium incorporates a program code readable by the computer, facilitating the execution of the disclosed method.

[0133] A person skilled in the art realises that the present disclosure is not limited to the preferred embodiments described above. The person skilled in the art further realizes that modifications and variations are possible within the scope of the appended claims.

[0134] Additionally, variations to the disclosed embodiments can be understood and effected by the skilled person in practicing the claimed disclosure, from a study of the drawings, the disclosure, and the appended claims.

Claims

CLAIMS1. A multi-rod actuator configuration (1) configured to control an airfoil control surface (2) comprising;- at least two elongated guide members (10),- at least one control actuator device (20) configured to control the movement of at least one of said elongated guide members (10),- a control circuitry (CC) coupled to a servo valve device (SV) for controlling the motion of a piston device (22) of the control actuator device (20); characterized in that- the multi-rod actuator configuration (1) comprises at least two airfoil control segments (30), each of which is coupled to the respective elongated guide member (10) and forms said airfoil control surface (2), and- a parking module (40) of the control actuator device (20) coupled to the control circuitry (CC) and a clamping selector valve device (CS) and configured to lock said at least one elongated guide member (10) stationary in position, wherein the parking module (40) comprises a holding member (41) configured to engage or disengage the associated elongated guide member (10).

2. The multi-rod actuator according to claim 1, wherein the control actuator device (20) comprises a cylinder device (21) configured to move said piston device (22) comprising at least two through-holes (23) through each of which the associated elongated guide member (10) extends, and wherein each through-hole (23) of the piston device (22) is associated with a respective clamping device (24), configured to engage or disengage the elongated guide member (10) extending through the associated through-hole (23), wherein the control circuitry (CC) is adapted to control the multi-rod actuator configuration (1) to perform; i) a first state wherein;- the clamping device (24) is configured to engage the associated elongated guide member (10) via provided fluid for the clamping selector valve device (CL); and- the piston device (22) is configured to move the associated elongated guide member (10) via provided fluid from the servo valve device (SV); ii) a second state wherein;- the clamping device (24) is configured to disengage the associated elongated guiding member (10); and- the associated elongated guide member (10) is permitted to freely move through the through-hole (23)3. The multi-rod actuator configuration (1) according to any one of the preceding claims, wherein the respective elongated guide member (10) comprises a linkage arrangement (LA', LA”) coupled between the airfoil control segment (30) and the elongated guide member (10).

4. The multi-rod actuator configuration (1) according to claim 3, wherein the linkage arrangement (LA) is configured to provide motion of the airfoil control segment (30) corresponding to a gear ratio of 1 to 10 times the motion of the elongated guide member (10).

5. The multi-rod actuator configuration (1) according to claim 4, wherein the linkage arrangement (LA) comprises a wire mechanism (WM) and / or a push rod mechanism (PM); and the airfoil control segment (30) comprises a hinge mechanism (31) configured to permit pivoting motion of the airfoil control segment (30) relative each other and relative an airfoil body, such as a wing of an aircraft.

6. The multi-rod actuator configuration (1) according to any one of the preceding claims, wherein the parking module (40) is associated with at least said control actuator device (20) configured to control the movement of at least one of said elongated guide members (10); wherein each control actuator device (20) comprises said cylinder device (21) configured to move said piston device (22) comprising at least two through-holes (23), through each of which the associated elongated guide member (10) extends;wherein each through-hole (23) of the piston device (22) is associated with a respective clamping device (24), configured to engage or disengage the elongated guide member(10) extending through the associated through-hole (23), the multi-rod actuator configuration (1) further comprises the control circuitry (CC) coupled to the clamping selector valve device (CS) and the servo valve device (SV) for controlling the motion of the piston device (22) and adapted to control the multi-rod actuator configuration (1) to perform; i) a first state wherein;- the clamping device (24) engages the associated elongated guide member (10', 10''); and- the piston device (22) moves the associated elongated guide member (10); ii) a second state wherein;- the clamping device (24) disengages the associated elongated guiding member (10); and- the associated elongated guide member (10) is permitted to freely move through the through hole (23); iii) a third state wherein;- the clamping device (24) engages the associated elongated guiding member (10) and the piston device (22) is held stationary in the cylinder device (21).

7. The multi-rod actuator configuration (1) according to any one of the preceding claims, wherein the plurality of elongated guides (10) comprises one of or a combination of rods(11) and / or wires (12) and / or pushrods (13) and / or pulleys (14) and / or linkage (15) and / or arms (16) and / or yokes (17).

8. The multi-rod actuator configuration (1) according to any one of the preceding claims, wherein the airfoil control surface (2) is a portion of a wing of an aircraft, and wherein the at least two airfoil control segments (30) form a combined transformable control surface area (2), which is at least one of or a combination of flaps and ailerons.

9. The multi-rod actuator configuration (1) according to any of the preceding claims, wherein the at least two airfoil control segments (30) partly form a portion of a sail member or entirely form a sail member.

10. The multi-rod actuator configuration (1) according to any of the preceding claims, wherein the at least two airfoil control segments (30) partly form a portion of a ruddermember or entirely form a rudder member.

11. The multi-rod actuator configuration (1) according to any one of the preceding claims, wherein the airfoil control surface (2) is an airfoil surface of a morphing wing of an aircraft with a compliant structure.

12. The multi-rod actuator configuration (1) according to any one of the preceding claims, further comprising the control circuitry (CC) programmed to control the clamping device (24) and / or the holding member (41).

13. The multi-rod actuator configuration (1) according to any one of the preceding claims, wherein each of the control actuator devices (20) comprises a position sensor (25), providing feedback to the control circuitry (CC) on real time positions of the elongated guide members (10).

14. A method for controlling an airfoil control surface (2) using the multi-rod actuator configuration (1) according to claim 1-13, the method comprises the steps of:- engaging the clamping device (24) to the associated elongated guide member (10);- moving the elongated guide member (10) by means of the piston device (22);- disengaging the clamping device (24) from the associated elongated guiding member (10);- permitting the associated elongated guide member (10) to freely move through the through-hole (23);- locking said at least one elongated guide member (10) stationary in position utilizing the parking module holding member (41);- reengaging the clamping device (24).

15. The method for controlling an airfoil control surface (2) using the multi-rod actuator configuration (1) according to claim 14, the method further comprising the steps of: a) operating the control circuitry (CC) to control the motion of the piston device (22) and the clamping device (24) to achieve the first state, wherein the clamping device engages the associated elongated guide member (10) and the piston device moves the associated elongated guide member; b) operating the control circuitry (CC) to control the motion of the piston device (22) and clamping device (24) to achieve the second state, wherein the clamping device disengages the associated elongated guiding member (10) allowing the associated elongated guide member to move freely through the through-hole (23); c) coupling each airfoil control segment (30) to a corresponding elongated guide member (10); d) utilizing the parking module (40) to lock at least one elongated guide member (10) stationary in position by engaging the holding member (41) with the associated elongated guide member; and e) adapting the control circuitry (CC) to lock at least one of said airfoil control segments (30) in position.

16. A data program (P), programmed for causing the multi-rod actuator configuration (1) according to any of claims 1 to 13 to execute the method according to any of claims 14- 15, wherein said data program (P) comprises a program code readable on a computer of the control circuitry (CC) for providing the steps of:- engaging the clamping device (24) to the associated elongated guide member (10);- moving the elongated guide member (10) by means of the piston device (22);- disengaging the clamping device (24) from the associated elongated guiding member (10);- permitting the associated elongated guide member (10) to freely move through the through-hole (23).

17. A data medium (M), configured for storing the data program (P) according to claim 16 , wherein the data medium comprises a program code being readable on the computer for performing the method according to any of claims 14-15.

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