High-fowler flap actuation apparatus and related methods

Abstract

The present invention relates to high Fowler flap actuation devices and related methods. Exemplary high Fowler flap actuation devices and related methods are disclosed. An exemplary device includes a control surface that is operably coupled to a wing of an aircraft by a first support arm and a drive arm, the drive arm being linearly extendable from a retracted position to a deployed position, the deployed position including the control surface extending away from the wing at a first angle relative to the wing.

Description

[0001] This application is a divisional application of Chinese patent application 201810905454.1 entitled "Goughfowler flap actuation device and related method", filed on August 10, 2018. Technical Field

[0002] This disclosure generally relates to aircraft, and more specifically to high-fowler flap actuators and related methods. Background Technology

[0003] When traveling at relatively slow speeds, many aircraft employ high-lift devices (such as flaps and slats) to increase the overall wing lift characteristics. This engagement of devices, operably linked to the aircraft's wings, increases lift but also increases drag. Therefore, such devices are disadvantageous at high speeds, where high drag is detrimental to flight performance and high lift is of little use. Summary of the Invention

[0004] One embodiment of the invention relates to an apparatus including a control surface operably coupled to the wing of an aircraft via a first support arm and a drive arm, the drive arm being linearly extendable from a retracted position to a deployed position, the deployed position including the control surface extending away from the wing at a first angle relative to the wing. The control surface may be a trailing edge flap. The apparatus may also include at least one second support arm. This enhances system operation. The first support arm may include a first body and a second body, the first body being pivotally coupled to the wing, and the second body extending pivotally from the first body. The first support arm may also include a third body and a fourth body, the third body extending pivotally from the second body, and the fourth body being pivotally coupled to the third body and the control surface. The first angle may be based on a second angle of the second body relative to the third body. The drive arm may include a first linear body, a second linear body, and a third linear body. The second linear body includes a first end and a second end, the first end being pivotally connected to the wing and the second end being pivotally connected to the first linear body. The first linear body includes a third end and a fourth end, the third end being pivotally connected to a control surface and the fourth end being operably connected to the wing via a pivotally movable bracket of the third linear body, the pivotally movable bracket being movable from a retracted position to an extended position. The first, second, and third ends may be pivotally connected via a universal joint. The second end may be pivotally connected to the midpoint of the first linear body. A first length of the second linear body may be equal to a second or third length of the first linear body, the second length including a first distance between the midpoint and the third end, and the third length including a second distance between the midpoint and the fourth end. The first and second linear bodies may be configured to move relatively perpendicularly along an axis that is relatively perpendicular to the trailing edge of the wing. The third linear body may be configured to move relatively parallel along an axis that is relatively parallel to the trailing edge of the wing. Another embodiment of the present invention relates to an apparatus comprising: a main wing portion of an aircraft, including an upper surface, a lower surface, control surfaces, and a cavity between a portion of the upper surface and the lower surface; and a drive arm disposed within the cavity, the drive arm including a first linear body and a second linear body, the first and second linear bodies being extendable from a retracted position to an deployed position. The second linear body may include a first end and a second end, the first end being operably coupled to the main wing portion and the second end being operably coupled to the first linear body; the first linear body includes a third end and a fourth end, the third end being operably coupled to the control surfaces and the fourth end being operably coupled to the main wing portion. The apparatus may further include a support arm disposed within the cavity, the support arm including a first body and a second body, the first body being coupled to the main wing portion and the second body being operably coupled to a third body of the support arm; the third body being operably coupled to a fourth body of the support arm; and the fourth body being coupled to the control surfaces.The second body can be operatively coupled to the third body at a first angle. The deployed position may include a control surface extending away from the main wing portion at a second angle relative to the main wing portion, the second angle being based on the first angle. Another embodiment of the invention relates to a method comprising: engaging an actuator coupled to a drive arm coupled to a control surface; extending the drive arm from a first position to a second position; extending the control surface from a retracted position to a deployed position, the deployed position including the control surface extending away from the main wing portion of an aircraft wing at a first angle relative to the main wing portion, the first angle being based on the second angle. The extended drive arm may include: extending a first linear body from the first position to the second position along a first axis and a second axis, the first linear body including a first end operatively coupled to the control surface, a midpoint operatively coupled to a second linear body, and a second end operatively coupled to the main wing portion via a third linear body; and extending a second linear body from the first position to the second position along the first axis and the second axis, the second linear body including a third end operatively coupled to the main wing portion and a fourth end operatively coupled to the first linear body. The method further includes extending the third linear body from the first position to the second position by moving the sliding member along the third linear body from the first position to the second position, the first position corresponding to the control surface being in the retracted position and the second position corresponding to the control surface being in the extended position. Attached Figure Description

[0005] Figure 1 This is an isometric view of an example Golfler flap actuator coupled to an example aircraft to implement the example disclosed herein.

[0006] Figure 2 yes Figure 1 Example plan view of the Golfler flap actuator.

[0007] Figure 3 It is a description Figure 1 and Figure 2 Isometric views of the example support arm and the example drive arm of the example High Fowler flap actuator.

[0008] Figure 4 yes Figure 1-3 A plan view of the example drive arm of the example High Fowler flap actuator.

[0009] Figure 5 This is in a collapsed position to implement the example disclosed in this article. Figure 1-4 Example plan view of the Golfler flap actuator.

[0010] Figure 6 This is an expanded position to implement the example disclosed in this article. Figure 1-5 Example plan view of the Golfler flap actuator.

[0011] Figure 7 yes Figure 1-6 An isometric view of the detailed portion of the example support arm of the example High Fowler flap actuator.

[0012] Figure 8 It is about Figure 1-6 Example support arm of the example High Fowler flap actuator Figure 7 Front view of the detailed parts.

[0013] Figure 9A This is a front view of an example support arm, including the camber angle.

[0014] Figure 9B This is a front view of another example support arm, including another curvature angle.

[0015] Figure 10 It's about the one in the collapsed position. Figure 1-6 Example support arm of the example High Fowler flap actuator Figure 7-8 The end view of the detailed part.

[0016] Figure 11 It is in the unfolded position. Figure 10 Example end view of the support arm.

[0017] Figure 12A Based on Figure 9A The curvature angle is in the unfolded position. Figure 1-6 Example of a side view of the trailing edge flap.

[0018] Figure 12B It is in the unfolded position based on another curvature angle. Figure 1-6 Example of a side view of the trailing edge flap.

[0019] Figure 12C It is based on another curvature angle in the unfolded position. Figure 1-6 Example of a side view of the trailing edge flap.

[0020] Figure 13 This indicates that it can be executed to operate. Figure 1-6 The flowchart shows an example method for the Golfler flap actuation system.

[0021] These figures are not drawn to scale. Wherever possible, the same reference numerals will be used throughout the figures and the accompanying written description to denote the same or similar parts. As used herein, the terms “connected” and “operably connected” are defined as being connected directly or indirectly (e.g., through one or more intermediate structures and / or layers). Detailed Implementation

[0022] A Golfler flap actuation device and related method are disclosed. One example device includes a control surface operatively coupled to the wing of an aircraft via a first support arm and a drive arm, the drive arm being linearly extendable from a retracted position to an extended position, the extended position including the control surface extending away from the wing at a first angle relative to the wing.

[0023] Another example device includes a main wing portion of an aircraft, the main wing portion including: an upper surface, a lower surface, control surfaces, and a cavity between a portion of the upper surface and the lower surface; and a drive arm disposed in the cavity, the drive arm including a first linear body and a second linear body, the first linear body and the second linear body being extendable from a retracted position to an deployed position.

[0024] One example method includes: engaging an actuator coupled to a drive arm coupled to a control surface; extending the drive arm from a first position to a second position; and extending the control surface from a retracted position to an extended position, the extended position including the control surface extending away from the main wing portion of an aircraft wing at a first angle based on the second angle.

[0025] Conventional aircraft use dynamic control surfaces (e.g., flaps and slats) to optimize their aerodynamic characteristics. Additionally or alternatively, conventional aircraft may use ailerons, elevators, rudders, spoilers, etc., to further optimize their aerodynamic characteristics. Flaps are aerodynamic surfaces on the leading edge (e.g., Kruger flaps) or trailing edge (e.g., Fowler flaps) of an aircraft's wing that can be used to increase the wing's lift at a given airspeed. For example, deploying one or more flaps during flight can increase the lift-to-drag ratio experienced by the aircraft, thereby reducing the aircraft's approach velocity and / or increasing the angle of attack (e.g., descent angle, etc.) at landing.

[0026] In some examples, the flap is operatively coupled to one or more actuators (e.g., electromechanical actuators, electrohydraulic actuators, electro-hydraulic actuators, hydraulic actuators, etc.) and / or one or more motors (e.g., electric motors, hydraulic motors, etc.) to move the flap from a retracted or stowed position to an deployed or intermediate position. In some examples, the flap is a Fowler flap. For example, the flap could be a trailing-edge segmented flap operatively coupled to the main part of an aircraft wing, which slides backward before hinged in the downward direction (e.g., opposite to the aircraft's path of travel). In such examples, the flap can first increase the chord of the main wing before increasing the camber of the main wing. The chord is an imaginary straight line connecting the leading edge and trailing edge of an airfoil, while camber refers to the asymmetry between the top and bottom surfaces of the airfoil.

[0027] In examples of existing technology, the use of Fowler flaps on an aircraft wing involves using one or more fairings to cover an external actuator mechanism that actuates, controls, etc., the Fowler flap. A fairing is a structure used to reduce drag (e.g., parasitic drag) by covering gaps or spaces or protrusions in structural features extending into the oncoming airflow. For example, a fairing may cover a mechanism extending from the wing surface, which supports the flap in a retracted or deployed orientation. For example, the Fowler flap may include an actuation system (e.g., a multi-link linkage, an external cantilever track, a deep-hinge support mechanism, etc.) that cannot be retracted into a cavity or recess in the aircraft wing, thus requiring one or more fairings to cover one or more components of the actuation system. For example, the actuation system may include one or more complex components to achieve the desired movement path of the Fowler flap. However, the use of fairings increases the complexity of manufacturing the components due to the added parts, and if the fairing protrudes into the airflow, it reduces the aircraft's operational efficiency by generating parasitic drag.

[0028] The example High Fowler flap actuation device and related methods disclosed herein are operable to deploy flaps, such as Fowler flaps, operably coupled to an aircraft via a linear drive actuation system. As used herein, the terms “High Fowler flap actuation device” and “High Fowler flap actuation system” are used interchangeably and refer to one or more Fowler flaps or Fowler flap assemblies that, when actuated, extend one or more Fowler flaps or Fowler flap assemblies a relatively large distance (e.g., approximately to the chord length of the flap) away from the main part of the aircraft wing.

[0029] In some publicly available examples, the High Fowler flap actuator includes one or more support arms (e.g., five support arms) and one or more drive arms (e.g., two drive arms), which are structurally independent of each other. For example, one or more support arms may not be coupled to one or more of the drive arms. For instance, a first end of a support arm may be coupled to the main wing portion of the aircraft at a first coupling position, while a second end of the support arm may be coupled to the Fowler flap at a second coupling position. In such an example, a first end of the drive arm may be operatively coupled to the main wing portion of the aircraft at a third coupling position, while a second end of the drive arm may be coupled to the Fowler flap at a fourth coupling position. In such examples, the first and third coupling positions, as well as the second and fourth coupling positions, may be different.

[0030] In some publicly available examples, one or more support arms and one or more drive arms are operable to move a Fowler flap from a first position (e.g., retracted position, stowed position, etc.) to a second position (e.g., deployed position, extended position, intermediate position, etc.) via linear movement of one or more support arms and one or more drive arms. For example, the drive arm may be a scissor-driven linkage including a linear actuator. As used herein, the term "linear movement" refers to the movement of one or more components along a direction or path defined by a straight line based on the movement of said one or more components and / or one or more associated components. For example, as the Fowler flap actuator deploys the trailing edge flap from the retracted position to the deployed position, a first universal joint of the drive arm may move relative to a second universal joint perpendicular to the drive arm.

[0031] In some disclosed examples, the drive arm is connected to the main wing section, Fowler flaps, etc., via a pivot bracket or pivot support, a universal joint such as a ball joint, etc. By eliminating complex actuation components (e.g., multi-link linkages, external cantilever tracks, deep hinge supports, etc.), the high-Fowler flap actuators and related methods disclosed herein reduce parasitic drag by reducing and / or eliminating external fairings from the aircraft wing. The disclosed example high-Fowler flap actuators reduce parasitic drag because they fit into a recess in the aircraft wing when retracted.

[0032] Figure 1 This is an isometric view of an example Golferer flap actuation system 100 coupled to an example aircraft 102 to implement the examples disclosed herein. In the example shown, aircraft 102 includes a first wing 104 and a second wing 106 coupled to a fuselage 108. A first engine 110 and a second engine 112 are coupled to wings 104 and 106. First to fourth slats 114, 116, 118, 120, a first leading-edge flap 122 and a second leading-edge flap 124, and first to fourth trailing-edge flaps 126, 128, 130, 132 are operatively coupled to wings 104 and 106. In the example shown, leading-edge flaps 122 and 124 are Kruger flaps. In the example shown, trailing-edge flaps 126, 128, 130, 132 are Fowler flaps (e.g., Golferer flaps) and are operatively coupled to the main portion of wings 104 and 106. In the example shown, the lower trailing edge panel 133 and the upper trailing edge panel 135 (e.g., lower recessed panel 133, upper recessed panel 135, etc.) of the trailing edge flaps 126, 128, 130, 132 have been made transparent.

[0033] The additional aircraft control surfaces of the aircraft include a first aileron 134 and a second aileron 136, a first elevator 138 and a second elevator 140 operably connected to a first horizontal stabilizer 142 and a second horizontal stabilizer 144, and a rudder 146 operably connected to a vertical stabilizer 148.

[0034] exist Figure 1 In the illustrated example, the first to fourth trailing edge flaps 126, 128, 130, and 132 are in the deployed position. For example, each of the first to fourth trailing edge flaps 126, 128, 130, and 132 can be extended from the retracted position to the deployed position by a corresponding Golfer flap actuation system in the Golfer flap actuation system 100. For example, the deployed position may include the first to fourth trailing edge flaps 126, 128, 130, and 132 fully extended away from the wings 104 and 106. In such an example, the first to fourth trailing edge flaps 126, 128, 130, and 132 may extend approximately as far as the chord length of the trailing edge flaps 126, 128, 130, and 132. Although the function of the example Golfer flap actuation system 100 described below is described in the singular, the function applies to all Golfer flap actuation systems 100.

[0035] In the example shown, the first trailing edge flap 126 and the second trailing edge flap 128 are each operably connected to the main wing portion of the first wing 104 via (1) the first to fifth support arms 150, 152, 154, 156, 158 and the first drive arm 160 and the second drive arm 162. In the example shown, the third trailing edge flap 130 and the fourth trailing edge flap 132 are each operably connected to the main wing portion of the first wing 104 via (1) the first to fifth support arms 150, 152, 154, 156, 158 and the first drive arm 160 and the second drive arm 162.

[0036] In the example shown, the first to fifth support arms 150, 152, 154, 156, and 158 support the first trailing edge flap 126, while the first drive arm 160 and the second drive arm 162 drive, extend, push, and extend the first trailing edge flap 126 from the retracted position to the deployed position via linear motion. For example, as the Golfler flap actuation system 100 deploys the trailing edge flaps 126, 128, 130, and 132 from the retracted position to the deployed position or a position between the retracted and deployed positions, the leading edge 164 of the trailing edge flaps 126, 128, 130, and 132 can move relative to the spar 166 (e.g., the rear spar 166) perpendicular to the wings 104 and 106. In such an example, as the trailing edge 168 of the trailing edge flaps 126, 128, 130, 132 moves in the Fowler direction or in a Fowler motion (e.g., sliding backward before hinged in the downward direction (e.g., opposite to the aircraft's path of travel)), the leading edge 164 can move relatively perpendicular to the rear spar 166.

[0037] Figure 2 Through Figure 1 The High Fowler flap actuation system 100 is operably coupled to Figure 1 The main part of the first wing 104 Figure 1 A plan view of the first trailing edge flap 126. Although the following description is based on the first trailing edge flap 126... Figure 2 The description includes the functions and / or structure of an example High Fowler flap actuation system 100, but the functions and / or structure are adapted to use with... Figure 1 All of the High Fowler flap actuation systems 100 related to the second to fourth trailing edge flaps 128, 130, and 132. For clarity, Figure 1 The example recessed panel 133 and the upper recessed panel 135 have been removed.

[0038] exist Figure 2 In the example shown, the first trailing edge flap 126 is in an intermediate position. For example, the first trailing edge flap 126 is between a retracted position and an extended position. In the example shown, the Golfler flap actuation system 100 includes... Figure 1The first to fifth support arms 150, 152, 154, 156, and 158 are shown. Each of the support arms 150, 152, 154, 156, and 158 in the illustrated example includes first to fourth main bodies (e.g., structural members, support members, etc.) 200, 202, 204, and 206 to support the first trailing edge flap 126 when it moves from a retracted position, an intermediate position, etc., to an deployed position. Additionally or alternatively, when the first trailing edge flap 126 extends or retracts, the first to fourth example support members 200, 202, 204, and 206 can be used to control the orientation, position, etc., of the first trailing edge flap 126. Similarly, when the first trailing edge flap 126 returns from an deployed position to an intermediate position, a retracted position, etc., the first to fourth support members 200, 202, 204, and 206 can be used to support the first trailing edge flap 126.

[0039] In the example shown, the first support member 200 and the fourth support member 206 are fixed support members, anchored in place by one or more fasteners (e.g., rivets, bolts, etc.), brackets, structural adhesives, and / or combinations thereof. For example, the first support member 200 can be fixedly connected to the first wing 104 by a non-movable bracket or any other fixed support mechanism. Similarly, the fourth support member 206 can be fixedly connected to the first trailing edge flap 126 by one or more non-movable brackets or any other fixed support mechanism.

[0040] In the illustrated example, the second support member 202 and the third support member 204 are pivotable support members for supporting the first trailing edge flap 126 when it is retracted and / or extended relative to the first wing 104. For example, the second support member 202 and the third support member 204 pivot about their respective coupling connections to support the retraction and / or extension of the first trailing edge flap 126 relative to the first wing 104. In the illustrated example, the second support member 202 is operatively coupled to the first support member 200 and the third support member 204. In the illustrated example, the second support member 202 is pivotally coupled (e.g., rotatably mounted) to the first support member 200 via a first pivot hinge 208. In the illustrated example, the second support member 202 is pivotally coupled to the third support member 204 via a second pivot hinge 210. In the illustrated example, the second support member 202 is pivotally rotatable about the first pivot hinge 208 and the second pivot hinge 210.

[0041] In the example shown, the third support member 204 is operatively connected to the second support member 202 and the fourth support member 206. In the example shown, the third support member 204 is pivotally connected to the fourth support member 206 via a third pivot hinge 212. In the example shown, the third support member 204 is pivotally rotatable about the second pivot hinge 210 and the third pivot hinge 212.

[0042] In the illustrated example, the first to fourth support members 200, 202, 204, and 206 are hybrid material support arms, comprising both metallic and non-metallic mechanical structures. Alternatively, the first to fourth support members 200, 202, 204, and 206 may be made of a single metallic or non-metallic material (e.g., aluminum, carbon fiber, titanium, etc.). For example, the first support member 200 may be made entirely of titanium. In the illustrated example, the first end 242 and the second end 244 of the second support member 202 are joint ends made of titanium. Alternatively, the joint ends at the first end 242 and the second end 244 may be made of any other metal or metal alloy (e.g., aluminum, stainless steel, etc.) and / or combinations thereof. In the illustrated example, the arm portion 246 of the second support member 202 is made of carbon fiber. Alternatively, the arm portion 246 may be made of any other non-metallic material (e.g., ceramic, plastic, etc.) and / or combinations thereof.

[0043] exist Figure 2 In the example shown, the Golfler flap actuation system 100 includes Figure 1 The first drive arm 160 and the second drive arm 162. Although the function and / or structure of the example drive arms 160, 162 described below are described in conjunction with the first example drive arm 160, the function and / or structure also apply to the second drive arm 162. The first drive arm 160 of the example shown is operable to move the first trailing edge flap 126 from a first position (e.g., retracted position) to a second position (e.g., deployed position) by linear motion. For example, the first drive arm 160 can move along a path defined by a straight line (e.g., from the retracted position to the deployed position). In such an example, the first drive arm 160 includes components that move relatively parallel (e.g., parallel or within tolerances of 1 degree, 3 degrees, etc.) to and relatively perpendicular to the rear spar 166 as the first trailing edge flap 126 moves in a Fowler motion manner from the retracted position to the deployed position.

[0044] In the example shown, the first trailing edge flap 126 is supported by the first to fifth support arms 150, 152, 154, 156, and 158, while the first drive arm 160 and the second drive arm 162 extend or retract the first trailing edge flap 126. In the example shown, the first drive arm 160 and the second drive arm 162 are not connected to any of the first to fifth example support arms 150, 152, 154, 156, and 158. In the example shown, the first drive arm 160 and the second drive arm 162 are independent of the first to fifth example support arms 150, 152, 154, 156, and 158.

[0045] In the example shown, the first drive arm 160 is a scissor link (e.g., a cross-shaped actuator). For example, a scissor link uses a cross-shaped “X” pattern of connecting folding supports to extend the body from a first position to a second position by applying force to the outer portion of a set of supports at one end of the scissor link. The first drive arm 160 in the example shown includes a first linear body 214 and a second linear body 216. The first linear body 214 in the example shown is a linear drive arm, for example, a beam including a first end and a second end to linearly move the first trailing edge flap 126 from the first position to the second position. The first end of the first linear body 214 in the example shown is operably coupled to the first trailing edge flap 126 via a first universal joint 218, such as a ball joint. Alternatively, the first end of the first example linear body 214 can be operably coupled to the first example trailing edge flap 126 via any other movable coupling attachment mechanism that provides a substantially similar range of motion compared to the first universal joint 218.

[0046] In the illustrated example, the first drive arm 160 includes a second end of a first linear body 214, which is operatively coupled to the first wing 104 via a third linear body 220 including the first and second ends. In the illustrated example, the second end of the first linear body 214 is operatively coupled to the third linear body 220 via a pivotally movable bracket 222. Alternatively, the second end of the first example linear body 214 may be operatively coupled to the third example linear body 220 via any other pivotally and / or movable coupling attachment mechanism. Alternatively, the first to third linear bodies 214, 216, 220 may have alternating geometries and / or shapes. For example, the first to third linear bodies 214, 216, 220 may be characterized by cross-sectional areas, densities, materials, etc., that are substantially similar or different from each other. The third linear body 220 in the illustrated example is a mechanical linear actuator, such as a ball screw drive shaft (e.g., a ball screw, a threadless ball screw drive rod, etc.), which includes a first end and a second end to support the linear movement of the pivotally movable support 222. Alternatively, the third example linear body 220 can be a rod, wherein the pivotally movable support 222 can slide along the third linear body 220. For example, the pivotally movable support 222 can be slidably coupled to the third linear body 220. The third linear body 220 in the illustrated example can be fixedly coupled to the first wing 104. In the illustrated example, the third linear body 220 is mountably coupled to the first wing 104 by a first attachment support 224 at the first end of the third linear body 220 and a second attachment support 226 at the second end of the third linear body 220. For example, the first attachment support 224 and the second attachment support 226 can be mountably connected to the main part of the first wing 104 by one or more fasteners (e.g., one or more bolts, nuts, rivets, screws, washers, etc. and / or combinations thereof), attachment mechanisms, bracket supports, etc. and / or combinations thereof.

[0047] In the illustrated example, the pivotable support 222 includes a first pivot support 228 coupled to the movable member 230. The first pivot support 228 in the illustrated example allows the first linear body 214 to pivot about the pivotable support 222 (e.g., rotate upwards, downwards, etc. relative to the pivotable support 222) as the first trailing edge flap 126 moves from a first position to a second position. For example, the first linear body 214 can linearly move from the first position to the second position due to the movement achieved by the pivotable support 222. For example, as the first trailing edge flap 126 extends from a retracted position to an extended position, the pivotable support 222 can move along the third linear body 220 while pivoting about the first pivot support 228.

[0048] The movable member 230 in the example shown is a drive shuttle, such as a ball nut. The movable member 230 can be actuated, moved, and moved from a first position to a second position. For example, the first position may include positioning the movable member 230 at a first end of the third linear body 220. In another example, the second position may include positioning the movable member 230 at a second end of the third linear body 220, opposite to the first end.

[0049] In the example shown, the movable member 230 can be moved from a first position to a second position via an actuator 232. For example, the actuator 232 can be a drive mechanism, such as a motor (e.g., an electric motor, hydraulic motor, electro-hydraulic motor, etc.), a gearbox, etc., which is rotatably and / or movably coupled to the actuator shaft 234 (e.g., a rotatable shaft, a rotatable actuation shaft, etc.). In such an example, the actuator 232 can be actuated or engaged to rotate the actuator shaft 234, causing the movable member 230 to move from the first position to the second position, and thus causing the first trailing edge flap 126 to extend from the first position to the second position (e.g., via an extension of the first linear body 214). In the example shown, the flap drive motor shaft 236 operatively connects the actuator shaft 234 together to help ensure that the actuator 232 actuates, moves, operates, etc., at the same or substantially similar rates.

[0050] In the example shown, the second linear body 216 is a linear drive arm, such as a rod, which includes a first end and a second end to drive, guide, and / or support the movement of the first linear body 214. The first end of the second linear body 216 in the example shown is operatively coupled to a second universal joint 238, such as a ball joint. The second end of the second linear body 216 in the example shown is operatively coupled to approximately the midpoint of the first linear body 214 via a third universal joint 240, such as a ball joint. Alternatively, the second end of the second example linear body 216 may be operatively coupled to any other location of the first example linear body 214 via any other type of movable coupling attachment mechanism.

[0051] In the example shown, the second universal joint 238 is a pivotable support anchored to a pivot point at the first end of the second linear body 216. The second universal joint 238 in the example shown can be fixedly coupled to the first wing 104. In the example shown, the second universal joint 238 is mountably coupled to the first wing 104 via one or more fasteners (e.g., one or more bolts, nuts, rivets, screws, washers, etc. and / or combinations thereof), attachment mechanisms, bracket supports, etc. and / or combinations thereof. In the example shown, the first to third universal joints 218, 238, 240 are relatively identical (e.g., identical within machining tolerances, mechanical tolerances, etc.). Alternatively, the first to third universal joints 218, 238, 240 can be different from each other. In the example shown, the first centerline of the actuator shaft 234 intersects the second centerline of the second universal joint 238 to achieve linear movement of the Golfler flap actuation system 100, wherein the first and second centerlines extend parallel to the rear wing spars 166.

[0052] Combination Figure 2 The example shown illustrates that the structure, function, and / or operation of each of the first example support arm 150 and the first drive arm 160 are identical to the corresponding structure, function, and / or operation of the second to fifth support arms 152, 154, 156, 158, and the second drive arm 162 as described above. Therefore, for the sake of brevity, Figure 2 The structure, function and / or operation of these components and structural parts will not be described in detail in this article.

[0053] In the example shown, when in the retracted position, the Golfler flap actuation system 100 fits within a cavity or recess 248 of the first wing 104. The recess 248 in the example shown is defined as (1) between the first wing 104 and the first trailing edge flap 126 and (2) between the top surface (not shown) of the upper recessed panel 135 and the bottom surface (not shown) of the lower recessed panel 133. In the example shown, because the Golfler flap actuation system 100 fits completely within the recess 248, one or more external fairings are not required.

[0054] Figure 3 It is a description Figures 1 to 2 An isometric view of the detailed portions of the first support arm 150, the second support arm 152, and the first drive arm 160. For clarity, Figure 1 The example recessed panel 133 and example recessed panel 135 have been removed. In the example shown, the first support arm 150 and the second support arm 152, the first drive arm 160, the first trailing edge flap 126, and the corresponding components are in a retracted position. For example, the actuator 232 can be actuated to rotate the actuator shaft 234, thereby engaging the movable member 230 from the retracted position (e.g., from...). Figure 2The first linear body 214 and the second linear body 216 move to the deployed position (e.g., to the second end of the third linear body 220). In such an example, as the example movable member 230 moves to the deployed position, the first linear body 214 and the second linear body 216 move to the deployed position. As the first example linear body 214 and the second example linear body 216 move to the deployed position, the first support arm 150 and the second support arm 152 support the first example trailing edge flap 126 when it moves to the deployed position.

[0055] Figure 4 It is operably connected to Figure 1-3 The first example trailing edge flap 126 is connected to Figure 1-3 The first wing 104 Figure 1-3 The first example is a plan view of the drive arm 160. For clarity, Figure 1 The example recessed panel 133 and example recessed panel 135 have been removed. In the example shown, the first drive arm 160 moves relative to the first axis 400 and the second axis 402 from a retracted position (e.g., when actuated) to an extended position. The first axis 400 and the second axis 402 in the example shown are in the same geometric plane. The first axis 400 in the example shown is connected by... Figure 2-3 The first universal joint 218 and the second universal joint 238 are formed by imaginary lines. The second axis 402 in the example shown is formed by a second imaginary line connecting the second universal joint 238 and the third linear body 220. In the example shown, the first axis 400 and the second axis 402 are perpendicular to each other (e.g., perpendicular or perpendicular within tolerances of 1 degree, 3 degrees, etc.).

[0056] exist Figure 4 In the example shown, the first drive arm 160 moves the first example trailing edge flap 126 by linear motion because one or more components of the first drive arm 160 move along one or both of the first axis 400 and the second axis 402. In the example shown, Figure 2-3 The first end of the first linear body 214 moves along the first axis 400. For example, the first end of the first linear body 214 may move in a direction defined by a straight line along the first axis 400. In the example shown, the second end of the first linear body 214 and the movable member 230 move along the second axis 402. In the example shown, the first end of the second linear body 216 pivots about the point where the first axis 400 and the second axis 402 intersect at the second universal joint 238. In the example shown, as the first linear body 214 and the third universal joint 240 move from a first position to a second position (e.g., from a stowed position to an unfolded position), the second end of the second linear body 216 moves along the first axis and the second axis.

[0057] In the illustrated example, the movement path of the first linear body 214 is controlled along the second axis 402 at the first end of the first linear body 214 by a pivotally movable bracket 222 driven along the third linear body 220. In the illustrated example, the movement path of the third universal joint 240 is driven by the second linear body 216 as the second linear body 216 pivots about the second universal joint 238. In the illustrated example, the linear movement at the first end and the arcuate movement (e.g., bending movement, pivoting movement, etc.) at the third universal joint 240 are combined to drive the second end of the first linear body 214 in a linear direction along the first axis 400. As the first linear body 214 drives the first trailing edge flap 126 from the retracted position to the deployed position, the first linear body 214 falls out of the plane of the first axis 400 and the second axis 402, allowing the first trailing edge flap 126 to droop below the wing 104.

[0058] In the example shown, the first drive arm 160 moves the first trailing edge flap 126 by linear motion due to the lengths (e.g., design lengths) of the first linear body 214 and the second linear body 216. For example, the first length 404 can be defined as a first distance between (1) the first centerline 406 of the first universal joint 218 and (2) the second centerline 408 intersecting the midpoint of the first linear body 214. In such an example or another example, the second length 410 can be defined by a second distance between (1) the second centerline 408 intersecting the midpoint of the first linear body 214 and (2) the third centerline 412 intersecting the first connection point 414 of the pivotable support 222.

[0059] In the example shown, the midpoint of the first linear body 214 is defined as half the distance between the first universal joint 218 and the first mounting point 414. In such an example, the third length 416 may be defined by a third distance between (1) a fourth centerline 418 intersecting the midpoint of the first linear body 214 and (2) a fifth centerline 420 intersecting the second universal joint 238. In the example shown, the first length 404, the second length 410, and the third length 416 are relatively equal (e.g., equal or equal within tolerances such as 0.1 mm, 0.5 mm, etc.). Since the first to third lengths 404, 410, 416 are relatively equal in the example shown, the first drive arm 160 moves the first trailing edge flap 126 from a first position to a second position by the linear movement of the first drive arm 160. For example, as the first drive arm 160 moves the first trailing edge flap 126 from a retracted position to an deployed position, the first universal joint 218 may move relatively vertically away from the second universal joint 238. In such an example, the pivotable support 222 rotates about the second axis 402 such that as the linear drive arm 160 extends the first universal joint 218 away from the second universal joint 238 linearly, thereby extending the first trailing edge flap 126 in a Fowler motion, the first trailing edge flap 126 can droop under the wing 104 by a camber motion.

[0060] Figure 5 This is to implement the examples disclosed in this article. Figure 1-4 Example plan view of the High Fowler flap actuation system 100. Figure 5 In the example shown, the Golfler flap actuation system 100 is in the retracted position. For clarity, Figure 1 The example lower recessed panel 133 and example upper recessed panel 135 of the first trailing edge flap 126 have been made transparent. In the example shown, when in the retracted position, the Golfler flap actuation system 100 fits within a recess 248 of the first wing 104. The recess 248 shown in the example is defined (1) between the first wing 104 and the first trailing edge flap 126 and (2) in Figure 1 The area between the top surface of the upper recessed panel 135 and the bottom surface of the lower recessed panel 133. In the example shown, since the Golfler flap actuation system 100 fits perfectly within the recess 248, one or more external fairings are not required.

[0061] Figure 6 It is in the unfolded position. Figure 1-5 A plan view of an example Highfowler flap actuation system 100. For clarity, Figure 1 The example concave panel 135 of the first trailing edge flap 126 has been removed, and Figure 1The example recessed panel 133 of the first trailing edge flap 126 has been made transparent. In the example shown, the first trailing edge flap 126 moves from a retracted position to an deployed position by a linear movement based on the first drive arm 160 and the second drive arm 162 that moves the first universal joint 218 away from the second universal joint 238 relatively vertically.

[0062] Figure 7 The link is in the collapsed position. Figure 1-6 The first wing 104 Figure 1-3 and Figure 5-6 An isometric view of the detailed portion of the first example support arm 150. In some examples, Figure 1-6 The High Fowler flap actuation system 100 guides the overall camber, curl, droop, etc., of the trailing edge flaps 126, 128, 130, and 132 based on a camber angle 700. The camber angle 700 in the illustrated example determines the overall camber angle, overall droop, overall curl, etc., of the first trailing edge flap 126 when extended (e.g., fully extended). In the illustrated example, the camber angle 700 is an angle relative to a first longitudinal axis 702 and a second longitudinal axis 704. The first longitudinal axis 702 in the illustrated example is a first reference vertical axis. The third longitudinal axis 706 in the illustrated example is a second reference vertical axis parallel to an imaginary vertical line connecting the upper wing skin 708 and the lower wing skin 710 of the rear wing spars 166 of the first wing 104. In the illustrated example, the first support member 200 of the first example support arm 150 is connected to the rear wing spars 166. The following is in conjunction with... Figure 8 Further details regarding the third longitudinal axis 706 are described.

[0063] In the example shown, the second longitudinal axis 704 is offset from the first longitudinal axis 702 by a curvature angle 700. In some examples, Figure 1 The desired amount of camber movement of one or more of the trailing edge flaps 126, 128, 130, and 132 can be determined based on adjusting, configuring, and generating a constant camber angle 700. For example, by configuring the second support member 202 relative to... Figure 1-6 The connection of the third support member 204 generates a camber angle 700, which can achieve the desired amount of flap camber. For example, the amount of camber of the first trailing edge flap 126 can increase as the camber angle 700 increases.

[0064] The illustrated example further shows a fourth longitudinal axis 712 that is relatively parallel to the fifth longitudinal axis 714 when the first support arm 150 is in the retracted position. Alternatively, when the first example support arm 150 is in the retracted position, the fourth example longitudinal axis 712 and the fifth example longitudinal axis 714 may not be relatively parallel to each other. In the illustrated example, the fourth longitudinal axis 712 is a reference vertical axis that is relatively parallel to an imaginary vertical line connecting the top surface 716 and the bottom surface 718 of the first pivot hinge 208. In the illustrated example, the fifth longitudinal axis 714 is a vertical axis that is relatively parallel to an imaginary vertical line connecting the top surface 720 and the second surface 722 of the third pivot hinge 212. The first longitudinal axis 702 of the illustrated example is relatively parallel to the fourth longitudinal axis 712 and the fifth longitudinal axis 714.

[0065] Figure 8 The link is in the collapsed position. Figure 1-7 The first wing 104 Figure 1-3 and Figure 5-7 The first example of a support arm 150 Figure 7 A front view of the detailed section. In the example shown, the camber angle 70° is relative to... Figure 7 The angle between the first longitudinal axis 702 and the second longitudinal axis 704. In the example shown, the connection between the second support member 202 and the third support member 204 produces a bending angle 700. For example, the form or shape of the second support member 202 and / or the third support member 204, and the connection between the second support member 202 and the third support member 204, can cause, produce, induce, etc., a bending angle 700.

[0066] Figure 9A yes Figure 2-3 and Figure 5-8 Example: Front view of the second support member 202. In the example shown, the second support member 202 is configured to generate... Figure 7-8 The curvature angle is 70°. In the example shown, the curvature angle 70° is relative to the horizontal axis 90° and... Figure 2-3 and Figure 5-8 The angle of the top surface 902 of the second end 244 of the support member 202. For example, the bending angle is based on the angle formed by the end of the support member being connected to the arm of the support member.

[0067] Figure 9BThis is a front view of the fifth example support member 904. In the example shown, the fifth support member 904 includes a first end 906, a second end 908, and an arm 910 connecting the first end 906 and the second end 908. The first end 906 and the second end 908 are lugs for forming a pivot hinge by connection with other support members. The first end 906, the second end 908, and the arm 910 can be made of metallic or non-metallic materials. For example, the first end 906 and the second end 908 can be made of titanium, while the arm 910 can be made of carbon fiber. The fifth example support member 904 shown is configured, formed, constructed, etc., to produce another example bend angle 912. Figure 9B The curvature angle 912 is the angle relative to the top surface 914 of the fifth example support member 904 and the horizontal axis 900. This is because the connection angle of the second end 908 of the fifth support member 904 is greater than the connection angle of the second end 244 of the second support member 202. Figure 9B The curvature angle is greater than 700. Figure 7-9A The curvature angle is 700.

[0068] Figure 10 It is connected to Figure 1-8 The first wing 104 Figure 1-3 and Figure 5-8 The first example support arm 150 in the retracted position Figure 7-8 A detailed end view of the portion. In the example shown, the third longitudinal axis 706, as described above, is connected to... Figure 7-8 The imaginary lines of the upper wing skin 708 and the lower wing skin 710 are parallel to the reference vertical axis. Figure 7-8 In the example shown, the rear wing spar 166 is connected to the first support member 200 of the first support arm 150. In the example shown, when the first support arm 150 is in the retracted position, the first longitudinal axis 702 and the second longitudinal axis 704 are relatively parallel to the fourth longitudinal axis 712 and the fifth longitudinal axis 714. Alternatively, when the first support arm 150 is in the retracted position, the second longitudinal axis 704, the fourth longitudinal axis 712, and the fifth longitudinal axis 714 may not be relatively parallel to each other. In the example shown, the camber angle 700 is not visible from this viewpoint and is not explicitly shown.

[0069] In the example shown, Figure 1The camber of one or more of the trailing edge flaps 126, 128, 130, and 132 can be determined based on the connection of the second support member 202 and the third support member 204, the form or shape of the second support member 202 and the third support member 204, and / or combinations thereof, to produce a camber angle 700. For example, the amount of camber of the first trailing edge flap 126 can be increased by increasing the camber angle 700. In the example shown, the camber retraction angle 1000 is the angle between the fifth longitudinal axis 714 and the horizontal axis 1002. In the example shown, the horizontal axis 1002 is a reference horizontal axis that is relatively perpendicular to the third longitudinal axis 706. In the example shown, the horizontal axis 1002 passes through the relative midpoint of an illusory vertical line between the upper wing skin 708 and the lower wing skin 710.

[0070] Figure 11 It is a connection in the unfolded position. Figure 1-8 and Figure 10 The first wing 104 Figure 1-3 and Figure 5-8 The first example of a support arm 150 Figure 7-8 A detailed end view of the portion. In the example shown, the second support member 202 and the third support member 204 extend fully. In the example shown, based on... Figure 7-8 and Figure 9A The bending angle is 700°, and the third support member 204 is relative to Figure 10 The fifth longitudinal axis 714 and the horizontal axis 1002 form a first flap droop angle 1100. In the example shown, the camber angle 700 is the angle relative to the second longitudinal axis 704 and the fourth longitudinal axis 712. In the example shown, the camber angle 700 is also the angle relative to the second longitudinal axis 704 and the fifth longitudinal axis 714.

[0071] In some examples, the first flap droop angle 1100 is adjusted based on the configured camber angle 700. For example, the first flap droop angle 1100 may increase due to an increase in the camber angle 700. In another example, the first flap droop angle 1100 may decrease due to a decrease in the camber angle 700.

[0072] Figure 12A Based on Figure 7-9A and Figure 11 The curvature angle of 70° is in the unfolded position. Figure 1-6 A side view of the first example trailing edge flap 126. In the example shown, the first trailing edge flap 126 is... Figure 11 The first flap droops at an angle of 1100°, extending away from the main portion of the first wing 104. In the example shown, the droop of the first trailing edge flap 126 is based on... Figure 11The first flap droop angle is 110°. In the example shown, Figure 11 The first flap droop angle is 1100° based on a camber angle of 700°.

[0073] Figure 12B yes Figure 12A The side view depicts the unfolded position based on the second curvature angle of 120°. Figure 1-6 The first example is the trailing edge flap 126. In the example shown, the second camber angle 120° is relative to... Figure 7-8 , Figure 10-11 and Figure 12A The angle between the second longitudinal axis 704 and the fourth longitudinal axis 712. In the example shown, the second camber angle 1200 is also the angle relative to the second longitudinal axis 704 and the fifth longitudinal axis 714. In the example shown, the first trailing edge flap 126 is relative to... Figure 10-11 and Figure 12A The horizontal axis 1002 extends away from the main portion of the first wing 104 at a second flap droop angle 1202. In the example shown, the amount of flap camber of the first trailing edge flap 126 is based on the second flap droop angle 1202. In the example shown, the second flap droop angle 1202 is based on a second camber angle 1200. Figure 12B In the example shown, the second curvature angle 120° is greater than Figure 7-9A , Figure 11 and Figure 12A The camber angle is 70°, which results in the second flap drooping angle being 120° greater than... Figure 11 and Figure 12A The first flap in the middle droops at an angle of 1100 degrees.

[0074] Figure 12C yes Figure 12A and Figure 12B The side view depicts the unfolded position based on the third camber angle of 1204. Figure 1-6 The first example is the trailing edge flap 126. In the example shown, the third camber angle 1204 is relative to... Figure 7-8 , Figure 10-11 and Figure 12A-12B The angle between the second longitudinal axis 704 and the fourth longitudinal axis 712. In the example shown, the third camber angle 1204 is also the angle relative to the second longitudinal axis 704 and the fifth longitudinal axis 714. In the example shown, the first trailing edge flap 126 is relative to... Figure 10-11 and Figure 12A The horizontal axis 1002 extends away from the main portion of the first wing 104 at a third flap droop angle 1206. In the example shown, the amount of flap camber of the first trailing edge flap 126 is based on the third flap droop angle 1206.

[0075] In the example shown, the third flap droop angle 1206 is based on the third camber angle 1204. Figure 12C In the example shown, the third curvature angle 1204 is greater than Figure 7-9A , Figure 11 and Figure 12A The camber angle is 70°, which results in the third flap drooping angle of 120° being greater than... Figure 11 and Figure 12A The first flap droop angle is 1100°. In addition, the third camber angle 1204 is greater than the second camber angle 1200°, which results in the third flap droop angle 1206 being greater than the second flap droop angle 1202.

[0076] exist Figure 13 The diagram shows the operation. Figure 1-6 A flowchart of an example method for the High Fowler flap actuation system 100. (See reference...) Figure 13 The flowchart shown illustrates this example method, but many other methods of operating the example Golfler flap actuation system 100 can be used instead. For example, the execution order of the blocks can be changed, and / or some of the blocks can be changed, removed, or combined.

[0077] Figure 13 This is a flowchart representing example method 1300, which can be executed to be based on... Figure 7-9A and Figure 11-12A The curvature angle is 700 degrees. Figure 1-8 and Figure 10-12C Example of a high-fowler flap actuation system 100 extension Figure 1 One or more of trailing edge flaps 126, 128, 130, and 132. Example method 1300 includes engaging one or more actuators coupled to one or more drive arms coupled to the trailing edge flaps (block 1302). For example, flap drive motor shaft 236 can be rotated to engage actuator 232 to operably engage to... Figure 1-6 The actuator shaft 234 of the first drive arm 160 rotates, and the first drive arm 160 is operatively coupled to the first trailing edge flap 126. For example, the first trailing edge flap 126 can be extended or retracted by a cross-shaped actuator such as the first drive arm 160. For example, the flap position of the first trailing edge flap 126 can be controlled by a movable member 230 of a third linear body 220 that moves relatively parallel to the rear spar 166 (e.g., along the second axis 402).

[0078] Example method 1300 also includes extending (one or more) drive arms from a first position to a second position (block 1304). For example, actuator shaft 234 may be rotated to extend first drive arm 160 from a retracted position to an extended position.

[0079] Example method 1300 also includes extending a trailing edge flap from a first position to a second position, the second position extending away from the main portion of the aircraft wing relative to the main portion of the wing at a first angle, the first angle being based on the second angle (box 1306). For example, the Golfler flap actuation system 100 can extend a first trailing edge flap 126 from a retracted position to an deployed position, the deployed position extending away from the main portion of the first wing 104 at a first angle (box 1306). Figure 12C The third flap droop angle 1206 extends away from the main portion of the first wing 104, wherein the third wing droop angle 1206 is based on the third camber angle 1204. In such an example, the extension of the first trailing edge flap 126 may occur during testing, such as during assembly, manufacturing, or flight operations of the Golfler flap actuation system 100. Example method 1300 then ends.

[0080] Although example method 1300 includes extending (one or more) drive arms and corresponding (one or more) trailing edge flaps, the method can be applied to retracting (one or more) drive arms and corresponding (one or more) trailing edge flaps.

[0081] As used herein, the terms “comprising” and “including” (and all their forms and tenses) are used as open-ended terms. Therefore, whenever a claim lists anything following any form of “comprising” or “including” (e.g., including (singular form), including (singular form), including, comprising, etc.), it should be understood that additional elements, terms, etc., may be present without exceeding the scope of the corresponding claim. As used herein, when the phrase “at least” is used as a transitional term in the preamble of a claim, it is as open-ended as the terms “comprising” and “including” are.

[0082] In summary, it should be recognized that exemplary devices and related methods have been disclosed that implement a high-fowler flap actuation system. The exemplary high-fowler flap actuation system can be actuated to move from a retracted position to an extended position via linear movement of one or more support members and one or more drive arms of the high-fowler flap actuation system. The exemplary high-fowler flap actuation system can use linear movement to retract or deploy flaps via scissor-driven linkages and corresponding support arms. By configuring the camber angle relative to the connection of the two support arm support members, the exemplary high-fowler flap actuation system can achieve high-fowler movement, desired flap camber, desired flap droop, etc. The exemplary high-fowler flap actuation system can reduce parasitic drag by reducing and / or eliminating external fairings from the aircraft wing.

[0083] Although certain example apparatuses, methods, and articles of manufacture have been disclosed herein, the scope of this patent is not limited thereto. Rather, this patent covers all apparatuses, methods, and articles of manufacture that fall fully within the scope of the claims of this patent.

Claims

1. An apparatus comprising: A control surface, operably coupled to the wing of the aircraft via a first support arm and a drive arm, the drive arm being linearly extendable from a retracted position to an extended position, the extended position including the control surface extending away from the wing at a first angle relative to the wing.

2. The device according to claim 1, wherein the control surface is a trailing edge flap.

3. The device according to claim 1 or claim 2, further comprising at least one second support arm.

4. The apparatus according to claim 1, claim 2 or claim 3, wherein the first support arm comprises a first body and a second body, the first body being pivotally coupled to the wing, and the second body extending pivotally from the first body.

5. The apparatus of claim 4, wherein the first support arm further comprises a third body and a fourth body, the third body extending pivotally from the second body, and the fourth body being pivotally connected to the third body and the operating surface.

6. The apparatus of claim 5, wherein the first angle is based on a second angle of the second body relative to the third body.

7. The apparatus according to claim 1, claim 2, claim 3, claim 4, claim 5 or claim 6, wherein the drive arm comprises a first linear body, a second linear body and a third linear body, the second linear body comprising a first end and a second end, the first end being pivotally coupled to the wing and the second end being pivotally coupled to the first linear body, the first linear body comprising a third end and a fourth end, the third end being pivotally coupled to the control surface and the fourth end being operably coupled to the wing via a pivotally movable bracket of the third linear body, the pivotally movable bracket being movable from the retracted position to the deployed position.

8. The apparatus of claim 7, wherein the first end, the second end and the third end are pivotally connected by a universal joint.

9. The apparatus of claim 7, wherein the second end is pivotally connected to the midpoint of the first linear body.

10. The apparatus of claim 9, wherein the first length of the second linear body is equal to the second length or the third length of the first linear body, the second length including a first distance between the midpoint and the third end, and the third length including a second distance between the midpoint and the fourth end.

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