A lift-enhancing device with guide vane double-slotted flaps

Abstract

A lift-enhancing device with a guide vane double-slotted flap, wherein the guide vane is connected to the main flap via a connecting arm, a cavity for accommodating the guide vane is provided in the trailing edge of the flap compartment, a primary slot is formed between the leading edge of the guide vane and the trailing edge of the flap compartment, and a secondary slot is formed between the trailing edge of the guide vane and the leading edge of the main flap; the flap actuator is mounted on the flap compartment, the flap arm is fixed below the flap compartment, the flap actuator is connected to the flap arm via a No. 1 connecting rod, and the flap arm is connected to the main flap via a No. 2 connecting rod and a No. 3 connecting rod so as to form a four-bar linkage in a motion plane with a combination of the No. 1 connecting rod, the flap arm, the No. 3 connecting rod, the main flap and the flap compartment. Compared with a trailing edge flap in the form of a pulley and slide rail, the four-bar linkage is more direct and fast, has a higher precision in controlling the position of the rear flap, has high reliability, and can achieve the same service life as the aircraft body.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft structures, in particular to a lift-enhancing device with a guide vane type double-slotted flap. Background Art

[0002] For aircraft that require high lift, in order to meet the performance requirements of take-off and landing, lift-enhancing devices such as single-slotted flaps are generally arranged on the trailing edge of the wing to increase lift; single-slotted flaps have a simple structure and motion mechanism, but the usable deflection angle is limited and cannot provide sufficient lift increments; double-slotted and multi-slotted flaps have two or more airflow slots, and can use a larger deflection angle, which can provide sufficient lift increments, but the structure and motion mechanism are complex, which is not conducive to aircraft that also pursue high-speed characteristics.

[0003] Patent CN102642616B discloses an aircraft lift-enhancing device with fixed double-slotted flaps. The patent adopts an aircraft lift-enhancing device with fixed main / rear double-slotted flaps with fixed-axis rotating trailing edges, including main flaps, rear flaps, Y-shaped brackets, main wing rear beam fixing rods, actuators, first linkage rods, second linkage rods, third linkage rods, spoilers, lower baffles, and sealing rubbers. Compared with the slide rail motion mechanism, the fixed-axis motion mechanism is lighter, more reliable, and has faster control response; the disadvantage is that the height of the support arm connecting the hinge is relatively large, which has a greater impact on the flow field of the lower wing surface, and is not suitable for large maneuverable aircraft and light / small aircraft;

[0004] Patent CN113104196A discloses a lift-enhancing device and lift-enhancing method for an aircraft, wherein the lift-enhancing device for an aircraft comprises: a connecting bracket, wherein the connecting bracket is used to connect the lift-enhancing device to the wing of the aircraft; a front wing section and a rear wing section fixed to the connecting bracket, wherein a slot is formed between the front wing section and the rear wing section, wherein the front wing section has a first surface facing the slot and the rear wing section has a second surface facing the slot; a first cover plate located on the rear wing section; and an actuator, wherein the actuator can control the first cover plate to extend into the slot between the front wing section and the rear wing section; the lift-enhancing device has an actively controllable internal slot, and when the aircraft takes off and lands, the lift-enhancing device can be actively controlled to form a slot between the front wing section and the rear wing section, so as to effectively introduce momentum into the boundary layer, and the actuator is used to drive the mechanism, and the mechanism adopts the form of a connecting bracket;

[0005] Patent CN203528807U discloses a lift-enhancing device for a single-slotted flap of an aircraft, comprising a flap compartment consistent with a conventional single-slotted flap and a movable deflector flap, on which a deflector vane is added, the upper surface of the deflector vane is a wing shape, and the lower surface connected to the flap compartment is a spline. When the movable deflector flap is in zero position, it is determined by the wing shape and the structural space of the movable deflector flap, and the sealing performance of the deflector vane and the movable deflector flap is ensured when both are in zero position;

[0006] Patent CN205059998U discloses a lift-enhancing device for an aircraft, the lift-enhancing device comprising a double-peak flap and ailerons located at the trailing edge of the aircraft wing, the double-slotted flaps being arranged on the side of the fuselage adjacent to the aircraft, and the combination of the trailing edge flaps and ailerons arranged at the trailing edge of the aircraft wing can solve the contradiction between high lift and roll control, and meet the characteristic requirements of aircraft take-off and landing, and the lift-enhancing effect of the two-stage slotted flaps can reach an angle of attack of 10°, and the lift system increases by 0.3; and the layout of the double-slotted flaps and ailerons can provide a certain lateral control capability, and can also cooperate with the differential horizontal tail to ensure the lateral control capability of the aircraft;

[0007] The lift-enhancing device disclosed in the above patent cannot simultaneously take into account the requirements of high lift for flap slots and the requirements of high-speed characteristics for simple structure and motion mechanism. Summary of the invention

[0008] The technical problem solved by the present invention is to provide a lift-enhancing device with a guide vane-type double-slotted flap to solve the problems in the above-mentioned background technology.

[0009] The technical problem solved by the present invention is achieved by adopting the following technical solutions:

[0010] A lift-enhancing device with a guide vane type double-slotted flap, comprising a flap compartment, a guide vane, a connecting arm, a main flap, a flap actuator, a No. 1 connecting rod, a flap arm, a No. 2 connecting rod and a No. 3 connecting rod, wherein the guide vane is connected to the main flap via the connecting arm, a cavity for accommodating the guide vane when the lift-enhancing device is in a retracted state is arranged in the rear edge of the flap compartment, and a primary slot is formed between the leading edge of the guide vane and the trailing edge of the flap compartment, and a secondary slot is formed between the trailing edge of the guide vane and the leading edge of the main flap, and when the lift-enhancing device is in a lowered state, the air flow on the lower surface of the wing is reduced. After the flow is accelerated and changes its flow direction through the two-stage slots, it flows backward along the guide vane and the upper surface of the main flap to suppress the airflow separation that occurs when the main flap has a large deflection, and the lift-increasing effect is obvious; the flap actuator is installed on the flap compartment, and the flap support arm is arranged below the flap compartment. The flap actuator is connected to the flap support arm through a No. 1 connecting rod, and the flap support arm is connected to the main flap through a No. 2 connecting rod and a No. 3 connecting rod, so as to cause the combination of the No. 1 connecting rod, the flap support arm, the No. 3 connecting rod, the main flap and the flap compartment to form a four-bar mechanism in the motion plane.

[0011] In the present invention, a connecting hinge is provided on the flap support arm, one end of the No. 1 connecting rod is connected to the flap actuator, the other end of the No. 2 connecting rod is fixedly connected to the main flap, and the other end of the No. 1 connecting rod is hingedly connected to the other end of the No. 2 connecting rod in space through a rotating hinge; one end of the No. 3 connecting rod is connected to the connecting hinge, and the other end of the No. 3 connecting rod is connected to the flap hinge provided on the main flap.

[0012] In the present invention, the angles between the No. 1 connecting rod, the No. 2 connecting rod and the rotating hinge are 15-45°. When the aircraft takes off, the angle is 15-25°; when the aircraft lands, the angle is 30-45°.

[0013] In the present invention, the guide plate is a streamlined structure with a large curvature and a negative installation angle, and the relative thickness of the guide plate is 16% to 23%.

[0014] In the present invention, the cavity matches the shape of the guide vane. When the main flap is in the retracted state, a small gap is retained between the main flap and the flap compartment to ensure the aircraft's cruising performance. During the rotation and rearward movement of the guide vane, a safe gap is maintained with the cavity of the flap compartment to achieve safety and reliability of the structure and mechanism.

[0015] In the present invention, when the aircraft is in a lowered state for takeoff or landing, the gap value between the guide vane and the primary slot of the flap compartment accounts for 0.7% to 1.5% of the chord length at different spanwise positions.

[0016] In the present invention, a plurality of connecting arms are arranged along the span direction, unfolding one by one from the root to the tip, and the connecting arms are thin-walled or streamlined structures to take into account both support stiffness and drag reduction requirements.

[0017] In the present invention, an angular displacement sensor is provided in the flap actuator.

[0018] In the present invention, a mechanical zero position and a structure for controlling the limit position are provided in the rotary actuator to limit the movement of the flap actuator.

[0019] In the present invention, a fairing is arranged below the flap support arm, and the fairing consists of a front fairing cover and a rear fairing cover, the front fairing cover is fixedly connected to the wing box, and the rear fairing cover is fixedly connected to the main flap. The fairing adopts a streamlined structure, and when the double-slotted flap is folded up, a movement gap is arranged between the front fairing cover and the rear fairing cover, and the movement gap is 1 to 2 mm.

[0020] In the present invention, the operation mode of the high-lift device is as follows:

[0021] When the aircraft takes off or lands, the double-slotted flap with guide vane is lowered, and after the flap actuator rotates, it drives the No. 1 connecting rod and the No. 2 connecting rod to move backward, and the No. 3 connecting rod rotates backward adaptively to drive the main flap, the connecting arm, and the guide vane to rotate and move backward, so that the primary slot between the leading edge of the guide vane and the trailing edge of the flap compartment reaches 0.7% to 1.5% of the chord length at different spanwise positions; in the aircraft take-off state, the flap actuator is driven to rotate so that the angle between the No. 1 connecting rod and the No. 2 connecting rod is between 15 and 25 degrees, and in the aircraft landing state, the flap actuator is driven to rotate so that the angle between the No. 1 connecting rod and the No. 2 connecting rod is between 30 and 45 degrees.

[0022] Beneficial effect: The structural weight of the lift-enhancing device prepared by the present invention is 60% to 70% of the weight of the non-fixed double-slotted flap. Compared with the trailing edge flap in the form of a pulley and slide rail, the four-bar linkage is more direct and fast, and the position of the rear flap is more accurately controlled, the reliability is high, and the service life can be the same as that of the aircraft body. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the double-slotted flap in the retracted state in the preferred embodiment of the present invention.

[0024] Figure 2 It is a schematic diagram of the double-slotted flap in the lowered state in the preferred embodiment of the present invention.

[0025] Figure 3 It is a schematic diagram of the state of the double-slotted flap during the movement process in the preferred embodiment of the present invention.

[0026] Figure 4 It is a schematic diagram of the fairing when the double-slotted flaps in the preferred embodiment of the present invention are in the retracted state.

[0027] Figure 5 It is a schematic diagram of the fairing when the double-slotted flaps in the preferred embodiment of the present invention are in the lowered state.

[0028] Figure 6 It is a schematic diagram of the structure of the flap actuator in a preferred embodiment of the present invention. DETAILED DESCRIPTION

[0029] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below with reference to specific diagrams.

[0030] See also Figures 1 to 6 A lift-enhancing device with a guide vane double-slotted flap comprises a flap compartment 1, a guide vane 2, a connecting arm 3, a main flap 4, a flap actuator 5, a No. 1 connecting rod 6, a flap arm 7, a rotating hinge 8, a No. 2 connecting rod 9, a connecting hinge 10, a No. 3 connecting rod 11, a flap hinge 12, a primary slot 13, a secondary slot 14, a front fairing cover 15 and a rear fairing cover 16, wherein the guide vane 2 is connected to the main flap 4 through the connecting arm 3; a cavity for accommodating the guide vane 2 when the lift-enhancing device is in a retracted state is provided in the trailing edge of the flap compartment 1, the guide vane 2 enters the cavity, and the flap compartment 1 is combined with the main flap 4 to ensure the smoothness of the upper and lower surfaces of the wing.

[0031] The first-level slot 13 is formed between the leading edge of the guide vane 2 and the trailing edge of the flap compartment 1 of the present invention, and the second-level slot 14 is formed between the trailing edge of the guide vane 2 and the leading edge of the main flap 4. Figure 1 and Figure 2, the guide vane 2 and the main flap 4 are connected by a connecting arm 3, but it can be understood by those skilled in the art that the connecting arm 3 only occupies a part of the area between the guide vane 2 and the main flap 4, and along the span direction of the wing, the other area between the guide vane 2 and the main flap 4, which occupies most of the other area, is a non-structural cavity, thereby forming a secondary slot 14. When the lift-enhancing device is in the lowered state, the airflow on the lower surface of the wing is accelerated and the flow direction is changed through the two-stage slot, and then flows upward along the primary slot 13 and the secondary slot 14, and then flows backward along the guide vane 2 and the upper surface of the main flap 4, thereby suppressing the airflow separation that occurs when the main flap 4 has a large deflection, and the lift-enhancing effect is improved by 20% to 30% relative to the single-slot flap; the flap actuator 5 is installed on the flap compartment 1, the flap support arm 7 is arranged below the flap compartment 1, and a A connecting hinge 10, one end of the No. 1 connecting rod 6 is connected to the flap actuator 5, the other end of the No. 1 connecting rod 6 is connected to a rotating hinge 8 without a fixed position, one end of the No. 2 connecting rod 9 is connected to the rotating hinge 8, the other end of the No. 2 connecting rod 9 is fixedly connected to the main flap 4, one end of the No. 3 connecting rod 11 is connected to the connecting hinge 10, and the other end of the No. 3 connecting rod 11 is connected to a flap hinge 12 arranged on the main flap 4, so as to promote the combination of the No. 1 connecting rod 6, the flap support arm 7, the No. 3 connecting rod 11 and the main flap 4 and the flap compartment 1 to form a four-bar linkage in the motion plane. The connecting rod structure is relative to the slide rail mechanism. While ensuring the same amount of retreat of the trailing edge flap, the length, width and height of the flap support arm 7 will be reduced. The connecting arm 3 as a fixed component is smaller in size than the moving component of the slide rail structure, thereby reducing the weight of the entire trailing edge flap by 30% to 40%.

[0032] In this embodiment, the guide plate 2 is a streamlined structure with a large curvature and a negative installation angle, and the relative thickness of the guide plate 2 is 16% to 23%.

[0033] It should be noted that the reference Figure 1 The guide plate 2 extends from the left end to the right end. The extension direction defines the length of the guide plate. The direction perpendicular to the length of the guide plate is the thickness of the guide plate. Figure 1 It can be seen that the thickness of the guide vane is constantly changing to form a predetermined distance with the inner surface of the cavity of the flap compartment 1. The relative thickness of the guide vane 2 here refers to the ratio of the thickness of the guide vane at each location to the length of the guide vane in the extension direction. The ratio at any location is selected within the range of 16% to 23%.

[0034] In this embodiment, the cavity matches the shape of the guide vane 2. When the main flap 4 is in the retracted state, a small gap is retained between the main flap 4 and the flap compartment 1 to ensure the aircraft's cruising performance. During the rotation and rearward movement of the guide vane 2, a safe gap is maintained with the cavity of the flap compartment 1 to achieve safety and reliability of the structure and mechanism.

[0035] In this embodiment, when the high-lift device is in the lowered state during takeoff or landing, the gap value between the guide vane 2 and the primary slot 13 of the flap compartment 1 accounts for 0.7% to 1.5% of the chord length at different spanwise positions.

[0036] In this embodiment, the angles between the No. 1 connecting rod 6, the No. 2 connecting rod 9 and the rotation hinge 8 are 15-45°. When the aircraft takes off, the angle is 15-25°; when the aircraft lands, the angle is 30°-45°.

[0037] In this embodiment, five connecting arms 3 are arranged in the span direction, namely arms No. 1 to No. 5 from the root to the tip, and the connecting arms 3 are thin-walled or streamlined structures to take into account both support stiffness and drag reduction requirements.

[0038] In this embodiment, the flap actuator 5 is the driving source of the lift-enhancing device, which drives the movement of each connecting rod mechanism, thereby driving the guide vane 2 and the main flap 4 to deflect and retreat at the same time, so as to form a two-level gap between the flap compartment 1, the guide vane 2, and the main flap 4.

[0039] In this embodiment, the operation mode of the high-lift device is as follows:

[0040] Example 1

[0041] When the aircraft takes off or lands, the double-slotted flap with guide vane is lowered, and the flap actuator 5 rotates to drive the No. 1 connecting rod 6 and the No. 2 connecting rod 9 to move backward, and the No. 3 connecting rod 11 rotates backward adaptively to drive the main flap 4, the connecting arm 3, and the guide vane 2 to rotate and move backward, so that the primary slot 13 between the leading edge of the guide vane 2 and the trailing edge of the flap compartment 1 reaches 0.7% to 1.5% of the chord length at different spanwise positions, such as Figure 2 As shown;

[0042] Example 2

[0043] The flap actuator 5 is driven by the actuator cylinder, which drives the No. 1 connecting rod 6 and the No. 2 connecting rod 9 to move backward, and the No. 3 connecting rod 11 rotates backward adaptively to drive the main flap 4, the connecting arm 3, and the guide vane 2 to rotate and move backward, so that the primary slot 13 between the leading edge of the guide vane 2 and the trailing edge of the flap compartment 1 reaches 0.7% to 1.5% of the chord length at different spanwise positions;

[0044] Example 3

[0045] When the aircraft takes off or lands, the double-slotted flap with guide vane is lowered. After the flap actuator 5 rotates, it drives the No. 1 connecting rod 6 and the No. 2 connecting rod 9 to move backward, and the No. 3 connecting rod 11 rotates backward adaptively to drive the main flap 4, the connecting arm 3, and the guide vane 2 to rotate and move backward. The rotation and backward movement of the guide vane 2 and the main flap 4 can be accurately controlled and can be stopped at two rear flap angles. The rear flap angle here is the angle change of the main flap 4 relative to the flap compartment 1, which is controlled by the angle between the No. 1 connecting rod 6 and the No. 2 connecting rod 9 at the rotation hinge 8. The angle changes between a small angle and a large angle. When the aircraft takes off, the angle is controlled to be in a small angle state, and the small angle takes any value between 15 and 25 degrees; when the aircraft lands, the angle is controlled to be in a large angle state, and the large angle takes any value between 30 degrees and 45 degrees.

[0046] Example 4

[0047] An angular displacement sensor is provided in the flap actuator 5, and a rotation angle signal of the flap actuator 5 is outputted through the angular displacement sensor, and closed-loop control of the flap is realized through the aircraft electromechanical control system; the electrical zero position and electrical limit position of the flap actuator 5 are provided in the electromechanical control system, and a mechanical zero position and a structure for controlling the limit position are provided in the rotary actuator 5 to limit the movement of the flap actuator 5. When the guide vane 2 is retracted with the main flap 4, it can only reach the set zero position and cannot move in the reverse direction; when the guide vane 2 is lowered with the main flap 4, it can only reach the set maximum limit and cannot move beyond the stroke;

[0048] Example 5

[0049] When the guide vane 2 and the main flap 4 are in the retracted state, a small gap is reserved between the guide vane 2 and the main flap 4 and the flap compartment 1 on their upper and lower surfaces, so as to ensure that when the guide vane 2 and the main flap 4 are retracted and extended during the take-off and landing phase of the aircraft and when they are retracted in place during cruising flight in the air, the guide vane 2 and the main flap 4 do not interfere with the flap compartment 1 when they are elastically deformed by aerodynamic loads, and there is sufficient gap;

[0050] Example 6

[0051] A fairing is provided below the flap support arm 7, and the fairing is composed of a front fairing cover 15 and a rear fairing cover 16. The front fairing cover 15 is fixedly connected to the wing box, and the rear fairing cover 16 is fixedly connected to the main flap 4. The fairing adopts a streamlined structure. When the double-slotted flap is in the folded state, a movement gap of 1 to 2 mm is provided between the front fairing cover 15 and the rear fairing cover 16 to meet the dual requirements of reducing aerodynamic resistance and manufacturing and assembly processability, and has the function of preventing foreign objects and rainwater; when the double-slotted flap is in the lowered state, the front fairing cover 15 is separated from the rear fairing cover 16, which does not affect the normal movement of the guide vane 2 and the main flap 4;

[0052] In the above embodiment, the flap actuator 5, the No. 1 connecting rod 6, the No. 2 connecting rod 9, and the No. 3 connecting rod 11 can be adjusted in length and angle within a small range. The length adjustment of the No. 1 connecting rod 6, the No. 2 connecting rod 9, and the No. 3 connecting rod 11 is achieved through the segmented threaded structure of the connecting rod, and the angle is adjusted through the length relationship of different connecting rods; the flap actuator 5 achieves length adjustment by adjusting the positioning position of its own mounting structure, and achieves angle adjustment by adjusting the internal mechanical zero position and the electrical zero position adjustment in the electromechanical control system. The length and angle of the flap actuator 5, the No. 1 connecting rod 6, the No. 2 connecting rod 9, and the No. 3 connecting rod 11 are adjusted to eliminate the motion gap, ensure the accuracy of the position of the guide vane 2 with the main flap 4 in the retracted state and the lowered state, and make the rear flap stable, reliable, and shake-free in all states.

[0053] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A lift-enhancing device with a guide vane double-slotted flap, comprising a flap compartment, a guide vane, a connecting arm, a main flap, a flap actuator, a No. 1 connecting rod, a flap arm, a No. 2 connecting rod, a No. 3 connecting rod, a rotating hinge, a connecting hinge and a flap hinge, characterized in that: The guide vane is connected to the main flap through a connecting arm, a cavity for accommodating the guide vane is provided in the trailing edge of the flap compartment, and a primary slot is formed between the leading edge of the guide vane and the trailing edge of the flap compartment, and a secondary slot is formed between the trailing edge of the guide vane and the leading edge of the main flap; the flap actuator is installed on the flap compartment, the flap support arm is arranged below the flap compartment, a connecting hinge is arranged on the flap support arm, one end of the No. 1 connecting rod is connected to the flap actuator, the other end of the No. 2 connecting rod is fixedly connected to the main flap, and the other end of the No. 1 connecting rod is hingedly connected to the other end of the No. 2 connecting rod in space through a rotating hinge; one end of the No. 3 connecting rod is connected to the connecting hinge, and the other end of the No. 3 connecting rod is connected to the flap hinge arranged on the main flap, so as to cause the combination of the No. 1 connecting rod, the flap support arm, the No. 3 connecting rod, the main flap and the flap compartment to form a four-bar linkage in the motion plane; The operation mode of the lift-enhancing device is as follows: When the aircraft takes off or lands, the double-slotted flap with guide vane is lowered, and after the flap actuator rotates, it drives the No. 1 connecting rod and the No. 2 connecting rod to move backward, and the No. 3 connecting rod rotates backward adaptively to drive the main flap, the connecting arm, and the guide vane to rotate and move backward, so that the primary slot between the leading edge of the guide vane and the trailing edge of the flap compartment reaches 0.7% to 1.5% of the chord length at different spanwise positions; when the aircraft is in the take-off state, the flap actuator is driven to rotate so that the angle between the No. 1 connecting rod and the No. 2 connecting rod is between 15 and 25 degrees, and when the aircraft is in the landing state, the flap actuator is driven to rotate so that the angle between the No. 1 connecting rod and the No. 2 connecting rod is between 30 and 45 degrees.

2. The lift-enhancing device with guide vane double-slotted flaps according to claim 1, characterized in that: The guide plate is a streamlined structure with a large curvature and a negative installation angle, and the relative thickness of the guide plate is 16% to 23%.

3. The lift-enhancing device with guide vane double-slotted flaps according to claim 1, characterized in that: The cavity matches the shape of the guide plate.

4. The lift-enhancing device with guide vane double-slotted flaps according to claim 1, characterized in that: A plurality of connecting arms are arranged along the span direction, and the connecting arms are thin-walled or streamlined structures.

5. The lift-enhancing device with guide vane double-slotted flaps according to claim 1, characterized in that: An angular displacement sensor is arranged in the flap actuator.

6. The lift-enhancing device with guide vane double-slotted flaps according to claim 1, characterized in that: The flap actuator is provided with a mechanical zero position and a structure for controlling the extreme position.

7. The lift-enhancing device with guide vane double-slotted flaps according to claim 1, characterized in that: A fairing is arranged below the flap support arm, and the fairing consists of a front fairing cover and a rear fairing cover. The front fairing cover is fixedly connected to the wing box, and the rear fairing cover is fixedly connected to the main flap.

8. The lift-enhancing device with guide vane double-slotted flaps according to claim 7, characterized in that: The fairing is a streamlined structure.

9. The lift-enhancing device with guide vane double-slotted flaps according to claim 7, characterized in that: When the double-slotted flaps are retracted, a movement gap is provided between the front fairing cover and the rear fairing cover, and the movement gap is 1 to 2 mm.

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