CN115783242A - A high-lift device with deflector type double-slotted flaps - Google Patents

Abstract

A high lift device with a guide vane type double-slit flap comprises a guide vane and a main flap, wherein the guide vane is connected with the main flap through a connecting support arm, a containing cavity for containing the guide vane is arranged in the rear edge of a flap cabin, a primary slit channel is formed between the front edge of the guide vane and the rear edge of the flap cabin, and a secondary slit channel is formed between the rear edge of the guide vane and the front edge of the main flap; the flap actuator is installed on the wing flap cabin, the flap support arm is fixed in wing flap cabin below, the flap actuator is connected with the flap support arm through a connecting rod, the flap support arm is connected with main flap through No. two connecting rods, no. three connecting rods and is connected in order to make the combination of a connecting rod, flap support arm, no. three connecting rods and main flap and wing flap cabin form four-bar linkage in the motion plane, and relative pulley slide rail form's trailing edge flap, four-bar linkage realize more directly quick, and control back front of a garment position precision higher, and the reliability is high, can realize with aircraft body longevity.

Description

A high-lift device with deflector type double-slotted flap

technical field

The invention relates to the technical field of aircraft structures, in particular to a lift-increasing device with deflector-type double-slotted flaps.

Background technique

For aircraft that require high lift, in order to meet the performance requirements for take-off and landing, generally a single-slot flap and other lift-increasing devices are arranged on the trailing edge of the wing to increase lift; the single-slot flap structure and motion mechanism are simple, but the deflection angle can be used Limited, unable to provide sufficient lift increase; double-slot and multi-slot flaps have two or more airflow slots, which can use a large deflection angle and can provide sufficient lift increase, but the structure and kinematic mechanism are complicated, and the Aircraft that pursue high-speed characteristics at the same time are disadvantageous.

Patent CN102642616B discloses a kind of aircraft lift-increasing device with fixed double-slotted flaps, which adopts an aircraft-increased-lift device with fixed-axis rotating trailing edge fixed main/rear double-slotted flaps, including main flaps, rear flaps, Y-shaped bracket, main wing rear beam fixing rod, actuator, first linkage rod, second linkage rod, third linkage rod, spoiler, lower baffle, sealing rubber, relative to the sliding rail movement mechanism, the fixed axis movement mechanism is more Lightweight, higher reliability, and faster control response; the disadvantage is that the height of the arm connecting the hinge is too high, which has a greater impact on the flow field of the wing under the wing, and is not suitable for large maneuvering aircraft and light/small aircraft;

Patent CN113104196A discloses a lift-increasing device and a lift-increasing method for an aircraft. The lift-increasing device for an aircraft includes: a connecting bracket for connecting the lift-increasing device to the wing of the aircraft a front wing section and a rear wing section fixed on the connecting bracket, a slot is formed between the front wing section and the rear wing section, the front wing section has a first surface facing the slot and the the rear wing section has a second surface facing the slot; a first cover on the rear wing section; and an actuator capable of controlling the extension of the first cover to the front In the seam between the wing section and the rear wing section; the lift-increasing device has an internal seam that can be actively controlled. When the aircraft takes off and lands, the front wing section and the rear wing section can be formed by actively controlling the lift-increasing device. The seam between them can effectively guide the momentum into the boundary layer, and it is driven by an actuator, and the mechanism adopts the form of a connecting bracket;

Patent CN203528807U discloses a lift-increasing device for an aircraft single-slot flap, including a flap compartment consistent with a conventional single-slot flap, and a movable deflectable flap. On this basis, a deflectable deflector is added. The surface is the shape of the wing, and the lower surface connected to the flap compartment is a spline. The movable deflectable flap is determined by the wing shape and the structural space of the movable deflectable flap at zero position, and the deflectable flow guide is guaranteed The airtightness of flaps and movable deflectable flaps are at zero position;

Patent CN205059998U discloses a lift-increasing device for aircraft. The lift-increasing device in the patent includes a double-peak flap and an aileron positioned at the trailing edge of the wing of the aircraft, and the double-slit flap is arranged near the On the fuselage side of the aircraft, through the combination of trailing edge flaps and ailerons set on the trailing edge of the aircraft wings, the contradiction between high lift and roll control can be resolved, and the characteristics of aircraft takeoff and landing can be met. The lift-increasing effect of the first-stage slotted flaps can reach an angle of attack of 10° and the lift system can be increased by 0.3; and the layout of the double-slotted flaps and ailerons can provide a certain degree of lateral control capability, and can also cooperate with the differential stabilizer to ensure the lateral control of the aircraft control ability;

The high-lift device in the above-mentioned disclosed patent cannot simultaneously take into account the high-lift requirement for the flap slot and the high-speed requirement for a simple structure and kinematic mechanism.

Contents of the invention

The technical problem to be solved by the present invention is to provide a high-lift device with a deflector type double-slotted flap to solve the above-mentioned problems in the background technology.

The technical problem solved by the present invention adopts following technical scheme to realize:

A high-lift device with a deflector type double-slotted flap, including a flap cabin, a deflector, a connecting support arm, a main flap, a flap actuator, a connecting rod No. 1, a flap support arm, a second No. 1 connecting rod and No. 3 connecting rod, wherein, the deflector is connected to the main flap through the connecting arm, and the rear edge of the flap cabin is provided with a device for containing and guiding when the high-lift device is in the retracted state. The cavity of the deflector, and a primary slot is formed between the leading edge of the deflector and the rear edge of the flap compartment, and a secondary gap is formed between the trailing edge of the deflector and the leading edge of the main flap. When the high-lift device is in When the airfoil is lowered, the airflow on the lower surface of the wing passes through the two-stage slots to increase speed and change the flow direction, and then flows backward along the upper surface of the deflector and the main flap, so as to suppress the separation of the airflow that occurs when the main flap is highly deflected. The effect of increasing the lift is obvious; the flap actuator is installed on the flap cabin, the flap support arm is arranged under the flap compartment, and the flap actuator is connected to the flap support arm through the No. 1 connecting rod , the flap support arm is connected with the main flap through the No. 2 connecting rod and the No. 3 connecting rod, so as to promote the combination of the No. A four-bar linkage is formed in the motion plane.

In the present invention, the flap arm is provided with a connecting hinge point, one end of the No. 1 connecting rod is connected to the flap actuator, and the other end of the No. 2 connecting rod is fixedly connected to the main flap. 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 point; one end of the No. 3 connecting rod is connected to the connecting hinge point, and the other end of the No. 3 connecting rod is connected to the Flap hinge connection on the main flap.

In the present invention, the included angle between the No. 1 connecting rod, the No. 2 connecting rod and the pivot point is 15-45°. When the aircraft takes off, the included angle is 15-25°; when the aircraft lands, the included angle is 30°～45°.

In the present invention, the deflector is a streamlined structure with a large curvature and a negative installation angle, and the relative thickness of the deflector is 16%-23%.

In the present invention, the cavity is matched with the shape of the deflector, and when the main flap is in the retracted state, a small gap is reserved between the main flap and the flap compartment to ensure the cruising performance of the aircraft; the rotation of the deflector and During the backward movement, a safe gap is maintained with the cavity of the flap cabin, so as to realize the safety and reliability of the structure and mechanism.

In the present invention, when the aircraft is in the lowered state for take-off or landing, the gap between the deflector and the primary slot of the flap compartment accounts for 0.7% to 1.5% of the chord length at different spanwise positions.

In the present invention, a plurality of connecting arms are arranged along the span direction, and are deployed one by one from the root to the tip, and the connecting arms are thin-walled or streamlined to meet the requirements of support stiffness and drag reduction.

In the present invention, the flap actuator is provided with an angular displacement sensor.

In the present invention, the rotary actuator is provided with a mechanical zero position and a structure for controlling the limit position, so as to limit the movement of the flap actuator.

In the present invention, a fairing is arranged below the flap arm, and the fairing is composed of a fairing and a fairing, the fairing is fixedly connected with the wing box, and the fairing is fixedly connected with the main flap. The fairing adopts a streamlined structure. When the double-slot flaps are retracted, there is a movement gap between the front fairing and the rear fairing, and the movement gap is 1-2mm.

In the present invention, the operating mode of the lifting device is as follows:

When the aircraft takes off or lands, put down the double-slotted flap with deflector, after the flap actuator rotates, it will drive the No. 1 and No. 2 links to move backward, and the No. Drive the main flap, the connecting arm, and the deflector to rotate and move backward, so that the primary seam between the leading edge of the deflector and the rear edge of the flap cabin reaches 0.7% to 1.5% of the chord length at different spanwise positions ; In the take-off state of the aircraft, by driving the flap actuator to rotate, so that the angle between the No. 1 connecting rod and the No. 2 connecting rod is between 15° and 25°; The flap actuator is driven to rotate so that the included angle between the No. 1 connecting rod and the No. 2 connecting rod is between 30° and 45°.

Beneficial effects: the structural weight of the high-lift 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 pulley slide rails, the four-bar linkage mechanism is more direct and fast, and after control The position accuracy of the flap is higher, the reliability is high, and it can achieve the same life as the aircraft body.

Description of drawings

Fig. 1 is a schematic diagram of the retracted state of the double-slit flap in a preferred embodiment of the present invention.

Fig. 2 is a schematic diagram of the lowered state of the double-slit flap in a preferred embodiment of the present invention.

Fig. 3 is a schematic diagram of the state during the movement of the double-slit flap in a preferred embodiment of the present invention.

Fig. 4 is a schematic view of the fairing when the double-slotted flaps are retracted in a preferred embodiment of the present invention.

Fig. 5 is a schematic view of the fairing when the double-slotted flaps are lowered in a preferred embodiment of the present invention.

Fig. 6 is a structural schematic diagram of the flap actuator in a preferred embodiment of the present invention.

Detailed ways

In order to make the technical means, creative features, goals and effects achieved by the present invention easy to understand, the present invention will be further described below in conjunction with specific illustrations.

Referring to Figures 1 to 6, a high-lift device with a deflector type double-slotted flap includes a flap cabin 1, a deflector 2, a connecting arm 3, a main flap 4, a flap actuator 5, No. 1 connecting rod 6, flap support arm 7, rotating hinge point 8, No. 2 connecting rod 9, connecting hinge point 10, No. 3 connecting rod 11, flap hinge point 12, primary seam 13, secondary seam 14. Front fairing 15 and rear fairing 16, wherein, the deflector 2 is connected to the main flap 4 through the connecting arm 3; When in the upper state, it is used to accommodate the cavity of the deflector 2, the deflector 2 enters the cavity, and the flap compartment 1 is combined with the main flap 4 to ensure that the upper and lower surfaces of the wing are smooth.

In the present application, a primary slot 13 is formed between the leading edge of the deflector 2 and the rear edge of the flap compartment 1, and a secondary slot 14 is formed between the rear edge of the deflector 2 and the leading edge of the main flap 4, as shown in FIG. 1 As shown in Fig. 2, the guide vane 2 and the main flap 4 are connected through the connecting arm 3, but those skilled in the art can understand that the connecting arm 3 only occupies the space between the guide vane 2 and the main flap 4 In some areas, along the spanwise direction of the wing, other areas occupying most of the area between the deflector 2 and the main flap 4 are unstructured cavities, thereby forming a secondary slot 14. When the high-lift device is put down state, the airflow on the lower surface of the wing speeds up through the two-stage slots and changes the flow direction, then flows upward along the primary slot 13 and the secondary slot 14, and then along the upper surface of the deflector 2 and the main flap 4 Flow backwards, so that the airflow separation that occurs under the large deflection of the main flap 4 can be suppressed, and the lift effect is improved by 20% to 30% compared with the single-slot flap; the flap actuator 5 is installed in the flap compartment 1 Above, the flap support arm 7 is arranged below the flap compartment 1, and a connection hinge point 10 is arranged on the flap support arm 7, and one end of the No. 1 connecting rod 6 is connected with the flap actuator 5, so that The other end of the No. 1 connecting rod 6 is connected to the rotating hinge point 8 without a fixed position, one end of the No. 2 connecting rod 9 is connected to the rotating hinge point 8, and 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 point 10, and the other end of the No. 3 connecting rod 11 is connected to the flap hinge point 12 arranged on the main flap 4, so that the No. 1 connecting rod 6, the flap The combination of wing support arm 7, No. 3 connecting rod 11, main flap 4 and flap cabin 1 forms a four-bar linkage mechanism in the motion plane, and the linkage structure is relative to the slide rail mechanism. Next, the length, width and height of the flap arm 7 will be reduced, and the size of the connecting arm 3 as a fixed part relative to the moving part of the slide rail structure will be smaller, thereby reducing the weight of the entire trailing edge flap by 30% to 40%. %.

In this embodiment, the guide vane 2 is a streamlined structure with a large curvature and a negative installation angle, and the relative thickness of the guide vane 2 is 16%-23%.

It should be noted that, referring to Figure 1, the guide vane 2 extends from the left end to the right end, the extension direction defines the length of the guide vane, and the direction perpendicular to the length of the guide vane is the thickness of the guide vane, as can be seen from Figure 1 on the right , the thickness of the guide vane is constantly changing to form a predetermined distance with the inner surface of the cavity of the flap cabin 1, and the relative thickness of the guide vane 2 here refers to the thickness of the guide vane at each place and the guide vane in the direction of extension. The ratio of the length of the tape-out, the ratio of any position is selected within the range of 16% to 23%.

In this embodiment, the shape of the cavity matches the deflector 2, and when the main flap 4 is retracted, a small gap is reserved between the main flap 4 and the flap compartment 1 to ensure the cruising performance of the aircraft; During the rotation and backward movement of the deflector 2, a safety gap is maintained with the cavity of the flap compartment 1, so as to realize the safety and reliability of the structure and mechanism.

In this embodiment, when the high-lift device is put down during take-off or landing, the gap between the deflector 2 and the primary slot 13 of the flap compartment 1 accounts for 0.7%-1.5% of the chord length at different spanwise positions.

In this embodiment, the included angle between the No. 1 connecting rod 6, No. 2 connecting rod 9 and the pivot point 8 is 15-45°. When the aircraft takes off, the included angle is 15-25°; , the included angle is 30°～45°.

In this embodiment, five connecting arms 3 are arranged along the span direction, and they are No. 1 to No. 5 arms from the root to the tip, and the connecting arms 3 are of thin-walled or streamlined structure, so Taking into account the requirements of support stiffness and drag reduction.

In this embodiment, the flap actuator 5 is the driving source of the high-lift device, which drives the movement of each linkage mechanism, thereby driving the deflector 2 and the main flap 4 to deflect and retreat at the same time, so that in the flap compartment 1. A two-stage seam is formed between the deflector 2 and the main flap 4 .

In this embodiment, the operation mode of the lifting device is as follows:

Example 1

When the aircraft takes off or lands, put down the double-slotted flap with deflector, after the flap actuator 5 rotates, it drives the first connecting rod 6 and the second connecting rod 9 to move backward, and the third connecting rod 11 adapts to Rear rotation, to drive the main flap 4, the connecting arm 3, and the deflector 2 to rotate and move backward, so that the primary seam 13 between the leading edge of the deflector 2 and the rear edge of the flap cabin 1 reaches different developments. 0.7% to 1.5% of the chord length to the position, as shown in Figure 2;

Example 2

The flap actuator 5 is driven by the actuator, 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 adaptably rotates backward to drive the main flap 4 and the connecting support. The arm 3 and the deflector 2 rotate and move backward, so that the primary seam 13 between the leading edge of the deflector 2 and the rear edge of the flap compartment 1 reaches 0.7% to 1.5% of the chord length at different spanwise positions;

Example 3

When the aircraft takes off or lands, put down the double-slotted flap with deflector, after the flap actuator 5 rotates, it drives the first connecting rod 6 and the second connecting rod 9 to move backward, and the third connecting rod 11 adapts to The rear rotation drives the main flap 4, the connecting arm 3, and the deflector 2 to rotate and move backward. The rotation and backward movement of the deflector 2 and the main flap 4 can be precisely controlled, and can be stopped at two rear Flap angle, the rear flap angle here is the angle change of the main flap 4 relative to the flap cabin 1, which is controlled by the angle between the first connecting rod 6 and the second connecting rod 9 at the pivot point 8, the The included angle changes between a small angle and a large angle. When the plane takes off, control the included angle to be in a small angle state, and the small angle can take any value from 15 to 25°; when the aircraft is landing, control the included angle to be in a large angle state , the large angle can take any value from 30° to 45°;

Example 4

The flap actuator 5 is provided with an angular displacement sensor, which outputs the flap actuator 5 rotation angle signal through the angular displacement sensor, and realizes the closed-loop control of the flap through the aircraft electromechanical control system; the electromechanical control system is provided with a flap actuation The electrical zero position and the electrical limit position of the device 5 are provided with a mechanical zero position and a structure for controlling the limit position in the rotary actuator 5 to limit the movement of the flap actuator 5, and the deflector 2 follows the main flap 4 When retracted, it can only reach the set zero position and cannot move in reverse; when the deflector 2 is lowered with the main flap 4, it can only reach the set maximum limit and cannot over-travel;

Example 5

When the deflector 2 and the main flap 4 are in the retracted state, a small gap is reserved between the deflector 2 and the main flap 4 and the flap compartment 1 on the upper surface and the lower surface thereof to ensure that the deflector 2 and the main flap 4. During the take-off and landing phase of the aircraft, when retracting and retracting in place during air cruise flight, the deflector 2 and the main flap 4 will not interfere with the flap compartment 1 when they are elastically deformed by the aerodynamic load, and there is a sufficient gap ;

Example 6

The flap arm 7 below is provided with fairing, and fairing is made up of fairing front cover 15 and fairing rear cover 16, and fairing front cover 15 is connected with wing wing box, and fairing rear cover 16 is fixedly connected with main flap 4, rectification The cover adopts a streamlined structure. When the double-slit flaps are retracted, there is a movement gap of 1-2mm between the front fairing 15 and the rear fairing 16 to meet the dual requirements of reducing aerodynamic resistance and manufacturing and assembling process. It has the function of preventing foreign matter and rain; when the double-slotted flap is in the lowered state, the fairing front cover 15 is separated from the fairing rear cover 16, which does not affect the normal movement of the deflector 2 and the main flap 4;

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 adjust the length and angle in a small range. The No. 1 connecting rod 6 and the No. 2 connecting rod 9 1. The length adjustment of No. 3 connecting rod 11 is realized through the segmented thread structure of the connecting rod, and the angle is adjusted through the length relationship of different connecting rods; The mechanical zero position and the electrical zero position adjustment in the electromechanical control system realize the adjustment angle adjustment. By adjusting the length and angle of the flap actuator 5, the first connecting rod 6, the second connecting rod 9, and the third connecting rod 11, To eliminate the movement gap, ensure the accuracy of the positions of the deflector 2 in the retracted state and the lowered state with the main flap 4, and make the states of the rear flap stable and reliable without shaking.

The above is only a specific embodiment of the application, but the scope of protection of the application is not limited thereto. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the application. All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application should be determined by the protection scope of the claims.

Claims (13)

1. A lift-increasing device with deflector-type double-slot flaps, including flap cabin, deflector, connecting support arm, main flap, flap actuator, No. 1 connecting rod, flap support arm . No. 2 connecting rod and No. 3 connecting rod, characterized in that the deflector is connected to the main flap through a connecting arm, and the rear edge of the flap compartment is provided with a cavity for containing the deflector, In addition, a primary seam is formed between the leading edge of the deflector and the rear edge of the flap compartment, and a secondary seam is formed between the trailing edge of the deflector and the leading edge of the main flap; the flap actuator is installed on the flap On the cabin, the flap support arm is arranged under the flap compartment, the flap actuator is connected to the flap support arm through the No. 1 connecting rod, and the flap support arm is connected to the No. The rod is connected with the main flap to promote the combination of the No. 1 connecting rod, the flap support arm, the No. 3 connecting rod, the main flap and the flap cabin to form a four-bar linkage mechanism in the motion plane. 2. The lift-increasing device with deflector type double-slotted flap according to claim 1, characterized in that, the flap support arm is provided with a connecting hinge point, and one end of the No. 1 connecting rod is connected to the flap The actuator is connected, the other end of the No. 2 connecting rod is fixedly connected with the main flap, and the other end of the No. 1 connecting rod is hingedly connected with the other end of the No. 2 connecting rod through a rotating hinge point in space; One end of the No. 3 connecting rod is connected with the connecting hinge point, and the other end of the No. 3 connecting rod is connected with the flap hinge point arranged on the main flap. 3. The lift-increasing device with deflector type double-slotted flaps according to claim 2, wherein the included angle between the No. 1 connecting rod, the No. 2 connecting rod and the rotation hinge point is 15～ 45°, when the plane takes off, the angle is 15-25°; when the plane is landing, the angle is 30°-45°. 4. The lift-increasing device with baffle-type double-slotted flaps according to claim 1, wherein the baffle is a streamlined structure with a large camber and a negative installation angle, and the relative height of the baffle is The thickness is 16% to 23%. 5. The high-lift device with deflector type double-slotted flap according to claim 1, characterized in that, the cavity is matched with the shape of the deflector. 6. The lift-increasing device of band deflector type double-slotted flap according to claim 1, is characterized in that, when the aircraft takes off or lands and is in put down state, the first-order seam of deflector and flap cabin The gap value accounts for 0.7%-1.5% of the chord length at different spanwise positions. 7. The high-lift device with deflector type double-slotted flap 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 shaped structure. 8 . The high-lift device with deflector type double-slot flap according to claim 1 , wherein an angular displacement sensor is arranged in the flap actuator. 9. The high-lift device with deflector type double-slotted flap according to claim 1, characterized in that, the rotary actuator is provided with a mechanical zero position and a structure for controlling the limit position. 10. The lift-increasing device of the band deflector type double-slot flap according to claim 1, wherein a fairing is arranged below the flap support arm, and the fairing is composed of a front fairing and a rear fairing. Composition, the fairing is fixedly connected with the wing box, and the fairing is fixedly connected with the main flap. 11. The high-lift device with deflector type double-slotted flaps according to claim 10, characterized in that, the fairing is a streamlined structure. 12. The lift-increasing device with deflector type double-slotted flaps according to claim 10, characterized in that, in the retracted state of the double-slotted flaps, a movement gap is provided between the fairing front cover and the fairing rear cover, The movement gap is 1~2mm. 13. The high-lift device with deflector type double-slotted flap according to any one of claims 1 to 12, characterized in that the operation mode of the high-lift device is as follows: When the aircraft takes off or lands, put down the double-slotted flap with deflector, after the flap actuator rotates, it will drive the No. 1 and No. 2 links to move backward, and the No. Drive the main flap, the connecting arm, and the deflector to rotate and move backward, so that the primary seam between the leading edge of the deflector and the rear edge of the flap cabin reaches 0.7% to 1.5% of the chord length at different spanwise positions ; In the take-off state of the aircraft, by driving the flap actuator to rotate, so that the angle between the No. 1 connecting rod and the No. 2 connecting rod is between 15° and 25°; The flap actuator is driven to rotate so that the included angle between the No. 1 connecting rod and the No. 2 connecting rod is between 30° and 45°.

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