CN115783242A - High lift device with guide vane type double-slit flap - Google Patents
High lift device with guide vane type double-slit flap Download PDFInfo
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- CN115783242A CN115783242A CN202211624701.3A CN202211624701A CN115783242A CN 115783242 A CN115783242 A CN 115783242A CN 202211624701 A CN202211624701 A CN 202211624701A CN 115783242 A CN115783242 A CN 115783242A
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- 238000006073 displacement reaction Methods 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 3
- 230000003416 augmentation Effects 0.000 claims 1
- 238000010276 construction Methods 0.000 claims 1
- 108010066057 cabin-1 Proteins 0.000 description 17
- 230000007246 mechanism Effects 0.000 description 12
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000002265 prevention Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
- B64C9/26—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by multiple flaps
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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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
Technical Field
The invention relates to the technical field of airplane structures, in particular to a high lift device with a guide vane type double-slit flap.
Background
For an airplane requiring high lift force, in order to meet the performance requirements of take-off and landing, high lift devices such as single slit flaps and the like are generally arranged at the trailing edge of a wing to improve the lift force; the single-slit flap has simple structure and motion mechanism, but can use a limited deflection angle and cannot provide enough lift increment; the double-slit flap and the multi-slit flap have two or more airflow slits, can use a large deflection angle and can provide enough lift increment, but have complex structures and motion mechanisms, and are unfavorable for airplanes simultaneously pursuing high-speed characteristics.
The patent CN102642616B discloses an airplane high lift device with a fixed double-slit flap, which adopts an airplane high lift device with a fixed-shaft rotating rear edge fixed main/rear double-slit flap, and comprises a main flap, a rear flap, a Y-shaped bracket, a main wing rear beam fixing rod, an actuating cylinder, a first linkage rod, a second linkage rod, a third linkage rod, a spoiler, a lower baffle plate and a sealing rubber sheet, wherein the fixed-shaft movement mechanism is lighter, higher in reliability and faster in operation reaction relative to a sliding rail movement mechanism; the defects are that the height of the support arm of the connecting hinge is large, the influence on the flow field of the lower airfoil surface of the wing is large, and the support arm is not suitable for large-sized motor aircrafts and light/small aircrafts;
patent CN113104196a discloses a high lift device and a high lift method for an aircraft, the high lift device for the aircraft includes: a connection bracket for connecting the high lift device to a 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 is provided with a first surface facing the slot, and the rear wing section is provided with a second surface facing the slot; a first cover plate located on the rear panel; and an actuator capable of controlling the first cover plate to extend into the seam between the front wing section and the rear wing section; the high lift device is provided with an internal seam channel capable of being actively controlled, when the airplane takes off and lands, the high lift device can be actively controlled to form a seam channel between the front wing panel and the rear wing panel, momentum is effectively guided into the boundary layer, the high lift device is driven by an actuator, and a mechanism adopts a connecting support form;
the patent CN203528807U discloses a high lift device of an airplane single slit flap, which comprises a flap cabin and a movable deflection flap, wherein the flap cabin and the movable deflection flap are consistent with the conventional single slit flap, a deflectable flow deflector is additionally arranged on the basis, the upper surface of the deflectable flow deflector is in the shape of a wing, the lower surface connected with the flap cabin is a sample line, the movable deflection flap is determined by the shape of the wing and the structural space of the movable deflection flap together when the movable deflection flap is in a zero position, and the sealing performance of the deflectable flow deflector and the movable deflection flap when the deflectable flow deflector and the movable deflection flap are in the zero position is ensured;
the patent CN205059998U discloses a high lift device for an airplane, which comprises a double-peak flap and an aileron which are positioned at the trailing edge of the wing of the airplane, wherein the double-slit flap is arranged at one side close to the fuselage of the airplane, the contradiction between high lift force and rolling control can be solved through the combination of the trailing edge flap and the aileron which are arranged at the trailing edge of the wing of the airplane, the characteristic requirements of take-off and landing of the airplane are met, and the high lift effect of the two-stage slit flap can reach the lift system with the attack angle of 10 degrees and be increased by 0.3; the layout of the double-slit flap and the aileron can provide certain transverse control capability, and the transverse control capability of the airplane can be ensured by matching with a differential horizontal tail;
the high lift devices of the above-mentioned publications do not simultaneously address the need for high lift to the flap slot and the need for simple structure and motion for high speed characteristics.
Disclosure of Invention
The invention provides a high lift device with a guide vane type double-slit flap, which solves the problems in the background art.
The technical problem solved by the invention is realized by adopting the following technical scheme:
a high lift device with a guide vane type double-slit wing flap comprises a wing flap cabin, a guide vane, a connecting support arm, a main wing flap, a wing flap actuator, a first connecting rod, a wing flap support arm, a second connecting rod and a third connecting rod, wherein the guide vane is connected with the main wing flap through the connecting support arm, a containing cavity used for containing the guide vane when the high lift device is in a folded state is arranged in the rear edge of the wing flap cabin, a first-stage slot way is formed between the front edge of the guide vane and the rear edge of the wing flap cabin, and a second-stage slot way is formed between the rear edge of the guide vane and the front edge of the main wing flap; the flap actuator is installed on the flap cabin, the flap support arm is arranged below the flap cabin, the flap actuator is connected with the flap support arm through a first connecting rod, and the flap support arm is connected with the main flap through a second connecting rod and a third connecting rod so as to enable the first connecting rod, the flap support arm and the third connecting rod to form a four-link mechanism with the main flap and the flap cabin in a movement plane.
In the invention, a connecting hinge point is arranged on the flap support arm, one end of the first connecting rod is connected with the flap actuator, the other end of the second connecting rod is fixedly connected with the main flap, and the other end of the first connecting rod is hinged with the other end of the second connecting rod through a rotating hinge point in space; one end of the third connecting rod is connected with the connecting hinge point, and the other end of the third connecting rod is connected with the flap hinge point arranged on the main flap.
In the invention, the included angle between the first connecting rod and the second connecting rod and the rotating hinge point is 15-45 degrees, and the included angle is 15-25 degrees when the airplane takes off; when the airplane lands, the included angle is 30-45 degrees.
In the invention, the flow deflector is of a streamline structure with large camber and negative installation angle, and the relative thickness of the flow deflector is 16-23%.
In the invention, the shape of the containing cavity is matched with that of the flow deflector, and when the main flap is in a folded state, a small gap is reserved between the main flap and the flap cabin so as to ensure the cruising performance of the airplane; the guide vane keeps a safe clearance with the containing cavity of the flap cabin in the rotating and backward moving processes so as to realize the safety and reliability of the structure and the mechanism.
In the invention, when the plane takes off or lands and is in a laid down state, the gap value of the first-level seam road of the guide vane and the flap cabin accounts for 0.7-1.5% of the chord length at different unfolding positions.
In the invention, a plurality of connecting support arms are arranged in a spanwise direction and are unfolded one by one from the root to the tip, and the connecting support arms are of a thin-wall or streamline structure so as to meet the requirements of supporting rigidity and resistance reduction.
In the invention, an angular displacement sensor is arranged in the flap actuator.
In the present invention, a mechanical zero position and a structure for controlling the extreme position are provided in the rotary actuator to limit the movement of the flap actuator.
According to the invention, a fairing is arranged below the flap support arm, the fairing consists of a front fairing and a rear fairing, the front fairing is fixedly connected with the wing box of the wing, the rear fairing is fixedly connected with the main flap, the fairing adopts a streamline structure, and in a state that the double-slit flap is folded, a movement gap is arranged between the front fairing and the rear fairing and is 1-2 mm.
In the present invention, the operation modes of the high lift device are as follows:
when the airplane takes off or lands, the double-slit wing flap with the guide vane is put down, the first connecting rod and the second connecting rod are driven to move backwards after the wing flap actuator rotates, and the third connecting rod rotates backwards adaptively to drive the main wing flap, the connecting support arm and the guide vane to rotate and move backwards so as to promote the first-stage seam road between the front edge of the guide vane and the rear edge of the wing flap cabin to reach 0.7-1.5% of the chord length at different spanwise positions; in the takeoff state of the airplane, the included angle between the first connecting rod and the second connecting rod is 15-25 degrees by driving the flap actuator to rotate, and in the landing state of the airplane, the included angle between the first connecting rod and the second connecting rod is 30-45 degrees by driving the flap actuator to rotate.
Has the advantages that: the weight of the high lift device structure prepared by the invention is 60-70% of the weight of the non-fixed double-slit flap, the four-bar mechanism is more direct and rapid to realize relative to the trailing edge flap in the form of a pulley and a slide rail, the position of the rear flap is controlled to be higher in precision and high in reliability, and the high lift device can have the same service life as an airplane body.
Drawings
FIG. 1 is a schematic view of a double-slit flap in a retracted state in a preferred embodiment of the invention.
FIG. 2 is a schematic view of a double-slotted flap in a down position in accordance with a preferred embodiment of the present invention.
FIG. 3 is a schematic view of the double-slit flap during movement in a preferred embodiment of the present invention.
FIG. 4 is a schematic view of the fairing in a stowed position for a double-slit flap in accordance with a preferred embodiment of the invention.
FIG. 5 is a schematic view of a fairing in a preferred embodiment of the invention with a double-slit flap down.
Fig. 6 is a schematic view of a flap actuator according to a preferred embodiment of the invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained by combining the specific drawings.
Referring to fig. 1 to 6, the high lift device with the guide vane type double-slit flap comprises a flap cabin 1, a guide vane 2, a connecting support arm 3, a main flap 4, a flap actuator 5, a first connecting rod 6, a flap support arm 7, a rotary hinge point 8, a second connecting rod 9, a connecting hinge point 10, a third connecting rod 11, a flap hinge point 12, a first-level seam way 13, a second-level seam way 14, a fairing 15 and a fairing rear fairing 16, wherein the guide vane 2 is connected with the main flap 4 through the connecting support arm 3; the rear edge of the flap cabin 1 is internally provided with a containing cavity used for containing the flow deflector 2 when the high lift device is in a folded state, the flow deflector 2 enters the containing cavity, and the flap cabin 1 is combined with the main flap 4 to ensure the smoothness of the upper surface and the lower surface of the wing.
According to the application, a primary slot 13 is formed between the leading edge of a guide vane 2 and the trailing edge of a flap cabin 1, a secondary slot 14 is formed between the trailing edge of the guide vane 2 and the leading edge of a main flap 4, and referring to fig. 1 and 2, the guide vane 2 and the main flap 4 are connected through a connecting support arm 3, but a person skilled in the art can understand that the connecting support arm 3 only occupies a partial area between the guide vane 2 and the main flap 4, and other areas occupying most parts between the guide vane 2 and the main flap 4 are unstructured cavities along the wingspan direction, so that the secondary slot 14 is formed, when a lift-increasing device is in a put-down state, airflow on the lower surface of a wing flows upwards along the primary slot 13 and the secondary slot 14 after the speed is increased and the flow direction is changed, and then flows backwards along the upper surfaces of the guide vane 2 and the main flap 4, so that airflow separation occurring under the condition of large skewness of the main flap 4 can be inhibited, and the lift-increasing effect is improved by 20% -30% relative to that of a single-slit flap; the flap actuator 5 is installed on the flap cabin 1, the flap support arm 7 is arranged below the flap cabin 1, a connecting hinge point 10 is arranged on the flap support arm 7, one end of the first connecting rod 6 is connected with the flap actuator 5, the other end of the first connecting rod 6 is connected with a rotating hinge point 8 without a fixed position, one end of the second connecting rod 9 is connected with the rotating hinge point 8, the other end of the second connecting rod 9 is fixedly connected with the main flap 4, one end of the third connecting rod 11 is connected with the connecting hinge point 10, the other end of the third connecting rod 11 is connected with a flap hinge point 12 arranged on the main flap 4, so that the combination of the first connecting rod 6, the flap 7 and the third connecting rod 11 with the main flap 4 and the flap cabin 1 forms a four-bar mechanism in a moving plane, the connecting rod structure is opposite to the slide rail mechanism, under the condition that the same rear edge flap retraction amount is ensured, the length, the width and the height of the flap support arm 7 are all reduced, and the connecting rod 3 is smaller than the moving part of the slide rail structure as a fixed part, so that the weight of the whole rear edge support arm is reduced by 30% -40%.
In this embodiment, the flow deflector 2 has a streamline structure with a large curvature and a negative installation angle, and the relative thickness of the flow deflector 2 is 16% to 23%.
It should be noted that, referring to fig. 1, the flow deflector 2 extends from the left end to the right end, the extending direction defines the length of the flow deflector, the direction perpendicular to the length of the flow deflector is the thickness of the flow deflector, as can be seen from the right fig. 1, the thickness of the flow deflector is constantly changing to form a predetermined distance with the inner surface of the cavity of the flap cabin 1, the relative thickness of the flow deflector 2 here refers to the ratio of the thickness of the flow deflector at each position to the length of the flow deflector in the extending direction, and the ratio at any position is selected within the interval of 16% to 23%.
In the embodiment, the shape of the accommodating cavity is matched with that of the flow deflector 2, and when the main flap 4 is in a folded state, a small gap is reserved between the main flap 4 and the flap cabin 1 so as to ensure the cruising performance of the airplane; the guide vane 2 keeps a safety clearance with the containing cavity of the flap cabin 1 in the rotating and backward moving processes so as to realize the safety and reliability of the structure and the mechanism.
In the embodiment, when the high lift device is in a laid-down state during takeoff or landing of an airplane, the gap value of the flow deflector 2 and the first-level seam channel 13 of the flap cabin 1 accounts for 0.7-1.5% of the chord length at different unfolding positions.
In this embodiment, the included angle between the first connecting rod 6, the second connecting rod 9 and the rotating hinge point 8 is 15-45 degrees, and the included angle is 15-25 degrees when the airplane takes off; when the airplane lands, the included angle is 30-45 degrees.
In this embodiment, the connecting arms 3 are arranged in 5 in the spanwise direction, the first to fifth arms are arranged from the root to the tip, and the connecting arms 3 are thin-walled or streamlined structures so as to meet the requirements of supporting rigidity and resistance reduction.
In the embodiment, the flap actuator 5 is a driving source of the high lift device, and drives each link mechanism to move, so as to drive the guide vane 2 and the main flap 4 to deflect and retreat simultaneously, so as to form a two-stage slot between the flap cabin 1, the guide vane 2 and the main flap 4.
In the present embodiment, the operation mode of the high lift device is as follows:
example 1
When the airplane takes off or lands, the double-slit flap with the guide vanes is put down, the flap actuator 5 rotates to drive the first connecting rod 6 and the second connecting rod 9 to move backwards, and the third connecting rod 11 adaptively rotates backwards to drive the main flap 4, the connecting support arm 3 and the guide vane 2 to rotate and move backwards, so that the primary slit channel 13 between the front edge of the guide vane 2 and the rear edge of the flap cabin 1 reaches 0.7-1.5% of the chord length at different spanwise positions, as shown in fig. 2;
example 2
The flap actuator 5 is driven by an actuating cylinder, the actuating cylinder drives a first connecting rod 6 and a second connecting rod 9 to move backwards, and a third connecting rod 11 adaptively rotates backwards to drive the main flap 4, the connecting support arm 3 and the guide vane 2 to rotate and move backwards, so that a first-level slot 13 between the front edge of the guide vane 2 and the rear edge of the flap cabin 1 reaches 0.7-1.5% of the chord length at different spanwise positions;
example 3
When the airplane takes off or lands, the double-slit flap with the guide vanes is put down, the flap actuator 5 rotates to drive the first connecting rod 6 and the second connecting rod 9 to move backwards, the third connecting rod 11 rotates backwards adaptively to drive the main flap 4, the connecting support arm 3 and the guide vane 2 to rotate and move backwards, the rotation and the backward movement of the guide vane 2 and the main flap 4 can be accurately controlled and can be stopped at 2 backward opening angles, wherein the backward opening angle is the angle change of the main flap 4 relative to the flap cabin 1, and is controlled by the included angle of the first connecting rod 6 and the second connecting rod 9 at a rotating hinge point 8, the included angle changes between a small angle and a large angle, when the airplane takes off, the included angle is controlled to be in a small-angle state, and the small angle takes any value from 15-25 degrees; when the airplane lands, the included angle is controlled to be in a large angle state, and any value of the large angle is taken from 30 degrees to 45 degrees;
example 4
An angular displacement sensor is arranged in the flap actuator 5, a rotation angle signal of the flap actuator 5 is output through the angular displacement sensor, and closed-loop control of the flap is realized through an electromechanical control system of the airplane; the electromechanical control system is provided with an electric zero position and an electric limit position of the flap actuator 5, the rotary actuator 5 is internally provided with a mechanical zero position and a structure for controlling the limit position to limit the movement of the flap actuator 5, and the deflector 2 can only reach the set zero position and cannot move reversely when being folded along with the main flap 4; when the guide vane 2 is put down along with the main flap 4, the set maximum limit can be reached only, and the overtravel movement cannot be realized;
example 5
When the guide vane 2 and the main flap 4 are in a folded state, small gaps are reserved on the upper surface and the lower surface of the guide vane 2, the main flap 4 and the flap cabin 1 so as to ensure that when the guide vane 2 and the main flap 4 carry out folding and unfolding movement in the taking-off and landing stage of an airplane and are folded in place during air cruising flight, the guide vane 2 and the main flap 4 do not interfere with the flap cabin 1 when subjected to elastic deformation under pneumatic load, and sufficient gaps exist;
example 6
A fairing is arranged below the flap support arm 7 and consists of a fairing front cover 15 and a fairing rear cover 16, the fairing front cover 15 is fixedly connected with a wing box of the wing, the fairing rear cover 16 is fixedly connected with the main flap 4, the fairing adopts a streamline structure, and when the double-slit flap is in a folded state, a movement gap of 1-2 mm is arranged between the fairing front cover 15 and the fairing rear cover 16, so that the double requirements of reducing aerodynamic resistance and manufacturing and assembling manufacturability are met, and the double requirements of foreign matter prevention and rainwater prevention are achieved; when the double-slit flap is in a laid-down state, the fairing front cover 15 is separated from the fairing rear cover 16, and the normal movement of the flow deflector 2 and the main flap 4 is not influenced;
in the above embodiment, the flap actuator 5, the first connecting rod 6, the second connecting rod 9, and the third connecting rod 11 can perform small-range length and angle adjustment, the length adjustment of the first connecting rod 6, the second connecting rod 9, and the third connecting rod 11 is realized by the segmented thread structures of the connecting rods, and the angle is adjusted by the length relationship of different connecting rods; the flap actuator 5 realizes length adjustment by adjusting the positioning position of the mounting structure, realizes angle adjustment by adjusting the internal mechanical zero position and the electric zero position in the electromechanical control system, eliminates the movement gap by adjusting the length and the angle of the flap actuator 5, the first connecting rod 6, the second connecting rod 9 and the third connecting rod 11, ensures the accuracy of the position of the deflector 2 in the folding state and the laying state along with the main flap 4, and ensures that each state of the rear flap is stable, reliable and free from shaking.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (13)
1. A high lift device with a guide vane type double-slit flap comprises a flap cabin, a guide vane, a connecting support arm, a main flap, a flap actuator, a first connecting rod, a flap support arm, a second connecting rod and a third connecting rod, and is characterized in that the guide vane is connected with the main flap through the connecting support arm, a containing cavity used for containing the guide vane is arranged in the rear edge of the 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 flap cabin, the flap support arm sets up in flap cabin below, the flap actuator through a connecting rod with the flap support arm be connected the flap support arm through No. two connecting rods, no. three connecting rods and main flap are connected to impel the combination of a connecting rod, flap support arm, no. three connecting rods and main flap and flap cabin to form four-bar linkage in the motion plane.
2. The high lift device with the guide vane type double-slit flap as claimed in claim 1, wherein the flap support arm is provided with a connecting hinge point, one end of the first connecting rod is connected with the flap actuator, the other end of the second connecting rod is fixedly connected with the main flap, and the other end of the first connecting rod is hinged with the other end of the second connecting rod through a rotating hinge point in space; one end of the third connecting rod is connected with the connecting hinge point, and the other end of the third connecting rod is connected with the flap hinge point arranged on the main flap.
3. The high lift device with the guide vane type double-slit flap of claim 2, wherein an included angle between the first connecting rod, the second connecting rod and the rotating hinge point is 15-45 degrees, and the included angle is 15-25 degrees when the airplane takes off; when the airplane lands, the included angle is 30-45 degrees.
4. The high lift device with the guide vane type double-slit flap of claim 1, wherein the guide vane is a streamline structure with large curvature and negative installation angle, and the relative thickness of the guide vane is 16-23%.
5. The high lift device with a double slotted vane as claimed in claim 1, wherein the receptacle is contoured to match the vane.
6. The high lift device with the guide vane type double-slit flap of claim 1, wherein when the aircraft takes off or lands in a laid down state, the gap value between the guide vane and the first-level slit channel of the flap cabin accounts for 0.7-1.5% of the chord length at different spanwise positions.
7. The high lift device with the two-slit flap of claim 1, wherein the connecting arms are arranged in a plurality in the span-wise direction, and the connecting arms are of a thin-walled or streamlined structure.
8. The high lift device with a two-slot flap of air guide vane type of claim 1, wherein an angular displacement sensor is provided in the flap actuator.
9. The high lift device with a two-slit flap of the spoiler claim 1, characterized in that a mechanical zero position and a structure for controlling the extreme positions are provided in the rotary actuator.
10. The lift augmentation device with the guide vane type double-slit flap of claim 1, wherein a fairing is arranged below the flap support arm and consists of a fairing front cover and a fairing rear cover, the fairing front cover is fixedly connected with the wing box of the wing, and the fairing rear cover is fixedly connected with the main flap.
11. The high lift device with the vaned double slit flap of claim 10, wherein the fairing is of streamlined construction.
12. The high lift device with the double slit flap of claim 10, wherein a movement gap is provided between the fairing front cover and the fairing rear cover in the folded-up state of the double slit flap, and the movement gap is 1-2 mm.
13. The high-lift device with the double-slotted flap with air deflectors of any one of claims 1 to 12, wherein the high-lift device is operated in the following mode:
when the airplane takes off or lands, the double-slit wing flap with the guide vanes is put down, the first connecting rod and the second connecting rod are driven to move backwards after the wing flap actuator rotates, and the third connecting rod adaptively rotates backwards to drive the main wing flap, the connecting support arm and the guide vanes to rotate and move backwards so as to promote the first-stage slit path between the front edge of the guide vanes and the rear edge of the wing flap cabin to reach 0.7-1.5% of the chord length of different spanwise positions; in the take-off state of the airplane, the included angle between the first connecting rod and the second connecting rod is 15-25 degrees by driving the flap actuator to rotate, and in the landing state of the airplane, the included angle between the first connecting rod and the second connecting rod is 30-45 degrees by driving the flap actuator to rotate.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211624701.3A CN115783242A (en) | 2022-12-16 | 2022-12-16 | High lift device with guide vane type double-slit flap |
| PCT/CN2022/140189 WO2024124600A1 (en) | 2022-12-16 | 2022-12-20 | High-lift device with guide vane type double-slotted flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211624701.3A CN115783242A (en) | 2022-12-16 | 2022-12-16 | High lift device with guide vane type double-slit flap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115783242A true CN115783242A (en) | 2023-03-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211624701.3A Pending CN115783242A (en) | 2022-12-16 | 2022-12-16 | High lift device with guide vane type double-slit flap |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN115783242A (en) |
| WO (1) | WO2024124600A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131833A (en) * | 2018-09-28 | 2019-01-04 | 成都飞机工业（集团）有限责任公司 | A kind of high aspect ratio wing of high lift-rising |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0272396A2 (en) * | 1986-12-20 | 1988-06-29 | Dornier Gmbh | Aerodynamic aircraft wing flap system, in particular for slot flaps |
| US4995575A (en) * | 1988-09-26 | 1991-02-26 | The Boeing Company | Wing trailing edge flap mechanism |
| US20060226297A1 (en) * | 2005-04-11 | 2006-10-12 | Eads Deutschland Gmbh | Wing with extendable aerodynamic pivoted flaps |
| US20180065731A1 (en) * | 2016-09-05 | 2018-03-08 | Embraer S.A. | Deflection mechanism of the flap panels of an aircraft |
| CN112339987A (en) * | 2020-10-29 | 2021-02-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Double-slit flap with flap fixedly connected with additional wing |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB519236A (en) * | 1937-10-28 | 1940-03-20 | Messerschmitt Boelkow Blohm | Improvements in and relating to supporting surfaces for aircraft |
| US4120470A (en) * | 1976-09-28 | 1978-10-17 | The Boeing Company | Efficient trailing edge system for an aircraft wing |
| US5788190A (en) * | 1996-10-22 | 1998-08-04 | The Boeing Company | Slotted cruise trailing edge flap |
| CN102040002A (en) * | 2010-12-02 | 2011-05-04 | 北京航空航天大学 | Curve slide-connecting rod mechanism in high lift device of large aircraft |
| EP3301018A1 (en) * | 2016-09-30 | 2018-04-04 | Airbus Operations GmbH | System for driving and guiding of a multifunctional trailing edge control surface on an aircraft |
| US10766600B2 (en) * | 2017-07-28 | 2020-09-08 | The Boeing Company | Articulation assemblies for retracting aircraft flap support fairings and related methods |
| US11001371B2 (en) * | 2018-08-07 | 2021-05-11 | The Boeing Company | Hydraulic droop control for aircraft wing |
-
2022
- 2022-12-16 CN CN202211624701.3A patent/CN115783242A/en active Pending
- 2022-12-20 WO PCT/CN2022/140189 patent/WO2024124600A1/en unknown
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0272396A2 (en) * | 1986-12-20 | 1988-06-29 | Dornier Gmbh | Aerodynamic aircraft wing flap system, in particular for slot flaps |
| US4995575A (en) * | 1988-09-26 | 1991-02-26 | The Boeing Company | Wing trailing edge flap mechanism |
| US20060226297A1 (en) * | 2005-04-11 | 2006-10-12 | Eads Deutschland Gmbh | Wing with extendable aerodynamic pivoted flaps |
| US20180065731A1 (en) * | 2016-09-05 | 2018-03-08 | Embraer S.A. | Deflection mechanism of the flap panels of an aircraft |
| CN112339987A (en) * | 2020-10-29 | 2021-02-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Double-slit flap with flap fixedly connected with additional wing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131833A (en) * | 2018-09-28 | 2019-01-04 | 成都飞机工业（集团）有限责任公司 | A kind of high aspect ratio wing of high lift-rising |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2024124600A1 (en) | 2024-06-20 |
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