Device and method for checking involution of moving and static wings of airplane empennage

Abstract

The invention discloses a dynamic and static wing involution inspection device and method for an airplane empennage. Comprising a positioning mechanism (1), the positioning mechanism (1) comprises a sliding rail (3), a pulley main frame (4) is connected to the sliding rail (3) in a sliding mode, and a folding mechanism (2) is arranged at the end of the sliding rail (3); the pulley main frame (4) is provided with a static wing V-shaped groove zero point positioner (6) used for supporting and positioning an airplane empennage static wing. A movable wing turnover mechanism is further arranged on the pulley main frame (4), the movable wing turnover mechanism comprises a movable wing turnover frame (12) rotationally connected to the pulley main frame (4), and a movable wing V-shaped groove zero-point positioner (7) used for supporting and positioning an airplane empennage movable wing is arranged on the movable wing turnover frame (12); a driving mechanism A (5) is further arranged on the pulley main frame (4), and the movable wing overturning frame (12) can overturn under the driving of the driving mechanism A (5); the folding mechanism (2) comprises a fixed frame (10) arranged at the end part of the sliding rail (3), the fixed frame (10) is rotationally connected with a static wing turning plate (9), and the fixed frame (10) is also provided with a driving mechanism B (11); and the static wing turning plate (9) can turn over under the driving of a driving mechanism B (11). According to the invention, the folding and checking efficiency and quality of the movable and static wings of the airplane are improved, and the folding consistency and stability of products are greatly improved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft assembly, and in particular relates to a device and method for checking the alignment of a dynamic and static wing of an aircraft tail. Background Art

[0002] The vertical tail and horizontal tail structures of tilt-rotor aircraft and fixed-wing aircraft are composed of static wings and moving wings. The static wings generally adopt the main load-bearing structure layout of single beam (or double beam) and wing ribs. Several hinge joints are installed on the static wing beam to support the moving wing. One of the hinge joints also bears the vertical load of the moving wing. Several control joints are installed on the static wing beam to connect the moving wing servo control system to control the swinging movement of the moving wing. The moving wing and the static wing are assembled independently. The coordination state between the two, including the gap, step difference, thrust, etc., as well as the minimum gap between the moving wing and the static wing within the deflection range of the moving wing, is very important and directly affects the flight performance and safety performance of the aircraft. Therefore, before the final assembly of the fuselage structure, it is an urgent problem to align the moving wing with the static wing and check the compliance of various indicators. Summary of the invention

[0003] The purpose of the present invention is to provide a device and method for checking the alignment of the dynamic and static wings of an aircraft tail wing. The present invention improves the alignment and inspection efficiency and quality of the dynamic and static wings of an aircraft, and greatly improves the alignment consistency and stability of the product.

[0004] The technical solution of the present invention is: a device for checking the alignment of the moving and static wings of an aircraft tail, comprising a positioning mechanism, the positioning mechanism comprising a slide rail, a pulley main frame is slidably connected to the slide rail, and an alignment mechanism is arranged at the end of the slide rail; a static wing V-groove zero point locator for supporting and positioning the static wing of the aircraft tail is arranged on the pulley main frame; a moving wing flipping mechanism is also arranged on the pulley main frame, the moving wing flipping mechanism comprises a moving wing flipping frame rotatably connected to the pulley main frame, and the moving wing flipping frame is provided with a moving wing V-groove zero point locator for supporting and positioning the moving wing of the aircraft tail; a driving mechanism A is also arranged on the pulley main frame, and the moving wing flipping frame can be flipped under the drive of the driving mechanism A; the alignment mechanism comprises a fixed frame arranged at the end of the slide rail, a static wing flap is rotatably connected to the fixed frame, and a driving mechanism B is also arranged on the fixed frame; the static wing flap can be flipped under the drive of the driving mechanism B.

[0005] In the aforementioned dynamic and static wing alignment inspection device for the aircraft tail wing, a fine-tuning handwheel mechanism capable of driving the static wing V-groove zero point locator to rise / fall is provided on the static wing.

[0006] In the aforementioned aircraft tail wing dynamic and static wing alignment inspection device, a fine-tuning hand wheel mechanism capable of driving the dynamic wing V-groove zero point locator to rise / fall is provided on the dynamic wing.

[0007] In the aforementioned aircraft tail wing dynamic and static wing alignment inspection device, a locking sensor is integrated on the static wing flap.

[0008] In the aforementioned aircraft tail wing dynamic and static wing alignment inspection device, the driving mechanisms A and B are both electric telescopic cylinders.

[0009] The method for using the above-mentioned device for checking the alignment of the dynamic and static wings of the aircraft tail comprises the following steps:

[0010] S1. Install the stationary wing onto the pulley main frame, with the root of the stationary wing facing the stationary wing flap, and position and tighten it using the zero-point locators of the stationary wing V-grooves at four locations;

[0011] S2. Push the pulley main frame along the slide rail to the vicinity of the mating mechanism; drive mechanism B drives the stationary wing flap to flip, so that the stationary wing flap is docked with the stationary wing root and locked;

[0012] S3. The V-groove zero point positioner of the static wing releases the static wing, and the static wing flap turns over to erect the static wing;

[0013] S4. Push the pulley main frame away from the matching mechanism, then install the moving wing onto the moving wing flip frame, and position and press it through the four moving wing V-groove zero point locators;

[0014] S5. Push the pulley main frame along the slide rail to the vicinity of the matching mechanism; drive mechanism A drives the moving wing flip frame to flip the moving wing upright;

[0015] S6. Near the mating mechanism, the erected moving and stationary wings are mated and connected through multiple sets of hinge joints;

[0016] S7. Release the moving wing from the V-groove zero point positioner of the moving wing and check the coordination between the moving wing and the stationary wing.

[0017] In the aforementioned method for using the dynamic and static wing alignment inspection device for the tail wing of an aircraft, in step S2, when the static wing flap is docked with the static wing root, the fine-tuning handwheel mechanism on the static wing V-groove zero point locator is used to fine-tune the static wing attitude to assist docking.

[0018] In the aforementioned method of using the dynamic and static wing alignment inspection device for the aircraft tail, in step S2, when the sensor signal light connected to the locking sensor lights up, it indicates that the static wing flap and the static wing root are completely locked together; only after confirming that the locking is completed, step S3 can be executed.

[0019] In the method for using the above-mentioned dynamic and static wing alignment inspection device for an aircraft tail wing, in step S6, when the dynamic and static wings are aligned, the fine-tuning hand wheel mechanism on the dynamic wing V-groove zero point locator is used to fine-tune the dynamic wing attitude to assist the alignment.

[0020] In the aforementioned method for using the dynamic and static wing alignment inspection device for an aircraft tail wing, in step S7, the coordination state of the dynamic wing and the static wing includes the gap, step difference, thrust, and the minimum gap between the dynamic and static wings within the deflection range of the dynamic wing.

[0021] The advantages of the present invention are as follows: according to the structural characteristics of the vertical tail and horizontal tail of tilt-rotor aircraft and fixed-wing aircraft, the present invention designs a universal and easy-to-operate dynamic and static wing alignment and inspection device and method, thereby improving the dynamic and static wing alignment and inspection efficiency and quality of tilt-rotor aircraft and fixed-wing aircraft.

[0022] The device of the present invention has a novel structure. The application of the V-groove zero-point locator allows the static wing and the moving wing to be quickly placed on the frame for positioning. The application of the fine-tuning handwheel mechanism can correct assembly errors and achieve accurate positioning of the static wing and the moving wing on the frame. The device has a high degree of automation. The integrated application of the drive mechanism, locking sensor and slide rail greatly reduces the operator's workload. Compared with the traditional manual alignment and inspection method, it can reduce the number of personnel by 70% and improve the efficiency by 300%.

[0023] The invention has strong versatility and can be used for the alignment and inspection of dynamic and static wings of various types of tilt-rotor aircraft and fixed-wing aircraft, greatly improving the consistency and stability of product alignment, and providing a feasible solution for model expansion and new model development. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the structure of the present invention;

[0025] Figure 2 yes Figure 1 A top view of

[0026] Figure 3 This is a schematic diagram of the positioning of the static wing on the rack;

[0027] Figure 4 This is a schematic diagram of the positioning of the moving wing mount. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0029] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.

[0030] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0031] Embodiment 1. The vertical tail of a certain type of aircraft is composed of two large parts: the static wing vertical stabilizer (i.e., the static wing) and the dynamic wing rudder (i.e., the dynamic wing). The vertical stabilizer adopts a main load-bearing structure layout of double beams + wing ribs, and its main structural member is the wing box. The leading edge, trailing edge, wing tip and other structural members are connected to the wing box and can be disassembled separately. The wing box is composed of a front beam, a rear beam, 12 ribs and left and right integral stiffened wall panels. It is made of carbon fiber composite materials. A certain number of holes are arranged on the beam to facilitate assembly and internal structure inspection. The leading edge, trailing edge, wing tip, etc. are sandwich structures. Seven hinge brackets are installed on the rear beam of the wing box to support the rudder, one of which is hinged. Joints also bear the vertical load of the rudder, and three control joints are connected to the rudder servo control system to control the movement of the rudder. The rudder structure consists of a front beam, two side panels and ribs. The 7 hinge joints on the front beam of the rudder connect the rudder to the vertical stabilizer, and the 3 control joints are connected to the servo control system on the vertical stabilizer to achieve rudder deflection control. According to engineering requirements, it is necessary to check the coordination status of the rudder and the vertical stabilizer, including the clearance, step difference, thrust, etc., as well as the minimum clearance between the rudder and the vertical stabilizer within the rudder deflection range.

[0032] The device and method used for the alignment and inspection of the vertical stabilizer and the rudder of the vertical tail of a certain type of aircraft refer to Figure 1-Figure 4 :

[0033] The dynamic and static wing alignment inspection device of the aircraft tail comprises a positioning mechanism 1, the positioning mechanism 1 comprises a slide rail 3, a pulley main frame 4 is slidably connected to the slide rail 3, and an alignment mechanism 2 is arranged at the end of the slide rail 3; a static wing V-groove zero point locator 6 for supporting and positioning the static wing of the aircraft tail is arranged on the pulley main frame 4; a dynamic wing flipping mechanism is also arranged on the pulley main frame 4, and the dynamic wing flipping frame 12 is provided with a dynamic wing V-groove zero point locator 7 for supporting and positioning the dynamic wing of the aircraft tail; a driving mechanism A5 is also arranged on the pulley main frame 4, and the dynamic wing flipping frame 12 can be flipped under the drive of the driving mechanism A5; the alignment mechanism 2 comprises a fixed frame 10 arranged at the end of the slide rail 3, a static wing flap 9 is rotatably connected to the fixed frame 10, and a driving mechanism B11 is also arranged on the fixed frame 10; the static wing flap 9 can be flipped under the drive of the driving mechanism B11.

[0034] The aforementioned stationary wing V-groove zero point positioner 6 is provided with a fine-tuning hand wheel mechanism 8 capable of driving the stationary wing to rise or fall.

[0035] The aforementioned moving wing V-groove zero point positioner 7 is provided with a fine-tuning hand wheel mechanism 8 capable of driving the moving wing to rise or fall.

[0036] The aforementioned stationary wing flap 9 is integrated with a locking sensor.

[0037] The aforementioned driving mechanisms A and B are both electric telescopic cylinders.

[0038] The method for using the above-mentioned device for checking the alignment of the dynamic and static wings of the aircraft tail comprises the following steps:

[0039] S1. The stationary wing is mounted on the pulley main frame 4, with the stationary wing root facing the stationary wing flap 9, and is positioned and pressed by the stationary wing V-groove zero point locator 6 at four locations;

[0040] S2. Push the pulley main frame 4 along the slide rail 3 to the vicinity of the matching mechanism 2; the drive mechanism B11 drives the stationary wing flap 9 to flip, so that the stationary wing flap 9 is docked with the stationary wing root and locked;

[0041] S3. The stationary wing V-groove zero point locator 6 releases the stationary wing, and the stationary wing flap 9 flips over to erect the stationary wing;

[0042] S4. Push the pulley main frame 4 away from the matching mechanism 2, and then install the moving wing to the moving wing flip frame 12, and position and tighten the moving wing through the four V-grooved zero point locators 7;

[0043] S5. Push the pulley main frame 4 along the slide rail 3 to the vicinity of the matching mechanism 2; the drive mechanism A5 drives the moving wing flip frame 12 to flip the moving wing upright;

[0044] S6. Near the matching mechanism 2, the erected moving and stationary wings are connected by multiple sets of hinge joints;

[0045] S7. The moving wing V-groove zero point positioner 7 releases the moving wing and checks the coordination status of the moving wing and the stationary wing.

[0046] In the aforementioned step S2, when the stationary wing flap 9 is docked with the stationary wing root, the fine-tuning hand wheel mechanism 8 on the stationary wing V-groove zero point locator 6 is used to fine-tune the stationary wing attitude to assist the docking.

[0047] In the aforementioned step S2, when the sensor signal light connected to the locking sensor lights up, it indicates that the docking and locking of the stationary wing flap 9 and the stationary wing root is completed; after confirming that the locking is completed, step S3 can be executed. Insert multiple sets of threaded locking pins and barrel nut locking pins, connect and fix the stationary wing joint with the stationary wing flap 9, observe the sensor signal light, and confirm that all pins are correctly installed in place. When a pin is not correctly installed, the sensor signal light will not light up, and no mechanism will be allowed to move.

[0048] In the aforementioned step S6, when the moving and stationary wings are aligned, the fine-tuning hand wheel mechanism 8 on the moving wing V-groove zero point positioner 7 is used to fine-tune the attitude of the moving wing to assist the alignment.

[0049] In the aforementioned step S7, the coordinated state of the moving wing and the stationary wing includes the gap, step difference, thrust, and the minimum gap between the moving wing and the stationary wing within the deflection range of the moving wing.

[0050] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed by the present invention, and these modifications or substitutions should all be covered within the protection scope of the present invention.

Claims

1. A device for checking the alignment of the dynamic and static wings of an aircraft tail, characterized in that: The invention comprises a positioning mechanism (1), wherein the positioning mechanism (1) comprises a slide rail (3), a pulley main frame (4) is slidably connected to the slide rail (3), and a matching mechanism (2) is arranged at the end of the slide rail (3); a stationary wing V-groove zero point positioner (6) for supporting and positioning the stationary wing of the tail wing of the aircraft is arranged on the pulley main frame (4); a moving wing flipping mechanism is also arranged on the pulley main frame (4), and the moving wing flipping mechanism comprises a moving wing flipping frame (12) rotatably connected to the pulley main frame (4), and a moving wing flipping frame (12) is arranged for supporting A V-groove zero point positioner (7) for supporting and positioning a dynamic wing of an aircraft tail wing; a driving mechanism A (5) is also provided on a pulley main frame (4); a dynamic wing flip frame (12) can flip under the drive of the driving mechanism A (5); the matching mechanism (2) comprises a fixed frame (10) provided at the end of a slide rail (3); a stationary wing flap (9) is rotatably connected to the fixed frame (10); a driving mechanism B (11) is also provided on the fixed frame (10); the stationary wing flap (9) can flip under the drive of the driving mechanism B (11).

2. The device for checking the alignment of the dynamic and static wings of an aircraft tail wing according to claim 1, characterized in that: The stationary wing V-groove zero point positioner (6) is provided with a fine-tuning hand wheel mechanism (8) capable of driving the stationary wing to rise or fall.

3. The device for checking the alignment of the dynamic and static wings of an aircraft tail wing according to claim 1, characterized in that: The moving wing V-groove zero point positioner (7) is provided with a fine-tuning hand wheel mechanism (8) capable of driving the moving wing to rise or fall.

4. The device for checking the alignment of the dynamic and static wings of an aircraft tail wing according to claim 1, characterized in that: A locking sensor is integrated on the stationary wing flap (9).

5. The device for checking the alignment of the dynamic and static wings of an aircraft tail wing according to claim 1, characterized in that: Driving mechanisms A and B are both electric telescopic cylinders.

6. A method for using the device for checking the alignment of the dynamic and static wings of an aircraft tail as claimed in any one of claims 1 to 5, characterized in that: The steps include: S1. The stationary wing is mounted on the pulley main frame (4), with the root of the stationary wing facing the stationary wing flap (9), and is positioned and pressed by the four stationary wing V-groove zero point locators (6); S2. Push the pulley main frame (4) along the slide rail (3) to the vicinity of the mating mechanism (2); the drive mechanism B (11) drives the stationary wing flap (9) to flip, so that the stationary wing flap (9) is docked with the stationary wing root and locked; S3. The stationary wing V-groove zero point locator (6) releases the stationary wing, and the stationary wing flap (9) flips the stationary wing upright; S4. Push the pulley main frame (4) away from the matching mechanism (2), and then install the moving wing to the moving wing flip frame (12), and position and press the moving wing through the four V-grooved zero point locators (7); S5. Push the pulley main frame (4) along the slide rail (3) to the vicinity of the matching mechanism (2); the drive mechanism A (5) drives the moving wing flip frame (12) to flip the moving wing upright; S6. Near the matching mechanism (2), the erected moving and stationary wings are connected by multiple sets of hinge joints; S7. Release the moving wing V-groove zero point positioner (7) and check the coordination between the moving wing and the stationary wing.

7. The method for using the device for checking the alignment of the dynamic and static wings of an aircraft tail wing according to claim 6, characterized in that: In step S2, when the stationary wing flap (9) is docked with the stationary wing root, the fine-tuning hand wheel mechanism (8) on the stationary wing V-groove zero point positioner (6) is used to fine-tune the stationary wing attitude to assist docking.

8. The method for using the device for checking the alignment of the dynamic and static wings of an aircraft tail wing according to claim 6, characterized in that: In step S2, when the sensor signal light connected to the locking sensor lights up, it indicates that the docking and locking of the stationary wing flap (9) and the stationary wing root are completed; only after confirming that the locking is completed, step S3 can be executed.

9. The method for using the device for checking the dynamic and static wing alignment of an aircraft tail wing according to claim 6, characterized in that: In step S6, when the moving and stationary wings are aligned, the fine-tuning hand wheel mechanism (8) on the moving wing V-groove zero point positioner (7) is used to fine-tune the attitude of the moving wing to assist the alignment.

10. The method for using the device for checking the alignment of the dynamic and static wings of an aircraft tail wing according to claim 6, characterized in that: In step S7, the coordination state of the moving wing and the stationary wing includes the gap, step difference, thrust, and the minimum gap between the moving wing and the stationary wing within the deflection range of the moving wing.

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