Airplane flap experiment detection bracket

Abstract

The utility model provides an airplane flap experiment detection bracket, and belongs to the technical field of airplane structure detection. The bracket is flexible in structure, high in adaptability, high in practicability and good in application effect. A fixed seat and a sliding seat are arranged on a base of the bracket, lifting shells are mounted on the fixed seat and the sliding seat in a lifting manner, connecting discs are rotatably mounted on the two lifting shells, a flap is detachably and fixedly mounted between the two connecting discs, the lifting shells perform lifting movement, the connecting discs rotate, and the position of the flap is adjusted for experimental detection. The bracket is provided with the fixed seat and the sliding seat in a combined manner, so that the bracket can adapt to experimental detection of flaps of various models, the universality and the adaptability are high, the height and the angle of the flaps supported by the bracket can be freely adjusted, multi-position angle experimental detection of the flaps can be met, the practicability is high, the bracket is provided with the covering curtain and the sleeve shell, and the practicability is high. The formation of turbulent flow of detection airflow is reduced, the application effect is good, and more accurate detection data is ensured.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft structure testing technology, and in particular relates to an aircraft flap test bracket. Background Technology

[0002] In aircraft design and testing, flap performance testing is a crucial step. Flaps are the movable rear section of the aircraft wing, primarily used to increase lift and improve takeoff and landing performance. Traditional flap testing methods mostly rely on simple, fixed support structures. Different flap models require different supports, resulting in limited support coverage. During testing, the relatively fixed structure of the support can lead to discrepancies between the experimental results and actual performance, reducing the significance of the testing. Therefore, a support structure capable of meeting various testing conditions is needed to support the flaps during testing. Utility Model Content

[0003] To address the problems existing in the background art, this utility model provides an aircraft flap test bracket. This bracket has a flexible structure, high adaptability, strong practicality, and good application effect.

[0004] The technical solution adopted by this utility model to solve its technical problem is as follows: an aircraft flap test bracket, including a base, a fixed base, a sliding base, two connecting plates, two lifting shells, two stepper motors, and multiple hydraulic rods. An installation groove is formed in the middle of the upper surface of the base along its length. The sliding base is slidably inserted into the installation groove. The fixed base is fixedly set on the upper surface of the base and is positioned close to one end of the installation groove along its length. Both the fixed base and the sliding base have mounting cavities, each with an open top. The two lifting shells are slidably inserted into the two mounting cavities, and a hydraulic rod is fixedly installed in each mounting cavity. The lifting shell is fixedly connected to the vertically upward-pointing telescopic end of the hydraulic rod. Stepper motors are fixedly installed in both lifting shells, and the drive ends of the two stepper motors protrude from the opposing sidewalls of the two lifting shells. The two connecting plates are fixedly installed on the drive ends of the two stepper motors. The flap to be tested is detachably and fixedly installed between the two connecting plates.

[0005] A lead screw and a guide rod are installed in parallel in the mounting groove. Two transmission holes are opened on the sliding seat to match the positions of the lead screw and the guide rod. The lead screw and the guide rod are respectively installed in the two transmission holes. A drive motor is embedded in the base. The drive motor is connected to the lead screw and the guide rod. The operation of the drive motor causes the lead screw to rotate and drives the sliding seat to slide along the mounting groove. The guide rod limits and guides the sliding seat.

[0006] The aircraft flap test bracket also includes two cover curtains, both of which are embedded in the base. The two cover curtains are located at both ends of the length direction of the mounting groove. The two groove walls along the length direction of the mounting groove are provided with through grooves. The pull-out ends of the two cover curtains pass through the two through grooves and are detachably and fixedly connected to the base of the sliding seat. The two cover curtains are respectively installed on the groove openings of the mounting grooves on the front and rear sides of the sliding seat along the moving direction.

[0007] The aircraft flap test bracket also includes two housings, which are respectively fitted onto two lifting housings. The housings are located between the lifting housings and the cavity walls of the mounting cavity. Guide strips are protruding from the two opposite cavity walls of the mounting cavity and arranged vertically. Two guide grooves are formed on the outer wall of the housing to match the two guide strips. Guide strips are protruding from the two opposite inner walls of the housing and arranged longitudinally. Two guide grooves are formed on the lifting housing to match the guide strips on the housing. Multiple guide grooves are correspondingly engaged with multiple guide strips.

[0008] A boss protrudes from the lower end of the outer wall of the lifting shell, and a second boss protrudes from the inner wall of the housing corresponding to the first boss. The first boss and the second boss are intermittently connected. A third boss protrudes from the lower end of the outer wall of the housing, and a fourth boss protrudes from the upper end of the cavity wall of the placement cavity in conjunction with the third boss. The third boss and the fourth boss are intermittently connected.

[0009] An avoidance groove is provided on the upper edge of the side wall corresponding to the connecting plate of the casing, and an avoidance groove is also provided on the cavity wall of the mounting cavity at the corresponding position of the connecting plate.

[0010] The beneficial effects of this utility model are as follows: The bracket is equipped with a sliding seat that can be freely adjusted in position, combined with a fixed seat that can be fixed in position, allowing the bracket to be adapted to the experimental testing of various types of flaps, with strong versatility and high adaptability; the lifting shell of the bracket can be freely raised and lowered, while the connecting plate can be rotated at a custom angle, which can meet the multi-angle experimental testing of flaps, making it highly practical; the bracket is equipped with a covering curtain on the mounting groove, and a sleeve is also provided, which reduces the formation of turbulence in the test airflow, resulting in good application effect and ensuring more accurate test data. Attached Figure Description

[0011] In the attached diagram:

[0012] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0013] Figure 2 This is a schematic diagram of the installation structure of the lifting shell of this utility model;

[0014] Figure 3 yes Figure 2 Enlarged view of part A in the middle;

[0015] In the diagram: 1. Base; 2. Fixed base; 3. Sliding base; 4. Connecting plate; 5. Covering curtain; 6. Lifting shell; 7. Stepper motor; 8. Housing; 9. Hydraulic rod; 11. Mounting groove; 12. Lead screw; 13. Guide bar; 14. Insertion groove; 21. Clearance groove; 31. Installation cavity; 32. Guide bar; 61. Guide groove. Detailed Implementation

[0016] The present invention will now be described in further detail with reference to the accompanying drawings. The drawings are simplified schematic diagrams, illustrating only the basic structure of the present invention, and therefore only show the components relevant to the present invention.

[0017] An aircraft flap testing bracket includes a base 1, a fixed base 2, a sliding base 3, two connecting discs 4, two lifting shells 6, two stepper motors 7, and multiple hydraulic rods 9. A mounting groove 11 is formed along the length of the upper surface of the base 1. The sliding base 3 is slidably inserted into the mounting groove 11. The fixed base 2 is fixedly disposed on the upper surface of the base 1 and is positioned close to one end of the mounting groove 11 along its length. Both the fixed base 2 and the sliding base 3 have a mounting cavity 31, each cavity 31 having an open top. The two lifting shells 6 are slidably inserted into the two mounting cavities 31 respectively. Hydraulic rods 9 are fixedly installed in each of the mounting cavities 31. The lifting shell 6 is fixedly connected to the end of the vertically upward telescopic end of the hydraulic rod 9. When the hydraulic rod 9 extends or shortens, it drives the lifting shell 6 to rise or fall vertically. Stepper motors 7 are fixedly installed in both of the lifting shells 6. The drive ends of the two stepper motors 7 protrude from the opposite side walls of the two lifting shells 6. Two connecting plates 4 are fixedly installed on the drive ends of the two stepper motors 7 respectively. When the two stepper motors 7 operate, they drive the two connecting plates 4 to rotate. The flap to be tested is detachably and fixedly installed between the two connecting plates 4.

[0018] The lead screw 12 and the guide rod 13 are installed in parallel in the mounting groove 11. Two transmission holes are opened on the sliding seat 3 to match the positions of the lead screw 12 and the guide rod 13. The lead screw 12 and the guide rod 13 are respectively installed in the two transmission holes. The base 1 is embedded with a drive motor. The drive motor is driven by the lead screw 12 and the guide rod 13. The operation of the drive motor causes the lead screw 12 to rotate and drives the sliding seat 3 to slide along the mounting groove 11. The guide rod 13 limits and guides the sliding seat 3. The drive connection between the lead screw 12 and the guide rod 13 and the drive motor is a technical means known to those skilled in the art at present. At the same time, the transmission connection between the lead screw 12 and the guide rod 13 and the sliding seat 3 is also a technical means known to those skilled in the art at present.

[0019] The aircraft flap test bracket also includes two cover curtains 5, both of which are embedded in the base 1. The two cover curtains 5 are located at both ends of the mounting groove 11 along its length. The two groove walls along the length of the mounting groove 11 are provided with mounting slots 14. The pull-out ends of the two cover curtains 5 pass through the two mounting slots 14 and are detachably and fixedly connected to the base of the sliding seat 3. The two cover curtains 5 are respectively installed on the slot openings of the mounting groove 11 on the front and rear sides of the sliding seat 3 along the moving direction, so that the upper surface of the base 1 remains relatively flat and avoids the flap from causing turbulence to the test airflow during the test.

[0020] The covering curtain 5 is arranged in the base 1 in a wound form. A coil spring is provided at the core of the winding of the covering curtain 5. When the sliding seat 3 is adjusted, the covering curtain 5, whose coverage area is reduced, will be rolled into the base 1 under the restoring action of the coil spring.

[0021] The aircraft flap test bracket also includes two housings 8, which are respectively fitted onto two lifting housings 6. The housings 8 are located between the lifting housings 6 and the cavity walls of the mounting cavity 31. Guide strips 32 are protruding vertically arranged on the two opposite cavity walls of the mounting cavity 31. Two guide grooves 61 are formed on the outer wall of the housing 8 to cooperate with the two guide strips 32. Guide strips 32 are protruding longitudinally arranged on the two opposite inner walls of the housing 8. Two guide grooves 61 are formed on the lifting housing 6 to cooperate with the guide strips 32 on the housing 8. Multiple guide grooves 61 are correspondingly engaged with multiple guide strips 32. The hydraulic rod 9 extends and pushes the lifting housing 6 to raise it. The guide grooves 61 and guide strips 32 cooperate with each other to achieve guidance and reduce the probability of the lifting housing 6 shaking.

[0022] A protrusion is provided at the lower end of the outer wall of the lifting shell 6. A protrusion is provided on the inner wall of the sleeve 8 corresponding to the position of the first protrusion. The first protrusion and the second protrusion are intermittently connected. A third protrusion is provided at the lower end of the outer wall of the sleeve 8. A fourth protrusion is provided at the upper end of the cavity wall of the placement cavity 31 in conjunction with the third protrusion. The third protrusion and the fourth protrusion are intermittently connected.

[0023] When the hydraulic rod 9 extends, and the extended length causes the lifting shell 6 to completely detach from the mounting cavity 31 in the longitudinal direction, the first boss engages with the second boss. At this time, the sleeve 8 is pulled out of the mounting cavity 31 by the lifting shell 6 and blocked in the gap between the lifting shell 6 and the fixed seat 2 or the sliding seat 3, so that the surface of the device adjacent to the flap remains relatively flat and the formation of turbulence is reduced. When the hydraulic rod 9 extends to a certain height, the third boss engages with the fourth boss. At this time, the hydraulic rod 9 will not be able to extend further, thus preventing the sleeve 8 from being pulled out of the mounting cavity 31.

[0024] A clearance groove 21 is provided on the upper edge of the side wall corresponding to the connecting plate 4 of the sleeve 8. A clearance groove 21 is also provided on the cavity wall of the mounting cavity 31 at the corresponding position of the connecting plate 4. The clearance groove 21 is used to avoid the journal of the stepper motor 7 connected to the connecting plate 4. When the lifting shell 6 and the sleeve 8 are both inserted into the mounting cavity 31, the journal is embedded in the clearance groove 21.

[0025] Working principle: Start the drive motor to rotate the lead screw 12, causing the sliding seat 3 to move in the mounting slot 11. Adjust the distance between the sliding seat 3 and the fixed seat 2 according to the size of the flap to be tested. Detachably and fix both ends of the flap to the two connecting plates 4. The flap is then installed and can be put into the test.

[0026] During the testing process, if it is necessary to raise the position of the flap, the hydraulic rod 9 can be adjusted to extend and raise the lifting shell 6 appropriately. When it is necessary to adjust the angle of the flap, the stepper motor 7 can be adjusted to rotate the connecting plate 4 at an appropriate angle.

[0027] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. An aircraft flap experimental test carriage characterised in that: Including base (1), fixed seat (2), sliding seat (3), two connecting discs (4), two lifting shells (6), two step motors (7), and multiple hydraulic rods (9), the upper surface of the base (1) is provided with an installation slot (11) in the middle along the length direction, the sliding seat (3) is slidingly inserted into the installation slot (11), the fixed seat (2) is fixedly arranged on the upper surface of the base (1) and arranged close to one end of the installation slot (11) along the length direction, the fixed seat (2) and the sliding seat (3) are both provided with a placement cavity (31), the top of each placement cavity (31) is open, two lifting shells (6) are slidingly inserted into two placement cavities (31) respectively, a hydraulic rod (9) is fixedly installed in each placement cavity (31), the lifting shell (6) is fixedly connected to the end of the vertically upward extending end of the hydraulic rod (9), a step motor (7) is fixedly installed in each of the two lifting shells (6), the driving ends of the two step motors (7) are inserted out of the opposite side walls of the two lifting shells (6), two connecting discs (4) are fixedly installed on the driving ends of the two step motors (7), and a detachable wing flap to be detected is fixedly installed between the two connecting discs (4).

2. An experimental test cradle for an aircraft flap as claimed in claim 1, characterised in that: The installation slot (11) is provided with a lead screw (12) and a light screw (13) arranged in parallel, the sliding seat (3) is provided with two transmission holes at positions matched with the lead screw (12) and the light screw (13), the lead screw (12) and the light screw (13) are respectively inserted into the two transmission holes, a driving motor is embedded in the base (1), the driving motor is drivingly connected with the lead screw (12) and the light screw (13), and the driving motor is operated to rotate the lead screw (12) and drive the sliding seat (3) to slide along the installation slot (11), and the light screw (13) guides and limits the sliding seat (3).

3. An experimental test cradle for an aircraft flap as claimed in claim 1 or 2, characterised in that: The aircraft wing flap experimental detection bracket further comprises two covering curtains (5), the two covering curtains (5) are embedded in the base (1), the two covering curtains (5) are located at the two ends of the installation slot (11) along the length direction, the two slot walls of the installation slot (11) along the length direction are provided with a through slot (14), the pulling ends of the two covering curtains (5) are respectively inserted out of the two through slots (14) and detachably fixedly connected to the seat body of the sliding seat (3), and the two covering curtains (5) are respectively covered on the slot openings of the installation slot (11) on the front and rear sides of the sliding seat (3) along the moving direction.

4. An experimental test cradle for an aircraft flap as claimed in claim 3, characterised in that: The aircraft flap experimental detection bracket further comprises two sleeves (8), the two sleeves (8) are sleeved on the two lifting shells (6) respectively, the sleeve (8) is located between the lifting shell (6) and the cavity wall of the installation cavity (31), the two opposite cavity walls of the installation cavity (31) are provided with guide strips (32) arranged in the vertical direction, the outer wall of the sleeve (8) is provided with two guide grooves (61) matched with the two guide strips (32), the two opposite inner walls of the sleeve (8) are provided with guide strips (32) arranged in the longitudinal direction, the lifting shell (6) is provided with two guide grooves (61) matched with the guide strips (32) on the sleeve (8), and the plurality of guide grooves (61) are correspondingly buckled on the plurality of guide strips (32).

5. An experimental test cradle for an aircraft flap as defined in claim 4, characterized in that: The lower end of the outer wall of the lifting shell (6) is provided with a boss, the inner wall of the sleeve (8) is provided with a boss two at a position corresponding to the boss one, the boss one and the boss two are intermittently hung, the lower end of the outer wall of the sleeve (8) is provided with a boss three, the cavity wall of the installation cavity (31) is provided with a boss four matched with the boss three at the upper end, and the boss three and the boss four are intermittently hung.

6. An experimental test cradle for an aircraft flap as defined in claim 5, characterized in that: The side wall of the sleeve (8) corresponding to the connecting disc (4) is provided with an avoiding groove (21) at the position, and the cavity wall of the installation cavity (31) is also provided with an avoiding groove (21) at the corresponding position matched with the connecting disc (4).

Images