Airplane control surface angle measuring device

Abstract

The utility model relates to an aircraft control surface angle measuring device, which comprises a fixed platform, the cross section of the fixed platform is L-shaped, the vertical part of the fixed platform is provided with an extension part, and the bottom of the fixed platform is provided with a goniometer; the tail end of the horizontal part of the fixed platform is provided with a locking assembly which is matched with the extending part to fix the fixed platform on an aircraft platform, and the vertical part of the fixed platform is provided with an adjusting assembly which is attached to an aircraft control surface; the two adjusting assemblies are arranged in parallel in the width direction of the fixed platform, and each adjusting assembly comprises a maintaining part attached to the control surface of the aircraft to prevent the control surface from sliding laterally and a moving mechanism hinged to the maintaining part and driving the maintaining part to move in the horizontal direction. The length and the angle can be adjusted according to the change of sweepback angles of different control surfaces to be attached to the airfoil to ensure that the goniometer is perpendicular to the airfoil, meanwhile, the goniometer has good fastening performance and is not prone to deflection and looseness along with the control surfaces, and the measurement precision is improved.

Description

Technical Field

[0001] This utility model relates to the field of aviation repair equipment, specifically an aircraft control surface angle measuring device. Background Technology

[0002] The deflection angle of aircraft control surfaces in response to control commands is a crucial indicator for verifying the handling performance of its flight control system, and measuring the deflection angle is an important part of aircraft ground maintenance and debugging. Taking a conventional aerodynamic layout aircraft as an example, a single aircraft involves four types of control surfaces (eight in total) requiring deflection angle measurement: two leading-edge flaps, two ailerons, two horizontal stabilizers, and two rudders. Modern aircraft designs, to adapt to high-altitude, high-speed flight and reduce aerodynamic drag to improve high-speed performance, often employ sweep angle designs for wings, tails, and vertical stabilizers. This creates an angle between the line connecting the mean aerodynamic chord of the wing and the fuselage centerline, and the sweep angle is different for each type of control surface.

[0003] Existing control surface angle gauge clamps are not designed to accommodate wing sweep angles and rely solely on locking devices for clamping. These clamps are highly susceptible to loosening due to vibrations caused by control surface deflection, and cannot guarantee the angle gauge's perpendicularity to the control surface axis, introducing mechanical errors into the measurement results. Loosening of the control surface measurement device during ground pressurization testing could damage the aircraft or even cause personnel injury, posing a significant risk. Therefore, a new aircraft control surface angle measurement device needs to be designed. Summary of the Invention

[0004] In order to solve the above-mentioned technical problems, this utility model proposes an aircraft control surface angle measuring device.

[0005] The technical problem to be solved by this utility model is achieved by the following technical solution:

[0006] An aircraft control surface angle measuring device includes a fixed platform with an L-shaped cross-section, an extension on the vertical portion of the fixed platform, and an angle measuring instrument at the bottom of the fixed platform.

[0007] The horizontal portion of the fixed platform is provided with a locking component that cooperates with the extension to fix the fixed platform to the aircraft platform, and the vertical portion of the fixed platform is provided with an adjustment component that fits with the aircraft control surface.

[0008] Two sets of adjustment components are arranged parallel to each other along the width of the fixed platform. Each adjustment component includes a retaining part that fits against the aircraft control surface to prevent sideslip of the control surface and a moving mechanism that is hinged to the retaining part and drives the retaining part to move in the horizontal direction.

[0009] The beneficial effects of this utility model are:

[0010] 1. This utility model can adjust the length and angle to fit the wing surface according to the different sweep angles of the control surfaces to ensure that the angle measuring instrument is perpendicular to the wing surface. At the same time, it has good fastening and is not easy to loosen with the deflection of the control surfaces, thus increasing the measurement accuracy.

[0011] 2. By adjusting the bolts, the second adjusting screw, and the first adjusting screw, the retaining part can be adjusted to change its angle arbitrarily according to the sweep angle of the rudder surface, so as to adapt to different rudder surface thicknesses and angle changes, and to adapt to various types of rudder surfaces.

[0012] 3. The angle measuring instrument can be selected as mechanical or electronic according to the actual use situation to meet the measurement accuracy requirements under different conditions. Attached Figure Description

[0013] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0014] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0015] Figure 2 This is a three-dimensional structural diagram of the locking component of this utility model;

[0016] Figure 3 This is a three-dimensional structural diagram of the adjustment component of this utility model;

[0017] Figure 4 This is an exploded view of the present invention.

[0018] The figure shows: 1. Fixed platform; 2. Extension; 3. Locking assembly; 4. Adjustment assembly; 5. Angle measuring instrument; 6. Protrusion; 7. Hinge shaft; 31. Adjustment screw No. 1; 32. Pressing platform; 41. Holding part; 42. Moving mechanism; 43. Adjustment screw No. 2; 44. Adjustment bolt. Detailed Implementation

[0019] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be described more clearly and completely below with reference to the accompanying drawings in the embodiments. Of course, the described embodiments are only a part of the present utility model and not all of them. Based on this embodiment, other embodiments obtained by those skilled in the art without creative effort are all within the protection scope of this utility model.

[0020] like Figures 1 to 4 As shown, an aircraft control surface angle measuring device includes a fixed platform 1 with an L-shaped cross-section. An extension 2 is provided on the vertical part of the fixed platform 1, and an angle measuring instrument 5 is provided at the bottom of the fixed platform 1. The angle measuring instrument 5 can be either mechanical or electronic, and can be selected according to the actual use. The corners of the fixed platform 1 are designed with rounded corners to avoid other aircraft components.

[0021] The horizontal portion of the fixed platform 1 is provided with a locking component 3 that cooperates with the extension 2 to fix the fixed platform 1 to the aircraft platform, and the vertical portion of the fixed platform 1 is provided with an adjustment component 4 that fits with the aircraft control surface.

[0022] Two sets of adjustment components 4 are arranged parallel to each other along the width direction of the fixed platform 1. Each adjustment component 4 includes a retaining part 41 that fits against the aircraft control surface to prevent sideslip of the control surface, and a moving mechanism 42 that is hinged to the retaining part 41 and drives the retaining part 41 to move in the horizontal direction; Figure 1 As shown, the two moving mechanisms 42 are symmetrically installed along the axis of symmetry of the fixed platform 1 perpendicular to the horizontal direction, and the axis of the locking component 3 intersects perpendicularly with the axis of symmetry of the fixed platform 1 perpendicular to the horizontal direction.

[0023] The locking assembly 3 includes a first adjusting screw 31 that is threadedly engaged with the fixed platform 1, and the end of the first adjusting screw 31 is hinged to a pressing platform 32 that engages with the aircraft fuselage.

[0024] The extension 2 is provided with a protrusion 6 that cooperates with the clamping platform 32; the clamping platform 32 is located directly above the protrusion 6, and the clamping platform 32 is hinged to the end of the first adjusting screw 31. It can fit against the control surface and the wing surface with angle changes. Both the clamping platform 32 and the protrusion 6 that are in contact with the control surface are covered with anti-slip rubber to increase friction, improve the fastening effect, and prevent scratches on the control surface.

[0025] Both the pressing platform 32 and the protrusion 6 are provided with anti-slip rubber.

[0026] The moving mechanism 42 is threadedly engaged with the fixed platform 1 via a second adjusting screw 43. The second adjusting screw 43 is fitted with two adjusting bolts 44 distributed along its axial direction. The position of the holding part 41 is adjusted via the second adjusting screw 43. Simultaneously, the holding part 41 is hinged to the end of the second adjusting screw 43, allowing it to adapt to changes in the rudder surface angle, preventing the measuring device from loosening or deflecting relative to the rudder surface during measurement, thus preventing the measuring axis from becoming non-parallel. The position of the second adjusting screw 43 is achieved by rotating the adjusting bolts 44. Both the holding part 41 and the clamping platform 32 have large adjustment margins for screw adjustment to accommodate different rudder surface thicknesses and angles. Both the holding part 41 and the clamping platform 32 are fitted with hinge shafts 7.

[0027] Both the retaining part 41 and the clamping platform 32 are hinged and fixed, and can be replaced according to the airfoil of the control surface to achieve a better fastening and fitting effect.

[0028] The adjusting bolts 44 are distributed on both sides of the vertical part of the fixed platform 1.

[0029] The contact surface between the retaining part 41 and the rudder surface is arc-shaped and covered with soft rubber. The arc-shaped transition allows for better contact with the rudder surface, and the soft rubber prevents the retaining part 41 from scratching the rudder surface.

[0030] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. An aircraft control surface angle measuring device, characterized by: The utility model relates to a kind of aircraft platform test device, including fixed platform (1), the fixed platform (1) section is L type, the vertical portion of the fixed platform (1) is equipped with extension (2), the fixed platform (1) bottom is equipped with goniometer (5); The horizontal portion end of the fixed platform (1) is equipped with locking assembly (3) with extension (2) cooperation to fix the fixed platform (1) on aircraft platform, the vertical portion of the fixed platform (1) is equipped with adjusting assembly (4) with aircraft control surface fit; The adjusting assembly (4) is provided with two groups along the width direction of fixed platform (1) parallel, the adjusting assembly (4) includes retaining portion (41) with aircraft control surface fit to prevent the side slip of control surface and moving mechanism (42) with retaining portion (41) hinged connection and drive retaining portion (41) move along horizontal direction.

2. An aircraft control surface angle measuring device as claimed in claim 1, characterised in that: The locking assembly (3) includes No. 1 adjusting screw rod (31) with fixed platform (1) screw cooperation, the end of the No. 1 adjusting screw rod (31) is hingedly connected with the pressing platform (32) matched with aircraft fuselage.

3. An aircraft control surface angle measuring device as claimed in claim 2, characterised in that: The extension (2) is equipped with convex portion (6) matched with pressing platform (32).

4. An aircraft control surface angle measuring device as claimed in claim 3, characterised in that: The pressing platform (32) and convex portion (6) are all equipped with antiskid rubber.

5. An aircraft control surface angle measuring device as claimed in claim 1, characterised in that: The moving mechanism (42) is equipped with No. 2 adjusting screw rod (43) with fixed platform (1) screw cooperation, the No. 2 adjusting screw rod (43) is matched with two adjusting bolts (44) distributed along axis direction.

6. An aircraft control surface angle measuring device as claimed in claim 5, characterised in that: The adjusting bolt (44) is distributed at the vertical portion both sides of fixed platform (1).

7. An aircraft control surface angle measuring device as claimed in claim 2, characterised in that: The retaining portion (41) and control surface contact surface are arc transition and fit with soft rubber.

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