Aircraft aerodynamic profile detection device

Abstract

The application discloses an aircraft aerodynamic profile detection device for detecting positive and negative deviations of an aerodynamic profile, comprising a base, a support frame, a clamping structure and test templates, wherein the support frame and the clamping structure are arranged above the base and are position-adjustable, the support frame is at least two, and is used for supporting an aircraft or a part to be detected, the clamping structure is arranged in pairs and oppositely, and is used for clamping the test templates, the test templates are arranged in pairs and are respectively fixed on the clamping structure, the test templates are provided with openings matched with the aerodynamic profile of a position to be detected, and a measurement buffer strip is arranged on the inner periphery of the opening. The aircraft aerodynamic profile detection device has a reasonable structure, can be adjusted according to the aircraft or the part to be detected, is suitable for detection of different structures and different positions, and can also realize batch detection of the same specification and model to be detected.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aircraft detection and research, and particularly provides an aircraft aerodynamic profile detection device. BACKGROUND

[0002] An aircraft is an aircraft that flies in the atmosphere and balances its own weight by lift generated by air, and uses various aerodynamic forces to control its flight, so whether the aircraft aerodynamic profile meets the original design requirements has a crucial influence on the flight performance and flight safety of the aircraft. Among them, the aircraft aerodynamic profile mainly includes wing aerodynamic profile and fuselage aerodynamic profile.

[0003] The existing method for detecting whether the aircraft aerodynamic profile meets the original design requirements mainly includes two kinds: one is to use a laser scanning method, to compare the point cloud model collected with the design model to determine whether the actual aircraft aerodynamic profile meets the original design requirements. The disadvantage of this method is that the surface of the detected aircraft aerodynamic profile needs to be sprayed with a developing agent and a coordinate marker point is attached, which is troublesome to clean up later, and the laser scanning equipment is expensive. Another method is to use a forming mold as a detection mold, to restore the produced aircraft aerodynamic profile part to the forming mold, and to measure the difference between the aircraft aerodynamic profile and the forming mold using the forming mold as a standard. The main disadvantage of this method is that it only detects individual parts, ignoring the change difference of the aerodynamic profile after the individual parts are assembled into an aerodynamic profile as a whole.

[0004] Therefore, it is urgent to provide a new aircraft aerodynamic profile detection device that can adapt to different structures to be detected and can realize batch detection of the same type of structure to be detected. SUMMARY

[0005] In view of this, the purpose of the present application is to provide an aircraft aerodynamic profile detection device to solve the problems existing in the existing detection method.

[0006] The technical scheme provided by the present application is: an aircraft aerodynamic profile detection device for detecting the positive and negative deviations of the aerodynamic profile, comprising: a base, a support frame, a clamping structure and a detection template, wherein the support frame and the clamping structure are both arranged above the base and are position-adjustable, the support frame is at least two, used for supporting the aircraft or parts to be detected, the clamping structure is arranged in pairs and oppositely, used for clamping the detection template, the detection template is arranged in pairs and fixed on the clamping structure respectively, the detection template is provided with an opening matched with the aerodynamic profile of the position to be detected, and a measurement buffer strip is arranged on the inner wall of the opening.

[0007] Preferably, the base is a profile frame structure, each surface of the profile is provided with a notch, and the support frame and the clamping structure are bolted to the base through nut blocks embedded in the notches.

[0008] Further preferably, the support frame comprises a first worm screw lifting structure and a support frame body, the first worm screw lifting structure is installed on the base, and the support frame body is installed on the top end of the screw rod in the first worm screw lifting structure.

[0009] Further preferably, the upper end surface of the support frame body is provided with a protective strip.

[0010] Further preferably, the first worm screw lifting structure is connected to the base through a first boat-shaped seat.

[0011] Further preferably, the clamping structure comprises a longitudinal beam, a second worm screw lifting structure, and a clamping head, wherein the longitudinal beam is installed on the base, the second worm screw lifting structure is installed transversely on the longitudinal beam, and the clamping head is fixed to the free end of the screw rod in the second worm screw lifting structure for clamping the test sample plate.

[0012] Further preferably, the longitudinal beam is a profile structure, each surface is provided with a notch, and the longitudinal beam is connected to the base through a connecting corner piece.

[0013] Further preferably, the second worm screw lifting structure is fixedly connected to the longitudinal beam through a second boat-shaped seat.

[0014] Further preferably, the test sample plate is fitted and installed on the clamping head and is pressed by bolts.

[0015] Further preferably, the base is multiple and can be connected through connecting pins to form a stable large frame.

[0016] The aircraft aerodynamic profile detection device provided by the application has a reasonable structure, can be adjusted according to the aircraft or parts to be detected, is suitable for detection of different structures and different positions, and can also realize batch detection of the same specification and model of structures to be detected. BRIEF DESCRIPTION OF DRAWINGS

[0017] The application will be further described in detail below in combination with the drawings and embodiments:

[0018] Figure 1 The structure schematic view of the aircraft aerodynamic profile detection device provided by the application is shown in the figure;

[0019] Figure 2 The structure schematic view of the base is shown in the figure;

[0020] Figure 3 The connection diagram of the support frame and the base is shown in the figure;

[0021] Figure 4 Figure 1 is a connection diagram of the first worm screw lifting structure and the support frame body;

[0022] Figure 5 Figure 2 is a connection diagram of the clamping structure and the base;

[0023] Figure 6 Figure 3 is a perspective view of the clamping structure;

[0024] Figure 7 Figure 4 is a connection diagram of the inspection sample plate and the clamping structure;

[0025] Figure 8 Figure 5 is a use state diagram of the aircraft aerodynamic profile detection device provided by the present application;

[0026] Figure 9 Figure 6 is another use state diagram of the aircraft aerodynamic profile detection device provided by the present application;

[0027] Figure 10 Figure 7 is a connection diagram of the connecting pin and the base;

[0028] Figure 11 Figure 8 is an installation diagram of the second worm screw lifting structure auxiliary installation frame. DETAILED DESCRIPTION

[0029] The present application will be further explained in conjunction with specific embodiments, but is not limited to the present application.

[0030] In order to solve the problems of the complex detection process, the detection can only be carried out for individuals, and the change difference after the individual aerodynamic profiles are assembled into an aerodynamic profile whole is ignored in the prior art aircraft aerodynamic profile detection device, the present application provides an aircraft aerodynamic profile detection device for detecting the positive and negative deviations of the aerodynamic profile, as shown in Figures 1 to 11 The present application provides an aircraft aerodynamic profile detection device for detecting the positive and negative deviations of the aerodynamic profile, which comprises a base 1, a support frame 2, a clamping structure 3 and an inspection sample plate 4, wherein the support frame 2 and the clamping structure 3 are arranged above the base 1 and are position-adjustable, the support frame 2 is at least two and is used for supporting the aircraft or parts to be detected, the clamping structure 3 is arranged in pairs and oppositely, and is used for clamping the inspection sample plate 4, the inspection sample plate 4 is arranged in pairs and is fixed on the clamping structure 3 respectively, the inspection sample plate 4 is provided with an opening 41 matched with the aerodynamic profile of the position to be detected, and a measurement buffer strip 411 is arranged on the inner periphery of the opening, the measurement buffer strip is preferably made of polyurethane memory cotton material, and the thickness of the measurement buffer strip after being made is known.

[0031] The detection process of the aircraft aerodynamic profile detection device is as follows: when the positive and negative deviation of the aerodynamic profile of the structure (aircraft or part) to be detected needs to be detected, first, the positions of the support frame, the clamping structure and the test template are adjusted according to the size of the structure to be detected; the height of the structure to be detected is adjusted by the support frame; during the adjustment process, the adjustment can be completed by cooperating the projection instrument with the range ruler; after the position of the support frame is adjusted, it is fixed, and the structure to be detected is stably placed on the support frame; then, the positions of the clamping structure and the test template are adjusted, so that the test template is arranged on the two sides of the detected position of the structure to be detected and is in contact with the detected position; then, the positive and negative deviation of the aircraft aerodynamic profile can be judged according to the state of the measurement buffer strip on the test template; specifically: when the structure to be detected has a positive deviation at the detected position, the measurement buffer strip is in a compressed state, and the thickness reduction of the measurement buffer strip can be measured to obtain the deviation value of the structure to be detected at the detected position; when the structure to be detected has a negative deviation at the detected position, a gap will appear between the measurement buffer strip and the structure to be detected at the detected position, and the deviation value of the structure to be detected at the detected position can be measured by using the plug gauge; when the opening of the test template on the two sides of the detected position of the structure to be detected is completely in contact with the test template, the measurement buffer strip is neither compressed nor has a gap with the structure to be detected, which proves that the aerodynamic profile of the detected region of the structure to be detected completely conforms to the drawing.

[0032] As an improvement of the technical scheme, as shown in Figure 2 The base 1 is a profile frame structure, each surface of the profile is provided with a notched 11, the support frame 2 and the clamping structure 3 are bolted to the base 1 through the nut block embedded in the notched 11, when the position of the support frame or the clamping structure needs to be adjusted, the bolt can be loosened from the top of the base to adjust, preferably, the bottom of the base is also provided with a roller 12 to facilitate the movement of the device, further preferably, the roller is installed at the inner corner position of the base to prevent interference with the outside during the subsequent module assembly process.

[0033] As an improvement of the technical scheme, as shown in Figure 3 , Figure 4 The support frame 2 includes a first worm gear screw lifting structure 21 and a support frame body 22, the first worm gear screw lifting structure 21 is installed on the base 1, and the support frame body 22 is installed at the top end of the screw rod in the first worm gear screw lifting structure 21, the first worm gear screw lifting structure is a existing structure, preferably a hand-operated worm gear screw lifter, preferably, as shown in Figure 3As shown, the first worm screw lifting structure 21 is connected with the base 1 through a first boat-shaped seat 61, and the first boat-shaped seat is connected with the base through bolts. Loosening the bolts can adjust the position of the support frame on the base. Preferably, the first boat-shaped seat 61 and the base 1 are provided with scales correspondingly, which are used for positioning the structure to be detected. Further preferably, the 0 scale on the first boat-shaped seat corresponds to the axis projection of the lead screw in the first worm screw lifting structure.

[0034] As an improvement of the technical scheme, as shown in Figure 4 As shown, the upper end surface of the support frame body 22 is provided with a protective strip 221, which can prevent the structure to be detected from being damaged due to hard contact with the support frame. The protective strip can be made of polyurethane memory cotton material. Further preferably, the bottom of the support frame body is provided with a square hole, and the top end of the lead screw in the first worm screw lifting structure 21 is connected with a square plug 211. The two can be matched to realize quick and convenient connection. The shape of the support frame body is made according to the profile of the preset support position of the structure to be detected. The number of support frames can be increased as needed on the premise of avoiding detection points to realize multi-point support and prevent the structure to be detected from being deformed due to its own gravity.

[0035] As an improvement of the technical scheme, as shown in Figure 5 、 Figure 6 As shown, the clamping structure 3 includes a longitudinal beam 31, a second worm screw lifting structure 32, and a clamping head 33. The longitudinal beam 31 is installed on the base 1. The second worm screw lifting structure 32 is installed transversely on the longitudinal beam 31. The clamping head 33 is fixed to the free end of the lead screw in the second worm screw lifting structure 32, which is used for clamping the test sample plate 4. Preferably, the longitudinal beam 31 is a profile structure, each surface of which is provided with a notch. The longitudinal beam 31 is connected with the base 1 through a connecting corner piece 5. The connecting corner piece 5 and the base 1 are provided with scales correspondingly, so as to facilitate the adjustment of the position of the clamping structure. Preferably, the 0 scale of the connecting corner piece corresponds to the axis projection point of the lead screw in the second worm screw lifting structure.

[0036] As an improvement of the technical scheme, as shown in Figure 6 As shown, the second worm screw lifting structure 32 is fixedly connected with the longitudinal beam 31 through a second boat-shaped seat 62. The second boat-shaped seat 62 and the longitudinal beam 31 are provided with scales correspondingly. The 0 scale on the second boat-shaped seat corresponds to the axis projection of the lead screw in the second worm screw lifting structure, so as to facilitate the adjustment of the position of the test sample plate through the lead screw in the second worm screw lifting structure, and ensure that the test sample plate matches the aerodynamic profile of the structure to be detected.

[0037] As an improvement of the technical scheme, as shown in Figure 7As shown, the test sample plate 4 is fitted on the clamping head 33, and is pressed by bolts, preferably, the thickness of the test sample plate is consistent with the opening width of the clamping head, so that the central section of the test sample plate is coincident with the axis of the screw rod, and the testing accuracy is ensured.

[0038] As an improvement of the technical scheme, as Figures 8 to 10 As shown, the base 1 is multiple, and can be connected by connecting pins 7 to form a stable large frame, so as to adapt to different sizes of structures to be detected, wherein, as Figure 10 As shown, a groove is arranged on both sides of the connecting pin 7, which can be matched with the vertical beam of the connected base, and is inserted into the notch of the two vertical beams, so as to realize the connection of the two bases, and a pull ring can be arranged on the top of the connecting pin, so as to facilitate the insertion and extraction, and then realize the quick assembly and disassembly of the base, in addition, in the detection process, in order to prevent the interference between the vertical beam and the connecting pin, as Figure 11 As shown, the device further comprises a second worm screw rod lifting structure auxiliary mounting frame 8 with a known width, and the second worm screw rod lifting structure is installed on the second worm screw rod lifting structure auxiliary mounting frame 8 to avoid interference.

[0039] The specific embodiments of the present application are written in a progressive manner, and the differences between various embodiments are emphasized, and the similar parts can be referred to each other.

[0040] The embodiments of the present application are described in detail above in combination with the drawings, but the present application is not limited to the above-mentioned embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the purpose of the present application.

Claims

1. An apparatus for detecting positive and negative deviations of an aerodynamic profile of an aircraft, characterized in that The utility model relates to a kind of aircraft aerodynamic test device, including: Base (1), support frame (2), clamping structure (3) and test sample plate (4), wherein the support frame (2) and clamping structure (3) are both set to the top of the base (1) and position adjustable, the support frame (2) is at least two, for supporting aircraft or spare part to be detected, the clamping structure (3) is oppositely arranged in pairs, for clamping test sample plate (4), the test sample plate (4) is arranged in pairs and is respectively fixed on the clamping structure (3), the test sample plate (4) is provided with the opening (41) matched with the aerodynamic profile of the position to be detected, the inner periphery of the opening is provided with measuring buffer strip (411), the base (1) is profile frame structure, and each surface of profile is provided with notch (11), the support frame (2) and clamping structure (3) are bolted to the base (1) by nut block embedded in the notch (11), the support frame (2) includes first worm gear screw rod lifting structure (21) and support frame body (22), the first worm gear screw rod lifting structure (21) is installed on the base (1), and the support frame body (22) is installed on the top end of screw rod in the first worm gear screw rod lifting structure (21).

2. The apparatus for detecting the aerodynamic profile of an aircraft according to claim 1, characterized in that: The upper end surface of the support frame body (22) is provided with a protection strip (221).

3. The apparatus for detecting the aerodynamic profile of an aircraft according to claim 1, characterized in that: The first worm gear screw rod lifting structure (21) is connected with the base (1) by first boat-shaped seat (61).

4. The apparatus for detecting the aerodynamic profile of an aircraft according to claim 1, characterized in that: The clamping structure (3) includes longitudinal beam (31), second worm gear screw rod lifting structure (32) and clamping head (33), wherein the longitudinal beam (31) is installed on the base (1), the second worm gear screw rod lifting structure (32) is transversely installed on the longitudinal beam (31), and the clamping head (33) is fixed to the free end of screw rod in the second worm gear screw rod lifting structure (32), for clamping test sample plate (4).

5. Apparatus for detecting the aerodynamic profile of an aircraft according to claim 4, characterized in that: The longitudinal beam (31) is a profile structure, each surface is provided with a notch, and the longitudinal beam (31) is connected with the base (1) by connecting angle piece (5).

6. Apparatus for detecting the aerodynamic profile of an aircraft according to claim 5, characterized in that: The second worm gear screw rod lifting structure (32) is fixedly connected with the longitudinal beam (31) by second boat-shaped seat (62).

7. The apparatus for detecting the aerodynamic profile of an aircraft according to claim 4, characterized in that: The test sample plate (4) is cooperatively installed on the clamping head (33), and is pressed by bolt.

8. The apparatus for detecting the aerodynamic profile of an aircraft according to claim 1, characterized in that: The base (1) is multiple, and can be connected to form a stable large frame by connecting pin (7).

Images