Instrument for rapid detection of the angle of a projectile wing

Abstract

The utility model provides a kind of fast detection wing angle instrument, including pedestal, inclination detection mechanism, and the pedestal is provided with the positioning part for installing and positioning wing and the installation part for installing inclination detection mechanism;Inclination detection mechanism includes four distance detectors, four distance detectors are all installed on the installation part of pedestal;Four distance detectors are divided into two groups of relative arrangement, and detection zone is formed between two groups of distance detectors, and two distance detectors in the same group of distance detectors are distributed upside down.This application carries out ranging to wing by four distance detectors respectively, the distance between corresponding distance detector and wing can be obtained, and the coordinates of distance detector can be calculated by known distance detector, and the coordinates of detection point on the wing corresponding to the distance detector are fitted into oblique line, the included angle between oblique line and median line is the inclination of wing, so that whether the inclination of the wing piece is qualified can be quickly judged.

Description

Technical Field

[0001] This utility model relates to the field of tilt angle detection instruments, specifically to a rapid instrument for detecting the tilt angle of a missile wing. Background Technology

[0002] In the field of aircraft manufacturing, the tilt angle between the wing and the mounting surface of the missile body is a core indicator that directly affects the aerodynamic performance, flight stability and control accuracy of the aircraft. Therefore, this tilt angle parameter needs to be strictly tested.

[0003] Currently, the industry mostly uses coordinate measuring machines (CMMs) to detect the tilt angle of missile wings. Although this equipment can meet the accuracy requirements, it has obvious shortcomings in practical applications: On the one hand, the measurement process requires data to be collected point by point through the probe, which, combined with complex path planning and mechanical movement, results in a long time consumption for a single test, making it difficult to adapt to the high-efficiency testing needs of mass production scenarios; on the other hand, the operation requires high skill levels from personnel, and each test requires a cumbersome clamping and calibration process, which not only increases labor costs but also easily introduces additional errors due to differences in operation, affecting the stability of the test.

[0004] Therefore, for the detection of missile wing tilt angle, there is an urgent need for a dedicated testing device that can balance detection accuracy and efficiency and simplify the operation process, so as to solve the bottleneck problem of existing coordinate measuring machines in mass production testing. Utility Model Content

[0005] The purpose of this invention is to provide a rapid instrument for detecting missile wing tilt angle, aiming to solve the technical problem of slow detection speed in existing detection equipment. The specific technical solution is as follows:

[0006] A rapid wing tilt angle detection instrument includes a base and a tilt angle detection mechanism. The base is provided with a positioning part for mounting and positioning the wing and a mounting part for mounting the tilt angle detection mechanism. The tilt angle detection mechanism includes four distance detectors, all of which are mounted on the mounting part of the base. The four distance detectors are arranged in two groups, with the two groups of distance detectors arranged opposite each other, forming a detection area between the two groups of distance detectors. The two distance detectors in the same group are distributed vertically.

[0007] Furthermore, the tilt detection mechanism also includes a U-shaped bracket, through which four distance detectors are mounted on the mounting section of the base.

[0008] Furthermore, the U-shaped bracket includes two parallel mounting arms and a connecting arm for connecting the two mounting arms. The bottom ends of the two mounting arms are fixedly connected to the connecting arm, and the top ends of the two mounting arms are cantilevered upwards. Two sets of distance detectors are correspondingly mounted on the two mounting arms, and two distance detectors in the same set are mounted on the mounting arms at intervals along the height direction. The connecting arm is mounted on the mounting part of the base.

[0009] Furthermore, the positioning part includes a positioning frustum and a positioning step. The positioning frustum is arranged on the top of the machine base, and the positioning step is arranged on the outer periphery of the positioning frustum. The top of the positioning step has a positioning surface for positioning the part being measured.

[0010] Furthermore, the distance detector is a laser rangefinder sensor.

[0011] Furthermore, the tilt detection mechanism also includes two protective covers, both of which are mounted on the base. The two protective covers correspond to two sets of distance detectors respectively. The protective covers are provided with through holes, which are arranged on the side of the protective cover closer to the detection area. There are two through holes, which correspond to two distance detectors in the same set of distance detectors respectively.

[0012] Furthermore, a guide ramp is provided on the protective cover, and the guide ramp is arranged on the side close to the detection area.

[0013] Furthermore, four tilt angle detection mechanisms are set up, which are distributed at intervals along the circumference of the positioning frustum, and the central axis of the detection area of ​​the four tilt angle detection mechanisms is arranged radially along the positioning frustum.

[0014] Furthermore, it also includes a zeroing component, which includes a socket and a wing mounted on the socket. The socket is provided with a socket hole arranged along the height direction. The socket hole is positioned and positioned in conjunction with the positioning frustum. The bottom of the socket is positioned and positioned in contact with the positioning surface on the positioning step. The first end of the wing is mounted on the socket, and the second end of the wing extends outward into the detection area and is cantilevered.

[0015] Furthermore, the zeroing component also includes a positioning pin, a first positioning hole on the socket, a second positioning hole on the positioning platform, and the positioning pin coaxially passing through the first positioning hole and the second positioning hole.

[0016] The application of the technical solution of this utility model has the following beneficial effects:

[0017] When it is necessary to test the tilt angle of a missile wing, the missile tube with the wing installed is mounted on the mounting part of the fuselage, with the wing cantilevered outwards between the detection areas. Four distance detectors measure the distance between the wing and the distance detector. Since the positions of the distance detectors are fixed, their coordinates are known. Using the distance measured by each distance detector, the coordinates of the corresponding detection point on the wing can be calculated. The coordinates of the four detection points are processed to calculate the midpoints of the two upper and two lower detection points. A diagonal line is drawn connecting these two midpoints; the angle between this diagonal line and the perpendicular bisector is the tilt angle of the wing, thus determining whether the wing's tilt angle is acceptable. Using this testing method, the distance data from the four distance detectors can be obtained instantly after the missile tube with the wing is installed on the mounting part, greatly improving the testing speed.

[0018] In addition to the objectives, features, and advantages described above, this utility model has other objectives, features, and advantages. These will be described below with reference to... Figures 1-5 The present invention will be described in further detail below. Attached Figure Description

[0019] The accompanying drawings, which form part of this application, are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an undue limitation of the present invention. In the drawings:

[0020] Figure 1 This is a schematic diagram of the overall structure of the rapid missile wing tilt angle detection instrument of this application after removing the zeroing component;

[0021] Figure 2 This is an exploded view of a rapid wing tilt detection instrument of this application after the zeroing component has been removed;

[0022] Figure 3 This is a schematic diagram of the overall structure of a rapid missile wing tilt angle detection instrument according to this application;

[0023] Figure 4 This is a cross-sectional view of a rapid wing tilt angle detection instrument according to this application;

[0024] Figure 5 yes Figure 4 A magnified view of point A in the middle.

[0025] Among them, 1. Base; 11. Positioning part; 111. Positioning frustum; 1111. Second positioning hole; 112. Positioning step; 113. Positioning surface; 12. Mounting part; 2. Inclination detection mechanism; 21. Distance detector; 22. U-shaped bracket; 221. Mounting arm; 222. Connecting arm; 3. Detection area; 4. Protective cover; 41. Through hole; 42. Guide slope; 5. Zeroing component; 51. Socket; 511. Socket hole; 512. First positioning hole; 52. Wing; 53. Positioning pin. Detailed Implementation

[0026] To facilitate understanding of this invention, a more comprehensive description is provided below, along with preferred embodiments. However, this invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the disclosure of this invention.

[0027] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.

[0028] Example:

[0029] See Figures 1-5 This embodiment provides a rapid wing tilt angle detection instrument, including a base 1 and a tilt angle detection mechanism 2. The base 1 is provided with a positioning part 11 for installing and positioning the wing and a mounting part 12 for installing the tilt angle detection mechanism 2. The tilt angle detection mechanism 2 includes four distance detectors 21, all of which are mounted on the mounting part 12 of the base 1. The four distance detectors 21 are arranged in two groups, with the two groups of distance detectors 21 arranged opposite each other, and a detection area 3 is formed between the two groups of distance detectors 21. The two distance detectors 21 in the same group are distributed vertically.

[0030] It is known that when it is necessary to test the tilt angle of the missile wing, the missile tube with the wing installed is mounted on the mounting part 12 of the base 1, and the wing is made to be overhanging outward between the detection areas 3. The wing is measured by four distance detectors 21. By detecting the distance between the distance detector 21 and the wing, the distance between the corresponding distance detector 21 and the wing can be obtained. Since the position of the distance detector 21 is fixed, the coordinates of the distance detector 21 are known. By the distance detected by the corresponding distance detector 21, the coordinates of the detection point on the wing corresponding to the distance detector 21 can be calculated. The coordinates of the four detection points are processed to calculate the midpoints of the two upper detection points and the midpoints of the two lower detection points. The two midpoints are connected to form an oblique line. The angle between the oblique line and the perpendicular bisector is the tilt angle of the wing. Thus, it can be determined whether the tilt angle of the wing 52 is qualified. When using this detection method, the distance data of the four distance detectors 21 can be obtained instantly after the missile tube with the fins is installed in the mounting part 12, which greatly improves the detection speed. In addition, during the measurement process, multiple data can be measured, and the average value of the obtained data can be used for calculation, which further improves the accuracy of the data.

[0031] Furthermore, the tilt detection mechanism 2 also includes a U-shaped bracket 22, through which four distance detectors 21 are mounted on the mounting part 12 of the base 1.

[0032] It is known that by setting up the U-shaped bracket 22, four distance detectors 21 are installed on the inner side of the U-shaped bracket 22, and the transmitting ends of the four distance detectors 21 are all facing the inside of the U-shaped bracket 22, so as to form a detection area 3 inside the U-shaped bracket 22. Through this structural design, each distance detector 21 can be stably installed on the U-shaped bracket 22.

[0033] Furthermore, the U-shaped bracket 22 includes two parallel mounting arms 221 and a connecting arm 222 for connecting the two mounting arms 221. The bottom ends of the two mounting arms 221 are fixedly connected to the connecting arm 222, and the two mounting arms 221 are respectively fixed to the two ends of the connecting arm 222. The top ends of the two mounting arms 221 are cantilevered upwards. Two sets of distance detectors 21 are mounted on the two mounting arms 221 by screws. Two distance detectors 21 in the same set are mounted on the mounting arms 221 at intervals along the height direction. The two upper distance detectors 21 in the two sets of distance detectors 21 are arranged in the same plane, and the two lower distance detectors 21 in the two sets of distance detectors 21 are also arranged in the same plane. The connecting arm 222 is detachably mounted on the mounting part 12 of the base 1 by screws.

[0034] It is understood that the U-shaped bracket 22 provides stable support for the distance detector 21 and facilitates the formation of a detection area 3 between the two sets of distance detectors 21 to detect the workpiece.

[0035] Preferably, the positioning part 11 includes a positioning frustum 111 and a positioning step 112. The positioning frustum 111 is arranged on the top of the base 1, and the positioning step 112 is arranged on the outer periphery of the positioning frustum 111. The top of the positioning step 112 has a positioning surface 113 for positioning the part to be measured. Specifically, the positioning frustum 111 is located in the middle of the base 1 to facilitate the positioning of the finned cartridge. During operation, the finned cartridge is fitted onto the positioning frustum 111, and the inner wall of the cartridge abuts against the outer wall of the positioning frustum 111 for positioning, thereby achieving horizontal positioning of the cartridge. The bottom of the cartridge abuts against the positioning surface 113 on the positioning step 112 for positioning of the cartridge in the height direction. By setting up the positioning frustum 111 and the positioning step 112, when the missile tube with the missile wing is fitted onto the positioning frustum 111, the missile wing can extend into the detection area 3 located in the tilt angle detection mechanism 2, so that the tilt angle of the missile wing can be detected by the distance detector 21.

[0036] It should be noted that in some embodiments, the positioning part 11 can also be configured as a downwardly recessed positioning recess. By inserting the winged cartridge into the positioning recess for positioning, the winged cartridge can also be quickly installed and tested.

[0037] Preferably, in this embodiment, the distance detector 21 is a laser rangefinder. In some other embodiments of this application, the detector may also be an optical rangefinder such as an infrared rangefinder. Optical ranging allows for rapid acquisition of the distance, thus achieving rapid detection.

[0038] Furthermore, the tilt detection mechanism 2 also includes two protective covers 4, both mounted on the base 1, and each protective cover 4 is arranged corresponding to one of the two sets of distance detectors 21. The protective covers 4 cover the distance sensors from top to bottom, and the lower end of the protective covers 4 is detachably connected to the base 1 by screws. Two through holes 41 are provided on the protective covers 4, located on the side of the protective cover 4 closest to the detection area 3. Each through hole 41 corresponds to one of the two distance detectors 21 in the same set. The through holes 41 are arranged opposite to the detection ports of the distance detectors 21, so that the detection signals transmitted and received by the distance detectors 21 can pass smoothly through the through holes 41, preventing the protective covers 4 from obstructing the detection signals transmitted and received by the distance detectors 21.

[0039] Because the distance detector 21 is a precision instrument, it is easily damaged by impacts or vibrations from external objects. The protective cover 4 protects the distance detector 21, preventing the winged projectile from impacting the protective cover 4 during measurement, thus preventing damage to the distance detector 21 during measurement.

[0040] Preferably, a guide slope 42 is provided on the protective cover 4, and the guide slope 42 is arranged on the side close to the detection area 3.

[0041] It is known that the guide ramp 42 guides the missile wing to be measured, so that the missile wing can smoothly enter the detection area 3 for detection. At the same time, the protective ramps on the two protective covers 4 form a V-shaped detection area 3. The upper opening of the detection area 3 is large, which makes it easy to put the missile wing into the detection area 3, thus improving convenience.

[0042] Furthermore, four tilt angle detection mechanisms 2 are provided, which are distributed circumferentially along the positioning frustum 111. The central axis of the detection area 3 of the four tilt angle detection mechanisms 2 is arranged radially along the positioning frustum 111.

[0043] It is known that by setting up four tilt detection mechanisms 2 simultaneously, it is convenient to detect the four wings on the cartridge tube at the same time, which further improves the detection efficiency.

[0044] Furthermore, it also includes a zeroing component 5, which includes a socket 51 and a wing 52 mounted on the socket 51. The socket 51 is provided with a socket hole 511 arranged along the height direction. The socket hole 511 is fitted and positioned with the positioning frustum 111. The bottom of the socket 51 is abutted and positioned with the positioning surface 113 on the positioning step 112. The first end of the wing 52 is mounted on the socket 51, and the second end of the wing 52 extends outward into the detection area 3 and is cantilevered.

[0045] It should be noted that the zeroing component 5 is only used when zeroing is required, that is, at the beginning of the workday, to zero the distance sensor. During zeroing, the socket 51 of the zeroing component 5 is fitted onto the positioning frustum 111. The socket 51 is horizontally positioned by engaging with the positioning frustum 111 through the socket hole 511 on the socket 51. The socket 51 is positioned along the height direction by abutting against the positioning surface 113 on the positioning step 112 at its bottom. This positions the wing 52 of the zeroing component 5 within the detection area 3. The distance detector 21 is then calibrated and zeroed using the known angle of the wing 52.

[0046] Through the above structural design, the distance detector 21 can be calibrated in a timely manner to prevent equipment failure and thus avoid scrapping the detected parts, thereby reducing the probability of failure.

[0047] Furthermore, the zeroing component 5 also includes a positioning pin 53, a first positioning hole 512 is provided on the socket 51, a second positioning hole 1111 is provided on the positioning frustum 111, and the positioning pin 53 is coaxially inserted into the first positioning hole 512 and the second positioning hole 1111.

[0048] It is known that by setting the positioning pin 53, the socket 51 is rotated and positioned along the axial direction so that the wing 52 can zero the distance detector 21.

[0049] It also includes rubber supports, four of which are detachably connected to the four corners of the bottom of the base 1 by screws. The rubber supports improve the anti-slip ability and stability of the base 1.

[0050] The working principle and operation process of this utility model are as follows:

[0051] During the testing operation, zeroing is first performed using the zeroing component 5. It should be noted that zeroing is only required the first time it is used during a full day of testing. First, the socket 51 of the zeroing component 5 is fitted onto the positioning frustum 111, and the wing 52 in the adjusting component is positioned within the testing area 3. The first positioning hole 512 on the socket 51 is aligned with the second positioning hole 1111 on the positioning frustum 111. The positioning pin 53 is inserted to lock it in place. The distance detector 21 detects the wing 52 at a known angle. The detected data is compared with the known data of the wing 52. If the two data match, the data of the distance detector 21 is accurate. If the two data do not match, the data on the distance detector 21 is adjusted to match the known data of the wing 52, thus achieving zeroing and calibration. All distance detectors 21 are adjusted in sequence. The winged missile to be tested is fitted onto the positioning frustum 111, so that the wing extends into the detection area 3. The four distance detectors 21 in the tilt angle detection mechanism 2 simultaneously measure the distance of the wing. Through the four measured distance data and the known coordinates of the distance detectors 21, the position coordinates of the four measured points on the wing can be obtained. The coordinates of the four detection points are processed to calculate the midpoints of the two upper detection points and the midpoints of the two lower detection points. A diagonal line is formed by connecting the two midpoints. The angle between the diagonal line and the perpendicular bisector is the tilt angle of the wing. Thus, it can be determined whether the tilt angle of the wing 52 is qualified.

[0052] 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. A rapid instrument for detecting the tilt angle of a projectile wing, characterized in that: It includes a base (1) and an tilt angle detection mechanism (2). The base (1) is provided with a positioning part (11) for installing and positioning the missile wings and an installation part (12) for installing the tilt angle detection mechanism (2). The tilt angle detection mechanism (2) includes four distance detectors (21), all of which are mounted on the mounting part (12) of the base (1); The four distance detectors (21) are arranged in two groups, with the two groups of distance detectors (21) arranged opposite each other and forming a detection area (3) between the two groups of distance detectors (21). The two distance detectors (21) in the same group of distance detectors (21) are distributed vertically.

2. The rapid wing tilt angle detection instrument according to claim 1, characterized in that: The tilt detection mechanism (2) also includes a U-shaped bracket (22), and the four distance detectors (21) are mounted on the mounting part (12) of the base (1) via the U-shaped bracket (22).

3. The rapid wing tilt angle detection instrument according to claim 2, characterized in that: The U-shaped bracket (22) includes two parallel mounting arms (221) and a connecting arm (222) for connecting the two mounting arms (221). The bottom ends of the two mounting arms (221) are fixedly connected to the connecting arm (222), and the top ends of the two mounting arms (221) are cantilevered upwards. The two sets of distance detectors (21) are respectively installed on the two mounting arms (221), and the two distance detectors (21) in the same set are installed at intervals along the height direction on the mounting arms (221); The connecting arm (222) is mounted on the mounting part (12) of the base (1).

4. The rapid wing tilt angle detection instrument according to claim 1, characterized in that: The positioning part (11) includes a positioning frustum (111) and a positioning step (112). The positioning frustum (111) is arranged on the top of the base (1), and the positioning step (112) is arranged on the outer periphery of the positioning frustum (111). The top of the positioning step (112) has a positioning surface (113) for positioning the part to be measured.

5. The rapid wing tilt angle detection instrument according to claim 1, characterized in that: The distance detector (21) is a laser rangefinder.

6. A rapid wing tilt angle detection instrument according to any one of claims 1-5, characterized in that: The tilt detection mechanism (2) also includes two protective covers (4). Both protective covers (4) are mounted on the base (1), and the two protective covers (4) are respectively arranged corresponding to two sets of distance detectors (21). The protective cover (4) is provided with a through hole (41). The through hole (41) is arranged on the side of the protective cover (4) close to the detection area (3). There are two through holes (41), and the two through holes (41) are respectively arranged corresponding to two distance detectors (21) in the same set of distance detectors (21).

7. The rapid wing tilt angle detection instrument according to claim 6, characterized in that: The protective cover (4) is provided with a guide slope (42), which is arranged on the side close to the detection area (3).

8. The rapid wing tilt angle detection instrument according to claim 4, characterized in that: Four tilt angle detection mechanisms (2) are provided, and the four tilt angle detection mechanisms (2) are distributed circumferentially along the positioning frustum (111). The central axis of the detection area (3) of the four tilt angle detection mechanisms (2) is arranged radially along the positioning frustum (111).

9. A rapid wing tilt angle detection instrument according to claim 4, characterized in that: It also includes a zeroing component (5), which includes a socket (51) and a wing (52) mounted on the socket (51). The socket (51) is provided with a socket hole (511) arranged along the height direction. The socket hole (511) is socketed and positioned with the positioning frustum (111). The bottom of the socket (51) is abutted and positioned with the positioning surface (113) on the positioning step (112). The first end of the wing (52) is mounted on the socket (51), and the second end of the wing (52) extends outward into the detection area (3) and is cantilevered.

10. A rapid wing tilt angle detection instrument according to claim 9, characterized in that: The zeroing component (5) also includes a positioning pin (53), the socket (51) is provided with a first positioning hole (512), the positioning frustum (111) is provided with a second positioning hole (1111), and the positioning pin (53) is coaxially inserted into the first positioning hole (512) and the second positioning hole (1111).

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