A method for measuring the central angle of a launch tube

Abstract

The present invention discloses a method for measuring the center angle of a launch tube, which belongs to the field of metrology and detection technology, and solves the technical problems of large technical errors and long time consumption in the existing measurement of the angle deviation of the launch tube. The measurement method comprises the following steps: providing an autocollimating gyrotheodolite; obtaining the bow and stern lines of the carrier through the autocollimating gyrotheodolite, and taking the azimuth of the bow and stern lines as the azimuth reference; installing the autocollimating gyrotheodolite on one side of the head end of the launch tube, and determining the installation reference of the autocollimating gyrotheodolite with the azimuth reference; obtaining the center line of the launch tube; and obtaining the angle deviation of the center line of the launch tube through the autocollimating gyrotheodolite. The present invention can not only improve the measurement accuracy, but also greatly shorten the measurement time and improve the measurement efficiency through the autocollimating gyrotheodolite.

Description

Technical Field

[0001] The invention belongs to the technical field of metrology and detection, and in particular relates to a method for measuring the central angle of a transmitting tube. Background Art

[0002] The carrier is equipped with a launch tube, and the angular deviation of the launch tube will affect the accuracy of the launch. Currently, the angular deviation of the launch tube is measured by the micrometer collimation telescope method, but the mechanical reading error caused by the micrometer collimation telescope method is large, and the measurement takes a long time. Summary of the invention

[0003] The present application aims to at least to some extent solve the technical problems of large errors and long time consumption in the existing methods for measuring the angle deviation of the launch tube. To this end, the present application provides a method for measuring the center angle of the launch tube.

[0004] The technical solution of this application is as follows:

[0005] Provide autocollimating gyro theodolite;

[0006] A method for measuring the center angle of a transmitting tube comprises the following steps:

[0007] Acquiring the bow and stern line of the carrier by means of the self-collimating gyro theodolite, and taking the azimuth of the bow and stern line as an azimuth reference;

[0008] Installing the autocollimation gyro theodolite on one side of the head end of the launch tube, and determining the installation reference of the autocollimation gyro theodolite by using the azimuth reference;

[0009] Obtaining the center line of the launch tube;

[0010] The angular deviation of the center line of the transmitting tube is obtained by the autocollimating gyro theodolite.

[0011] In some embodiments, the obtaining the bow and stern line of the carrier by using the autocollimation gyro theodolite specifically includes:

[0012] The self-collimating gyro theodolite is set up in front of the azimuth mirror of the carrier, and the self-collimating gyro theodolite is started to perform north-seeking and orientation measurement.

[0013] In some implementations, determining the installation reference of the autocollimation gyrotheodolite based on the azimuth reference specifically includes:

[0014] Providing bow and stern mirrors, the axes of which are parallel to the bow and stern lines of the carrier;

[0015] After the autocollimation gyro theodolite is installed on one side of the head end of the launch tube, the autocollimation gyro theodolite obtains the deviation between the autocollimation gyro theodolite and the installation reference through the bow and stern mirrors;

[0016] The autocollimation gyrotheodolite is adjusted until the autocollimation gyrotheodolite meets the installation reference.

[0017] In some embodiments, obtaining the center line of the launch tube specifically includes:

[0018] Providing a head centering device and a tail centering device, the head centering device is arranged at the head end of the launch tube to obtain the head illumination target center of the launch tube, and the tail centering device is arranged at the tail end of the launch tube to obtain the tail illumination target center of the launch tube;

[0019] Among them, the line connecting the center of the bow lighting target and the center of the tail lighting target is the center line of the transmitting tube.

[0020] In some embodiments, the head centering device and the tail centering device are both three-claw centering devices.

[0021] In some embodiments, obtaining the angular deviation of the center line of the launch tube by the autocollimation gyro theodolite specifically includes:

[0022] Aim the center of the bow illumination target by the self-collimating gyro theodolite to obtain the azimuth and elevation angles of the center of the bow illumination target;

[0023] Aiming at the center of the tail illumination target by the self-collimating gyro theodolite, the azimuth and elevation angles of the center of the tail illumination target are obtained;

[0024] The angular deviation of the center line of the launch tube is obtained by obtaining the azimuth angle and the elevation angle of the center of the bow lighting target and the azimuth angle and the elevation angle of the center of the tail lighting target.

[0025] In some embodiments, the angular deviation of the centerline of the launch tube includes a horizontal deviation and a vertical deviation;

[0026] Obtain the horizontal deviation of the center line of the launch tube by the obtained azimuth angle of the center of the bow illumination target, the obtained azimuth angle of the center of the tail illumination target, the distance between the bow centering device and the autocollimation gyrotheodolite, and the distance between the tail centering device and the autocollimation gyrotheodolite;

[0027] The vertical deviation of the center line of the launch tube is obtained by obtaining the pitch angle of the center of the bow lighting target, the pitch angle of the center of the tail lighting target, the distance between the bow centering device and the autocollimation gyrotheodolite, and the distance between the tail centering device and the autocollimation gyrotheodolite.

[0028] In some embodiments, the horizontal deviation αY for:

[0029]

[0030] Where: Y2 = L2tanα2, Y 1＝ =L1tanα1, L = L2-L1

[0031] α1 is the angle of the central azimuth of the bow illumination target, α2 is the angle of the central azimuth of the tail illumination target, L1 is the distance between the bow locator and the autocollimation gyrotheodolite, L2 is the distance between the tail locator and the autocollimation gyrotheodolite;

[0032] The vertical deviation α Z for:

[0033]

[0034] In the formula: Z2=L2tanβ2, Z1=L1tanβ1, L=L2-L1

[0035] β1 is the pitch angle of the center of the bow illumination target, β2 is the pitch angle of the center of the tail illumination target, L1 is the distance between the bow locator and the autocollimation gyrotheodolite, and L2 is the distance between the tail locator and the autocollimation gyrotheodolite.

[0036] In some embodiments, a laser rangefinder is provided, and a distance between the bow centering device and the autocollimation gyrotheodolite and a distance between the tail centering device and the autocollimation gyrotheodolite are obtained by the laser rangefinder.

[0037] In some embodiments, in the step of installing the autocollimation gyrotheodolite on one side of the head end of the launch tube, the autocollimation gyrotheodolite is rigidly connected to the carrier.

[0038] The embodiments of the present application have at least the following beneficial effects:

[0039] It can be seen from the above technical scheme that the measurement method disclosed in the present invention can quickly determine whether the installation position of the self-collimation gyrotheodolite is accurate through the self-collimation function of the self-collimation gyrotheodolite, and quickly install the self-collimation fall-off theodolite to the accurate position by manually debugging the installation position, so as to shorten the test time and improve the test efficiency. In addition, the method improves the installation accuracy of the self-collimation gyrotheodolite by obtaining an accurate installation reference, which can greatly improve the measurement accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0041] Figure 1 A schematic diagram of the process of the measurement method in the embodiment of the present application is shown;

[0042] Figure 2 A schematic diagram of the structure of the measuring transmitting tube in an embodiment of the present application is shown;

[0043] Markings in the figure: 1-launching tube, 2-bow centering device, 3-tail centering device, 4-bow and stern mirrors, 5-autocollimation gyrotheodolite. DETAILED DESCRIPTION

[0044] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0045] In addition, the present application may repeat reference numbers and / or reference letters in different examples, and such repetition is for the purpose of simplicity and clarity, and does not in itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present application provides various specific examples of processes and materials, but those of ordinary skill in the art may recognize the application of other processes and / or the use of other materials.

[0046] The present application is described below with reference to the accompanying drawings and specific embodiments:

[0047] like Figure 1 and Figure 2 As shown, this embodiment provides a method for measuring the center angle of a transmitting tube, comprising the following steps:

[0048] Step 1: providing an autocollimating gyro theodolite 5;

[0049] Step 2: Obtain the bow and stern line of the carrier by using the autocollimation gyro theodolite 5, and use the azimuth of the bow and stern line as the azimuth reference;

[0050] Step 3: Install the autocollimation gyro theodolite 5 on one side of the head end of the launch tube 1, and determine the installation reference of the autocollimation gyro theodolite 5 with the azimuth reference;

[0051] Step 4: Obtain the center line of the launch tube 1;

[0052] Step 5: Obtain the angular deviation of the center line of the launch tube 1 through the autocollimation gyro theodolite 5.

[0053] By using the self-collimation function of the self-collimation gyrotheodolite 5, the self-collimation image can be visually observed from the eyepiece of the self-collimation gyrotheodolite 5. By comparing the self-collimation image with the crosshairs of the self-collimation gyrotheodolite 5, it can be quickly determined whether the installation position of the self-collimation gyrotheodolite 5 is accurate. In addition, by manually debugging the installation position, the self-collimation fall-off theodolite can be quickly installed to the accurate position, so as to shorten the test time and improve the test efficiency. In addition, the method improves the installation accuracy of the self-collimation gyrotheodolite 5 by obtaining an accurate installation reference, which can greatly improve the measurement accuracy.

[0054] In both step 2 and step 3, the autocollimation gyrotheodolite 5 is rigidly connected to the carrier through the tooling. It should be noted that in step 3, the autocollimation gyrotheodolite 5 does not contact the transmitting tube 1 to ensure the accuracy of the measurement.

[0055] In step 2, the bow and stern line of the carrier is obtained by the autocollimation gyrotheodolite 5, which specifically includes: setting up the autocollimation gyrotheodolite 5 in front of the azimuth mirror of the carrier, and starting the autocollimation gyrotheodolite 5 to perform north-seeking and orientation measurement. The azimuth mirror is a device carried by the carrier as a marine vehicle, and the axial direction of the azimuth mirror is parallel to the bow and stern line of the hull. The autocollimation gyrotheodolite 5 can obtain the current azimuth of the carrier through north-seeking and orientation measurement. It can be understood that the obtained azimuth is the heading of the carrier.

[0056] Step 3 obtains an installation reference through the obtained bow and stern line to ensure that the measurement reference of the autocollimation gyro theodolite 5 is parallel to the bow and stern line when it is installed, and then measures the deviation between the launch tube 1 and the bow and stern line. Step 3 specifically includes:

[0057] Step 301: Provide a bow and stern mirror 4, wherein the axis of the bow and stern mirror 4 is parallel to the bow and stern line of the carrier.

[0058] The bow and stern mirrors 4 can be any planar object with a reflective function. The axes of the bow and stern mirrors 4 are located on the same straight line as the axis of the launch tube 1. The launch tube 1 may be deformed by external force after launch. Considering that the bow and stern mirrors 4 are small in size and do not contact the launch tube 1 and are not easily deformed, the bow and stern mirrors 4 are used as a reference when installing the self-collimating gyro theodolite 5.

[0059] Step 302: After the autocollimation gyrotheodolite 5 is installed on one side of the head end of the launch tube 1, the autocollimation gyrotheodolite 5 obtains the deviation between the autocollimation gyrotheodolite 5 and the installation reference through the bow and stern mirrors 4.

[0060] Step 303: Adjust the autocollimation gyrotheodolite 5 until the autocollimation gyrotheodolite 5 meets the installation reference.

[0061] In the above steps 302-303, the self-collimation function of the self-collimation gyrotheodolite 5 can also be used to quickly determine whether the installation position of the self-collimation gyrotheodolite 5 matches the installation reference. If the installation position deviates from the installation reference, the self-collimation detached theodolite is quickly installed to a position that meets the installation reference by manually debugging the installation position.

[0062] In step 4 of this embodiment, two centering devices are used to obtain the center line of the launch tube 1. The specific steps include:

[0063] Step 401: Provide a bow centering device 2 and a tail centering device 3, set the bow centering device 2 at the bow end of the launch tube 1 to obtain the center of the bow lighting target of the launch tube 1, and set the tail centering device 3 at the tail end of the launch tube 1 to obtain the center of the tail lighting target of the launch tube 1; the line connecting the center of the bow lighting target and the center of the tail lighting target is the center line of the launch tube 1.

[0064] The centering device is preferably a three-claw centering device with precise positioning. Specifically, when installing the centering device, first, make the three positioning guide rods contact the inner wall of the launch tube 1 respectively, adjust the three guide rods so that the center of the centering device is as large as the center position of the launch tube 1, and use a wide seat angle ruler to ensure that the end face of the centering device is perpendicular to the axis of the launch tube 1. Then, install the rotary arm pseudo shaft equipped with a dial indicator on the centering device, adjust the position of the dial indicator, and make the dial indicator probe contact the measuring part of the inner wall of the launch tube 1 to the working state.

[0065] Finally, rotate the dummy shaft and measure the distance difference between the center of the centering device and each measuring position on the inner wall of the launch tube 1 using the dial indicator. Repeatedly adjust the three guide rods until the distance difference from the center of the centering device measured by the dial indicator to the three guide rails is no more than 0.01 mm to ensure the accuracy of obtaining the center of the optical target. Record the dial indicator reading, then lock the guide rods and remove the dummy shaft.

[0066] During the measurement process, operators can be divided into two groups. One group of operators performs steps 1-2, and the other group of operators installs the bow centering device 2 and the tail centering device 3 on the launch tube 1 to further save operation time.

[0067] Step 5 specifically includes:

[0068] Step 501: aiming at the center of the bow illumination target by the autocollimation gyro theodolite 5 to obtain the azimuth and elevation angles of the center of the bow illumination target;

[0069] Step 502: aiming at the center of the tail illumination target by the autocollimation gyro theodolite 5 to obtain the azimuth and elevation angles of the center of the tail illumination target;

[0070] Step 503: Obtain the angular deviation of the center line of the launch tube 1 by using the azimuth angle and elevation angle of the center of the bow illumination target obtained and the azimuth angle and elevation angle of the center of the tail illumination target obtained.

[0071] The center of the bow illumination target is the center of the bow of the launch tube 1 determined by the bow centering device 2 , and the center of the tail illumination target is the center of the tail of the launch tube 1 determined by the tail centering device 3 .

[0072] The angular deviation of the center line of the launch tube includes horizontal deviation and vertical deviation. Specifically, the horizontal deviation of the center line of the launch tube 1 is obtained by obtaining the azimuth angle of the center of the bow lighting target, the azimuth angle of the center of the tail lighting target, the distance between the bow centering device 2 and the autocollimation gyrotheodolite 5, and the distance between the tail centering device 3 and the autocollimation gyrotheodolite 5.

[0073] Among them, the distance between the bow centering device 2 and the auto-collimation gyro theodolite 5 and the distance between the tail centering device 3 and the auto-collimation gyro theodolite 5 are both obtained by a laser rangefinder, and the measurement accuracy is high.

[0074] Horizontal deviation α Y for:

[0075]

[0076] Where: Y2 = L2tanα2, Y 1＝ =L1tanα1, L = L2-L1

[0077] α1 is the angle of the central azimuth of the bow illumination target, α2 is the angle of the central azimuth of the tail illumination target, L1 is the distance between the bow locator 2 and the autocollimation gyrotheodolite 5, and L2 is the distance between the tail locator 3 and the autocollimation gyrotheodolite 5.

[0078] The vertical deviation of the center line of the launch tube 1 is obtained by obtaining the pitch angle of the center of the bow lighting target, the pitch angle of the center of the tail lighting target, the distance between the bow centering device 2 and the autocollimation gyrotheodolite 5, and the distance L between the tail centering device 3 and the autocollimation gyrotheodolite 5.

[0079] Vertical deviation α Z for:

[0080]

[0081] In the formula: Z2=L2tanβ2, Z1=L1tanβ1, L=L2-L1

[0082] β1 is the pitch angle of the center of the bow illumination target, β2 is the pitch angle of the center of the tail illumination target, L1 is the distance between the bow locator 2 and the autocollimation gyrotheodolite 5, and L2 is the distance between the tail locator 3 and the autocollimation gyrotheodolite 5.

[0083] The data obtained by the measurement of the self-collimating gyro theodolite 5 are used to calculate the horizontal deviation and vertical deviation of the current launch tube 1 according to the above formula, so as to obtain the deviation of the axis of the launch tube 1 compared to the bow and stern line of the carrier. In this embodiment, the carrier can be a ship, and the launch tube 1 can be a pipeline for launching missiles. After the deviation of the axis of the launch tube 1 compared to the bow and stern line of the carrier is obtained, the obtained deviation is calculated into the missile launch trajectory through simulation, so as to reduce the error of the missile launch and improve the accuracy of the missile launch. The prior art uses the micrometer collimation telescope method, which takes about 8 hours to complete. The test time after using the method of this embodiment is shortened to about 2 hours, which can obviously improve the measurement efficiency.

[0084] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0085] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise" and "counterclockwise" indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0086] It should be noted that all directional indications in the embodiments of the present application are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0087] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0088] In addition, the descriptions of "first", "second", etc. in this application are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0089] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0090] In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the fact that they can be implemented by ordinary technicians in this field. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0091] Although the embodiments of the present application have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that the scope of the present application is defined by the claims and their equivalents.

Claims

1. A method for measuring the center angle of a transmitting tube, characterized in that: The following steps are involved: Provide autocollimating gyro theodolite; Acquiring the bow and stern line of the carrier by means of the self-collimating gyro theodolite, and taking the azimuth of the bow and stern line as an azimuth reference; Installing the autocollimation gyro theodolite on one side of the head end of the launch tube, and determining the installation reference of the autocollimation gyro theodolite by using the azimuth reference; A bow centering device and a tail centering device are provided to obtain the center line of the launch tube. The bow centering device is arranged at the bow end of the launch tube to obtain the center of the bow illumination target of the launch tube. The tail centering device is arranged at the tail end of the launch tube to obtain the center of the tail illumination target of the launch tube. The line connecting the center of the bow illumination target and the center of the tail illumination target is the center line of the launch tube. Aim the center of the bow illumination target by the self-collimating gyro theodolite to obtain the azimuth and elevation angles of the center of the bow illumination target; Aiming at the center of the tail illumination target by the self-collimating gyro theodolite, the azimuth and elevation angles of the center of the tail illumination target are obtained; The angular deviation of the center line of the launch tube is obtained by obtaining the azimuth angle and the elevation angle of the center of the bow lighting target and the azimuth angle and the elevation angle of the center of the tail lighting target.

2. The method for measuring the center angle of a transmitting tube according to claim 1, characterized in that: The step of obtaining the bow and stern line of the carrier by using the autocollimation gyro theodolite specifically includes: The self-collimating gyro theodolite is set up in front of the azimuth mirror of the carrier, and the self-collimating gyro theodolite is started to perform north-seeking and orientation measurement.

3. The method for measuring the center angle of a transmitting tube according to claim 1, characterized in that: Determining the installation reference of the autocollimation gyro theodolite based on the azimuth reference specifically includes: Providing bow and stern mirrors, the axes of which are parallel to the bow and stern lines of the carrier; After the autocollimation gyro theodolite is installed on one side of the head end of the launch tube, the autocollimation gyro theodolite obtains the deviation between the autocollimation gyro theodolite and the installation reference through the bow and stern mirrors; The autocollimation gyrotheodolite is adjusted until the autocollimation gyrotheodolite meets the installation reference.

4. The method for measuring the center angle of a transmitting tube according to claim 1, characterized in that: The head centering device and the tail centering device are both three-claw centering devices.

5. The method for measuring the center angle of a transmitting tube according to claim 1, characterized in that: The angular deviation of the center line of the launch tube includes a horizontal deviation and a vertical deviation; Obtain the horizontal deviation of the center line of the launch tube by the obtained azimuth angle of the center of the bow illumination target, the obtained azimuth angle of the center of the tail illumination target, the distance between the bow centering device and the autocollimation gyrotheodolite, and the distance between the tail centering device and the autocollimation gyrotheodolite; The vertical deviation of the center line of the launch tube is obtained by obtaining the pitch angle of the center of the bow lighting target, the pitch angle of the center of the tail lighting target, the distance between the bow centering device and the autocollimation gyrotheodolite, and the distance between the tail centering device and the autocollimation gyrotheodolite.

6. The method for measuring the center angle of a transmitting tube according to claim 5, characterized in that: The horizontal deviation α Y for: where: Y2 = L2tanα2, Y 1＝ = L1tanα1, L = L2 - L1 α1 is the angle of the central azimuth of the bow illumination target, α2 is the angle of the central azimuth of the tail illumination target, L1 is the distance between the bow locator and the autocollimation gyrotheodolite, L2 is the distance between the tail locator and the autocollimation gyrotheodolite; The vertical deviation α Z for: In the formula: Z2=L2tanβ2, Z1=L1tanβ1, L=L2-L1 β1 is the pitch angle of the center of the bow illumination target, β2 is the pitch angle of the center of the tail illumination target, L1 is the distance between the bow locator and the autocollimation gyrotheodolite, and L2 is the distance between the tail locator and the autocollimation gyrotheodolite.

7. The method for measuring the center angle of a transmitting tube according to claim 5, characterized in that: A laser rangefinder is provided, and a distance between the bow centering device and the autocollimation gyrotheodolite and a distance between the tail centering device and the autocollimation gyrotheodolite are obtained by the laser rangefinder.

8. The method for measuring the center angle of a transmitting tube according to claim 5, characterized in that: In the step of installing the autocollimation gyrotheodolite on one side of the head end of the launch tube, the autocollimation gyrotheodolite is rigidly connected to the carrier.

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