Large-scale guided rocket projectile appearance structure parameter measurement method

Abstract

The invention belongs to the technical field of measurement, and particularly relates to a large-scale guided rocket projectile appearance structure parameter measurement method. According to the spatial placement mode of the laser tracker, the portable three-coordinate measuring instrument and the measured projectile body provided by the method, station transfer measurement in a leapfrog mode can be avoided, so that the purpose of collecting surface points of all cabin sections and all parts of the measured projectile body at a time is achieved; and the appearance structure characteristics of the measured projectile body are fitted through the integrated measurement system. Meanwhile, according to the characteristics of each measured feature, measurement requirements are provided, so that measurement errors caused by influences of misoperation or miscellaneous points and the like are avoided. The method has the advantages that measurement errors caused by manual operation or environmental influence are effectively avoided, the operation intensity in the measurement process is reduced, and the measurement efficiency is improved.

Description

Technical Field

[0001] The present invention belongs to the field of measurement technology, and particularly relates to a method for measuring the shape structure parameters of a large guided rocket. Background Art

[0002] The shape structure parameters of a large guided rocket, such as the missile length, missile diameter, rudder span, chordwise angle of the rudder wing, flatness of the slider, coaxiality, etc., have an important impact on various links of the missile during barrel (box) entry, rail hanging, launching, flying, etc. The measurement accuracy of the above parameters directly affects the flight performance of the missile body. For the measurement of the above parameters, the common traditional method is to measure each parameter through methods such as calipers, tape measures, spirit levels, and plumb line measurements. The traditional method not only requires repeated flipping of the single body during the measurement process, but also it is difficult to ensure the consistency of the measurement reference, making it difficult to guarantee the measurement accuracy, with a large operation labor intensity and long time consumption. In order to improve the measurement accuracy and measurement efficiency of the shape structure parameters, it is necessary to design a measurement method for the shape structure of a large guided rocket that is more adaptable to the actual measurement requirements. Summary of the Invention

[0003] (1) Technical Problem to be Solved

[0004] The technical problem to be solved by the present invention is: how to provide a method for measuring the shape structure parameters of a large guided rocket.

[0005] (2) Technical Solution

[0006] To solve the above technical problem, the present invention provides a method for measuring the shape structure parameters of a large guided rocket, and the method includes the following steps:

[0007] Step S1: Place the missile body on the missile body support device to ensure that the centroid position of the missile body is between the two support frames of the support device;

[0008] Step S2: Place the laser tracker in front of the warhead, and the placement position requirements are as follows:

[0009] (1) Position of the laser tracker along the missile axis direction:

[0010] The laser tracker is located along the missile axis direction, about 1 / 2 of the missile length away from the warhead;

[0011] (2) Position of the laser tracker along the horizontal missile diameter direction:

[0012] The laser tracker is located along the missile diameter direction, about 1 / 4 of the missile length away from the missile axis;

[0013] (3) Height of the laser tracker:

[0014] The laser emitter of the laser tracker is located between the missile axis and the contour generatrix of the missile body;

[0015] Step S3: Place the portable coordinate measuring machine behind the control cabin and on the same side of the projectile body as the laser tracker; the distance between the portable coordinate measuring machine and the control cabin shall be determined based on the condition that its measuring probe touches the 4 rudder wings of the control cabin and there is no large-area obstruction between it and the laser tracker.

[0016] Step S4: Set up a three-dimensional measurement space with the laser tracker as the coordinate origin through the matching of the laser tracker and the portable coordinate measuring machine.

[0017] Step S5: Use the laser tracker to perform dotting measurements on the outer surface of the required cabin section to be measured, fit the outer cylindrical surfaces of each cabin section, and fit the axis of the cylindrical surface based on the cylindrical surface.

[0018] Step S10: Perform dotting measurements on the outer surface at the very front end of the nose cone cabin using the laser tracker, and use this point as the front vertex of the projectile body.

[0019] Step S13: Use the laser tracker to perform dotting measurements on the contact surface between the front slider and the guide rail, and fit the plane where the front slider contacts the guide rail.

[0020] Step S16: Use the portable coordinate measuring machine to perform dotting measurements on the rear end face of the control cabin, and fit the rear end face of the projectile body.

[0021] Step S19: Use the portable coordinate measuring machine to perform dotting measurements on the outer surfaces on both sides of the 4 rudder wings respectively, and fit the respective two side planes of the 4 rudder wings.

[0022] Step S22: Find the bisecting plane of each of the two side planes of the rudder wings fitted in Step S19, and use this as the central plane of this rudder wing.

[0023] Step S25: Use the portable coordinate measuring machine to perform dotting measurements on the contact surface between the rear slider and the guide rail, and fit the plane where the rear slider contacts the guide rail.

[0024] Step S28: According to the structural characteristics of the projectile body outer shape fitted in Steps S5 to S11, find the outer shape structure parameters of the projectile body according to the measurement requirements.

[0025] Among them, the content in Steps S5 to S11 is selectively executed according to the measurement requirements.

[0026] Among them, in Step S5, when fitting the outer cylindrical surfaces of each cabin section, points shall be taken at three positions, namely the front, middle, and rear of the cabin section, and the number of points taken shall be no less than 9; and it is necessary to pay attention to whether the cylindricity of the fitted cylinder meets the design requirements of the structural parts of this cabin section. If not, re-measurement is required to avoid measurement errors caused by stray points.

[0027] Among them, in the step S5, according to the axes of each fitted compartment, and according to the measurement requirements, taking the axis of one of the compartments as the reference, the coaxiality parameters of the measured compartment are solved.

[0028] Among them, in the steps S7 - S11, when fitting each measured plane, points should be taken at the four corners of the measured plane as large as possible and at the center of the plane, and the number of points taken is not less than 5; and it is necessary to pay attention to whether the flatness of the fitted plane meets the design requirements of the plane. If not, re - measurement is required to avoid measurement errors caused by miscellaneous points.

[0029] Among them, through the step S5 and the step S9, taking the axis of a certain compartment as the axis of the projectile, the included angle between the central plane of the four fin wings in the step S4 and the axis of the projectile is solved, that is, the chord - wise angle of the fin wing.

[0030] Among them, through the step S6 and the step S11, the parallelism of the contact surfaces between the front slider, the rear slider and the guide rail is solved.

[0031] Among them, through the step S7 and the step S8, according to the measurement requirements, the distance from the very front end of the projectile body to the rear end face of the projectile body is solved, which is the length of the projectile.

[0032] (III) Beneficial Effects

[0033] The present invention provides a method for measuring the external shape structure parameters of a large - scale guided rocket projectile based on a laser tracker and a portable coordinate measuring machine. This method can, according to technical requirements, collect and measure the surface points of each compartment and each part of the projectile body, and fit all the required measured features of the projectile body at one time, and then solve the external shape structure parameters of each feature through the measurement system. It effectively avoids measurement errors caused by manual operation or environmental influence, reduces the operation intensity during the measurement process, improves the measurement efficiency, and effectively solves the problems existing in the background technology.

[0034] Compared with the prior art, the beneficial effects of the present invention are:

[0035] Through the combination of a laser tracker and a portable coordinate measuring machine, all the required measured structural features of the projectile body are sampled into the integrated measurement system at one time. Through modeling and fitting, according to the measurement requirements, the external shape structure parameters of the projectile body can be obtained. The present invention effectively avoids measurement errors caused by manual operation or environmental influence, reduces the operation intensity during the measurement process, improves the measurement efficiency, and has high practical application value in the measurement of the external shape parameters of large - scale guided rocket projectiles. Description of the Drawings

[0036] Figure 1 It is a top - view of the spatial layout of a laser tracker, a portable coordinate measuring machine and the measured projectile body.

[0037] Figure 2 It is the rear view of the spatial layout of the laser tracker, portable coordinate measuring machine and the missile body to be measured. Specific embodiments

[0038] To make the objectives, content and advantages of the present invention clearer, the following further describes in detail the specific embodiments of the present invention with reference to the accompanying drawings and embodiments.

[0039] To solve the above technical problems, the present invention provides a method for measuring the shape structure parameters of a large guided rocket, and the method includes the following steps:

[0040] Step S1: Place the missile body on the missile body support device to ensure that the centroid position of the missile body is between the two support frames of the support device;

[0041] Step S2: Place the laser tracker in front of the warhead, and the placement position is required to meet the following standards:

[0042] (1) Position of the laser tracker along the missile axis:

[0043] The laser tracker is located along the missile axis, about half of the missile length away from the warhead;

[0044] (2) Position of the laser tracker along the horizontal missile diameter:

[0045] The laser tracker is located along the missile diameter, about one-fourth of the missile length away from the missile axis;

[0046] (3) Height of the laser tracker:

[0047] The laser emitter of the laser tracker is located between the missile axis and the contour element line of the missile body;

[0048] Step S3: Place the portable coordinate measuring machine behind the control cabin and on the same side of the missile body as the laser tracker; the distance between the portable coordinate measuring machine and the control cabin is based on the condition that its measuring probe touches the 4 control surfaces of the control cabin and there is no large-area occlusion between the portable coordinate measuring machine and the laser tracker;

[0049] Step S4: In the integrated measurement system, set up a three-dimensional measurement space with the laser tracker as the coordinate origin through the matching of the laser tracker and the portable coordinate measuring machine;

[0050] Step S5: Use the laser tracker to perform dotting measurements on the outer surface of the required cabin section to be measured, and through the integrated measurement system, fit the outer cylindrical surfaces of each cabin section, and based on the cylindrical surface fitting, obtain the axis of the cylindrical surface;

[0051] Step S6: Use the laser tracker to perform dotting measurements on the outermost surface of the front end of the nose cone cabin, and use this point as the front vertex of the missile body;

[0052] Step S7: Use a laser tracker to make dot measurements on the contact surface between the front slider and the guide rail, and through the integrated measurement system, fit the plane contacted by the front slider and the guide rail;

[0053] Step S8: Use a portable coordinate measuring machine to make dot measurements on the rear end face of the control cabin, and through the integrated measurement system, fit the rear end face of the projectile body;

[0054] Step S9: Use a portable coordinate measuring machine to make dot measurements on the outer surfaces of both sides of the 4 fins respectively, and through the integrated measurement system, fit the respective two side planes of the 4 fins;

[0055] Step S10: Through the integrated measurement system, find the bisecting plane of the two side planes of each fin fitted in Step S9, and use this as the central plane of this fin;

[0056] Step S11: Use a portable coordinate measuring machine to make dot measurements on the contact surface between the rear slider and the guide rail, and through the integrated measurement system, fit the plane contacted by the rear slider and the guide rail;

[0057] Step S12: Through the integrated measurement system, according to the external shape structure characteristics of the projectile body fitted in Steps S5 - S11, and according to the measurement requirements, find out the external shape structure parameters of the projectile body.

[0058] Among them, the content in Steps S5 - S11 is selectively executed according to the measurement requirements.

[0059] Among them, in Step S5, when fitting the external cylindrical surfaces of each cabin section, points need to be taken at three positions, namely the front, middle, and rear of this cabin section, and the number of points taken is not less than 9; and it is necessary to pay attention to whether the cylindricity of the fitted cylinder meets the design requirements of the structural parts of this cabin section. If not, re - measurement is required to avoid measurement errors caused by stray points.

[0060] Among them, in Step S5, according to the axes of each cabin section fitted, through the integrated measurement system, and according to the measurement requirements, taking the axis of one cabin section as the reference, solve the coaxiality parameter of the measured cabin section.

[0061] Among them, in Steps S7 - S11, when fitting each measured plane, points need to be taken at 4 corners as large as possible on the measured plane and at the center of the plane, and the number of points taken is not less than 5; and it is necessary to pay attention to whether the flatness of the fitted plane meets the design requirements of this plane. If not, re - measurement is required to avoid measurement errors caused by stray points.

[0062] Among them, through Steps S5 and S9, taking the axis of a certain cabin section as the projectile axis, through the integrated measurement system, solve the angle between the central plane of the 4 fins in Step S4 and the projectile axis, that is, the chord - wise angle of the fins.

[0063] Among them, through the said step S6 and step S11, the parallelism of the contact surfaces between the front slider, the rear slider and the guide rail is solved.

[0064] Among them, through the said step S7 and step S8, according to the measurement requirements, the distance from the foremost end of the projectile to the rear end face of the projectile is solved, which is the projectile length.

[0065] Embodiment 1

[0066] According to the measurement method of the present invention, this embodiment gives a full-process operation method for measuring the external shape structure parameters of a large guided rocket based on the combination of a laser tracker and a portable coordinate measuring machine, so as to make the implementation purpose, technical solution and operation process of the present invention clearer.

[0067] A method for measuring the external shape structure parameters of a large guided rocket based on a laser tracker and a portable coordinate measuring machine according to the present invention is specifically implemented as follows:

[0068] Step S1: Reliably place the projectile on the projectile support device to ensure that the centroid position of the projectile is between the two support frames of the support device. If there is a slider, place the slider directly above;

[0069] Step S2: Place the laser tracker in front of the warhead. The laser tracker is along the projectile axis and is located at about 1 / 2 of the projectile length from the warhead; the laser tracker is along the horizontal projectile diameter direction and is located at about 1 / 4 of the projectile length from the projectile axis. The laser tracker XXX is between the projectile axis and the topmost generatrix of the projectile outer contour.

[0070] Step S3: Place the portable coordinate measuring machine behind the control cabin and on the same side of the projectile as the laser tracker. The distance between the portable coordinate measuring machine and the control cabin is such that its measuring probe can touch the 4 fins of the control cabin and there is no large-area obstruction between it and the laser tracker.

[0071] Step S4: In the integrated measurement system, through the matching of the laser tracker and the portable coordinate measuring machine, set a three-dimensional measurement space with the laser tracker XXX as the coordinate origin.

[0072] Step S5: Use the laser tracker to perform dot measurement on the outer wall surfaces of the control cabin, engine, instrument cabin, payload warhead cabin and nose cone cabin. Through the integrated measurement system, fit the outer shape cylindrical surfaces of each cabin section, and based on the cylindrical surfaces, fit the axes of the cylindrical surfaces.

[0073] When fitting the outer shape cylindrical surfaces of each cabin section, points need to be taken at three positions, namely the front, middle and rear of the cabin section, and the number of points taken is not less than 9. And it is necessary to pay attention to whether the cylindricity of the fitted cylinder meets the design requirements of the structural parts of the cabin section. If not, re-measurement is required to avoid measurement errors caused by stray points.

[0074] Step S6: Use a laser tracker to make dot measurements on the outermost surface at the very front end of the nose cone module, and take this point as the vertex of the projectile body.

[0075] Step S7: Use a laser tracker to make dot measurements on the contact surface between the front slider and the guide rail, and through the integrated measurement system, fit out the plane where the front slider contacts the guide rail.

[0076] Step S8: Use a portable coordinate measuring machine to make dot measurements on the rear end face of the control module, and through the integrated measurement system, fit out the rear end face of the projectile body.

[0077] Step S9: Use a portable coordinate measuring machine to make dot measurements on the outer surfaces on both sides of the 4 fin wings respectively, and through the integrated measurement system, fit out the planes on both sides of the 4 fin wings.

[0078] Step S10: Through the integrated measurement system, find the bisecting plane of each of the planes on both sides of the fin wings fitted in S9, and use this as the central plane of this fin wing.

[0079] Step S11: Use a portable coordinate measuring machine to make dot measurements on the contact surface between the rear slider and the guide rail, and through the integrated measurement system, fit out the plane where the rear slider contacts the guide rail.

[0080] In the above steps S7 to S11, when fitting each measured plane, points should be taken at 4 corners as large as possible on the measured plane and at the center of the plane, and the number of points taken should be no less than 5. Also, it is necessary to pay attention to whether the flatness of the fitted plane meets the design requirements of this plane. If not, re-measurement is required to avoid measurement errors caused by stray points.

[0081] In the above step S5, according to the axes of each module fitted out, with the engine axis as the reference, in the integrated measurement system, solve the coaxiality of the instrument module, the counterweight warhead module and the nose cone module.

[0082] Through the above steps S5 and S9, according to the measurement requirements, with the engine axis as the spine, through the integrated measurement system, solve the angle between the central plane of the 4 fin wings and the projectile axis, that is, the fin chord angle.

[0083] Through the above steps S7 and S11, according to the measurement requirements, solve the parallelism of the contact surfaces between the front slider, the rear slider and the guide rail.

[0084] Through the above steps S6 and S8, according to the measurement requirements, solve the distance from the very front end of the projectile body to the rear end face of the projectile body, which is the projectile length.

[0085] The present invention provides a fast, convenient and easy-to-operate measurement method for measuring the shape structure parameters of large guided rockets. This method can effectively avoid measurement errors caused by manual operation or environmental influence, reduce the operation intensity during the measurement process, improve the measurement accuracy and efficiency, and is applicable to the detection of the shape structure parameters of most large guided rockets.

[0086] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the technical principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be regarded as the protection scope of the present invention.

Claims

1. A method for measuring the appearance and structural parameters of a large guided rocket, characterized in that: The method comprises the following steps: Step S1: placing the projectile on the projectile support device, ensuring that the center of mass of the projectile is located between the two support frames of the support device; Step S2: Place the laser tracker in front of the warhead. The placement position requires the following standards: (1) Position of the laser tracker along the missile axis: The laser tracker is located along the missile axis, about 1 / 2 the missile length from the warhead; (2) Position of the laser tracker along the horizontal projectile path: The laser tracker is located along the projectile diameter, about 1 / 4 of the projectile length from the projectile axis; (3) Laser tracker height: The laser tracker laser emitter is located between the missile axis and the outer contour line of the missile; Step S3: placing a portable three-dimensional coordinate measuring instrument behind the control cabin and on the same side of the missile body as the laser tracker; the distance between the portable three-dimensional coordinate measuring instrument and the control cabin is determined by the measurement probe of the portable three-dimensional coordinate measuring instrument touching the four rudder wings of the control cabin and without a large area of ​​shielding between the portable three-dimensional coordinate measuring instrument and the laser tracker; Step S4: in the integrated measurement system, by matching the laser tracker with the portable three-dimensional coordinate measuring instrument, a three-dimensional measurement space is set with the laser tracker as the coordinate origin; Step S5: using a laser tracker to perform point measurement on the outer surface of the required measured compartment, fitting the outer cylindrical surface of each compartment through an integrated measurement system, and fitting the axis of the cylindrical surface based on the cylindrical surface; Step S6: Use a laser tracker to measure a point on the outer surface of the front end of the nose cone, and take the point as the front end vertex of the projectile; Step S7: using a laser tracker to perform point measurement on the contact surface between the front slider and the guide rail, and fitting the contact plane between the front slider and the guide rail through an integrated measurement system; Step S8: Use a portable three-dimensional coordinate measuring instrument to measure points on the rear end surface of the control cabin, and fit the rear end surface of the missile body through an integrated measurement system; Step S9: using a portable three-dimensional coordinate measuring instrument, respectively marking points on the outer surfaces of both sides of the four rudder wings for measurement, and fitting the respective two-side planes of the four rudder wings through an integrated measurement system; Step S10: by means of an integrated measurement system, a bisector plane is obtained for the two side planes of each rudder wing fitted in step S9, and the bisector plane is used as the center plane of the rudder wing; Step S11: using a portable three-dimensional coordinate measuring instrument, dot measurement is performed on the contact surface between the rear slider and the guide rail, and the plane where the rear slider and the guide rail are in contact is fitted through an integrated measurement system; Step S12: By means of the integrated measurement system, the projectile shape and structure characteristics fitted in steps S5 to S11 are used to determine the projectile shape and structure parameters according to the measurement requirements.

2. The method for measuring the appearance and structural parameters of a large guided rocket as claimed in claim 1, characterized in that: The contents of steps S5 to S11 are selectively executed according to measurement requirements.

3. The method for measuring the appearance and structural parameters of a large guided rocket as claimed in claim 1, characterized in that: In step S5, when fitting the cylindrical surface of each cabin section, points need to be taken at the front, middle and rear positions of the cabin section respectively, and the number of points taken is not less than 9; and attention needs to be paid to whether the cylindricity of the fitted cylinder meets the design requirements of the cabin section structure. If not, it needs to be re-measured to avoid measurement errors caused by miscellaneous points.

4. The method for measuring the appearance and structural parameters of a large guided rocket as claimed in claim 1, characterized in that: In step S5, according to the fitted axes of each cabin section, the coaxiality parameters of the measured cabin section are solved by an integrated measurement system according to the measurement requirements and taking the axis of one of the cabin sections as a reference.

5. The method for measuring the appearance and structural parameters of a large guided rocket according to claim 1, characterized in that: In the steps S7 to S11, when fitting each measured plane, points need to be taken at the four largest corners of the measured plane, and points need to be taken at the center of the plane, with the number of points being no less than 5; and attention needs to be paid to whether the flatness of the fitted plane meets the design requirements of the plane. If not, re-measurement is required to avoid measurement errors caused by noise points.

6. The method for measuring the appearance and structural parameters of a large guided rocket according to claim 1, characterized in that: Through the steps S5 and S9, taking a certain compartment axis as the missile axis, the angle between the central plane of the four rudder wings in step S4 and the missile axis, that is, the rudder wing chord angle, is solved through the integrated measurement system.

7. The method for measuring the appearance and structural parameters of a large guided rocket according to claim 1, characterized in that: Through the steps S6 and S11, the parallelism of the contact surfaces between the front slider, the rear slider and the guide rail is determined.

8. The method for measuring the appearance and structural parameters of a large guided rocket according to claim 1, characterized in that: Through the steps S7 and S8, according to the measurement requirements, the distance from the front end of the projectile to the rear end of the projectile is solved, that is, the projectile length.

9. The method for measuring the appearance and structural parameters of a large guided rocket according to claim 1, characterized in that: According to technical requirements, this method collects and measures surface points of each compartment and each part of the missile body, fits all the features that need to be measured of the missile body at one time, and then solves the shape and structural parameters of each feature through the measurement system.

10. The method for measuring the appearance and structural parameters of a large guided rocket according to claim 1, characterized in that: The method combines a laser tracker with a portable three-coordinate measuring instrument to sample all the measured structural features of the projectile into an integrated measurement system at one time; through modeling and fitting, the shape structural parameters of the projectile can be calculated according to measurement requirements; the method effectively avoids measurement errors caused by manual operation or environmental influences, reduces the operation intensity during the measurement process, and improves the measurement efficiency. In the measurement of the shape parameters of large guided rockets, the method has high practical application value.

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