Solid rocket engine radial circle runout detection device and use method thereof
By designing a radial circular jumping amount detection device for solid rocket engines, the stable rotation and horizontal state of the engine are achieved by using bearings and elevators, combined with the measurement mechanism of a rigid flat ruler and a dial gauge, the problem of difficult engine rotation and large measurement errors in traditional methods is solved, and the measurement efficiency and accuracy are improved.
Patent Information
- Application Number
- CN202510351190.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-24
- Publication Date
- 2025-06-27
AI Technical Summary
When traditional methods measure the radial circular jumping amount of solid rocket engines, there is a problem that the engine is difficult to rotate radially, especially when the engine is too large, the jitter during the rotation process will affect the measurement accuracy and the production efficiency is low.
A solid rocket engine radial circular jumping amount detection device is designed, including a movable support frame, a fixed support frame, a measuring and fixing mechanism. The circumferential rotation of the engine is achieved through the bearings and the height of the engine is adjusted by the lift to ensure that it is always in a horizontal state. The measurement and fixing mechanism uses a rigid flat ruler and a dial gauge to measure the circular jumping amount at different positions of the engine through the slider.
By replacing manual rotation by movable support frame, measurement errors are reduced and measurement efficiency is improved; the rigid flat ruler ensures the level of the measuring mechanism and the engine, and the measurement point adjustment efficiency is improved; the bearing, as a rotating component, reduces the system error and can measure the radial circular jumping amount of the variable-section engine.
Smart Images
Figure CN120212818A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the field of solid rocket engine testing, and particularly relates to a device for detecting the radial runout of a solid rocket engine and a method for using the same. Background Art
[0002] A solid rocket engine is a long-axis product. During the production process, in order to ensure that the shell of the long axis does not deform and affect the subsequent engine ignition, it is necessary to measure the radial runout of the cylinder section of the long axis of the solid rocket engine. The traditional measurement method uses V-shaped irons to fix two supporting planes of the shell, fixes a dial indicator at the measurement position, and realizes the acquisition of the clearance on the test circular surface by manually rotating the engine to achieve radial rotation. The radial runout of the engine shell is characterized by the change in the reading on the dial indicator.
[0003] However, this method is only suitable for products with light weight. Once the engine is too heavy, it will be difficult to rotate the engine radially. At the same time, the jitter during the rotation process greatly affects the measurement of the dial indicator, and it is necessary to continuously correct the error through multiple measurements, resulting in low production efficiency. Summary of the Invention
[0004] In order to solve the above problems, the invention provides a device for detecting the radial runout of a solid rocket engine, which is characterized by comprising a movable support frame 20, a fixed support frame 30, and a measuring and fixing mechanism 40; the movable support frame 20 and the fixed support frame 30 are placed opposite to each other, and each has a pair of bearings at the top for supporting both ends of the engine 10. The bottoms are connected through the measuring and fixing mechanism 40. The engine 10 is placed on the two pairs of bearings of the fixed support frame 30 and the movable support frame 20, and the circumferential rotation of the engine 10 is realized through the bearings. The movable support frame 20 is provided with a lift 204, and the height is adjusted through the lift 204 to ensure that the engine 10 is always in a horizontal state;
[0005] The measuring and fixing mechanism 40 is used for fixing and measuring the engine 10, and comprises a rigid flat ruler 402, a rigid measuring shaft 403, and a dial indicator 404. The rigid flat ruler 402 is fixedly parallel to the engine 10. The rigid measuring shaft 403 is installed on the rigid flat ruler 402 and can move horizontally along the rigid flat ruler 402 through a slider thereon. The dial indicator 404 is fixedly connected to the rigid measuring shaft 403 and is close to the measured position of the engine 10. The radial runout of different positions of the engine 10 is measured through the cooperation of the slider of the measuring and fixing mechanism 40.
[0006] Furthermore, the movable support frame 20 includes a movable bracket 201, a guide shaft assembly 202, a turntable 203, a lift 204, a connecting shaft 205, a positioning disk 206, and a pair of first bearings 209; the lower end surface of the positioning disk 206 is reliably connected to the steel platform; the lift 204 is fixed to the positioning disk 206; the movable bracket 201 is fixed to the driven component of the lift 204; the first bearings 209 are fixed to the movable bracket 201; the guide shaft assembly 202 is fixedly installed between the positioning disk 206 and the movable bracket 201; the connecting shaft 205 and the turntable 203 are connected to the driving component of the lift 204.
[0007] Furthermore, the movable support frame 20 further includes a first limit screw 207 and a first nut 208, and the first bearings 209 are fixed to the movable bracket 201 by the first limit screw 207 and the first nut 208.
[0008] Furthermore, the connection mode between the lift 204 and the positioning disk 206 is screw connection.
[0009] Furthermore, the guide shaft assembly 202 is connected to the positioning disk 203 and the movable bracket 201 by screws.
[0010] Furthermore, the connection mode between the movable bracket 201 and the driven component of the lift 204 is screw connection.
[0011] Furthermore, the fixed support frame 30 includes a fixed bracket 301 and a second bearing 302; the lower end surface of the fixed bracket 301 is reliably connected to the steel platform; the second bearing 302 is fixed to the fixed bracket 301 by a second limit screw 303 and a second nut 304.
[0012] Furthermore, the fixed support frame 30 further includes a second limit screw 303 and a second nut 304, and the second bearing 302 is fixed to the fixed bracket 301 by the second limit screw 303 and the second nut 304.
[0013] Furthermore, the measuring and fixing mechanism 40 further includes a limit plate 401, the limit plate 401 is fixedly connected between the positioning disk 206 and the fixed bracket 301, and the rigid flat ruler 402 is horizontally connected and fixed to the limit plate 401.
[0014] The present invention also provides a usage method of the above-mentioned radial runout detection device for solid rocket engines, and the specific steps are as follows:
[0015] S1. Adjust the distance between the movable support frame 20 and the fixed support frame 30 according to the position of the support points of the engine 10.
[0016] S2. Lift the engine 10 onto this device and ensure that the support points of the engine 10 are effectively supported on the first bearing 209 of the movable support frame 20 and the second bearing 302 of the fixed support frame 30;
[0017] S3. Use the dial indicator 404 on the measuring and fixing mechanism 40 to measure the height difference at the support points of the engine 10, and use the turntable 203 on the movable support frame 20 to drive the elevator 204 to adjust the height of the engine 10 until the height difference is eliminated;
[0018] S4. Move the dial indicator 404 on the measuring and fixing mechanism 40 to the test position, manually rotate the engine 10, and use the dial indicator 404 to measure the radial circular runout at the test position;
[0019] S5. Move the measuring and fixing mechanism 40 to the next test position and repeat the operation in S4.
[0020] Compared with the prior art, the beneficial effects achieved by the present invention are as follows:
[0021] 1. By using the movable support frame instead of manual rotation, the measurement error is reduced and the measurement efficiency is increased; the straight edge ensures the level of the measuring mechanism and the engine, improving the adjustment efficiency of the measurement points; using bearings as the rotating components of the engine, the consistency of the mechanism is strong, reducing the systematic error caused by rollers.
[0022] 2. By adjusting the height of the engine support position with the movable support frame, the radial circular runout of the variable cross-section engine can be measured. BRIEF DESCRIPTION OF THE DRAWINGS
[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.
[0024] Figure 1 It is a schematic diagram of a device for detecting the radial circular runout of a solid rocket engine according to the present invention;
[0025] Figure 2 It is a schematic diagram of the structure of the movable support frame according to the present invention;
[0026] Figure 3 It is a schematic diagram of the structure of the fixed support frame according to the present invention;
[0027] Figure 4 It is a schematic diagram of the measuring and fixing structure according to the present invention.
[0028] In the figure: 20 is a movable support frame; 201 is a movable support; 202 is a guide shaft assembly; 203 is a turntable; 204 is a lift; 205 is a connecting shaft; 206 is a positioning disk; 207 is a first limit screw; 208 is a first nut; 209 is a first bearing; 30 is a fixed support frame; 301 is a fixed support; 302 is a second bearing; 303 is a second limit screw; 304 is a second nut; 40 is a measuring and fixing mechanism; 401 is a limit plate; 402 is a rigid flat ruler; 403 is a rigid measuring shaft; 404 is a dial indicator. Specific Embodiments
[0029] The following specific examples illustrate the embodiments of the present invention. Those skilled in the art can easily understand the other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention.
[0030] It should be noted that the diagrams provided in the following embodiments only illustrate the basic concept of the present invention in a schematic manner. Therefore, only the components related to the present invention are shown in the diagrams, rather than being drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and proportion of each component in actual implementation can be arbitrarily changed, and the component layout type may also be more complex.
[0031] The following combines the attached Figures 1 to 4 to further elaborate on the present invention in detail.
[0032] The present invention relates to a tooling for measuring the circular runout of a solid rocket engine, which is a circular runout measuring device that realizes the rotation of the product through bearings, realizes the measurement of circular runout through a dial indicator, and realizes the translation of the test point through a slider.
[0033] Specifically, the present invention provides a device for detecting the radial circular runout of a solid rocket engine, as Figure 1 shown. Its overall structure includes a movable support frame 20, a fixed support frame 30, and a measuring and fixing mechanism 40. The movable support frame 20 and the fixed support frame 30 are placed opposite to each other, and each has a pair of bearings at the top for supporting both ends of the engine 10, and are connected at the bottom through the measuring and fixing mechanism 40. The measuring and fixing mechanism 40 is used for fixing and measuring the engine 10. The product to be tested, i.e., the engine 10, is placed on the four bearings that support the engine 10, and the circumferential rotation of the engine 10 is realized through the four bearings that support the engine 10. The height of the movable support frame 20 is adjusted by the lift 204 to ensure that the engine 10 is always in a horizontal state. The measurement of the circular runout at different positions of the engine 10 is realized through the cooperation of the slider of the measuring and fixing mechanism 40.
[0034] The straight-edge 402 in the measuring and fixing mechanism 40 is fixedly arranged in parallel with the engine 10.
[0035] The dial indicator 404 in the measuring and fixing mechanism 40 is close to the measured position of the engine 10 and points to the radial center of the engine 10. The engine 10 can rotate, and the radial circular run-out of the engine 10 is measured by the change in the reading of the dial indicator 404.
[0036] A device for detecting the radial circular run-out of a solid rocket engine provided by the present invention can be used for measuring the radial circular run-out of a solid rocket engine.
[0037] As Figure 2 shown, the movable support frame 20 includes a movable bracket 201, a guide shaft assembly 202, a turntable 203, a lift 204, a connecting shaft 205, a positioning disk 206, a first limit screw 207, a first nut 208, and a first bearing 209. Among them, the lower end surface of the positioning disk 206 is reliably connected to the steel platform; the lift 204 is fixed to the positioning disk 206 by screws; the movable bracket 201 is fixed to the driven part of the lift 204 by screws; the first bearing 209 is fixed to the movable bracket 201 by the first limit screw 207 and the first nut 208; the guide shaft assembly 202 is fixedly installed between the positioning disk 206 and the movable bracket 201 by screws; the connecting shaft 205 is connected to the turntable 203 on the driving part of the lift 204. The vertical movement of the movable support frame 20 adjusts and calibrates the position and attitude of the engine 10. The engine 10 is always in a horizontal position through the lift 204 of the movable support frame 20.
[0038] There are two first bearings 209, which are used to support the solid rocket engine 10 and enable the solid rocket engine 10 to rotate circumferentially during the measurement process.
[0039] The circumferential rotation of the product is realized through 4 bearings supporting the product.
[0040] The lift 204 and the positioning disk 206 are fixedly connected by screws.
[0041] The movable bracket 201 and the driven part of the lift 204 are fixedly connected by screws.
[0042] The guide shaft assembly 202 is connected to the positioning disk 206 and the movable bracket 201 by screws.
[0043] As Figure 3As shown, the fixed support frame 30 includes a fixed bracket 301, a second bearing 302, a second limit screw 303, and a second nut 304. Among them, the lower end surface of the fixed bracket 301 is reliably connected to the steel platform; the second bearing 302 is fixed on the fixed bracket 301 by the second limit screw 303 and the second nut 304.
[0044] There are two second bearings 302, which are used to support the solid rocket engine 10 and enable the solid rocket engine 10 to achieve circumferential rotation during the measurement process.
[0045] The elevator 204 keeps the engine 10 in a horizontal position all the time, enabling the engine 10 to have the conditions for measuring the radial circular runout.
[0046] The engine 10 is placed on the first bearing 209 and the second bearing 302 between the movable support frame 20 and the fixed support frame 30. The engine 10 is always in a horizontal position through the elevator 204 of the movable support frame 20, enabling the engine 10 to have the conditions for measuring the radial circular runout.
[0047] As Figure 4 As shown, the measuring and fixing mechanism 40 includes a limit plate 401, a rigid flat ruler 402, a rigid measuring shaft 403, and a dial indicator 404. Among them, the limit plate 401 is fixedly connected between the positioning disk 206 and the fixed bracket 301; the rigid flat ruler 402 is horizontally connected and fixed to the limit plate 401; the rigid measuring shaft 403 is installed on the rigid flat ruler 402 and can move horizontally along the rigid flat ruler 402 through the slider thereon; the dial indicator 404 is fixedly connected to the rigid measuring shaft 403.
[0048] The limit plate 401 in the measuring and fixing mechanism 40 is used for the rigid connection of the movable support frame 20 and the fixed support frame 30.
[0049] The dial indicator 404 in the measuring and fixing mechanism 40 is used for measuring the radial circular runout at the test position of the engine 10.
[0050] The dial indicator 404 in the measuring and fixing mechanism 40 is moved to the position to be tested of the engine 10, the engine 10 is manually rotated, and the radial circular runout at the test position is measured with the dial indicator 404.
[0051] The dial indicator 404 in the measuring and fixing mechanism 40 is horizontally moved to the next test position of the engine 10 through the slider along the rigid flat ruler 402, and the operation of claim 6 is repeated for measurement.
[0052] The measurement function for products of different lengths is realized through the adjustment of the fixing mechanism. The accurate measurement of the circular runout at multiple positions of the product is realized through the movement of the slider of the measuring device.
[0053] The present invention also provides a method for using a device for detecting the radial runout of a solid rocket motor, and the specific steps are as follows:
[0054] S1. Adjust the distance between the movable support frame 20 and the fixed support frame 30 according to the position of the support points of the motor 10.
[0055] S2. Lift and move the motor 10 onto this device, and make the support points of the motor 10 effectively supported on the first bearing 209 of the movable support frame 20 and the second bearing 302 of the fixed support frame 30.
[0056] S3. Use the dial indicator 404 on the measuring and fixing mechanism 40 to measure the height difference at the support point position of the motor 10, and use the turntable 203 on the movable support frame 20 to drive the elevator 204 to adjust the height of the motor 10 until the height difference is eliminated.
[0057] S4. Move the dial indicator 404 on the measuring and fixing mechanism 40 to the test position, manually rotate the motor 10, and use the dial indicator 404 to measure the radial runout at the test position.
[0058] S5. Move the measuring and fixing mechanism 40 to the next test position, and repeat step 4.
[0059] Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.
Claims
1. A solid rocket engine radial runout detection device, characterized in that: The invention comprises a movable support frame (20), a fixed support frame (30), and a measuring and fixing mechanism (40); the movable support frame (20) and the fixed support frame (30) are placed opposite to each other, and each has a pair of bearings at the top for supporting two ends of the engine (10); the bottom is connected via the measuring and fixing mechanism (40); the engine (10) is placed on the two pairs of bearings of the fixed support frame (30) and the movable support frame (20); the circumferential rotation of the engine (10) is achieved via the bearings; the movable support frame (20) has a lift (204); the lift (204) is used to adjust the height so that the engine (10) is always in a horizontal state; The measuring and fixing mechanism (40) is used for fixing and measuring an engine (10), and comprises a rigid ruler (402), a rigid measuring shaft (403), and a dial indicator (404). The rigid ruler (402) is fixed in parallel with the engine (10). The rigid measuring shaft (403) is mounted on the rigid ruler (402) and can move horizontally along the rigid ruler (402) through a slider thereon. The dial indicator (404) is fixedly connected to the rigid measuring shaft (403) and is close to a measured position of the engine (10). The measurement of the circular runout at different positions of the engine (10) is achieved by cooperating with the slider of the measuring and fixing mechanism (40).
2. A solid rocket engine radial runout detection device as claimed in claim 1, characterized in that: The movable support frame (20) comprises a movable bracket (201), a guide shaft assembly (202), a turntable (203), an elevator (204), a connecting shaft (205), a positioning plate (206), and a pair of first bearings (209); the lower end surface of the positioning plate (206) is reliably connected to the steel platform; the elevator (204) is fixed on the positioning plate (206); the movable bracket (201) is fixed on the driven component of the elevator (204); the first bearing (209) is fixed on the movable bracket (201); the guide shaft assembly (202) is fixedly installed between the positioning plate (206) and the movable bracket (201); the connecting shaft (205) and the turntable (203) are connected to the active component of the elevator (204).
3. A solid rocket engine radial runout detection device as claimed in claim 2, characterized in that: The movable support frame (20) further comprises a first limiting screw (207) and a first nut (208), and the first bearing (209) is fixed on the movable support frame (201) via the first limiting screw (207) and the first nut (208).
4. A solid rocket engine radial runout detection device as claimed in claim 2, characterized in that: The elevator (204) and the positioning plate (206) are fixedly connected by screws.
5. A solid rocket engine radial runout detection device as claimed in claim 2, characterized in that: The guide shaft assembly (202) is connected to the positioning plate (203) and the movable bracket (201) via screws.
6. A solid rocket engine radial runout detection device as claimed in claim 2, characterized in that: The movable bracket (201) and the driven component of the elevator (204) are fixedly connected by screw connection.
7. A solid rocket engine radial runout detection device as claimed in claim 1, characterized in that: The fixed support frame (30) comprises a fixed support (301) and a second bearing (302); the lower end surface of the fixed support (301) is reliably connected to the steel platform; the second bearing (302) is fixed to the fixed support (301) by a second limit screw (303) and a second nut (304).
8. A solid rocket engine radial runout detection device as claimed in claim 7, characterized in that: The fixed support frame (30) further comprises a second limiting screw (303) and a second nut (304), and the second bearing (302) is fixed to the fixed support frame (301) via the second limiting screw (303) and the second nut (304).
9. A solid rocket engine radial runout detection device as claimed in claim 1, characterized in that: The measuring and fixing mechanism (40) further comprises a limiting plate (401), wherein the limiting plate (401) is fixedly connected between the positioning plate (206) and the fixing bracket (301), and the rigid level ruler (402) is horizontally connected and fixed to the limiting plate (401).
10. A method for using the solid rocket engine radial runout detection device as claimed in claim 1, comprising the following specific steps: S1. Adjust the distance between the movable support frame (20) and the fixed support frame (30) according to the position of the support point of the engine (10); S2. The engine (10) is hoisted onto the device, and the supporting point of the engine (10) is effectively supported on the first bearing (209) and the second bearing (302) of the movable support frame (20) and the fixed support frame (30); S3. Use the dial indicator (404) on the measuring and fixing mechanism (40) to measure the height difference of the support point of the engine (10), and use the turntable (203) on the movable support frame (20) to drive the elevator (204) to adjust the height of the engine (10) until the height difference is eliminated; S4. The dial indicator (404) on the measuring and fixing mechanism (40) is moved to the test position, the engine (10) is manually rotated, and the radial runout of the test position is measured with the dial indicator (404); S5. Move the measuring and fixing mechanism (40) to the next test position and repeat the operation of S4.