Device and method for testing performance of composite folding wing

Abstract

The invention discloses a device and a method for testing the performance of a composite folding wing, and belongs to the technical field of folding wing testing. A composite folding wing performance testing device comprises a bottom plate, a cushion block, a mounting seat and a loading mechanism, two groups of connecting holes are formed in the outer side of the bottom plate, and the bottom plate is connected with a universal testing machine lower chuck through one group of connecting holes and connected with the cushion block through the other group of connecting holes. The cushion block is in a concave shape, two positions of the concave shape are respectively provided with a through hole which is used for connecting the base plate and the installation seat, and the installation seat is composed of a locking pin, a locking spring, a threaded connection hole and a product installation hole. The device for testing the performance of the composite folding wing can provide continuous work, so that the detection efficiency of a product is improved, and meanwhile, the device can also be used for carrying out secondary confirmation on the connection size of a metal piece of the composite folding wing, so that the installation effectiveness of the connection size of the metal piece is ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of folding wing testing, and more particularly to a device and method for testing the performance of composite material folding wings. Background Art

[0002] The folding wing is a composite material, connected to the missile body through a folding mechanism, and can be folded inside or on the surface of the missile body before the missile is launched. The folding wing can reduce the lateral size of the missile, making it easier to transport and launch; it can save storage and transportation space for missiles, increase the transportation capacity of vehicles or ships, and improve combat effectiveness. Folding wings are increasingly used in missile weapons due to their simple structure and small space occupation. The tail fins of rockets usually use folding wings, so that the rocket can be loaded into the launch tube with the smallest volume.

[0003] After the rocket is launched, the folding wings need to bear a certain load and cannot have too much deformation. Therefore, it is necessary to perform a performance test on the folding wings to simulate the load that the folding wings bear during the flight of the rocket. However, in the prior art, when performing performance tests on the folding wings, the tests are generally performed manually by staff. Since manual tests cannot accurately confirm the magnitude of the force, the loaded force is inaccurate, which in turn affects the test results of the folding wings and reduces the test effect of the folding wings. Based on this, the present invention designs a performance test device and method for composite material folding wings to solve the above problems. Summary of the invention

[0004] The purpose of the present invention is to provide a device and method for testing the performance of composite material folding wings to solve the problems raised in the above background technology:

[0005] After the rocket is launched, the folding wings need to bear a certain load and cannot have too much deformation. Therefore, it is necessary to perform a performance test on the folding wings to simulate the load that the folding wings bear during the flight of the rocket. However, in the prior art, when performing performance tests on the folding wings, the tests are generally performed manually by staff. Since manual tests cannot accurately confirm the magnitude of the force, the loaded force is inaccurate, which in turn affects the test results of the folding wings and reduces the test effect of the folding wings. Based on this, the present invention designs a performance test device and method for composite material folding wings to solve the above problems.

[0006] A composite material folding wing performance test device, comprising a bottom plate, a cushion block, a mounting seat and a loading mechanism, wherein two groups of connecting holes are opened on the outer side of the bottom plate, and the bottom plate is connected to the lower chuck of a universal testing machine through one group of connecting holes, and is connected to the cushion block through another group of connecting holes, so as to facilitate fixed support of the entire test device, the cushion block is in a concave shape, and each of the two concave positions has a through hole for connecting the bottom plate and the mounting seat, and the mounting seat is composed of a locking pin, a locking spring, a threaded connection hole and a product mounting hole, and the locking pin One side of the device is hollow, the locking spring is connected to the hollow, the mounting seat is connected to the pad through a threaded connection hole, the product mounting hole is used to install the elastic wing, the loading mechanism is composed of a loading block and a loading rod, the loading block is rectangular, and has a row of horizontal holes on each side for installing the chuck on the universal testing machine, and a row of horizontal holes on the front side of the loading block for installing the loading rod, the loading rod includes a mounting hole and a loading head, the mounting hole is used to connect to the loading block, and the loading head is used to transmit the force of the universal testing machine to the elastic wing.

[0007] Preferably, the base plate, mounting seat, locking spring, loading block and loading rod are all made of No. 45 steel, so that the service life of the device is longer, the detection efficiency is improved, and the detection cost is reduced.

[0008] A method for testing the performance of a composite material folding wing, comprising the following steps:

[0009] S1. Select a matching universal testing machine and procedure according to the test device to ensure that the function of the testing machine matches the test type of the folding wing performance and avoid test errors caused by improper selection of the testing machine;

[0010] S2. Installation of test equipment and products, ensuring that the test equipment and products are installed firmly and in the correct position, so as to avoid reducing the safety performance of the equipment due to installation errors;

[0011] S3, test loading step, using a test machine to replace manual testing, thereby greatly improving the accuracy of the folding wing performance test;

[0012] S4. Test data processing and qualification judgment: Process and analyze the collected data to evaluate whether the performance of the folding wings meets the expectations or the requirements of relevant standards.

[0013] Preferably, S2 comprises the following steps:

[0014] S2-1, install the test device on the universal testing machine and ensure that the test device is installed firmly and in the correct position, so as to improve the safety performance and test accuracy of the device;

[0015] S2-2, installing the composite folding wing on the test device, thereby avoiding the need for workers to manually perform performance tests on the folding wing, reducing the labor intensity of the workers, and improving the accuracy of the folding wing performance test;

[0016] S2-3, align the tooling loading head with the product loading point to avoid loading the force to the wrong test position, thereby improving the accuracy of the folding wing performance test;

[0017] S2-4, place the dial indicator on the front and rear edges of the product wing tip respectively, ensure that the dial indicator is firmly fixed and the reading is clearly visible, so as to provide accurate data support for the subsequent loading and unloading process.

[0018] Preferably, S3 comprises the following steps:

[0019] S3-1, check the product installation status to ensure there is no looseness or interference, so as to ensure the accuracy and safety of the test and avoid poor product installation results that may cause damage to the staff;

[0020] S3-2, observe and record the readings of two dial indicators, namely the leading edge U1-1 and the trailing edge U1-2, so as to facilitate recording the displacement readings in the initial state for subsequent comparison and improve the accuracy of the device for folding wing performance testing;

[0021] S3-3, load 200N and hold the load for 30s, so as to facilitate the test of the material response. When the load reaches 200N, the composite folding wing does not undergo plastic deformation and the wing tip deflection is less than or equal to 10mm, indicating that the performance of the folding wing is qualified;

[0022] S3-4, observe whether there is plastic deformation and record the readings of two dial indicators, namely the leading edge U2-1 and the trailing edge U2-2, so as to facilitate the staff to detect the deformation of the folding wing under a load of 200N;

[0023] S3-5, unloading to 0N, so that the staff can prepare for the next stage of testing, avoiding the test error caused by directly loading 300N from 200N, thereby improving the accuracy of the device for folding wing performance testing;

[0024] S3-6, load 300N, hold the load for 30s, increase the load, and further test the pressure resistance of the material. When the loading force reaches 300N, the composite folding wing does not break, indicating that the performance of the folding wing is qualified.

[0025] S3-7, observe whether the composite folding wing is damaged.

[0026] Preferably, the step 4 comprises the following steps:

[0027] S4-1, calculate U1 according to the leading edge deflection U1 = (U2-1) - (U1-1), this difference reflects the deformation degree of the leading edge under the load;

[0028] S4-2, calculate U2 according to the trailing edge deflection U2 = (U2-2)-(U1-2), and this difference represents the deformation of the trailing edge under the load;

[0029] S4-3, the test results are calculated based on the front and rear edge height difference △ = |U2-U1|. This value is used to evaluate the deformation of the composite folding wing under load.

[0030] Compared with the prior art, the advantages of the present invention are:

[0031] 1) In the present invention, by adopting a universal testing machine for force loading, the magnitude of the force can be accurately confirmed, avoiding the factor of inaccuracy of the loading force. At the same time, by adopting a dial indicator for data recording, the test data can be accurately recorded, avoiding the factor of measurement error.

[0032] 2) In the present invention, the composite material folding wing performance test device can provide continuous operation, thereby improving the inspection efficiency of the product. At the same time, the device can also perform secondary confirmation of the connection dimensions of the composite material folding wing metal parts to ensure the effectiveness of the installation of the metal parts connection dimensions. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0034] Figure 2 It is a schematic diagram of the bottom plate structure of the present invention;

[0035] Figure 3 It is a schematic diagram of the cushion block structure of the present invention;

[0036] Figure 4 It is a schematic diagram of the mounting seat structure of the present invention;

[0037] Figure 5 It is a schematic diagram of the structure of the loading rod of the present invention;

[0038] Figure 6 It is a schematic diagram of the loading block structure of the present invention.

[0039] Explanation of the numbers in the figure: 1. Base plate; 2. Pad; 3. Mounting seat; 31. Locking pin; 32. Locking spring; 33. Threaded connection hole; 34. Product mounting hole; 4. Loading mechanism; 41. Loading block; 42. Loading rod. DETAILED DESCRIPTION

[0040] In the description of the present invention, 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", "counterclockwise" and the like 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 invention 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 limiting the present invention.

[0041] In the description of the present invention, “plurality” means two or more than two, unless otherwise clearly and specifically defined.

[0042] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "mounted / connected", "connected", etc. should be understood in a broad sense. For example, "connected" 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 it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] Example: See Figure 1-6 A composite material folding wing performance test device, comprising a bottom plate 1, a cushion block 2, a mounting seat 3 and a loading mechanism 4, wherein two groups of connecting holes are opened on the outer side of the bottom plate 1, and the bottom plate 1 is connected to the lower chuck of the universal testing machine through one group of connecting holes, and is connected to the cushion block 2 through another group of connecting holes, so as to facilitate the fixed support of the entire test device, the cushion block 2 is in a concave shape, and each of the two concave parts has a through hole for connecting the bottom plate 1 and the mounting seat 3, and the mounting seat 3 is composed of a locking pin 31, a locking spring 32, a threaded connection hole 33 and a product mounting hole 34, and the locking pin 31 One side of the device is hollow, the locking spring 32 is connected to the hollow, the mounting seat 3 is connected to the cushion block 2 through a threaded connection hole 33, the product mounting hole 34 is used to install the elastic wing, the loading mechanism 4 is composed of a loading block 41 and a loading rod 42, the loading block 41 is rectangular, with a row of horizontal holes on each side for installation on the chuck of the universal testing machine, and a row of horizontal holes on the front side of the loading block 41 for installing the loading rod 42, the loading rod 42 includes a mounting hole and a loading head, the mounting hole is used to connect to the loading block, and the loading head is used to transmit the force of the universal testing machine to the elastic wing.

[0044] The base plate 1, the mounting seat 3, the locking spring 32, the loading block 41 and the loading rod 42 are all made of 45# steel, so that the device has a longer service life, improves the detection efficiency and reduces the detection cost.

[0045] By using a universal testing machine for force loading, the magnitude of the force can be accurately confirmed, avoiding the factor of inaccurate loading force. At the same time, by using a dial indicator for data recording, the test data can be accurately recorded, avoiding the factor of measurement error. This composite material folding wing performance test device can provide continuous work, thereby improving the inspection efficiency of the product. At the same time, this device can also perform secondary confirmation of the connection dimensions of the composite material folding wing metal parts to ensure the effectiveness of the installation of the metal parts connection dimensions.

[0046] A method for testing the performance of a composite material folding wing, comprising the following steps:

[0047] S1. Select a matching universal testing machine and procedure according to the test device to ensure that the function of the testing machine matches the test type of the folding wing performance and avoid test errors caused by improper selection of the testing machine;

[0048] S2. Installation of test equipment and products, ensuring that the test equipment and products are installed firmly and in the correct position, so as to avoid reducing the safety performance of the equipment due to installation errors;

[0049] S3, test loading step, using a test machine to replace manual testing, thereby greatly improving the accuracy of the folding wing performance test;

[0050] S4. Test data processing and qualification judgment: Process and analyze the collected data to evaluate whether the performance of the folding wings meets the expectations or the requirements of relevant standards.

[0051] As a preferred embodiment of the present invention, S2 comprises the following steps:

[0052] S2-1, install the test device on the universal testing machine and ensure that the test device is installed firmly and in the correct position, so as to improve the safety performance and test accuracy of the device;

[0053] S2-2, installing the composite folding wing on the test device, thereby avoiding the need for workers to manually perform performance tests on the folding wing, reducing the labor intensity of the workers, and improving the accuracy of the folding wing performance test;

[0054] S2-3, align the tooling loading head with the product loading point to avoid loading the force to the wrong test position, thereby improving the accuracy of the folding wing performance test;

[0055] S2-4, place the dial indicator on the front and rear edges of the product wing tip respectively, ensure that the dial indicator is firmly fixed and the reading is clearly visible, so as to provide accurate data support for the subsequent loading and unloading process.

[0056] As a preferred embodiment of the present invention, S3 comprises the following steps:

[0057] S3-1, check the product installation status to ensure there is no looseness or interference, so as to ensure the accuracy and safety of the test and avoid poor product installation results that may cause damage to the staff;

[0058] S3-2, observe and record the readings of two dial indicators, namely the leading edge U1-1 and the trailing edge U1-2, so as to facilitate recording the displacement readings in the initial state for subsequent comparison and improve the accuracy of the device for folding wing performance testing;

[0059] S3-3, load 200N and hold the load for 30s, so as to facilitate the test of the material response. When the load reaches 200N, the composite folding wing does not undergo plastic deformation and the wing tip deflection is less than or equal to 10mm, indicating that the performance of the folding wing is qualified;

[0060] S3-4, observe whether there is plastic deformation and record the readings of two dial indicators, namely the leading edge U2-1 and the trailing edge U2-2, so as to facilitate the staff to detect the deformation of the folding wing under a load of 200N;

[0061] S3-5, unloading to 0N, so that the staff can prepare for the next stage of testing, avoiding the test error caused by directly loading 300N from 200N, thereby improving the accuracy of the device for folding wing performance testing;

[0062] S3-6, load 300N, hold the load for 30s, increase the load, and further test the pressure resistance of the material. When the loading force reaches 300N, the composite folding wing does not break, indicating that the performance of the folding wing is qualified.

[0063] S3-7, observe whether the composite folding wing is damaged.

[0064] As a preferred embodiment of the present invention, the 4 comprises the following steps:

[0065] S4-1, calculate U1 according to the leading edge deflection U1 = (U2-1) - (U1-1), this difference reflects the deformation degree of the leading edge under the load;

[0066] S4-2, calculate U2 according to the trailing edge deflection U2 = (U2-2)-(U1-2), and this difference represents the deformation of the trailing edge under the load;

[0067] S4-3, the test results are calculated based on the front and rear edge height difference △ = |U2-U1|. This value is used to evaluate the deformation of the composite folding wing under load.

[0068] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the present invention and are not intended to limit the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A composite material folding wing performance test device, comprising a base plate (1), a cushion block (2), a mounting seat (3) and a loading mechanism (4), characterized in that: Two groups of connection holes are provided on the outer side of the base plate (1), and the base plate (1) is connected to the lower chuck of the universal testing machine through one group of connection holes, and is connected to the cushion block (2) through the other group of connection holes. The cushion block (2) is in a concave shape, and there is a through hole at each of the two concave positions, which is used to connect the base plate (1) and the mounting seat (3). The mounting seat (3) is composed of a locking pin (31), a locking spring (32), a threaded connection hole (33) and a product mounting hole (34). One side of the locking pin (31) is hollow, and the locking spring (32) is connected to the hollow. The mounting seat ( 3) connected to the cushion block (2) through a threaded connection hole (33), the product installation hole (34) is used to install the elastic wing, the loading mechanism (4) is composed of a loading block (41) and a loading rod (42), the loading block (41) is rectangular, and has a row of horizontal holes on the left and right sides respectively, which is used to be installed on the chuck of the universal testing machine, and the front side of the loading block (41) has a row of horizontal holes, which is used to install the loading rod (42), the loading rod (42) includes a mounting hole and a loading head, the mounting hole is used to connect with the loading block, and the loading head is used to transmit the force of the universal testing machine to the elastic wing.

2. A composite material folding wing performance test method according to claim 3, characterized in that: The base plate (1), the mounting seat (3), the locking spring (32), the loading block (41) and the loading rod (42) are all made of No. 45 steel.

3. A method for testing the performance of composite material folding wings, applied to the device for testing the performance of composite material folding wings as claimed in claim 1, comprising the following steps: S1. Select a matching universal testing machine and procedure according to the test device; S2. Test equipment and product installation; S3, test loading step; S4. Test data processing and qualification determination.

4. A composite material folding wing performance test method according to claim 3, characterized in that: The S2 comprises the following steps: S2-1, install the test device on the universal testing machine; S2-2, install the composite folding wing on the test device; S2-3, align the tool loading head with the product loading point; S2-4, place the dial indicator on the leading and trailing edges of the product wing tip.

5. A composite material folding wing performance test method according to claim 3, characterized in that: The S3 comprises the following steps: S3-1, check the product installation status, and check if there is any looseness or interference; S3-2, observe and record the readings of two dial indicators, which are the leading edge U1-1 and the trailing edge U1-2; S3-3, load 200N, hold load for 30s; S3-4, observe whether there is plastic deformation and record the readings of two dial indicators, which are the leading edge U2-1 and the trailing edge U2-2 respectively; S3-5, unloading to 0N; S3-6, load 300N, hold load for 30s; S3-7, observe whether the composite folding wing is damaged.

6. A composite material folding wing performance test method according to claim 3, characterized in that: The 4 steps include the following steps: S4-1, calculate U1 according to the leading edge deflection U1=(U2-1)-(U1-1); S4-2, calculating U2 according to the trailing edge deflection U2=(U2-2)-(U1-2); S4-3, calculate the test results based on the front and rear edge height difference △ = |U2-U1|.

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