A device and method for simulating the environmental force of fuze release when launching a rocket on the ground

Abstract

The present invention discloses a device and method for simulating the environmental force of fuze release when launching a rocket on the ground. The device includes a load-bearing tool, a test frame track, a test box and an energy storage mechanism; the load-bearing tool is used to install the fuze under test, and the test box is arranged on the load-bearing tool, which is used to provide power for the fuze under test, and at the same time, the state information output by the fuze under test is uploaded to the ground test computer, and the working and release state of the fuze under test is displayed in real time; the load-bearing tool moves along the test frame track, and the launch overload direction that the fuze under test needs to sense intersects vertically with the movement direction of the load-bearing tool on the horizontal plane; the energy storage mechanism is arranged at the end of the test frame track, which is used to provide initial power for the fuze under test, so that the load-bearing tool with the fuze under test accelerates from static to linear motion along the test frame track, and instantly changes to circular motion. The present invention can simulate the fuze launch overload when launching a rocket, and has high test efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of fuzes, and in particular to a device and method for simulating the environmental force of fuze release during rocket launch on the ground. Background Art

[0002] As a product with high safety and reliability requirements, the fuze needs to undergo actual centrifugal arming test during product development or mass production to confirm the effectiveness and reliability of the arming of its safety fuse.

[0003] The usual practice is to use high-precision centrifugal equipment to fix the safety device of the fuze on the rotating platform of the centrifuge, and make the acceleration sensing direction of the safety device coincide with the centrifugal acceleration direction of the centrifugal equipment. When the centrifugal equipment drives the safety device of the fuze to rotate around the center of the centrifuge and reaches a certain speed, the overload acceleration module of the safety device detects that the overload acceleration exceeds the design threshold and maintains this release condition for a certain period of time. After that, the safety device will complete the first-level insurance release action. For purely mechanical fuzes or electromechanical fuzes, it is necessary to wait until the centrifugal equipment stops rotating, disassemble and observe whether the first-level release device of the fuze has moved into place to determine the effectiveness of the first-level release. For fully electronic fuzes, when the centrifugal equipment is still rotating, the release status is monitored through the electrical interface to confirm the effectiveness of the first-level release. This method has the following disadvantages:

[0004] 1. Unable to simulate real launch conditions, low test efficiency

[0005] When a rocket is launched, the rate of increase of the launch overload acceleration can reach 100g / s. When using high-precision centrifugal equipment, it takes no less than 30s for the equipment platform to rotate from the beginning to the stable overload acceleration state that can meet the needs of the first-level release, and the acceleration change rate does not exceed 0.3g / s. Therefore, it is impossible to truly simulate the overload acceleration change conditions when a rocket is launched. Moreover, it is necessary to conduct experimental verification through multiple actual rocket-mounted tests. Rocket-mounted tests are not only expensive, but also require coordination among multiple parties, pre-arrangement of experimental plans, and processing of matching rockets, which is time-consuming and labor-intensive.

[0006] In addition to installing the tested product on the turntable of the centrifugal device, the test also requires a certain amount of time to increase or decrease the rotation speed, so the test efficiency is also low.

[0007] 2. The full process test of the fuze safety release function cannot be realized

[0008] According to the specifications, the fuze must be designed with at least two safety insurance release functions, and there must be a sequential logic requirement, that is, the first-level insurance must be released first, and then the second-level insurance can be released.

[0009] Therefore, when the fuse is tested for safety release, the two safety release devices also need to be tested. However, the existing centrifugal device can only test the first-level release, and cannot complete the test of the first and second-level sequential release. Summary of the invention

[0010] In view of this, the present invention provides a device and method for simulating the environmental force of the fuze release during rocket launch on the ground, which can simulate the fuze launch overload during rocket launch and has high test efficiency.

[0011] The technical solution adopted by the present invention is as follows:

[0012] A device for simulating the environmental force of fuze release when launching a rocket on the ground, comprising a load-bearing tool, a test frame track, a test box and an energy storage mechanism;

[0013] The carrier tooling is used to install the fuze under test, and the test box is arranged on the carrier tooling to provide power to the fuze under test and upload the status information output by the fuze under test to the ground test computer to display the working and release status of the fuze under test in real time;

[0014] The carrying fixture moves along the test frame track, and the launch overload direction that the fuze under test needs to sense intersects vertically with the movement direction of the carrying fixture on a horizontal plane;

[0015] The energy storage mechanism is arranged at the end of the test frame track, and is used to provide initial power for the tested fuze, so that the load-bearing tooling with the tested fuze is accelerated from static to linear motion along the test frame track, and instantly changes to circular motion.

[0016] Furthermore, the test stand track includes a linear guide rail, a circular guide rail, a position sensor, and a dual electric push rod linkage mechanism;

[0017] The 1 / 4 arc segment of the annular guide rail can be opened and closed, and the dual electric push rod linkage mechanism is connected to the 1 / 4 arc segment and the linear guide rail respectively;

[0018] In the initial state, the 1 / 4 arc segment is open, the linear guide rail abuts against the open end of the 3 / 4 arc segment, and the tangent direction of the linear guide rail coincides with the abutment; after the position sensor detects that the load-bearing tooling has completely passed through the abutment, the dual electric push rod linkage mechanism drives the 1 / 4 arc segment to close and the linear guide rail to move away.

[0019] Furthermore, the energy storage mechanism includes a lead screw, a limit block, a spring, a buckle and a force measuring display;

[0020] The rotation of the lead screw drives the limit block to move, compressing the spring to store energy; the force measuring display is used to read the compression force of the spring in real time, and when the spring reaches the set compression force, the limit block is limited by the buckle.

[0021] Furthermore, the device also includes a deceleration mechanism, which is a tensioning mechanism. The load-bearing tooling rolls with the test frame track through rollers, and the tensioning mechanism is used to provide pressure to the rollers to increase the friction between the rollers and the test frame track.

[0022] The present invention also provides a method for simulating the environmental force of fuze release during rocket launch on the ground. First, initial power is provided to the fuze under test to accelerate it from static to linear motion. Then, the linear motion state of the fuze under test is instantly changed to circular motion, and the overload acceleration in the launch overload direction is instantly increased from zero to a set launch overload state and maintained for a certain period of time, thereby providing the first-level release of the fuze under test with environmental force conditions that are the same as the overload acceleration change during rocket launch.

[0023] The present invention also provides a method for simulating the environmental force of the fuze release when launching a rocket on the ground, using the above-mentioned device, and the method steps are as follows:

[0024] Step 1: fix the fuze to be tested on the carrying fixture, and ensure that the launch overload direction that the fuze to be tested needs to sense intersects vertically with the movement direction of the carrying fixture on the horizontal plane;

[0025] Step 2: Install the load-bearing fixture with the fuze to be tested on the linear guide rail of the test frame, and the energy storage mechanism provides initial power to the load-bearing fixture to accelerate the movement along the linear guide rail of the test frame from a static state;

[0026] Step 3: When the load-bearing tool moves to the abutment point between the linear guide and the circular guide, the position sensor synchronously detects the position of the load-bearing tool, and after ensuring that the load-bearing tool has completely passed the abutment point, the electric push rod is controlled to move, driving the 1 / 4 arc segment to close and the linear guide to move away, thereby changing the motion state of the load-bearing tool from linear motion to centrifugal motion;

[0027] Step 4: The overload acceleration in the launch overload direction of the fuze under test rises from zero to the set launch overload state instantly, and is maintained for a certain period of time under the centrifugal motion of the carrying tooling, so as to provide the same environmental force conditions for the first-level release of the fuze under test as the change of overload acceleration during rocket launch; at the same time, the test box uploads the status information output by the fuze under test to the ground test computer, and the ground test computer displays the working and release status of the fuze under test in real time;

[0028] Step 5: If the fuze under test detects the environmental force condition and normally completes the first-level release, and the test box detects in real time that the fuze under test has completed the first-level release, it will provide the fuze under test with the second-level release condition;

[0029] Step 6: When the tested fuze detects that the secondary release condition is met, the secondary release is completed immediately;

[0030] Step seven, when it is necessary to end the test, decelerate the load-bearing fixture until it stops moving.

[0031] Furthermore, in the step 2, the method for the energy storage mechanism to provide initial power is: the rotation of the lead screw drives the limit block to move, the compression spring stores energy, the force measuring display reads the compression force of the spring in real time, and when the spring reaches the set compression force, the limit block is limited by the buckle; the buckle is released, and the load-bearing tooling with the fuze to be tested accelerates along the linear guide rail under the push of the spring force.

[0032] Beneficial effects:

[0033] 1. The present invention changes the linear motion of the tested fuze into circular motion instantly, truly simulates the fuze launch overload during rocket launch, and the tested fuze takes a short time to move from static to motion, with high efficiency. The present invention reduces the number of rocket-mounted tests, verifies and tests the release reliability and safety of the fuze and fuze safety device through ground tests, reduces the number of real rocket flight tests, improves test efficiency, reduces the development cycle and test costs, and provides a technical approach for efficient testing under ground conditions for the mass production and development of fuze products.

[0034] 2. The present invention can complete the full release process test of the tested fuze, verify the effectiveness of the two-stage release sequence logic, and record the process in real time to facilitate fault problem analysis.

[0035] 3. The energy storage mechanism of the present invention can provide initial power for the fuze under test to reach the overload acceleration of the first level of release, and has a simple structure and is easy to implement. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 It is a schematic diagram of the structure of the device of the present invention.

[0037] Among them, 1-tested fuze, 2-carrying fixture, 3-test box, 4-spring, 5-buckle, 6-linear guide, 7-annular guide, 8-double electric push rod linkage mechanism, 9-position sensor, 10-1 / 4 arc segment. DETAILED DESCRIPTION

[0038] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0039] The present invention provides a device for simulating the environmental force of fuze release when launching a rocket on the ground, comprising a load-bearing tool 2, a test frame, a test box 3 and an energy storage mechanism.

[0040] like Figure 1As shown, the carrier tooling 2 is used to install the fuze 1 under test, and the fuze 1 under test can be a fuze safety insurance device or a de-fire fuze; the test box 3 is set on the carrier tooling 2, and is used to provide power to the fuze 1 under test, and at the same time upload the status information output by the fuze 1 under test to the ground test computer, and display the working and release status of the fuze 1 under test in real time.

[0041] The carrying fixture 2 moves along the test frame track, and the direction of the launch overload that the tested fuze 1 needs to sense intersects vertically with the movement direction of the carrying fixture 2 in the horizontal plane; the energy storage mechanism is arranged at the end of the test frame track, which is used to provide initial power for the tested fuze 1, so that the carrying fixture 2 with the tested fuze 1 is accelerated from static to linear motion along the test frame track, and instantly changes to circular motion.

[0042] As a result, the carrying tooling 2 enters the circular orbit by relying on the inertia of movement, and the fuze or fuze safety device changes from linear motion to circular motion. The overload acceleration in the launch overload direction rises from zero to the set launch overload state instantly and is maintained for a certain time, so that the launch overload acceleration that the fuze 1 under test needs to sense is instantly changed from zero to the required overload state. This process simulates the overload change state during rocket launch, thereby providing a rocket launch overload condition for the fuze or fuze safety device under test to simulate on the ground.

[0043] In this embodiment, the test frame track includes a linear guide rail 6, a circular guide rail 7, a position sensor 9, and a dual electric push rod linkage mechanism 8. The linkage structure composed of two electric push rods with different movement directions is called a dual electric push rod linkage mechanism 8. The linear guide rail 6 and the 1 / 4 arc segment 10 are driven to move by the telescopic control linkage structure of the electric push rod. The movement mode is as follows:

[0044] The 1 / 4 arc segment 10 of the annular guide 7 can be opened and closed, and the dual electric push rod linkage mechanism 8 is respectively connected to the 1 / 4 arc segment 10 and the linear guide 6, and the movement of the 1 / 4 arc segment 10 and the linear guide 6 is respectively controlled under the extension and retraction of the two electric push rods; in the initial state, the 1 / 4 arc segment 10 is open (located obliquely above the outer side of the annular guide 7), and the linear guide 6 abuts against the open end of the 3 / 4 arc segment, and the tangent direction of the linear guide 6 coincides with the abutment; the position sensor 9 is arranged at the abutment between the linear guide 6 and the 3 / 4 arc segment. After the position sensor 9 detects that the load-bearing tooling 2 has completely passed through the abutment, the dual electric push rod linkage mechanism 8 drives the 1 / 4 arc segment 10 to close and the linear guide 6 to move away. Specifically, the 1 / 4 arc segment 10 tilts downward and abuts against the open end of the 3 / 4 arc segment to achieve closure, and the linear guide 6 moves downward to clear the abutment.

[0045] The energy storage mechanism includes a lead screw, a limit block, a spring 4, a buckle 5 and a force measuring display. In this embodiment, the buckle 5 is a trigger-type buckle. The lead screw rotates to drive the limit block to move, compressing the spring 4 to store energy. The force measuring display is used to read the compression force of the spring 4 in real time. When the spring 4 reaches the set compression force, the limit block is limited by the buckle 5. When it is necessary to launch, the buckle 5 is released, and the load-bearing tooling 2 with the fuze 1 to be tested accelerates along the linear guide 6 under the push of the spring 4.

[0046] The device of the present invention also includes a deceleration mechanism, which is a tensioning mechanism. The load-bearing tool 2 rolls with the test frame track through rollers. The tensioning mechanism is used to provide pressure to the rollers, increase the friction between the rollers and the test frame track, and reduce the circular motion speed of the load-bearing tool 2 until the load-bearing tool 2 stops circular motion.

[0047] The present invention also provides a method for simulating the environmental force of fuze release during rocket launch on the ground, that is, first providing initial power to the fuze 1 under test to accelerate it from static to linear motion; then the linear motion state of the fuze 1 under test is instantly changed to circular motion, and the overload acceleration in the launch overload direction instantly rises from zero to a set launch overload state and maintains it for a certain period of time. This process simulates the overload change state during rocket launch, thereby providing the first-level release of the fuze 1 under test with the same environmental force conditions as the overload acceleration change during rocket launch, and providing a ground test method for evaluating whether the fuze can achieve overload detection and release during rocket launch.

[0048] The present invention also provides a method for simulating the environmental force of the fuze release when launching a rocket on the ground, using the above-mentioned device, and the method steps are as follows:

[0049] Step 1: fix the fuze 1 under test on the carrying fixture 2 to ensure that the launch overload direction that the fuze 1 under test needs to sense intersects vertically with the movement direction of the carrying fixture 2 in the horizontal plane.

[0050] Step 2: Install the load-bearing fixture 2 with the fuze 1 to be tested on the linear guide rail 6 of the test frame, and the energy storage mechanism provides initial power for the load-bearing fixture 2 to accelerate the movement along the linear guide rail 6 of the test frame from a static state;

[0051] Specifically, when the energy storage mechanism provides initial power, the lead screw can be driven to rotate through the capstan, thereby driving the limit block to move the compression spring 4 to store energy; the force measuring display reads the compression force of the spring 4 in real time, and when the spring 4 reaches the set compression force, the limit block is limited by the buckle 5; the buckle 5 is released, and the load-bearing tooling 2 with the fuze 1 to be tested accelerates along the linear guide rail 6 under the push of the spring force.

[0052] Step three, when the load-bearing tooling 2 slides to the point where the linear guide 6 and the annular guide 7 abut, the position sensor 9 synchronously detects the position of the load-bearing tooling 2, and after ensuring that the load-bearing tooling 2 has completely passed the abutment, controls the double electric push rod linkage mechanism 8 to operate, driving the 1 / 4 arc segment 10 to close and the linear guide 6 to move away, thereby changing the motion state of the load-bearing tooling 2 from linear motion to centrifugal motion.

[0053] Step four, the overload acceleration in the launch overload direction of the tested fuze 1 rises from zero instantaneously to the set launch overload state, and is maintained for a certain period of time under the centrifugal motion of the carrying tooling 2, providing the same environmental force conditions as the overload acceleration change during rocket launch for the first-level release of the tested fuze 1; at the same time, the test box 3 uploads the status information (such as serial port information or level information) output by the tested fuze 1 to the ground test computer, and after the special software in the ground test computer interprets the information, it displays the working and release status of the tested fuze 1 in real time in text or image on the display screen.

[0054] Step five: if the tested fuze 1 can complete the first-level safety release normally after detecting the environmental force conditions, and the test box 3 detects in real time that the tested fuze 1 has completed the first-level safety release, it will provide the tested fuze 1 with the second-level safety release conditions, such as providing a safe power supply (pyrotechnic power supply), issuing a second-level safety release instruction, sending time parameters, etc.

[0055] Step six, when the tested fuze 1 detects that the secondary release condition is met, the secondary release is completed immediately.

[0056] Step seven, all process states of the above-mentioned fuze 1 under test are uploaded to the ground test computer through the test box 3, and are displayed and automatically recorded in real time; when it is necessary to end the test, the load-bearing tooling 2 is decelerated until the circular motion stops.

[0057] Specifically, the tensioning mechanism can be used to provide pressure for the roller, thereby increasing the friction between the roller and the test frame track, and reducing the circular motion speed of the load-bearing fixture 2 until the load-bearing fixture 2 stops the circular motion.

[0058] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A device for simulating the environmental force of the fuze release when launching a rocket on the ground, characterized in that: Including load-bearing fixtures, test frame tracks, test boxes and energy storage mechanisms; The carrier tooling is used to install the fuze under test, and the test box is arranged on the carrier tooling to provide power to the fuze under test and upload the status information output by the fuze under test to the ground test computer to display the working and release status of the fuze under test in real time; The carrying fixture moves along the test frame track, and the launch overload direction that the fuze under test needs to sense intersects vertically with the movement direction of the carrying fixture on a horizontal plane; The energy storage mechanism is arranged at the end of the test frame track, and is used to provide initial power for the tested fuze, so that the load-bearing tooling with the tested fuze is accelerated from static to linear motion along the test frame track, and instantly changes to circular motion.

2. The device for simulating the environmental force of fuze release during rocket launch as claimed in claim 1, characterized in that: The test frame track includes a linear guide rail, a circular guide rail, a position sensor, and a double electric push rod linkage mechanism; The 1 / 4 arc segment of the annular guide rail can be opened and closed, and the dual electric push rod linkage mechanism is connected to the 1 / 4 arc segment and the linear guide rail respectively; In the initial state, the 1 / 4 arc segment is open, the linear guide rail abuts against the open end of the 3 / 4 arc segment, and the tangent direction of the linear guide rail coincides with the abutment; after the position sensor detects that the load-bearing tooling has completely passed through the abutment, the dual electric push rod linkage mechanism drives the 1 / 4 arc segment to close and the linear guide rail to move away.

3. The device for simulating the environmental force of fuze release during rocket launch as claimed in claim 1, characterized in that: The energy storage mechanism includes a lead screw, a limit block, a spring, a buckle and a force measuring display; The rotation of the lead screw drives the limit block to move, compressing the spring to store energy; the force measuring display is used to read the compression force of the spring in real time, and when the spring reaches the set compression force, the limit block is limited by the buckle.

4. The device for simulating the fuze release environment force when launching a ground rocket as described in any one of claims 1 to 3, characterized in that: The device also includes a deceleration mechanism, which is a tensioning mechanism. The load-bearing tooling rolls with the test frame track through rollers, and the tensioning mechanism is used to provide pressure for the rollers to increase the friction between the rollers and the test frame track.

5. A method for simulating the environmental force of fuze release during rocket launch on the ground, characterized in that: First, initial power is provided to the fuze under test to accelerate it from static to linear motion; then the linear motion state of the fuze under test is instantly changed to circular motion, and the overload acceleration in the launch overload direction instantly rises from zero to the set launch overload state and is maintained for a certain period of time, providing the first-level release of the fuze under test with environmental force conditions that are the same as the overload acceleration change during rocket launch.

6. A method for simulating the environmental force of fuze release during rocket launch on the ground, characterized in that: Using the device as described in any one of claims 2 to 4, the method steps are as follows: Step 1: fix the fuze to be tested on the carrying fixture, and ensure that the launch overload direction that the fuze to be tested needs to sense intersects vertically with the movement direction of the carrying fixture on the horizontal plane; Step 2: Install the load-bearing fixture with the fuze to be tested on the linear guide rail of the test frame, and the energy storage mechanism provides initial power to the load-bearing fixture to accelerate the movement along the linear guide rail of the test frame from a static state; Step 3: When the load-bearing tool moves to the abutment point between the linear guide and the circular guide, the position sensor synchronously detects the position of the load-bearing tool, and after ensuring that the load-bearing tool has completely passed the abutment point, the electric push rod is controlled to move, driving the 1 / 4 arc segment to close and the linear guide to move away, thereby changing the motion state of the load-bearing tool from linear motion to centrifugal motion; Step 4: The overload acceleration in the launch overload direction of the fuze under test rises from zero to the set launch overload state instantly, and is maintained for a certain period of time under the centrifugal motion of the carrying tooling, so as to provide the same environmental force conditions for the first-level release of the fuze under test as the change of overload acceleration during rocket launch; at the same time, the test box uploads the status information output by the fuze under test to the ground test computer, and the ground test computer displays the working and release status of the fuze under test in real time; Step 5: If the fuze under test detects the environmental force condition and normally completes the first-level release, and the test box detects in real time that the fuze under test has completed the first-level release, it will provide the fuze under test with the second-level release condition; Step 6: When the tested fuze detects that the secondary release condition is met, the secondary release is completed immediately; Step seven, when it is necessary to end the test, decelerate the load-bearing fixture until it stops moving.

7. The method for simulating the environmental force of fuze release during rocket launch on the ground as claimed in claim 6, characterized in that: In the step 2, the method for the energy storage mechanism to provide initial power is: the screw rotates to drive the limit block to move, the compression spring stores energy, the force measuring display reads the compression force of the spring in real time, and when the spring reaches the set compression force, the limit block is limited by the buckle; the buckle is released, and the load-bearing tooling with the fuze to be tested accelerates along the linear guide rail under the push of the spring force.

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