Device and method for testing instantaneous impact resistance of gyroscope

Abstract

The invention relates to a device and a method for testing the instantaneous impact resistance of a gyroscope, and solves the problems that the output error of the gyroscope introduced by impact cannot be directly measured and the width of an impact peak is relatively wide in the impact resistance test of the gyroscope in the existing method. The device comprises a base (1), a gyroscope (2), an inertial navigation device (3) and an impact baffle (4), the base (1) is horizontally placed on the ground, the gyroscope (2) and the inertial navigation device (3) are installed on the horizontal plane of the base (1), the gyroscope (2) is axially perpendicular to the horizontal plane of the base (1), and the impact baffle (4) is installed on the side face of the base (1). According to the invention, a reliable reference value is provided for the angle change value measured by the gyroscope, the measurement precision of the angle integral error of the gyroscope in the instantaneous impact process is improved, and the application range of the device and the method is expanded.

Description

Technical Field

[0001] The invention relates to a device and method for testing the instantaneous impact resistance of a gyroscope, belonging to the technical field of gyroscope testing, and is particularly suitable for testing the instantaneous impact resistance of a high-precision fiber optic gyroscope. Background Art

[0002] For gyroscopes, shock and vibration resistance is a crucial performance metric. As gyroscopes continue to expand in scope and face increasingly stringent requirements, modern high-precision gyroscopes are increasingly being applied to autonomous vehicles, smart cars, and other fields, creating increasingly complex operating environments. Gyroscope output errors caused by occasional transient shocks are a critical issue that urgently needs attention and resolution. This presents a significant challenge for high-precision gyroscopes in current and future applications. Therefore, testing the transient shock resistance of gyroscopes, particularly high-precision gyroscopes, is crucial to further enhance their performance.

[0003] Currently, shock testing of gyroscopes is limited by the test equipment used. The width of the shock peak is usually on the order of milliseconds or longer. In addition, traditional shock testing of gyroscopes only focuses on the change in their zero bias value, without measuring the angular velocity integral error generated during the shock process. This does not directly correspond to the output error of the gyroscope during the shock process in actual application, and cannot directly and effectively characterize its shock resistance. Existing devices and methods do not propose a method that can directly test the error generated by the gyroscope during the shock process, and the width of the shock peak also fails to meet the conditions of actual application. Therefore, there is an urgent need for a device and method that can directly test the output error generated by the gyroscope when responding to instantaneous shocks, and has the ability to provide a shock peak with a width less than the order of milliseconds. Summary of the invention

[0004] The technical problem solved by the present invention is to overcome the problems that the existing method cannot directly measure the gyroscope output error introduced by the impact and the impact peak width is relatively wide in the gyroscope impact resistance test, and provide a testing device and method for the instantaneous impact resistance of the gyroscope.

[0005] In order to achieve the above purpose, the technical solution adopted by the present invention is:

[0006] A device for testing the instantaneous impact resistance of a gyroscope comprises a base 1, a gyroscope 2, an inertial navigation device 3 and an impact baffle 4; the base 1 is placed horizontally on the ground, the gyroscope 2 and the inertial navigation device 3 are mounted on the horizontal plane of the base 1, the gyroscope 2 is axially perpendicular to the horizontal plane of the base 1, and the impact baffle 4 is mounted on the side of the base 1.

[0007] The base 1 has good rigidity and needs to be ensured not to deform or resonate during the impact process.

[0008] The described gyroscope 2 is tightly and rigidly connected to the base 1 to ensure that there is no relative displacement between the gyroscope 2 and the base 1 and the impact acting on the base 1 can be directly transmitted to the gyroscope 2.

[0009] The described inertial navigation device 3 is tightly connected to the base 1 to ensure that there is no relative displacement between the inertial navigation device 3 and the base 1. The inertial navigation device 3 and the base 1 are connected through a shock absorber to ensure that the impact acting on the base 1 does not affect the attitude measurement accuracy of the inertial navigation device 3.

[0010] The described impact baffle 4 can be disassembled and replaced, and different rigid materials can be used to change the width of the impact acting on the base 1.

[0011] Furthermore, a method for testing using the device of the present invention: When starting the test, the output data of the gyroscope 2 is collected, and at the same time, the inertial navigation device 3 is used for attitude measurement to obtain the attitude parameters in the initial state; subsequently, an impact is applied to the impact baffle 4. After the impact is completed, the inertial navigation device 3 is used again for attitude measurement to obtain the attitude parameters in the termination state; according to the difference between the two (initial state and termination state) attitude measurements of the inertial navigation device 3 and the angular velocity integration of the output data of the gyroscope 2, the measurement error generated by the gyroscope 2 during the impact process can be calculated, and this error characterizes the anti-instantaneous impact ability of the gyroscope 2.

[0012] The impact acting on the impact baffle 4 is generated by a rigid mass block hitting, and the size of the impact can be changed according to actual needs.

[0013] The advantages of the present invention compared with the prior art are as follows: For the impact test of existing gyroscopes, the change value of the zero bias of the gyroscope is measured as a sign, which cannot be directly corresponding to the output error generated by the gyroscope during impact in actual use, and the width of the impact peak is in the millisecond and above magnitude, which is not completely consistent with the sub-millisecond magnitude that can be achieved in actual use. The test device and method for the anti-instantaneous impact ability of the gyroscope involved in the present invention measure the attitude before and after impact using an inertial navigation device during the impact process to obtain the reference value of the angle change during the impact process, and calculate the output error of the gyroscope based on this reference value, thereby measuring the anti-impact ability of the gyroscope. This result can be directly corresponding to the error that may be generated by the gyroscope during impact in actual use. And in the test method involved in the present invention, the impact is applied by the way of a mass block hitting, and an impact peak width lower than the millisecond magnitude can be obtained. By changing the material of the impact baffle, the impact peak width can be changed, so as to cover the instantaneous impact conditions in the actual use environment. Description of the Drawings

[0014] Figure 1 It is a schematic structural diagram of the device of the present invention.

[0015] Figure 2 It is a top view of the structure of the device of the present invention.

[0016] In the figure: 1. Base; 2. Gyroscope; 3. Inertial navigation unit; 4. Impact baffle. DETAILED DESCRIPTION

[0017] The present invention will be described in detail below with reference to the accompanying drawings and embodiments.

[0018] like Figure 1 As shown, a test device for the instantaneous impact resistance of a gyroscope of the present invention includes a base 1, a gyroscope 2, an inertial navigation device 3 and an impact baffle 4; the base 1 is placed horizontally on the ground, the gyroscope 2 and the inertial navigation device 3 are installed on the horizontal plane of the base 1, the gyroscope 2 is axially perpendicular to the horizontal plane of the base 1, and the impact baffle 4 is installed on the side of the base 1.

[0019] The base 1 has good rigidity and needs to be ensured not to deform or resonate during the impact process.

[0020] The gyroscope 2 is tightly and rigidly connected to the base 1 to ensure that the gyroscope 2 and the base 1 do not undergo relative displacement and that the impact energy acting on the base 1 is directly transmitted to the gyroscope 2 .

[0021] The inertial navigation device 3 is tightly connected to the base 1 to ensure that the inertial navigation device 3 and the base 1 do not undergo relative displacement. The inertial navigation device 3 and the base 1 are connected via a shock absorber to ensure that the impact acting on the base 1 does not affect the attitude measurement accuracy of the inertial navigation device 3.

[0022] The impact baffle 4 can be disassembled and replaced, and materials with different rigidities can be used to change the width of the impact acting on the base 1.

[0023] Furthermore, a method for testing using the device of the present invention is as follows: when the test starts, the output data of the gyroscope 2 is collected, and the inertial navigation device 3 is used to perform attitude measurement to obtain initial state attitude parameters; then, an impact is applied to the impact baffle 4, and after the impact is completed, the inertial navigation device 3 is used again to perform attitude measurement to obtain the attitude parameters of the final state; based on the difference between the two attitude measurements (initial state and final state) of the inertial navigation device 3 and the angular velocity integral of the output data of the gyroscope 2, the measurement error generated by the gyroscope 2 during the impact process can be calculated, and the error represents the ability of the gyroscope 2 to resist instantaneous impact.

[0024] The impact on the impact baffle 4 is generated by the impact of the rigid mass block, and the magnitude of the impact can be changed according to actual needs.

[0025] In summary, the present invention is a test device and method for anti-instantaneous impact ability, which is particularly applicable to the field of high-precision gyroscope testing. For the test of the anti-instantaneous impact ability of the gyroscope, during the impact process, an inertial navigation device is used to measure the attitude before and after the impact to obtain a reference value of the angle change during the impact process, and the output error of the gyroscope is calculated based on this reference value, thereby measuring the anti-impact ability of the gyroscope. This result can directly correspond to the error that may occur during the impact in the actual use of the gyroscope. And in the test method involved in the present invention, the impact is applied by the way of the mass block impact, and an impact peak width lower than the millisecond level can be obtained. By changing the material of the impact baffle, the impact peak width can be changed, so as to cover the instantaneous impact conditions in the actual use environment.

[0026] The content not described in detail in the specification of the present invention belongs to the prior art well-known to those skilled in the art.

Claims

1. A test device for the instantaneous impact resistance of a gyroscope, characterized in that: It includes a base (1), a gyroscope (2), an inertial navigation device (3) and a shock baffle (4); the base (1) is horizontally placed on the ground, the gyroscope (2) and the inertial navigation device (3) are installed on the horizontal plane of the base (1), the axis of the gyroscope (2) is perpendicular to the horizontal plane of the base (1), and the shock baffle (4) is installed on the side of the base (1).

2. The test device for the instantaneous impact resistance of a gyroscope according to claim 1, characterized in that: The base (1) has good rigidity and will not deform or resonate during the impact process.

3. A test device for the anti-instantaneous impact ability of a gyroscope according to claim 1, characterized in that: The gyroscope (2) is tightly and rigidly connected to the base (1), and there will be no relative displacement between the gyroscope (2) and the base (1), and the impact acting on the base (1) can be directly transmitted to the gyroscope (2).

4. The test device for the anti-instantaneous impact ability of a gyroscope according to claim 1, characterized in that: The inertial navigation device (3) is tightly connected to the base (1), and there will be no relative displacement between the inertial navigation device (3) and the base (1). The inertial navigation device (3) and the base (1) are connected through a shock absorber, and the impact acting on the base (1) will not affect the attitude measurement accuracy of the inertial navigation device (3).

5. The testing device for the anti-instantaneous impact ability of a gyroscope according to claim 1, characterized in that: The shock baffle (4) can be disassembled and replaced, and materials with different rigidities can be used to change the width of the impact acting on the base (1).

6. A method of testing using the device described in claim 1, characterized in that: It includes the following steps: When starting the test, the output data of the gyroscope (2) is collected, and at the same time, the inertial navigation device (3) is used to measure the attitude to obtain the attitude parameters in the initial state; then an impact is applied to the shock baffle (4). After the impact is completed, the inertial navigation device (3) is used again to measure the attitude to obtain the attitude parameters in the termination state; according to the difference between the two attitude measurements of the inertial navigation device (3) in the initial state and the termination state and the angular increment, i.e., the angular velocity integral, of the output data of the gyroscope (2), the measurement error generated by the gyroscope (2) during the impact process is calculated, and this error characterizes the anti-instantaneous impact ability of the gyroscope (2).

7. A test method for the anti-instantaneous impact ability of a gyroscope according to claim 6, characterized in that: The impact acting on the shock baffle (4) is generated by the impact of a rigid mass block, and the magnitude of the impact can be adjusted according to actual requirements.

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