CN110470174A - The high precision position measuring device and method of class air bubble inertia device test macro - Google Patents

Abstract

The invention provides a high-precision position measuring device and method for an air cannon-like inertial device testing system, and belongs to the technical field of ground testing of inertial devices. In the device of the present invention, the projectile velocity measuring tube is installed on the air cannon launch tube, and the axes of the two coincide. There is a miniature observation hole on the projectile velocity measuring tube, and the gas can enter and exit through the observation hole. The sensor, the micro-motion sensor can sense the change of gas, and the signal line of the micro-motion sensor is connected with the signal demodulation processor. When in use, install the projectile and start the air cannon; when the projectile is launched, the micro-motion sensor will have a signal output when passing through the observation hole, and the signal demodulation processor will calculate the speed through each observation hole according to the output of each micro-motion sensor. value; then analyze the data and eliminate outliers. The invention has a simple realization mode, does not need to modify the test device, does not need to add a projectile velocity measuring tube, and has strong adaptability.

Description

High-precision position measurement device and method for air cannon-like inertial device test system

technical field

The invention relates to a high-precision position measuring device and method for an air cannon-like inertial device testing system, and belongs to the technical field of ground testing of inertial devices.

Background technique

Due to the special operating environment of aircraft, missiles, and satellites, the debugging and optimization of the system operation control through the actual flight test of the prototype is costly, long-term, and even difficult to achieve. The most critical is its navigation core component—— For the testing of inertial devices, it is necessary to develop a low-cost, high-precision ground simulation system that is relatively easy to implement to complete the testing, analysis and verification of related technologies.

Compressed air cannon is a very effective and practical impact dynamic loading test equipment, which has an important application in the test of inertial devices. The rocket sled test is an effective means to verify the error model of the inertial navigation system in a composite environment, evaluate the accuracy of the error model of the guidance system, and separate the error coefficient of the inertial navigation system under the condition of large overload. The above test methods all need to accurately measure the position and velocity of the load to be tested,

The paper "Research on High-g-value Acceleration Shock Test Technology" (Xu Peng, Vibration and Shock, 2011, Volume 30, No. 4, Page 241-245) in the prior art is based on the acceleration test during the high-speed penetration of the projectile into a hard target. characteristics, developed a high-g impact test device. It consists of a first-stage air cannon, an acceleration storage test device, shells, a reflective laser velocimeter and a laser Doppler velocimeter, etc., and a high-g impact test of the bomb-loaded acceleration storage test device was carried out on the impact test device . However, the high overload test devices represented by the above-mentioned ones use reflective laser velocimeters and laser Doppler velocimeters to measure speed, which requires external modification of the device to be tested, or even exposes the entire device, which is costly to implement and has certain advantages. limitation;

Chinese Patent No. CN201711019863.3 titled "A Non-Contact Air Cannon Velocity Measuring Device and Its Method" discloses a non-contact air cannon velocity measuring device, including an air cannon launch tube and a projectile velocity test tube; an air cannon launch tube The launching trajectory of the projectile and the speed measuring trajectory of the projectile velocity measuring tube are arranged concentrically, and the inner diameter of the velocity measuring trajectory is greater than the inner diameter of the launching trajectory; the air cannon launching tube includes a tube body and a launching tube head, and the launching tube head is smaller than the size of the tube body; the air cannon The launch tube head at the front end of the launch tube is inserted into the projectile entrance of the velocity-measuring trajectory; the projectile velocity-measuring tube is provided with a projectile velocity measuring unit; the method in this patent adds a projectile velocity-measuring tube on the gun barrel, and there are detection holes on the velocity-measuring tube. There is an ultraviolet light emitting head in the detection hole. When the test device passes by, the elastic fluorescent pigment belt on the test device will capture the ultraviolet light and produce a fluorescent reaction, and then the visible light probe target in the detection hole will capture the signal. The test tube has With two consecutive detection holes, the speed of the test device can be calculated according to the distance between the detection holes and the capture time difference of the visible light probe target. However, the device of this method is relatively complicated, and the test device needs to be modified, which has certain limitations.

The invention intends to provide a high-precision position measuring device and method capable of realizing an air cannon-like inertial device testing system, without the need to modify the testing device with load, the testing principle is simple, and the engineering realization is strong.

Contents of the invention

The purpose of the present invention is to solve the above-mentioned problems in the prior art that the device to be tested needs to be modified, the device is complex, and has limitations, and then provide a high-precision position measurement device and method for a similar air cannon inertial device testing system.

The purpose of the present invention is achieved through the following technical solutions:

A high-precision position measurement device for an air cannon inertial device test system, including: an air cannon launch tube, a projectile velocity measurement tube, an observation hole, a micro-motion sensor and a signal demodulation processor;

Among them, the projectile velocity measuring tube is installed on the air cannon launch tube, and the axes of the two coincide. There is a miniature observation hole on the projectile velocity measuring tube, and the gas can enter and exit through the observation hole. A micro-motion sensor is installed on the outer end surface of the observation hole close to the projectile velocity measuring tube. The micro-motion sensor can sense the change of gas, and the signal line of the micro-motion sensor is connected with the signal demodulation processor.

The number of the observation holes is three or more.

The microsensor can be replaced by other sensors, for example: capacitive microswitch, inductive microswitch, resistive microswitch, optical microswitch and so on.

A measuring method for a high-precision position measuring device of an air cannon inertial device testing system comprises the following steps:

Step 1: Install the projectile velocity measuring tube on the air cannon launch tube, install the micro-motion sensor above the observation hole of the projectile velocity measuring tube, and connect the signal line of the micro-motion sensor to the signal demodulation processor;

Step 2: Install the projectile and start the air cannon;

Step 3: The projectile is launched. When the projectile passes through the observation hole, the micro-motion sensor will have a signal output. The signal demodulation processor performs calculation according to the output of each micro-motion sensor, and calculates the speed value passing through each observation hole;

Step 4: Analyze the data and eliminate outliers.

The fourth step also includes the following steps: using the experimental calibration method to measure the actual microdynamic value of the projectile passing through the observation hole through several experiments, and then setting an appropriate threshold to prevent mismeasurement and improve accuracy.

The beneficial effects of the present invention are:

The invention has a simple implementation mode, does not need to modify the projectile (test device), and can realize high-precision position measurement without complicated sensors.

The invention can directly add an observation hole and a micro-motion sensor on the basis of the original air cannon launch tube, without adding a projectile velocity measuring tube, simplifies the process design, and has strong adaptability.

Description of drawings

Fig. 1 is a structural schematic diagram of a high-precision position measuring device of the air cannon-like inertial device testing system of the present invention.

Fig. 2 is a schematic structural diagram of Embodiment 2 of the high-precision position measuring device of the air cannon-like inertial device testing system of the present invention.

Reference numerals in the figure, 1 is an air cannon launch tube, 2 is a projectile velocity measuring tube, 3 is an observation hole, 4 is a micro-motion sensor, and 5 is a signal demodulation processor.

Detailed ways

The present invention will be described in further detail below in conjunction with the accompanying drawings: the present embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation is provided, but the protection scope of the present invention is not limited to the following embodiments.

As shown in Figure 1, the high-precision position measuring device of the air cannon inertial device test system involved in this embodiment includes: air cannon launch tube 1, projectile velocity measuring tube 2, observation hole 3, micro-motion sensor 4 and signal solution call processor 5;

Among them, the projectile velocity measuring tube 2 is installed on the air cannon launch tube 1, and the axes of the two coincide. There is a miniature observation hole 3 on the projectile velocity measuring tube 2, and gas can enter and exit through the observation hole 3. A micro-motion sensor 4 is installed on the end face, and the micro-motion sensor 4 can sense the change of gas, and the signal line of the micro-motion sensor 4 is connected with the signal demodulation processor 5 .

The number of the observation holes 3 is three or more.

The microsensor 4 can be replaced by other sensors, such as capacitive microswitches, inductive microswitches, resistive microswitches, optical microswitches and the like.

A measuring method for a high-precision position measuring device of an air cannon inertial device testing system comprises the following steps:

Step 1: install the projectile velocity measuring tube 2 on the air cannon launch tube 1, install the micro-motion sensor 4 above the observation hole 3 of the projectile velocity measuring tube 2, and connect the signal line of the micro-motion sensor 4 to the signal demodulation processor 5;

Step 2: Install the projectile and start the air cannon;

Step 3: The projectile is launched, and the micro-motion sensor 4 will have a signal output when passing through the observation hole 3, and the signal demodulation processor 5 performs calculation according to the output of each micro-motion sensor 4, and calculates the speed value passing through each observation hole 3;

Step 4: Analyze the data and eliminate outliers.

The fourth step also includes the following steps: using the experimental calibration method to measure the actual micro-dynamic value of the projectile passing through the observation hole 3 through several experiments, and then setting an appropriate threshold to prevent mismeasurement and improve accuracy.

Example 1

As shown in Figure 1, in this embodiment, the projectile velocity measuring tube 2 is installed on the air cannon launching tube 1, the axes of the two coincide, and the projectile velocity measuring tube 2 and the air cannon launching tube 1 have the same diameter, which will not change or affect the original system After the projectile is launched, it can enter the projectile velocimetry tube 2 through the air cannon launch tube 1, and the projectile velocimetry tube 2 is provided with a miniature observation hole 3, and the gas when the projectile is launched can enter and exit through the observation hole 3, and in the observation hole 3 A micro-motion sensor 4 is installed near the outer end surface of the projectile velocity measuring tube 2, and the micro-motion sensor 4 can sense the change of the gas. The signal is passed to the signal demodulation processor 5 .

In actual work, the air bomb explodes, and after the projectile is launched, the gas behind the projectile expands rapidly. When the projectile passes through the velocity measuring tube 2, the gas will be ejected from the observation hole 3. The micro-motion sensor 4 can record the signal and demodulate the signal The processor 5 can measure and record the time passing through each observation hole 3, the distance of these observation holes 3 is known, and the speed of the projectile passing can be calculated according to the time difference, in order to eliminate the large deviation value, three consecutive observations can be used The velocity values of holes 3 are averaged, and more observation holes 3 can be set, so that the velocity values passing through multiple observation holes 3 within a certain distance can be recorded.

Example 2

As shown in Figure 2, the difference between this embodiment and Embodiment 1 is that this embodiment does not need to set the projectile velocity measuring tube 2, and the observation hole 3 and the micro-motion sensor can be directly added on the basis of the original air cannon launch tube 1 4. The specific structure is: the air cannon launch tube 1 is provided with a miniature observation hole 3, and the gas can enter and exit through the observation hole 3 when the projectile is launched, and a micro-motion sensor is installed on the outer end surface of the observation hole 3 close to the air cannon launch tube 1 4. The micro-motion sensor 4 can sense the change of gas, the signal line of the micro-motion sensor 4 is connected to the signal demodulation processor 5, and the micro-motion sensor 4 can transmit the signal to the signal demodulation processor 5 through the signal line. During actual work, the air bomb explodes, and after the projectile is launched, the gas behind the projectile expands rapidly. When passing through the air cannon launch tube 1, the gas will eject from the observation hole 3. The micro-motion sensor 4 can record the signal, and the signal solution Adjustment processor 5 can measure and record the time passing through each observation hole 3, the distance of these observation holes 3 is known, can calculate the velocity of projectile passing through according to time difference, in order to eliminate large deviation value, can use three consecutive The velocity values of the observation holes 3 are averaged, and more observation holes 3 can be set, so that the velocity values passing through a plurality of observation holes 3 within a certain distance can be recorded. Compared with Embodiment 1, this embodiment does not need to add a projectile velocity measuring tube, simplifies the process design, and has strong adaptability.

Example 3

The measuring method of the high-precision position measuring device using the above-mentioned air cannon inertial device testing system comprises the following steps:

Step 1, install the projectile velocity measuring tube 2 on the air cannon launch tube 1, install the micro-motion sensor 4 above the observation hole 3 of the projectile velocity measuring tube 2, and connect the signal line of the micro-motion sensor 4 to the signal demodulation processor 5.

Step 2. Install the projectile and start the air cannon;

Step 3, the projectile is launched, and the micro-motion sensor 4 will have a signal output when passing through the observation hole 3, and the signal demodulation processor 5 performs calculation according to the output of each micro-motion sensor 4, and calculates the speed passing through each observation hole 3 value;

Step 4. Analyze the data and eliminate outliers.

This method is simple to implement, does not need to modify the projectile (test device), does not require complicated sensors, and can even directly add observation holes and micro-motion sensors on the basis of the original air cannon launch tube without adding a projectile velocity measuring tube. That is, the process design is simplified and the adaptability is strong.

Further, other sensors, such as capacitive microswitches, inductive microswitches, resistive microswitches and optical microswitches, can also be used to realize the measurement of projectiles passing through the observation hole 3 .

Further, in order to distinguish whether the projectile passes through the observation hole 3, the experimental calibration method can be used, that is, to measure the actual micro-dynamic value of the projectile passing through the observation hole 3 through several experiments, and then set an appropriate threshold to prevent mismeasurement and improve Accuracy.

The above are only preferred specific implementations of the present invention. These specific implementations are all based on different implementations under the overall concept of the present invention, and the scope of protection of the present invention is not limited thereto. Anyone familiar with the technical field Within the technical scope disclosed in the present invention, any changes or substitutions that can be easily conceived by a skilled person shall fall within the protection scope of the present invention. Therefore, the protection scope of the present invention should be determined by the protection scope of the claims.

Claims (5)

1. the high precision position measuring device of class air bubble inertia device test macro characterized by comprising air bubble transmitting Manage (1), bullet pitot tube (2), peephole (3), jogging sensor (4) and signal demodulation processor (5)；

Wherein, bullet pitot tube (2) is mounted on air bubble transmitting tube (1), and the two axis is overlapped, and bullet pitot tube has on (2) Miniature peephole (3), gas can be entered and left by peephole (3), and in peephole (3), the outer end face close to bullet pitot tube (2) is pacified Equipped with jogging sensor (4), jogging sensor (4) can perceive the variation of gas, the signal wire and signal of jogging sensor (4) Demodulation processor (5) is connected.

2. the high precision position measuring device of class air bubble inertia device test macro according to claim 1, feature It is, the number of the peephole (3) is three or three or more.

3. the high precision position measuring device of class air bubble inertia device test macro according to claim 1, feature It is, the jogging sensor (4) could alternatively be other sensors, such as: condenser type microswitch, inductance type fine motion are opened Pass, resistance-type microswitch, optics microswitch etc..

4. the high precision position measuring device of class air bubble inertia device test macro according to claim 1,2 or 3 Measurement method, which comprises the following steps:

Step 1: bullet pitot tube (2) is mounted on air bubble transmitting tube (1), and jogging sensor (4) is mounted on bullet and tests the speed Above the peephole (3) for managing (2), the signal wire of jogging sensor (4) is connected with signal demodulation processor (5)；

Step 2: installation bullet starts air bubble；

Step 3: pellet injection has signal output, signal demodulation processor by jogging sensor (4) when peephole (3) (5) it is resolved according to the output of each jogging sensor (4), calculates the velocity amplitude by each peephole (3)；

Step 4: analysis data reject outlier.

5. wanting the measurement side of the 4 high precision position measuring devices for seeking the class air bubble inertia device test macro according to right Method, which is characterized in that the step 4 is further comprising the steps of: using experimental calibration method, is passed through by measuring bullet several times The practical microkinetic numerical value of peephole (3) is crossed, a threshold value appropriate is then set, is accidentally surveyed for preventing, improves accuracy.