CN110440829B - High-overload testing device and method for inertial device - Google Patents
High-overload testing device and method for inertial device Download PDFInfo
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- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
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Abstract
The invention provides a high overload test device and method for an inertia device, and belongs to the field of ground test of inertia devices. The parachute cabin, the main test cabin and the auxiliary cabin are arranged in the bomb body, the parachute cabin, the main test cabin and the auxiliary cabin in the test bomb are sequentially connected, the adjustable outer wings are arranged outside the bomb body, a parachute is stored in the parachute cabin, the high-precision test assembly and the controller are arranged in the main test cabin, and the inertial measurement unit to be tested is arranged in the auxiliary cabin; the gun platform is arranged on the ground, the gun platform is connected with the gun platform controller through a cable, the shell is arranged on the gun platform, and the match box and the test shell are arranged in the shell. The invention provides the device and the method for testing the high overload performance of the inertia device, which can realize high overload, long effective test interval of error excitation and convenient engineering realization, and has the advantages of simple principle, low cost, strong engineering realization, capability of having a plurality of effective test intervals in each test and high test efficiency.
Description
Technical Field
The invention relates to a high overload test device and method for an inertia device, and belongs to the field of ground test of inertia devices.
Background
Typical high overload tests include precision centrifuge tests and low frequency line shaker table tests in a laboratory environment, as well as on-board, and rocket sled tests that simulate the environment in which the inertial instrument is used. Among the test methods, the centrifuge with the reverse rotation platform (also called a dual-shaft centrifuge) can provide a constant or harmonic linear acceleration reference person with large overload for a meter to be tested, and becomes an important means for evaluating the precision and performance of a gyro accelerometer and a flexible accelerometer. The low-frequency line vibration table can provide low-frequency large-overload sinusoidal linear acceleration for the inertia instrument to convey people, and compared with a precision centrifuge, the low-frequency line vibration table has the characteristics of small parasitic angular motion, low development and test cost, but slightly low precision. Vehicle-mounted and airborne tests are the commonly adopted precision assessment means of the inertial navigation system at present, and have the defect that error excitation is insufficient and can only reach a few g.
The rocket sled test is an effective means for verifying an error model of the inertial navigation system in a composite environment, evaluating the accuracy of the error model of the guidance system and separating an error coefficient of the inertial navigation system under a large overload condition. The rocket sled test technology of the inertial navigation system requires rigorous precision of rocket sled parameters and high cost, and belongs to a new test technology in China.
Xupeng et al developed a high-g-value impact test device in high-g-value acceleration impact test technology research (vibration and impact, 2011, 30 vol, 4 th, page number 241-. The impact test device is composed of a primary air cannon, an acceleration storage test device, a cannonball, a reflection type laser velocimeter, a laser Doppler velocimeter and the like, and a high-g-value impact test of the missile-borne acceleration storage test device is carried out on the impact test device; the high overload test device and method represented by high-g-value acceleration impact test technical research have the advantages of high implementation cost, few effective test intervals and certain limitation.
Liu Jian ripples et al in "inertia measurement device rocket sled test overload curve design method" (China technical science of inertia, 2012,20 volume, 1 st stage, 117) 210 pages) provide an overload curve design method suitable for an inertia measurement device rocket sled test, stress analysis is performed on main stress in the motion process of the rocket sled, on the basis, rocket sled motion is divided into three sections, including a driving section, a free sliding section and a water braking section, and a basic motion equation of the rocket sled is established; the inertial navigation system rocket sled test technology represented by the inertial measurement unit rocket sled test overload curve design method requires rigorous precision of rocket sled rail parameters and high cost, and belongs to a new test technology in China.
Chinese patent No. CN201020181149.1 entitled MEMS Gyro test System with double-shaft turntable discloses an MEMS gyro test system with double-shaft turntable, which combines a double-shaft turntable with a high-low temperature box and an MEMS gyro sensor test unit to form a full-automatic MEMS gyro comprehensive test system, the temperature box provides temperature environment conditions for MEMS gyro test so as to calibrate the MEMS gyro at various temperatures to increase the calibration accuracy, thereby solving the problems of high speed, test temperature control requirements and the like required by the MEMS gyro test and improving the test efficiency; the testing device and method based on the patent number CN201020181149.1 named as MEMS gyro testing system with double-shaft turntable can not realize high overload test, has insufficient error excitation, and still has certain limitation in practical application.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and further provides a device and a method for testing high overload of an inertial device.
The purpose of the invention is realized by the following technical scheme:
a high overload test device for an inertia device comprises a fort, a shell, a fort controller, a match box and a test bomb, wherein the test bomb comprises a parachute cabin, a main test cabin, an auxiliary cabin, a bomb body and outer wings, the parachute cabin, the main test cabin and the auxiliary cabin are installed in the bomb body, the parachute cabin, the main test cabin and the auxiliary cabin in the test bomb are sequentially connected, the outer part of the bomb body is provided with the adjustable outer wings, a parachute is stored in the parachute cabin, a high-precision test combination and a controller are installed in the main test cabin, and an inertia group to be tested is installed in the auxiliary cabin; the gun platform is arranged on the ground, the gun platform is connected with the gun platform controller through a cable, the shell is arranged on the gun platform, and the match box and the test shell are arranged in the shell.
The invention relates to a high overload test device for an inertial device, wherein a bullet body is made of titanium alloy.
According to the high overload test device for the inertia device, the cannonball can be replaced by cannonball pipes with different specifications according to test requirements, and the matchbox can be replaced by the matchbox according to the test requirements.
A high overload test method for an inertia device is provided, which comprises the following steps:
firstly, the method comprises the following steps: preparation process of the test:
calculating data of required shells, shell attack angles and explosive quantities according to the requirement of test indexes, then installing shells and gunpowder boxes with corresponding specifications, installing an inertial unit to be tested in an auxiliary bin of the test shell, placing the test shell into the shells, adjusting the shell attack angles through a gun platform controller and starting a system;
II, secondly: the testing process comprises the following steps:
the fire box is ignited for explosion, the high-pressure gas pushes the test bomb to move forward and lift off along the bomb, the test bomb starts to land and open after reaching the highest point, and the test bomb safely lands and is recovered at the last;
thirdly, the method comprises the following steps: determination of valid test intervals:
1) the section of the in-tube test interval for pushing the test bomb to move in the cannonball after the explosive box explodes is large in overload and can reach tens of thousands of grams;
2) the test bomb leaves the cannonball to reach the space free test interval before the parachute is opened, and the posture and the acceleration of the bomb body can be adjusted through the outer wing of the test bomb in the space free test interval;
3) the section from the parachute opening to the front of the landing ground is tested to form a parachute deceleration test interval, and different deceleration information is obtained mainly through active deceleration of the parachute, so that different excitations are provided for the inertia device to be tested;
fourthly, the method comprises the following steps: collecting test data:
1) the high-precision measurement combination is arranged in a main test cabin of the test bomb, and the inertial measurement unit to be tested is arranged in an auxiliary cabin, and the running information of the test bomb is measured and stored;
2) and determining the flight information of the test bomb through a photoelectric tracking device on the ground.
The invention relates to a high overload test method for an inertial device, wherein a GPS/Beidou, an inertial combination and a magnetic beacon are adopted in a high-precision measurement combination.
The invention provides a device and a method for testing the high overload performance of an inertia device, which can realize high overload, long effective test interval of error excitation and convenient engineering realization.
Drawings
Fig. 1 is a structural diagram of a high overload testing device for an inertial device according to the present invention.
Fig. 2 is a structural diagram of a test cartridge in the high overload test device for the inertia device according to the invention.
The reference numbers in the figures are: 1 is a fort; 2 is a shell; 3 is a gun platform controller; 4 is a match box; 5 is a test bomb; 5-1 is a parachute cabin; 5-2 is a main test bin; 5-3 is an auxiliary bin; 5-4 is an elastomer; 5-5 are outer wings.
Detailed Description
The invention will be described in further detail below with reference to the accompanying drawings: the present embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation is given, but the scope of the present invention is not limited to the following embodiments.
The first embodiment is as follows: as shown in fig. 1, the high overload test device for an inertia device according to the present embodiment includes a fort, a shell, a fort controller, a matchbox, and a test bomb, wherein the test bomb includes a parachute cabin, a main test cabin, an auxiliary cabin, a bomb body, and an outer wing, the parachute cabin, the main test cabin, and the auxiliary cabin are installed in the bomb body, the parachute cabin, the main test cabin, and the auxiliary cabin in the test bomb are sequentially connected, the adjustable outer wing is installed outside the bomb body, a parachute is stored in the parachute cabin, a high precision test assembly and a controller are installed in the main test cabin, and an inertial unit to be tested is installed in the auxiliary cabin; the gun platform is arranged on the ground, the gun platform is connected with the gun platform controller through a cable, the shell is arranged on the gun platform, and the match box and the test shell are arranged in the shell.
The material of the elastic body is titanium alloy.
The cannonball can be changed into cannonball pipes with different specifications according to the test requirements, and the matchbox can be changed into matchboxes with different specifications according to the test requirements.
The gun platform is arranged on the ground and is connected with the gun platform controller through a cable, the shell is arranged on the gun platform, the gun barrel can be replaced by gun barrels with different specifications according to test requirements, the gunpowder box also has different specifications and is replaced according to test requirements, the gunpowder box is arranged in the gun barrel, the test bomb is also arranged in the gun barrel, and the test bomb is pushed out of the gun barrel by thrust generated by combustion and explosion of the gunpowder box. The parachute cabin, the main test cabin and the auxiliary cabin of the test bomb are sequentially connected and finally loaded into the titanium alloy bomb body, and the bomb body plays a role in protecting the three cabins so that the bomb body can safely land on the ground. The parachute cabin is stored with parachutes for testing final safe recovery of the deceleration before the bomb lands, the main testing cabin is provided with a high-precision testing combination and a controller, the combination can measure the pose, speed, acceleration and other information of the testing bomb and serve as comparison data of the precision of the inertial group to be tested, the auxiliary cabin is provided with the inertial group to be tested, and the data is transmitted to the controller in the main testing cabin for storage. The controller of the main test bin is responsible for the parachute opening instruction of the parachute and the adjustment of the outer wings of the projectile body at the same time.
Example two: as shown in fig. 1, the method for testing high overload of an inertial device according to this embodiment includes the following specific steps:
firstly, preparation process of testing:
calculating a required gun barrel, a required gun barrel attack angle and required ignition charge according to the requirement of a test index, then installing the gun barrel and the ignition charge with corresponding specifications, installing an inertial unit to be tested in an auxiliary bin of a test bomb, setting an parachute opening instruction for a controller of a main test bin according to calculation data, placing the test bomb into the gun barrel, adjusting the gun barrel attack angle through a gun platform controller and starting a system;
II, measurement process:
the explosive box is ignited and exploded, high-pressure gas pushes the test bomb to move forward along the gun barrel, the test bomb is lifted off and starts to fall after reaching the highest point, the main test bin controller of the test bomb sends an parachute opening instruction after reaching the specified height, and the test bomb safely lands and is recovered at the last time;
thirdly, determining an effective test interval:
1) after the explosive box explodes, the test bomb is pushed to travel in the section of the 'in-tube test interval' of the gun tube, and the overload in the section of the 'in-tube test interval' is large and can reach tens of thousands of grams;
2) the test bomb leaves the gun barrel to the section of space free test interval before the parachute opening instruction is opened, and the posture and the acceleration of the bomb body are adjusted through the outer wing of the test bomb in the section of space free test interval;
3) the section from the parachute opening to the front of the landing ground is tested to form a parachute deceleration test interval, and different deceleration information is obtained mainly through active deceleration of the parachute, so that different excitations are provided for the inertia device to be tested;
fourthly, collecting test data:
1) the high-precision measurement combination is arranged in the main inertia bin of the test bomb and used for measuring and storing the running information of the test bomb;
2) and determining the flight information of the test bomb through a photoelectric tracking device on the ground.
The high-precision measurement combination adopts GPS/Beidou, inertia combination, magnetic beacons and the like.
In order to realize high-precision test of the inertia device to be tested, accurate actual flight data of the test bomb is required, and the actual flight data can be obtained by two methods in the collection of test data, but is not limited to the above method.
The above description is only a preferred embodiment of the present invention, and these embodiments are based on different implementations of the present invention, and the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (4)
1. The high overload test method of the inertia device is characterized by using an inertia device high overload test device, wherein the inertia device high overload test device comprises a gun platform (1), a shell (2), a gun platform controller (3), a gunpowder box (4), a test bullet (5) and a photoelectric tracking and aiming device;
the testing bomb (5) comprises a parachute cabin (5-1), a main testing cabin (5-2), an auxiliary cabin (5-3), a bomb body (5-4) and an outer wing (5-5), the parachute cabin (5-1), the main testing cabin (5-2) and the auxiliary cabin (5-3) are installed in the bomb body (5-4), the parachute cabin (5-1), the main testing cabin (5-2) and the auxiliary cabin (5-3) in the testing bomb (5) are sequentially connected, the adjustable outer wing (5-5) is installed outside the bomb body (5-4), a parachute is stored in the parachute cabin (5-1), a high-precision testing assembly and a controller are installed in the main testing cabin (5-2), and an inertial set to be tested is installed in the auxiliary cabin (5-3); the gun platform (1) is arranged on the ground, the gun platform (1) is connected with the gun platform controller (3) through a cable, the cannonball (2) is arranged on the gun platform (1), and the gunpowder box (4) and the test bomb (5) are arranged in the cannonball (2);
the photoelectric tracking and aiming device is positioned on the ground and used for determining the flight information of the test bomb (5);
the high overload test method of the inertia device comprises the following steps:
firstly, the method comprises the following steps: preparation process of the test:
calculating the required data of the attack angle and the explosive amount of the cannonball (2), the cannonball (2) according to the requirement of a test index, then installing the cannonball (2) and the explosive box (4) with corresponding specifications, installing the inertial measurement unit to be tested in an auxiliary bin (5-3) of the test bomb (5), placing the test bomb (5) into the cannonball (2), adjusting the attack angle of the cannonball (2) through a gun platform controller (3), and starting a system;
II, secondly: the testing process comprises the following steps:
the explosive box (4) is ignited for explosion, the high-pressure gas pushes the test bomb (5) to move forward and lift off along the cannonball (2), the test bomb starts to land and parachute after reaching the highest point, and the test bomb (5) finally lands and recovers safely;
thirdly, the method comprises the following steps: determination of valid test intervals:
1) after the fire medicine box (4) explodes, the test bomb (5) is pushed to move in the section of the 'in-tube test interval' of the cannonball (2), the overload in the section of the 'in-tube test interval' is large and can reach tens of thousands of g;
2) the test bomb (5) leaves the cannonball (2) to the section of space free test interval before the parachute is opened, and the posture and the acceleration of the bomb body can be adjusted through the outer wing (5-5) of the test bomb (5) in the space free test interval;
3) the section from the parachute opening of the test bomb (5) to the front of the landing ground is a parachute deceleration test section, and different deceleration information is obtained mainly through active deceleration of the parachute in the section, so that different excitations are provided for the inertia device to be tested;
fourthly, the method comprises the following steps: collecting test data:
1) the high-precision measurement combination is arranged in a main test bin (5-2) of the test bomb (5), and the inertial measurement unit to be tested is arranged in an auxiliary bin (5-3), and the running information of the test bomb (5) is measured and stored;
2) flight information of the test bomb (5) is determined through a photoelectric tracking device on the ground.
2. The high overload test method for the inertia device as claimed in claim 1, wherein the high precision measurement combination adopts GPS/Beidou, inertia combination and magnetic beacon.
3. An inertial device high overload test method according to claim 1, characterised in that the material of the projectile (5-4) is titanium alloy.
4. The method for testing the high overload of the inertia device as claimed in claim 1, wherein the cannonball (2) can be replaced by cannon tubes with different specifications according to the test requirement, and the gunpowder box (4) can be replaced by the gunpowder box with different specifications according to the test requirement.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5737239A (en) * | 1995-02-13 | 1998-04-07 | Hitachi, Ltd. | Shaking test method and system for a structure |
| CN101458152B (en) * | 2008-11-27 | 2010-12-29 | 中北大学 | High g value impact acceleration simulation test system and method , test method and application |
| CN102072968B (en) * | 2010-11-04 | 2012-03-21 | 国营红林机械厂 | Method for calibrating high-g value acceleration transducer |
| CN102506897B (en) * | 2011-10-21 | 2014-07-30 | 哈尔滨工大瑞驰高新技术有限公司 | Linear vibration and overload combinatorial testing method and apparatus thereof |
| CN203561295U (en) * | 2013-12-18 | 2014-04-23 | 中国人民解放军沈阳炮兵学院 | Simulated rocket projectile for emplacement reconnaissance radar training |
| CN105841559B (en) * | 2016-05-30 | 2017-11-21 | 中国工程物理研究院电子工程研究所 | A kind of air artillery equivalent loading test device for hanging |
| CN108344552B (en) * | 2018-03-16 | 2023-12-29 | 中国工程物理研究院总体工程研究所 | Separated experimental equipment for researching high-temperature high-speed impact response of structure |
| CN109506864A (en) * | 2018-12-12 | 2019-03-22 | 上海卫星装备研究所 | Spacecraft shock environment analogue means |
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