CN204228175U - Inertial navigation system integrated environment calibrating installation structure - Google Patents
Inertial navigation system integrated environment calibrating installation structure Download PDFInfo
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- CN204228175U CN204228175U CN201420674986.6U CN201420674986U CN204228175U CN 204228175 U CN204228175 U CN 204228175U CN 201420674986 U CN201420674986 U CN 201420674986U CN 204228175 U CN204228175 U CN 204228175U
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Abstract
The utility model belongs to environment calibration technical field, is specifically related to a kind of inertial navigation system integrated environment calibrating installation structure, and object is to solve existing ground checkout equipment cannot the problem of the working environment of simulated flight device completely.It is characterized in that: it comprises attitude-simulating device (3), temperature environment simulation device and vibration environment analogue means (4); Wherein, temperature environment simulation device comprises support (1) and casing (2), and the bottom of support (1) is arranged on testing laboratory's ground; Casing (2) is arranged on support (1) upper surface, has through hole (5) in the middle part of bottom surface; Vibration environment analogue means (4) is arranged on support (2) below of temperature environment simulation device; The casing (1) that attitude-simulating device (3) is arranged on temperature environment simulation device is inner, and is connected with the top of vibration environment analogue means (4).This device can not only carry out inertial navigation system fail-test, can also carry out testing, emulate and calibrating.
Description
Technical field
The utility model belongs to environment calibration technical field, is specifically related to a kind of inertial navigation system integrated environment calibrating installation structure.
Background technology
Inertial navigation system is the important Guidance Control Units of the aircraft such as aircraft, guided missile and rocket, and its precision determines the navigation accuracy of aircraft.Inertial navigation system is made up of gyro and accelerometer, these elements to vibration and temperature very responsive.But in actual use, vibration and temperature variation are inevitable.First, inertial navigation system directly bears the vibration of aircraft, impact and angular motion, can produce additional dynamic error; Secondly, along with the change of aircraft altitude, the temperature of environment residing for inertial navigation system also can acute variation, causes system to occur temperature drift errors.
In order to analyze and compensate the error of inertial navigation system, need to carry out a large amount of ground tests and calibration.Existing method normally carries out vibration and shock testing on a vibration table, in temperature control box, carry out thermocycling, in the enterprising Mobile state performance test of precision measurement turntable, or temperature control box and precise rotating platform be combined in high and low temperature environment under carry out detection calibration.But the form of expression of INS errors is quite complicated, can not fully demonstrate out under single experimental enviroment.At present, not yet have can carry out vibrating simultaneously, the relevant report of the calibrating installation of high/low temperature and dynamic performance testing.
Summary of the invention
The purpose of this utility model is to solve existing ground checkout equipment cannot the problem of the working environment of simulated flight device completely, provides a kind of inertial navigation system integrated environment calibrating installation structure.
The utility model is achieved in that
A kind of inertial navigation system integrated environment calibrating installation structure, it comprises attitude-simulating device, temperature environment simulation device and vibration environment analogue means; Wherein, temperature environment simulation device comprises support and casing, and the bottom of support is arranged on testing laboratory's ground; The rack-mount end face of casing, has through hole in the middle part of bottom surface; Vibration environment analogue means is arranged on below the support of temperature environment simulation device; Attitude-simulating device is arranged on the box house of temperature environment simulation device, and is connected with the top of vibration environment analogue means.
Support as above is metal stool shape, in the middle part of its supporting surface, have through hole.
Temperature environment simulation device as above adopts nonstandard temperature control box to realize.
Vibration environment analogue means as above adopts nonstandard shaking table to realize.
Attitude-simulating device as above adopts three shaft position single shaft rate tables to realize.
Three shaft position single shaft rate tables as above are arranged on nonstandard vibration table surface, and in turntable, inner axis system and three circles are placed in nonstandard temperature control box, and housing axle system is placed in outside nonstandard temperature control box.
The beneficial effects of the utility model are:
The utility model is by as a whole for the combination of attitude-simulating device, temperature environment simulation device and vibration environment analogue means.This device can not only carry out the fail-test of inertial navigation system, and can test it, emulates and calibrate.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of inertial navigation system integrated environment calibrating installation structure of the present utility model;
In figure, 1. casing, 2. support, 3. attitude-simulating device, 4. vibration environment analogue means, 5. through hole.
Embodiment
Below in conjunction with the drawings and specific embodiments, a kind of inertial navigation system integrated environment calibrating installation structure of the present utility model is described:
As shown in Figure 1, a kind of inertial navigation system integrated environment calibrating installation structure, comprises attitude-simulating device 3, temperature environment simulation device and vibration environment analogue means 4.Wherein, temperature environment simulation device comprises support 1 and casing 2, and support 1 is metal stool shape, in the middle part of its supporting surface, have through hole, and its bottom is arranged on testing laboratory's ground.Casing 2 is arranged on support 1 upper surface, has through hole 5 in the middle part of its bottom surface.Vibration environment analogue means 4 is arranged on below the support 2 of temperature environment simulation device, and it provides the vertical one dimension linearly coupled meeting index request.The casing 1 that attitude-simulating device 3 is arranged on temperature environment simulation device is inner, and is connected with the top of vibration environment analogue means 4.The system of being calibrated is arranged on attitude-simulating device inside casing work top.
In the present embodiment, temperature environment simulation device adopts nonstandard temperature control box to realize.Vibration environment analogue means 4 adopts nonstandard shaking table to realize.Attitude-simulating device 3 adopts three shaft position single shaft rate tables to realize.Wherein, nonstandard vibration table surface is installed three shaft position single shaft rate tables, in turntable, inner axis system and three circles are placed in nonstandard temperature control box, housing axle system is placed in outside nonstandard temperature control box, the system of being calibrated is arranged on three shaft position single shaft rate table inside casings, and nonstandard temperature control box is directly installed on testing laboratory's ground.Turntable housing axle system (azimuth axis) is through the through hole of nonstandard temperature control box tank floor, and the base of turntable is fixedly connected with nonstandard vibration table surface.Be not rigidly connected between three shaft position single shaft rate table stage bodies and temperature control box.
Described metal is stainless steel, alloy steel or cast iron.
The utility model is by as a whole for the combination of attitude-simulating device, temperature environment simulation device and vibration environment analogue means.This device can not only carry out the fail-test of inertial navigation system, and can test it, emulates and calibrate.
Claims (6)
1. an inertial navigation system integrated environment calibrating installation structure, is characterized in that: it comprises attitude-simulating device (3), temperature environment simulation device and vibration environment analogue means (4); Wherein, temperature environment simulation device comprises support (1) and casing (2), and the bottom of support (1) is arranged on testing laboratory's ground; Casing (2) is arranged on support (1) upper surface, has through hole (5) in the middle part of bottom surface; Vibration environment analogue means (4) is arranged on support (2) below of temperature environment simulation device; The casing (1) that attitude-simulating device (3) is arranged on temperature environment simulation device is inner, and is connected with the top of vibration environment analogue means (4).
2. a kind of inertial navigation system integrated environment calibrating installation structure according to claim 1, is characterized in that: described support (1) is metal stool shape, in the middle part of its supporting surface, have through hole.
3. a kind of inertial navigation system integrated environment calibrating installation structure according to claim 1, is characterized in that: described temperature environment simulation device adopts nonstandard temperature control box to realize.
4. a kind of inertial navigation system integrated environment calibrating installation structure according to claim 1, is characterized in that: described vibration environment analogue means (4) adopts nonstandard shaking table to realize.
5. according to a kind of inertial navigation system integrated environment calibrating installation structure of claim 1-4 described in any one, it is characterized in that: described attitude-simulating device (3) adopts three shaft position single shaft rate tables to realize.
6. a kind of inertial navigation system integrated environment calibrating installation structure according to claim 5, it is characterized in that: three described shaft position single shaft rate tables are arranged on nonstandard vibration table surface, in turntable, inner axis system and three circles are placed in nonstandard temperature control box, and housing axle system is placed in outside nonstandard temperature control box.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420674986.6U CN204228175U (en) | 2014-11-05 | 2014-11-05 | Inertial navigation system integrated environment calibrating installation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420674986.6U CN204228175U (en) | 2014-11-05 | 2014-11-05 | Inertial navigation system integrated environment calibrating installation structure |
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| CN204228175U true CN204228175U (en) | 2015-03-25 |
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| CN201420674986.6U Active CN204228175U (en) | 2014-11-05 | 2014-11-05 | Inertial navigation system integrated environment calibrating installation structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107643156A (en) * | 2017-10-30 | 2018-01-30 | 长春工业大学 | Three axle rotational shaking tables |
| CN112212886A (en) * | 2019-07-10 | 2021-01-12 | 九江精密测试技术研究所 | Micro-electromechanical inertial unit scale production test system and method |
-
2014
- 2014-11-05 CN CN201420674986.6U patent/CN204228175U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107643156A (en) * | 2017-10-30 | 2018-01-30 | 长春工业大学 | Three axle rotational shaking tables |
| CN112212886A (en) * | 2019-07-10 | 2021-01-12 | 九江精密测试技术研究所 | Micro-electromechanical inertial unit scale production test system and method |
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