CN102175243A - Multi-high overload resistant device applicable to semi-strapdown inertia measurement system - Google Patents
Multi-high overload resistant device applicable to semi-strapdown inertia measurement system Download PDFInfo
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- CN102175243A CN102175243A CN2011100255789A CN201110025578A CN102175243A CN 102175243 A CN102175243 A CN 102175243A CN 2011100255789 A CN2011100255789 A CN 2011100255789A CN 201110025578 A CN201110025578 A CN 201110025578A CN 102175243 A CN102175243 A CN 102175243A
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Abstract
The invention relates to an inertial navigation measurement technology, in particular to a multi-high overload resistant device applicable to a semi-strapdown inertia measurement system. The invention solves the problem that a special device for protecting the semi-strapdown inertia measurement system against damage under a large overload is absent at present. The multi-high overload resistant device applicable to the semi-strapdown inertia measurement system comprises an outer cylinder, an inner cylinder, an inertia measurement unit, a mass eccentric module and a circuit board; a first bearing and a second bearing are arranged between the outer cylinder and the inner cylinder; and the device also comprises a combined cushion pad module, an opposite vortex semi-spherical buffer module and a shock absorbing pad array. The device performs overload resistant protection on the semi-strapdown inertia measurement system through the multistage buffer module, so the problem that a special device for protecting the semi-strapdown inertia measurement system against damage under the large overload is absent at present is radically and effectively solved, and the device is applicable to the overload resistant protection of the semi-strapdown inertia measurement system in the altitude measurement process of a flying object rotating at a high speed.
Description
Technical field
The present invention relates to the inertial navigation measuring technique, specifically is a kind of multiple anti high overload device that is applicable to the semi-strapdown type inertial measurement system.
Background technology
The semi-strapdown type inertial measurement system is a kind of novel measuring system that is applicable to high speed rotating flying body attitude measurement, and this system realized on sense of rotation and flying body strapdown not, and keeps strapdown with flying body at two other on axially; The high speed rotating flying body can stand big emission overload, high speed rotating flight then usually earlier; Therefore, how protection semi-strapdown type inertial measurement system is not damaged under big overload, and the semi-strapdown type inertial measurement system can operate as normal when guaranteeing the high speed rotating flight later of big overload, just becomes very important problem; Be necessary to invent for this reason and a kind ofly be specifically designed to the device that protection semi-strapdown type inertial measurement system is not damaged under big overload, yet still do not have this type of device at present.
Summary of the invention
The present invention does not still have a kind of problem that is specifically designed to the device that protection semi-strapdown type inertial measurement system is not damaged under big overload at present in order to solve, and a kind of multiple anti high overload device that is applicable to the semi-strapdown type inertial measurement system is provided.
The present invention adopts following technical scheme to realize: a kind of multiple anti high overload device that is applicable to the semi-strapdown type inertial measurement system comprises urceolus, inner core, Inertial Measurement Unit, mass eccentricity module and circuit board; Be provided with the clutch shaft bearing and second bearing between urceolus and the inner core; Clutch shaft bearing outer ring and outer cylinder front end are fixed, and clutch shaft bearing inner ring and inner core front end are fixed; Second bearing outer ring is fixed with outer tube rear end, and second bearing inner race and interior tube rear end are fixed; Inertial Measurement Unit is installed on inner core front end bottom surface, and circuit board is installed on interior tube rear end bottom surface, and the mass eccentricity module is installed on the inner core sidewall; Also comprise combination cushion pad module, to top hemisphere buffer module and beam array; Wherein, combination cushion pad module comprises the first cylindricality polyurethane block and foamed aluminium array; The foamed aluminium array comprises that several evenly distribute and is fixed in cylindrical foam aluminium in the first cylindricality polyurethane block; Top hemisphere buffer module is comprised first hemisphere and second hemisphere; To top contact, first hemisphere bottom is fixed with bottom surface, the first cylindricality polyurethane block rear end between first hemisphere and second hemisphere, and second hemisphere bottom is fixed with the clutch shaft bearing inner ring; Urceolus, inner core, clutch shaft bearing, second bearing, the first cylindricality polyurethane block, first hemisphere, second hemisphere all are positioned on the same axis; The beam array comprises that several evenly distribute and is fixed in beam between inner core front end bottom surface and the Inertial Measurement Unit; Interior tube rear end bottom surface is fixed with the second cylindricality polyurethane block, and the circuit board embedding is in the second cylindricality polyurethane block.
During work, combination cushion pad module utilizes foamed aluminium to absorb the strong characteristics of impact capacity, and polyurethane has higher elasticity and characteristics such as intensity, fatigue durability and anti-vibration resistance, and the overload of entire system is cushioned; Utilize when hemisphere overload in top increased distortion along with big more characteristics to top hemisphere buffer module yet, the overload of entire system is cushioned, and protection clutch shaft bearing and second bearing are not subjected to irrecoverable property destruction; The clutch shaft bearing and second bearing can play buffer action to a certain extent; The effect of beam array is the overload that the buffering Inertial Measurement Unit is subjected to, and isolates the part vibrations that Inertial Measurement Unit is subjected to; The second cylindricality polyurethane block then plays a protective role to circuit board, prevents the destruction of big overload to circuit board, has effectively improved the anti high overload performance of circuit board; A kind of multiple anti high overload device of semi-strapdown type inertial measurement system that is applicable to of the present invention adopts the multi-buffer module combinations to form, it had both played the effect that protection semi-strapdown type inertial measurement system is not damaged under big overload, can guarantee that again the semi-strapdown type inertial measurement system can not lose efficacy in big overload later, and can be harmful to vibrations by isolated part; Therefore it is applicable to that double Strapdown Inertial Units measuring system carried out overload-resistant protection in high speed rotating flying body attitude measurement.
The present invention carries out overload-resistant protection by adopting double Strapdown Inertial Units measuring system of multi-buffer module; thoroughly having solved does not effectively still have at present a kind of problem that is specifically designed to the device that protection semi-strapdown type inertial measurement system is not damaged under big overload, is applicable to the overload-resistant protection of semi-strapdown type inertial measurement system in the high speed rotating flying body attitude measurement process.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Among the figure: 1-urceolus, 2-inner core, 3-Inertial Measurement Unit, 4-mass eccentricity module, 5-clutch shaft bearing, 6-second bearing, the 7-first cylindricality polyurethane block, 8-cylindrical foam aluminium, 9-first hemisphere, 10-second hemisphere, 11-beam, the 12-second cylindricality polyurethane block.
Embodiment
A kind of multiple anti high overload device that is applicable to the semi-strapdown type inertial measurement system comprises urceolus 1, inner core 2, Inertial Measurement Unit 3, mass eccentricity module 4 and circuit board; Be provided with the clutch shaft bearing 5 and second bearing 6 between urceolus 1 and the inner core 2; Clutch shaft bearing 5 outer rings and urceolus 1 front end are fixed, and clutch shaft bearing 5 inner rings and inner core 2 front ends are fixed; Second bearing, 6 outer rings and urceolus 1 rear end are fixed, and second bearing, 6 inner rings and inner core 2 rear ends are fixed; Inertial Measurement Unit 3 is installed on inner core 2 front end bottom surfaces, and circuit board is installed on bottom surface, inner core 2 rear end, and mass eccentricity module 4 is installed on inner core 2 sidewalls; Also comprise combination cushion pad module, to top hemisphere buffer module and beam array; Wherein, combination cushion pad module comprises the first cylindricality polyurethane block 7 and foamed aluminium array; The foamed aluminium array comprises that several evenly distribute and is fixed in cylindrical foam aluminium 8 in the first cylindricality polyurethane block 7; Top hemisphere buffer module is comprised first hemisphere 9 and second hemisphere 10; To top contact, first hemisphere, 9 bottoms and bottom surface, the first cylindricality polyurethane block, 7 rear end are fixed between first hemisphere 9 and second hemisphere 10, and second hemisphere, 10 bottoms and clutch shaft bearing 5 inner rings are fixed; Urceolus 1, inner core 2, clutch shaft bearing 5, second bearing 6, the first cylindricality polyurethane block 7, first hemisphere 9, second hemisphere 10 all are positioned on the same axis; The beam array comprises that several evenly distribute and is fixed in beam 11 between inner core 2 front end bottom surfaces and the Inertial Measurement Unit 3; Bottom surface, inner core 2 rear end is fixed with the second cylindricality polyurethane block 12, and the circuit board embedding is in the second cylindricality polyurethane block 12.
During concrete enforcement, the first cylindricality polyurethane block also can substitute with epoxy resin or other macromolecular materials; The second cylindricality polyurethane block also can substitute with epoxy resin or silicon rubber; First hemisphere and second hemisphere all adopt alloy steel or other high duty metal to make; The clutch shaft bearing and second bearing all adopt deep groove ball bearing, in the moment of big overload, deep groove ball bearing is limited because of bearing overload capacity, certain distortion can take place, and this moment, first hemisphere contacted with second hemisphere, and bore most of overload, thereby protected deep groove ball bearing, after transshipping greatly, deep groove ball bearing is because self elasticity will be recovered big overload state before; Combination cushion pad module adopts cast polyurethane to form, and Inertial Measurement Unit is inner Inertial Measurement Unit through polyurethane or epoxy resin or silicon rubber embedding; The beam array is made up of four Rubber shock-absorbing pads.
Claims (1)
1. a multiple anti high overload device that is applicable to the semi-strapdown type inertial measurement system comprises urceolus (1), inner core (2), Inertial Measurement Unit (3), mass eccentricity module (4) and circuit board; Be provided with clutch shaft bearing (5) and second bearing (6) between urceolus (1) and the inner core (2); Clutch shaft bearing (5) outer ring and urceolus (1) front end are fixed, and clutch shaft bearing (5) inner ring and inner core (2) front end are fixed; Second bearing (6) outer ring and urceolus (1) rear end are fixed, and second bearing (6) inner ring and inner core (2) rear end are fixed; Inertial Measurement Unit (3) is installed on inner core (2) front end bottom surface, and circuit board is installed on inner core (2) bottom surface, rear end, and mass eccentricity module (4) is installed on inner core (2) sidewall; It is characterized in that: also comprise combination cushion pad module, top hemisphere buffer module and beam array; Wherein, combination cushion pad module comprises first cylindricality polyurethane block (7) and the foamed aluminium array; The foamed aluminium array comprises that several evenly distribute and is fixed in cylindrical foam aluminium (8) in the first cylindricality polyurethane block (7); Top hemisphere buffer module is comprised first hemisphere (9) and second hemisphere (10); To top contact, first hemisphere (9) bottom is fixed with first cylindricality polyurethane block (7) bottom surface, rear end between first hemisphere (9) and second hemisphere (10), and second hemisphere (10) bottom is fixed with clutch shaft bearing (5) inner ring; Urceolus (1), inner core (2), clutch shaft bearing (5), second bearing (6), the first cylindricality polyurethane block (7), first hemisphere (9), second hemisphere (10) all are positioned on the same axis; The beam array comprises that several evenly distribute and is fixed in beam (11) between inner core (2) front end bottom surface and the Inertial Measurement Unit (3); Inner core (2) bottom surface, rear end is fixed with the second cylindricality polyurethane block (12), and the circuit board embedding is in the second cylindricality polyurethane block (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110025578A CN102175243B (en) | 2011-01-24 | 2011-01-24 | Multi-high overload resistant device applicable to semi-strapdown inertia measurement system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110025578A CN102175243B (en) | 2011-01-24 | 2011-01-24 | Multi-high overload resistant device applicable to semi-strapdown inertia measurement system |
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| CN102175243A true CN102175243A (en) | 2011-09-07 |
| CN102175243B CN102175243B (en) | 2012-10-17 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102494682A (en) * | 2011-12-07 | 2012-06-13 | 中北大学 | Comprehensive anti-overload protection method applicable to initiative type half-strapdown inertia measurement system |
| CN103017725A (en) * | 2012-12-07 | 2013-04-03 | 河北汉光重工有限责任公司 | Optical test method for return precision after impact test of mechanical buffer |
| CN103134540A (en) * | 2012-12-05 | 2013-06-05 | 中北大学 | High overload integrated protective structure |
| CN103411613A (en) * | 2013-07-12 | 2013-11-27 | 中北大学 | Missile-borne penetration attitude calculating device based on combination of geomagnetism and micro-inertia navigation information |
| CN106840146A (en) * | 2016-12-19 | 2017-06-13 | 中北大学 | A kind of method for designing for increasing by half strap down stability platform restoring moment |
| CN111237370A (en) * | 2020-02-03 | 2020-06-05 | 中北大学 | High-g-value impact acceleration buffering device and buffering method and application |
| CN113654552A (en) * | 2021-06-30 | 2021-11-16 | 贵州航天控制技术有限公司 | MEMS inertia measuring device capable of resisting large overload |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102494682A (en) * | 2011-12-07 | 2012-06-13 | 中北大学 | Comprehensive anti-overload protection method applicable to initiative type half-strapdown inertia measurement system |
| CN103134540A (en) * | 2012-12-05 | 2013-06-05 | 中北大学 | High overload integrated protective structure |
| CN103134540B (en) * | 2012-12-05 | 2015-10-21 | 中北大学 | High overload integrated protection structure |
| CN103017725A (en) * | 2012-12-07 | 2013-04-03 | 河北汉光重工有限责任公司 | Optical test method for return precision after impact test of mechanical buffer |
| CN103411613A (en) * | 2013-07-12 | 2013-11-27 | 中北大学 | Missile-borne penetration attitude calculating device based on combination of geomagnetism and micro-inertia navigation information |
| CN103411613B (en) * | 2013-07-12 | 2016-01-06 | 中北大学 | Based on the missile-borne penetration attitude algorithm device of earth magnetism/micro-inertial navigation information combination |
| CN106840146A (en) * | 2016-12-19 | 2017-06-13 | 中北大学 | A kind of method for designing for increasing by half strap down stability platform restoring moment |
| CN111237370A (en) * | 2020-02-03 | 2020-06-05 | 中北大学 | High-g-value impact acceleration buffering device and buffering method and application |
| CN111237370B (en) * | 2020-02-03 | 2021-06-15 | 中北大学 | High-g-value impact acceleration buffering device and buffering method and application |
| CN113654552A (en) * | 2021-06-30 | 2021-11-16 | 贵州航天控制技术有限公司 | MEMS inertia measuring device capable of resisting large overload |
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| CN102175243B (en) | 2012-10-17 |
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