CN206756172U - A kind of vibration insulating system of missile-borne optical fibre gyro combination - Google Patents
A kind of vibration insulating system of missile-borne optical fibre gyro combination Download PDFInfo
- Publication number
- CN206756172U CN206756172U CN201720591802.3U CN201720591802U CN206756172U CN 206756172 U CN206756172 U CN 206756172U CN 201720591802 U CN201720591802 U CN 201720591802U CN 206756172 U CN206756172 U CN 206756172U
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- optical fibre
- fibre gyro
- damper
- missile
- combination
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Abstract
The utility model discloses a kind of missile-borne optical fibre gyro combination vibration insulating system, comprising：Sensitive and damping means, eight dampers and optical fibre gyro combination shell；On the first end of each damper is arranged on the outside of the optical fibre gyro combined frame that sensitive and damping means are provided with, positioned at eight apexes of optical fibre gyro combined frame, and symmetrically；Sensitivity and damping means provided with damper are arranged on the optical fibre gyro combination enclosure, and the second end of the damper is combined enclosure with the optical fibre gyro and is connected.The utility model has simple, a good vibration resistance of overall assembling, symmetrical configuration, reduces design by the difficulty of vibration damping object barycenter and geometric center registration, the advantages of improving the measurement accuracy of optical fibre gyro combination.
Description
Technical field
Vibration insulating system is the utility model is related to, more particularly to a kind of vibration insulating system of missile-borne optical fibre gyro combination.
Background technology
The function of missile-borne optical fibre gyro combination is the angular speed and apparent acceleration on measurement three axles of guided missile in real time.Violent
Random vibration is the main mechanical environment that Methods of Strapdown Inertial Navigation System faces on bullet, and these vibrations are delivered on body
Optical fibre gyro combines, and it is produced measurement error or inertia device damage, influences the measurement accuracy of inertia production.It is good in order to provide
Good dynamic duty environment, the measurement error that vibration is brought is reduced, ensure guided missile optical fibre gyro combinative stability in flight course
Work is, it is necessary to using vibration reducing measure.
Due to geometrical conditions such as body structure, the available installation site of body, the design features of inertial navigation system itself
Limitation, the damping model used in practical structures design is than relatively limited.Existing shock absorber mounting means, more using integral planar
The diagonal four-point layout of four-point or space.The defects of such mounting means is to by the barycenter of damping body and geometric center coincidence
The requirement of degree is higher, and operation difficulty is big, easily produces the coupling of linearly coupled and angular oscillation, influences the measurement essence of optical fibre gyro combination
Degree.
Utility model content
The purpose of this utility model is to provide a kind of vibration insulating system of missile-borne optical fibre gyro combination, by damper in inertia
The internal mounting means for using 8 vibration dampings in space of combination, optical fibre gyro combination vibration insulating system is set to realize the purpose of integration.
In order to realize the above object the utility model is achieved through the following technical solutions：
A kind of vibration insulating system of missile-borne optical fibre gyro combination, comprising：Sensitive and damping means, eight dampers and optical fiber
Gyro shell；The first end of each damper is arranged on the optical fibre gyro combination that the sensitive and damping means are provided with
On on the outside of skeleton, positioned at eight apexes of the optical fibre gyro combined frame, and symmetrically；It is described quick provided with damper
Sense and damping means are arranged on the optical fibre gyro combination enclosure, the second end of the damper and the optical fibre gyro group
Enclosure is closed to be connected.
Preferably, the sensitive and damping means further include：
Three optical fibre gyros, three optical fibre gyros are separately positioned on three that the optical fibre gyro combined frame is provided with
In open area, and correspondingly it is fixed on the datum clamp face of the optical fibre gyro by screw, makes three optical fibre gyros mutual
It is orthogonal；Three quartz flexible accelerometers, three quartz flexible accelerometers are correspondingly fixed on described by screw respectively
On the mounting surface that optical fibre gyro combined frame is provided with, and mutual three axle of three quartz flexible accelerometers is orthogonal；Interface electricity
Road plate, it is arranged on the other end outside portion of the optical fibre gyro combined frame by screw；It is described sensitive and damping means
Barycenter and geometric center keep overlapping.
Preferably, the resonant frequency of each damper is 245Hz ± 25Hz.
Preferably, the resonance amplification factor of each damper is less than 3 times.
Preferably, for the amplitude versus frequency characte of each damper when frequency reaches 100Hz, amplitude amplification is no more than 2.5dB.
The utility model has advantages below compared with prior art：
Optical fibre gyro combination vibration insulating system realizes modularization, and overall assembling is simple, symmetrical configuration, reduces design by vibration damping
The difficulty of object barycenter and geometric center registration.
Under vibration, the coupling of linearly coupled and angular oscillation in same direction is avoided, there is good vibration resistance, carry
The high measurement accuracy of optical fibre gyro combination.
Brief description of the drawings
Fig. 1 is that a kind of sensitivity of vibration insulating system of missile-borne optical fibre gyro combination of the utility model and the structure of damping means are shown
It is intended to；
Fig. 2 is a kind of structural representation of the vibration insulating system of missile-borne optical fibre gyro combination of the utility model.
Embodiment
Below in conjunction with accompanying drawing, by describing a preferable specific embodiment in detail, the utility model is done and further explained
State.
As shown in figure 1, a kind of vibration insulating system of missile-borne optical fibre gyro combination, comprising：Sensitive and damping means are by vibration damping
Object, comprising：Optical fibre gyro combined frame 1, it is overall similar with rectangular parallelepiped structure, and is provided with inside its one end and passes through wallboard
Three open areas of isolation, corresponding three open areas are respectively equipped with the installation base of three orthogonal optical fibre gyros
Quasi- face；Three mutually orthogonal mounting surfaces are provided with inside the other end of the optical fibre gyro combined frame 1.
Three optical fibre gyros 2, three optical fibre gyros 2 are separately positioned in three open areas, and pass through spiral shell
Nail is corresponding to be fixed on the datum clamp face of the optical fibre gyro, makes three optical fibre gyros 2 mutually orthogonal.
Three quartz flexible accelerometers 5, three quartz flexible accelerometers 5 are correspondingly fixed on by screw respectively
On the mounting surface, and mutual three axle of three quartz flexible accelerometers 5 is orthogonal, ensures installation accuracy.
Interface card 4, it is arranged on the other end outside portion of the optical fibre gyro combined frame 1 by screw, made quick
The barycenter and geometric center of sense and damping means keep overlapping.
With reference to shown in Fig. 1 and Fig. 2, the vibration insulating system of the missile-borne optical fibre gyro combination further includes：Eight dampers
3, optical fibre gyro combination shell 6；
Eight dampers 3 are arranged on described by screw respectively, respectively positioned at the optical fibre gyro combined frame 1
Eight apexes, and eight dampers 3 are parallel two-by-two.
The optical fibre gyro combination shell 6 matches with the sensitive and damping means provided with eight dampers 3；
The sensitive and damping means for being provided with eight dampers 3 are arranged on inside the optical fibre gyro combination shell 6；It is logical
Screw is crossed each damper is fixed on the optical fibre gyro combination shell 6 through the mounting hole that damper is provided with,
Complete sensitive and damping means, damper combining shell integrated setting with optical fibre gyro, form vibration insulating system.
The vibration insulating system of the missile-borne optical fibre gyro combination is further provided with temperature sensor, and temperature sensor passes through screw
Fixed on optical fibre gyro combined frame 1.
According to missile vibration experimental condition and optical fibre gyro combination and quartz flexible accelerometer after vibrated
Frequency characteristic, the shock absorber meet following condition：Resonant frequency 245Hz ± 25Hz；Resonance amplification factor is less than 3 times；Amplitude-frequency
Characteristic:During 100Hz, amplitude amplification is no more than 2.5dB.
Although content of the present utility model is discussed in detail by above preferred embodiment, but it should be appreciated that on
The description stated is not considered as to limitation of the present utility model.After those skilled in the art have read the above, for
A variety of modifications and substitutions of the present utility model all will be apparent.Therefore, the scope of protection of the utility model should be by appended
Claim limit.
Claims (5)
1. a kind of vibration insulating system of missile-borne optical fibre gyro combination, it is characterised in that include：Sensitive and damping means,
Eight dampers and optical fibre gyro combination shell；
The first end of each damper is arranged on the outside of the optical fibre gyro combined frame that the sensitive and damping means are provided with
On, positioned at eight apexes of the optical fibre gyro combined frame, and symmetrically；
The sensitivity and damping means provided with damper are arranged on the optical fibre gyro combination enclosure, the damper
Enclosure is combined with the optical fibre gyro and is connected in the second end.
A kind of 2. vibration insulating system of missile-borne optical fibre gyro combination as claimed in claim 1, it is characterised in that the sensitive and vibration damping
Part further includes：
Three optical fibre gyros, three optical fibre gyros are separately positioned on three openings that the optical fibre gyro combined frame is provided with
In region, and correspondingly it is fixed on the datum clamp face of the optical fibre gyro by screw, makes three optical fibre gyros mutually orthogonal；
Three quartz flexible accelerometers, three quartz flexible accelerometers are correspondingly fixed on the light by screw respectively
On the mounting surface that fine Gyro skeleton is provided with, and mutual three axle of three quartz flexible accelerometers is orthogonal；
Interface card, it is arranged on the other end outside portion of the optical fibre gyro combined frame by screw；It is described sensitive and
The barycenter and geometric center of damping means keep overlapping.
A kind of 3. vibration insulating system of missile-borne optical fibre gyro combination as claimed in claim 1, it is characterised in that the damper it is humorous
Vibration frequency is 245Hz ± 25Hz.
4. a kind of vibration insulating system of missile-borne optical fibre gyro combination as claimed in claim 3, it is characterised in that described
The resonance amplification factor of damper is less than 3 times.
A kind of 5. vibration insulating system of missile-borne optical fibre gyro combination as claimed in claim 4, it is characterised in that
For the amplitude versus frequency characte of the damper when frequency reaches 100Hz, amplitude amplification is no more than 2.5dB.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720591802.3U CN206756172U (en) | 2017-05-25 | 2017-05-25 | A kind of vibration insulating system of missile-borne optical fibre gyro combination |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720591802.3U CN206756172U (en) | 2017-05-25 | 2017-05-25 | A kind of vibration insulating system of missile-borne optical fibre gyro combination |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206756172U true CN206756172U (en) | 2017-12-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720591802.3U Active CN206756172U (en) | 2017-05-25 | 2017-05-25 | A kind of vibration insulating system of missile-borne optical fibre gyro combination |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109459021A (en) * | 2018-12-13 | 2019-03-12 | 上海航天控制技术研究所 | A kind of circuit board vibration-proof structure of the used group of carrier rocket optical fiber |
| CN109682991A (en) * | 2018-12-12 | 2019-04-26 | 上海航天控制技术研究所 | A kind of carrier rocket high-altitude active off-load accelerometer device |
| CN110766930A (en) * | 2019-10-23 | 2020-02-07 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Distributed control system of civil owner flight control system direct mode |
| CN111215887A (en) * | 2019-12-04 | 2020-06-02 | 上海航天控制技术研究所 | Error-proof combined device for quick assembly alignment of sensitive package |
| CN114323006A (en) * | 2021-12-30 | 2022-04-12 | 率为科技(北京)有限责任公司 | Vibration reduction optical fiber inertial navigation system suitable for unmanned driving |
-
2017
- 2017-05-25 CN CN201720591802.3U patent/CN206756172U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109682991A (en) * | 2018-12-12 | 2019-04-26 | 上海航天控制技术研究所 | A kind of carrier rocket high-altitude active off-load accelerometer device |
| CN109459021A (en) * | 2018-12-13 | 2019-03-12 | 上海航天控制技术研究所 | A kind of circuit board vibration-proof structure of the used group of carrier rocket optical fiber |
| CN110766930A (en) * | 2019-10-23 | 2020-02-07 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Distributed control system of civil owner flight control system direct mode |
| CN111215887A (en) * | 2019-12-04 | 2020-06-02 | 上海航天控制技术研究所 | Error-proof combined device for quick assembly alignment of sensitive package |
| CN111215887B (en) * | 2019-12-04 | 2021-12-14 | 上海航天控制技术研究所 | Error-proof combined device for quick assembly alignment of sensitive package |
| CN114323006A (en) * | 2021-12-30 | 2022-04-12 | 率为科技(北京)有限责任公司 | Vibration reduction optical fiber inertial navigation system suitable for unmanned driving |
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