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[China]
Trade Verify
Address: 803, Block A, Building B5-1, Junfeng Industrial Complex, HepingCommunity, Fuhai Street, Bao an District, Shenzhen
Contact name:Caine
Shenzhen Avionics Technology Co.,Ltd |
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1 axis gyro optical fiber gyro sensor inertial angular rate sensor based on the principle of Sagnac
Descriptions
This product is an inertial angular rate sensor based on the principle of Sagnac, which is used to measure the angular rate motion of the carrier around the sensitive axis of the product. This product with fiber ring for angular rate sensing unit, based on the closed-loop detection circuit, the phase difference caused by sensitive angular rate of optical fiber ring, change into intensity signal by interference , detecting circuit change the intensity signal into voltage signal, and the signal is detected through the modulation and demodulation,Then feedback signal back to the optical path, to realize the closed-loop control.
This product is an inertial sensor composed of optical system and corresponding power supply and data processing circuit, which can provide incremental information of single axis angle.
This product is mainly used in inertial measurement system of high precision inertial navigation system and positioning & orientation system.
Features
● All-fiber design -long lifespan, small package size, high stability and more resistance to interference.
● Integrated fiber polarizer -minimum insertion loss and high extinction ratio, offering more resistance to temperature and mechanical shock, as well as intense vibration.
● Reliable compact package -operationally robust for all kinds of environments, ideal for a wide of applications in both civilian and military areas.
● QuichLaunch technology -minium activation time with no external calibration required.
● Optimal wavelength -improves the sensibility by 50% with the same structure, size and cost.
● Noise isolation and compression -significantly reduces the angle random walk.
● SelfTrack technology -improves the gyro dynamic range
Applications
●UAV/AUV/Helicopter ●Tactical nuclear weapons ●Aeronautics and astronautics
●Integrated navigation system ●inertial platform stabilizing ●Vehicle navigation
Performance Characteristics
| No. | Parameter | F98-400 | Unit | Remarks | ||||||
| 1 | Maximum angular rate | ±400 | °/s | |||||||
| 2 | Scale factor | 1650000× (1±10%) | SP/°/s | |||||||
| 3 | Scale factor nonlinearity in room temperature | ≤20 | ppm | @25℃ | ||||||
| 4 | Scale factor repeatability in room temperature | ≤20 | ppm | @25℃ | ||||||
| 5 | Scale factor repeatability in full temperature
| ≤50 | ppm | -40℃~+70℃ | ||||||
| 6 | Bias stability in room temperature | ≤0.02 | 10s 1σ,°/h | @25℃ | ||||||
| 7 | Bias repeatability in room temperature | ≤0.01 | 1σ,°/h | Bias | ||||||
| 8 | Bias repeatability in tull temperature | ≤0.03 | 1σ,°/h | -40℃~+70℃ | ||||||
| 9 | Bias stability in changing temperature | ≤0.015 | 100s 1σ,°/h | 0.3℃/min,-40℃~+70℃ | ||||||
| 10 | Random walk | ≤0.003 | °/ | |||||||
| 11 | Activation time | 0 | min | |||||||
| 12 | Bias value during vibration/before vibration/after vibration | ≤0.05 | °/h | |||||||
| 13 | Bias value before/after vibration) | ≤0.05 | °/h | |||||||
| 14 | Magnetic sensitivity | ≤0.01 | °/h/Gs | |||||||
| 15 | Threshold value | ≤0.02 | °/h | |||||||
| 16 | Vibration | 20Hz～2000Hz
| Hz/10min | |||||||
| X | Y | Z | ||||||||
Vibration spectrum | ||||||||||
| 17 | Impact | 15g(3times) | Half sine wave/11ms | |||||||
| ±X | ±Y | ±Z | ||||||||
Dimensions
