1
Background
Basic principle 2
3 Main application
Research status 4
The research status of abroad
For the first time in 1963, the Sperry, the company successfully developed the ring laser gyro.
Inertial components
Inertia measurement Inertial navigation Inertial stabilization Inertial guidance
Inertial device is the core of the inertial technology
The actual model ----laser gyro relative interferometer
1
Background
Basic principle 2
3 Main application
① Most of the aircraft and civil aviation abroad F - 22, F - 35, SU - 30 aircraft, B747 and A320 civilian planes
The Principle and Application of Ring Laser Gyro
1
Background
Gyroscope: A sensor which has the ability to perceive
the running speed and maintain the direction of the type.
③ All kinds of tactical and strategic missiles Small intercontinental ballistic missiles "dwarf" The Block III tomahawk cruise missile.
④ Observe the tiny seismic effect and the solid ground tidal effect
② Conventional weapons such as tanks, artillery "Latin" howitzer Swedish BKAN1A and FH - 77 - b howitzers Precision measurement reconnaissance vehicles
the condition of low speed it is easy to closure.
Fiber optic gyro
Ring laser gyro
④ The precision of RLG is high , but the price also high.
1
Background
Basic principle 2
Rotation free condition, two beams of light transmission time, which is,
tCCW
tCW

L 2R
cc
Under the condition of rotating,
M CCW
CCCW
M
l
M ’

(a)
(b)
• The time of two directions
② The optical path of RLG must be kept in a solid component, so the degree of FOG on the surrounding environment sensitiver than RLG.
③ RLG has some inherent drawbacks, such as mirrors, gas, and under
In 1975, Honeywell company developed the mechanical dithering frequency laser gyro, adopting the technology of laser gyro strapdown inertial navigation system truly entered the practical stage.
Tro
① RLG's zero bias and scale factor of the system parameters are stability compared with FOG, so the calibration difficulty relatively easy.
2R
t CCW
c R
tCW

2R
c R
• Transmission time
t
tCCW
tCW

4R2
c2
M CCW
CCCW
(a)
M
l
M ’

(b)
Constitute of the RLS
Partial frequency components Cheng long control component Signal readout system Ring laser Logic circuit The power component The installation structure Electromagnetic shielding cover, etc
• Traditional inertial gyro has a high requirement on the process structures, complex structure, and the precision is restricted.
• R i n g l a s e r g y r o rotor rotating parts, not angular momentum, ring frame, also do not need direction angle sensor moving parts, such as simple structure, long working life, convenient maintenance, high reliability.