To solve the problem of inflight alignment of roll angle for inertial components used in integrated navigation of guided projectile, according to principles of projectile moving around its mass center, the inflight alignment method was derived based on the data measured by triaxial angle-rate gyroscope and Global Positioning System(GPS). The effects of initial disturbance on flight attitude was neglected, and the theory of dynamic balance angle was applied. Through the simulation for the sensor noise, the initial roll angle of the fin-stable projectile was clculated based on compound measurement data, and the error range of roll angle was within 5°. The results indicate that the simulated roll angle is approximately equal to the theoretical value, and this method can satisfy the requirement of inflight alignment for roll angle.
Key words
guided projectile /
roll angle /
dynamic equilibrium angle /
angle-rate gyroscope /
global positioning system
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References
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Footnotes
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