Showing papers on "Inertial reference unit published in 1986"

Self-adaptive IRU correction loop design interfacing with the target state estimator for multi-mode terminal handoff

Abstract: A method and apparatus for identifying inertial reference unit (IRU) errors in a guided missile employing a multi-mode guidance system and constructing correction terms to recover the missile true position. Discrepancy parameters are introduced to indicate misalignment between missile and launching platform (or ship) inertial frames where the missile onboard executive computer simultaneously processes the data provided from missile onboard sensors and target relevant data uplinked from the launching platform. The discrepancy parameters are employed to construct correction factors used to reduce the discrepancies. This updated missile configuration is then coupled with the target state estimator outputs to reconstruct smoothed line-of-sight (LOS) angles for terminal homing engagement.

Achievements And Perspectives Of Fiber Gyros

Abstract: The fiber gyro, utilizing the Sagnac effect and under development since the early 1980s, has reached production status as a low-cost rotation rate sensor for various high volume applications, satisfied by drift rates of 10°/h and more. Lower drift rates will be offered by series production fiber gyros within the next two years. Principles, technologies and performance data of SEL fiber gyros are discussed, as well as some principal applications. The paper introduces also the concept of a new class of inertial fiber motion sensors based upon the Kennedy-Thorndike interferometer. Such sensors for inertial velocity can enable inertial strapdown navigation without accelerometers.

Developments in Inertial Navigation

Abstract: Inertial navigation systems represent the ideal in automatic navigation. They operate entirely without external assistance, other than information as to their starting conditions, which makes them of great interest to both military and civil operators.

Mini-RIMS - A Miniature Roll-Stabilized Inertial Measurement System

Abstract: High-performance spinning-flight vehicle have always presented a difficult set of requirements for inertial measurement systems (IMSs). These requirements typically include high levels of vibration and shock, as well as high levels of acceleration and angular rate. In addition, the increasing complexity and size of payloads in these vehicles leave less volume and weight available for the IMS. The Mini-RIMS inertial measurement system offers a solution to these problems. The Mini-RIMS is composed of two major assemblies: an inertial platform assembly and an electronic assembly. The platform assembly consists of a single-axis platform containing gyroscopes and accelerometers oriented so that angular velocity and linear acceleration are sensed about or along three orthogonal axes: roll, pitch, and yaw. The platform can either be pinned to the base so that it moves with the host vehicle or stabilized about its roll axis. In the first case, an inertial strapdown mode is implemented about all three axes. In the second case, the roll axis is decouple from roll motions of the vehicle while the pitch and yaw axes continue to be instrumented in strapdown fashion.