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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Closed loop system with reference to different gyro stabilization loops present in modern space vehicle inertial measuring unit, using Prony exponential series curve fitting method as analytical tool
A theoretical study was made of a device which might be used to damp the angular motions of spin-stabilized space vehicles with constant moments of inertia. the device was assumed to consist of a rate gyro, a servo control, and a rotor mounted in a single gimbal. The investigation was conducted by considering the general equations of motion of the vehicle-damper system and noting that simplification would result if the damper had a spherical inertia distribution. Such a distribution was assumed thereafter, and a control command was defined so that the gimbal angle would be proportional to the angular velocity of the vehicle about the gimbal axis. The resulting equations were linearized, and the Routh-Hurwitz criterion was applied to determine the conditions for stability. The study included two numerical examples showing possible application of inertia-sphere rate dampers. The general conditions for stability were found to be feasible for practical applications. A simplified stability criterion covers a large class of practical problems.
Analysis of guidance system errors resulting from initial misalignments of both the accelerometer and stabilizing gyros, the drift of the stabilized element during flight and errors in measuring the vehicle motions
Generation mechanisms of radio and x-ray bursts from solar flares - bremsstrahlung from solar plasma, gyro and synchrotron radiation from electrons, and plasma radiation
The goal of this contract was to determine the g environment under which the GC159C Gas-Bearing Spinmotor (GBSM) could reliably operate. This was fulfilled by building and testing of four GBSM's, a test fixture, and a "dummy" gyro. The test program was divided into two phases when a gas bearing improvement was required to withstand JPL shock requirement of 200 g. Phase I determined existing g capabilities and performance of the GC159C GBSM and gimbal-case structure. Phase II increased GBSM capability to meet required JPL g environments. Life tests were run on two GBSM's which were shocked at a high level to obtain bearing contact while rotating at their operating speed of 23,000 rpm. A third (nonoperating) GBSM was exposed to JPL maximum shock levels, and a fourth (nonoperating) GBSM was exposed to random vibration. Both nonoperating GBSM's were then subjected to life testing.
Optical-inertial space navigation system combining gyros, image tube tracker, electrostatic accelerometer and advanced computer
Guidance and control technology examining inertial guidance systems, Apollo space system, gyros, accelerometers and computers
Porous tungsten plugs provide even airflow for frictionless bearings used in air bearing supported gyros. The plugs have their outer cylindrical surface sealed by an electron beam process to ensure unidirectional airflow through their exit ends.
Analytic platform inertial navigation system using single axis reference and pendulous integrating gyro accelerometer measuring devices
Gyro-inertial and optical sensor fine attitude control for pointing Aerobee 150 package at sun or series of stellar targets
Studies in mechanical damping in possible gyro materials, electron scattering from surface of tungsten, and control systems
Approximate steady state time response expression for RC commutated network used to investigate modifications of rate gyro blender
Dynamic testing and failure analyses of spin axis bearings in gyro assemblies for spacecraft guidance system applications
Disturbance envelope and experiment requirements for Apollo missions used to determine optimum control-moment gyro-jet system
Spacecraft control studies on antenna pointing, capsule sterilization, propulsive lander, optical sensing for soft landing spacecraft, and gyro data reduction computer programs
Microelectronics for air bearing gyro and accelerometer servo loops
Circuitry, fabrication, and performance characteristics of 75-VA integrated static inverter for gyro platform power supply
Guidance and control technology examining inertial guidance systems, Apollo space system, gyros, accelerometers and computers