[go: up one dir, main page]

MILLER, 1965 - Google Patents

A highly reliable turning rate malfunction sensor for the Gemini launch vehicle(High reliability system for sensing excessive and potentially dangerous turning rates of …

MILLER, 1965

Document ID
10377359225651569681
Author
MILLER J
Publication year

External Links

Continue reading at scholar.google.com (other versions)

Similar Documents

Publication Publication Date Title
MILLER A highly reliable turning rate malfunction sensor for the Gemini launch vehicle(High reliability system for sensing excessive and potentially dangerous turning rates of Gemini launch vehicle)
BROWN Attitude control system for the direct measurement explorer-A satellite(Attitude control system, using magnetic interaction with geomagnetic field to check spin rate and spin axis orientation of spin-stabilized Explorer A satellite)
BURROUGHS et al. Discussion of the applications and essentials of signal flow graph techniques for reliability engineering
SAGALYN et al. Positive ion sensing system for the measurement of spacecraft pitch and yaw, Air Force D-10 experiment flown on Gemini 10 and 12(Positive ion sensing system used to measure pitch and yaw on Gemini 10 and 12 spacecraft)
KARDASHOV Quantitative analysis for decreasing the order of a differential equation of automatic control systems
NELSON On the use of optimization theory for practical control system design(Optimal control theory in system design evaluation and performance specification)
BOLLING et al. Electrostatic potential sensors for use on the NASA Scout evaluation vehicle S-131 R(Electrostatic potential sensors for use on NASA Scout vehicle S-131 R)
MYERS Description of the procedures needed to predict the reliability of highly redundant satellite systems
NAGEL Space navigation instrumentation is discussed, specifically the use of infrared sensors in space vehicles
CHAPMAN 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
BOURBEAU Determination of initial angle-of-attack, initial body rate and turning moment that a missile can tolerate when staging in the atmosphere
RYNDA Future trends in the inertial navigation viewed against a background of the past and present with consideration of cost, reliability and accuracy
BONGIORNO Adaptive control system which does not involve direct measurements and uses model as reference element and adaptive circuitry
SMITH Evaluation of achieved reliability of the minuteman guidance and control system from various test results
POOL et al. Signal conditioning in flight-test instrumentation(Flight test instrumentation applicable in airborne signal conditioning operations)
Levinson Nonlinear feedback control systems
KAVINOV Energy of self-oscillation used to determine the stability and control system
BASARGIN et al. A device for measuring the coordinates of the center of gravity of a body in space from a photograph(Theodolitic device for measuring coordinates of center of gravity of photographed missile in flight)
SARTURE Guidance and control of rocket vehicles examined through three types of guidance- radio, inertial and combination of the two
BERTOYA Description of a simple transistorized automatic-gain-control circuit which uses a thermistor as the control element
OBRIEN Automatic flight control and instrumentation
GREGORY Adaptive flight control summary
ROBINSON The system approach to microminiaturization(Production techniques for microminiaturized systems used in inertial guidance systems)
WILD Radio-compass nondirectional aircraft antenna location and its influence on correct flight indication
REID et al. Component reliability design and construction for the electronics package of the telstar satellite, including regulator and canister construction