Showing papers in "IFAC Proceedings Volumes in 1970"

TL;DR: Saturn launch vehicle navigation, guidance and control system, discussing optimal system design for flight path optimization as mentioned in this paper, discusses optimal trajectory optimization for a single-stage launch vehicle with a single launch vehicle.

TL;DR: In this paper, it was shown that a constant bias plus exponentially-correlated noise is a better approximation than white noise or a random walk process for the estimation of yaw-gyro drift.

TL;DR: In this paper, a minimum-time control law was developed for attitude control of the Apollo lunar module, which was implemented in the digital computer of the onboard primary navigation, guidance, and control system.

TL;DR: A proposed system of computers, multiplexers, dedicated processors, displays, sensors and effectors configured to execute all checkout, computation, control, communication, and data reduction formerly handled by independent systems on board and on the ground is outlined.

TL;DR: In this paper, the authors recall some mathematical aspects of the dynamics of a non-rigid satellite spin stabilized taking into consideration the behaviour of the liqiid propellant, and provide the mathematical frame for the experimental work in order to make the identification of the system possible.

TL;DR: In this paper, an approach to its solution based on fast numerical prediction of the future trajectory is described, and the program described here, however, is small and fast enough to fit the on-board computer.

TL;DR: In this paper, the authors used hydrazine or electric thrusters to control the attitude of a synchronous satellite, which can be achieved by spin stabilization or by more complex solutions.

TL;DR: The DODGE satellite was launched on July 1, 1967 into a near-synchronous orbit to demonstrate gravity-gradient stabilization at that high altitude and to experiment with various design parameters and damping techniques.

TL;DR: In this paper, the satellite system operation is subdivided naturally into two parts: satellite orbit determination and navigation by the user, where the satellite is tracked from one or more ground stations and the satellite ephemerides determined along with calibration information on on-board equipment, such as a precision oscillator.

TL;DR: In this paper, an electromagnetic control system to control the spin rate and spin axis orientation of the ISIS ionospheric research satellites is described, where a single air-cored coil around the periphery of the satellite with its axis at right angles to the spin axis is switched by signals originating from a flux gate magnetometer.

TL;DR: In this paper, the authors describe the operational functions performed by both spacecraft computers, their design, program organization, control options, displays, inputs, and crew interfaces, as well as a time history of the operations and procedures used by the crew, and the computer's role, in each vehicle during rendezvous.

TL;DR: In this paper, the dynamics of a satellite with a gravitational stabilization system is investigated, and the parameters providing minimum duration of the natural oscillation damping of the system are determined.

TL;DR: In this paper, the attitude translation motion coupling effect on stability of gravity-stabilized drag-free satellites is studied, and the effect of attitude translation on stability is discussed.

TL;DR: Gyroless attitude control system for pointing Aerobee sounding rocket payload at sun using solar sensors as mentioned in this paper was used to point the sounding rocket at the sun using a solar sensor.

TL;DR: In this article, the basic relations for the active magnetic orientation of the spin axis of a spinning satellite are discussed, and a simple logic control circuit is used for the generation of the control torques.

TL;DR: In this paper, the regularization of the free plane motion is introduced showing the role of time repolarization for the rendezvous problem, and the general KS transormation is described and applied for solving this problem.

TL;DR: In this article, a general procedure for solving the geometrical problems of rarefied gases is given, which can be extended to forces and torques due to solar pressure.

TL;DR: In these applications the Gauss-Newton algorithm has been compared with more classical methods (gradient, Partan) and has been proved much more efficient.

TL;DR: In this article, a comparison of roving, flying, and hopping devices is made based on vehicle weights and excursion durations, and predictions on implementation of flight models are given.

TL;DR: In this paper, the authors compared the performance of the augmented state and measurement differencing type filters for the radio-guided third stage of the EUROPA 1 carrier vehicle with a comparison of the estimation errors and covariances at individual instances.

TL;DR: The interest of using on-board processing systems for bandwidth compression and error correcting coding in telemetry and communication links is outlined and a convolutional coding system is in particular described with threshold decoding.

TL;DR: Tensor analysis is shown to be very helpful in this new approach to multiplexing schemes and evaluation of Crosstalk in terms of tensor forms results in simplification when automatic computing techniques are used.

TL;DR: In this paper, the need for orbit adjustment capability for operational satellites is established, not only on the basis of future mission requirements, but also as a solution to the ground data-handling problems occasioned by many low-altitude satellites orbiting at the same time.

TL;DR: In this article, the authors examined the case of an inertial platform for which the high accuracy requirements call for a sophisticated model of the random drift and the need of limiting the number of star-trackers requires that the device can run, almost for a short time, in the prediction mode.

TL;DR: A technique for determining trajectories that is based on adjusting the equation involving the direction of the thrust and a considerable number of parameters by taking into account the constraints and the final conditions is developed.