Networks of low-Earth orbit store-and-forward satellites

A slotted multiaccess protocol is proposed for networks of low-Earth orbit store-and-forward communications satellites. Networks of this type would provide communication between low cost geographically distributed Earth stations, and would be particularly attractive in areas where conventional terrestrial communications systems were not available. Applications of this type include data acquisition and remote process monitoring. The proposed protocol incorporates time division multiplexing (TDM) on the downlink, slotted Aloha with collision resolution on the uplink, and an automatic repeat request (ARQ) algorithm. Since the network connectivity is intermittent, analysis of networks of this type is difficult. Nevertheless, relationships among the performance parameters for a general network are deduced, and performance of three particular network configurations is studied via simulation     

Predicting the visibility of LEO satellites

We present a simple algorithm to determine the visibility-time function of a circular low Earth orbit (LEO) satellite at a terminal on the Earth's surface. The simplicity of the algorithm is based on approximating the ground trace of the satellite (which is not a great circle due to Earth's rotation) during a time interval of the order of in-view period, by a great-circle are. This enables us to use spherical geometry to compute the location and time epoch of the observation of the closest approach of the satellite's ground trace to the terminal. This is also the epoch of the observation of the maximum elevation angle from the terminal to the satellite. Applying a result derived relating the maximum elevation angle to the in-view period, we obtain the visibility-time function of the satellite at the terminal. Numerical results illustrate the accuracy of the algorithm for a wide range of LEO orbit altitudes     

Imaging of the outer planets and satellites

Imaging is the most widely applicable single means of exploring the outer planets and their satellites and also complements other planet-oriented instruments. Imaging generally is more effectively carried out from a three-axis stabilized spacecraft than from a spinning one.Both specific experimental and broader exploratory goals must be recognized. Photography of Jupiter from terrestrial telescopes has revealed features which were neither predictable or predicted. Close-up imaging from fly-bys and orbiters affords the opportunity for discovery of atmospheric phenomena on the outer planets forever beyond the reach of terrestrial laboratories and intuition. On the other hand, a large number of specific applications of close-up imaging to study the giant planets are suggested by experience in photography from Earth and Mars orbit, and by ground-based telescopic studies of Jupiter and Saturn. Photographic observations of horizontal and vertical cloud structure at both global and finer scale, and motions and other time changes, will be essential for the study of atmospheric circulation. Size and composition of cloud particles also is a credible objective of fly-by and orbiter missions carrying both imaging and photo-polarimeter experiments.The satellites of the outer planets actually constitute three distinct classes: lunar-sized objects, asteroidal-sized objects, and particulate rings. Imaging promises to be the primary observational tool for each category with results that could impact scientific thinking in the late 70's and 80's as significantly as has close-up photography of Mars and the Moon in the last 10 yr.Finally, it should be recognized that photography occupies a unique role in the interaction between science and the popular mind. This popular, educational aspect of imaging constitutes a unique aspect of 20th Century culture. Imaging therefore is not only a primary basis for scientific discovery in the exploration of the outer planets, but an important human endeavor of enduring significance.Contribution No. 2163 of the Division of Geological and Planetary Sciences, California Institute of Technology, Pasadena, California 91109.This is one of the publications by the Science Advisory Group.     

Detecting near collisions for satellites

A highly efficient algorithm is presented for detecting near collisions involving satellites. Rather than examine all possible pairings of a satellite with another orbiting object, the new approach examines trajectories at a sequence of coarse time steps. Objects which are spatially isolated cannot be involved in a collision, and are discarded. The time steps, orbit calculations, and discarding are repeatedly refined until the only remaining objects experience near collisions.     

The DAVID mission in the heritage of the SIRIO and ITALSAT satellites

The DAta and Video Interactive Distribution (DAVID) mission belongs to the Small Missions for Science and Technology Programme of the Italian Space Agency (ASI) and is aimed at pioneering the use of the W-band channel for telecommunications experiments. Furthermore, it envisages the test of a novel technique, for an optimal sharing of the satellite resources, among a grid of Earth terminals, that could be usefully exploited in future W-band operational systems.     

Third world radiation threats to satellites

The era of hardening military satellites against nuclear events, lasers, and high-power microwaves, appears to have come to an end. A case is made here for maintaining rudimentary nuclear, laser, and high-power microwave (HPM) hardening requirements in order to protect against developing third world threats. The third world nuclear threat is well known. Less appreciated is the fact that third world laser and microwave threats have changed radically in the past few years     

Optimal control in the east/west station-keeping manoeuvres for geostationary satellites

This paper addresses the optimal computation in terms of fuel consumption of the sequentially required tangential correction manoeuvres to control geostationary satellites within the longitude band. In fact, by using optimal control techniques, the Sun pointing perigee strategy (which only determines the best time of the day for the tangential manoeuvres) is formulated as a nonlinear programming problem with inequality constraints so that the proposed approach provides an optimal way to determine the remaining parameters for the station keeping, i.e., the time interval between successive corrections and the value for the eccentricity control to totally optimize the computation. Furthermore, by minimizing a cost function derived for the total manoeuvres sizes required in a year, a numerical simulation is performed to illustrate this approach. The computation shows how geostationary mission lifetimes may be extended up to half a year or more.

Resumen

En este papel se trata el cálculo óptimo en términos de consumo de fuel de las maniobras tangenciales periódicas necesarias para controlar satélites geoestacionarios dentro de la banda en longitud. En concreto, utilizando técnicas de control optimal, la estrategia perigeo hacia el Sol (que solo determina la mejor hora del día para las maniobras tangenciales) se formula como un problema de programación no lineal con constreñimientos, de tal forma que el tratamiento propuesto proporciona una forma óptima de determinar los parámetros restantes para el mantenimiento en estación, esto es, el intervalo de tiempo entre dos correciones sucesivas y el valor para el control de excentricidad para optimizar totalmente el cálculo. Además, mediante la minimización de una función de coste obtenida para todas las maniobras necesarias en un año, se realiza una simulación numérica para ilustrar esta metodología. Los cálculos muestran cómo se puede extender el tiempo de vida de una misión geostacionaria hasta medio año o más.     

Analysis of solar panel orientation in low altitude satellites

The computation of the optimal orientation of solar panels which are fixed to the body of the satellite, from the point of view of average power, is presented. In practical cases, some of the parameters which determine the optimal orientation vary during the lifetime of the satellite. In these cases we compute a worst case optimum, which maximizes the average power in the worst case situation. Finally, an application of these procedures to an Earth observation satellite is performed     

Wireless power transmission: the key to solar power satellites

Maturing of the enabling technologies has provided much of the infrastructure to support the development of a commercial Solar Power Satellite program. Solar Space Industries was formed to accomplish this goal. The basis of their development plan is to build a Ground Test Installation that will duplicate, in small scale on the Earth, all aspects of the power generating and power transmission systems except for the space environment and the range and size of the energy beam. Space operations issues will be separated from the power generation fixation and verified by testing. Doing the developmental testing on the ground instead of in space will result in a low cost program that can be accomplished in a very short time. The concept is to build a Ground Test Installation that couples an existing 100 kW terrestrial solar cell array to a phased-array wireless power transmitter based on a subarray. Power will be transmitted over a 1-¼ mile range to a receiving antenna and then fed into a commercial utility power grid. The objective is to demonstrate the complete function of the Solar Power Satellites, with the primary issue being the validation of practical wireless power transmission. The key features to demonstrate are: beam control, stability, steering, efficiency, reliability, cost, and safety     

Pictures from meteorological satellites and their interpretation

Summary It can thus be seen that organization in various stages of tropical storm development are frequently seen in satellite pictures. And it appears that further work will establish relationships between the size and organization of the cloud masses with the coarse magnitude of the wind speed in the storm area.     

Electrical power distribution on space based radar satellites

The radar payload on a space-based radar (SBR) satellite could require tens of kilowatts of power distributed to many small loads over a large area. This poses special problems for the power distribution and control system (PDCS). A study that examined the power requirements of an SBR spacecraft is reported. A baseline prime power system, generating about 30 kW, was derived. The proposed distribution network would transmit 240 V at 20 kHz. The voltage would be downconverted in one converter for about 100 transmit/receive modules. The design considerations are discussed, and the baseline PDCS is described