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Report Fsw003.1 Faculty Salary Survey, Ay87-88, Wku University Senate

Faculty Senate

1. Memo explaining this section of the salary survey
2. Average Salaries by Rank at WKU: Actual
3. Average Salaries by Rank at all Public Category IIA Institutions & at WKU

Rrs - A Multipurpose Reusable Reentry Satellite, John Givens, Richard Schaupp

Small Satellite Conference

This paper describes a low-cost, multipurpose Reusable Reentry Satellite (RRS) which can carry a variety of experiments into space, remain in orbit for up to 60 days, return autonomously to Earth and be refurbished for reuse. Potential user applications include life science, commercial, and others. As presently conceived, the vehicle is a blunt ballistic entry vehicle with an internal cavity for accommodating user payloads, including those utilizing the STS GetAway Special (GAS) canister. The spacecraft provides payload power, transmits payload data, receives payload commands, and controls payload cavity thermal conditions. A variety of vehicle sizes with base diameters within the …

Safety And The Small Satellite Builder, James Smith

Small Satellite Conference

The importance of safety and the early understanding and incorporation of safety requirements into all phases of the small satellite's life can not be over-emphasized. Safety is an engineering discipline, a mind set, a conscious practice of all involved in the small satellite. There are numerous safety requirements which must be complied with and there are numerous processes and procedures which the small satellite must be subjected to. Being aware of the requirements and procedures and assuring their accomplishment is a total project responsibility. Risk cannot be totally eliminated, but it can be managed and controlled. This paper was written …

Spin Stabilized Satellites, George Lawrence

Small Satellite Conference

During the six years of operation of the Solar Mesosphere Explorer (SME), LASP's mission analysis system has determined the attitude of this spinner to 0.03° rms. Suggestions to improve future system designs to achieve more accuracy are given in terms of: 1) Thermal expansion control. 2) Reduction of eddy current drag. 3) Reduction of aerodynamic torques. 4) Averaging of horizon sensor data. 5) Use of a star scanner. 6) Commandable dynamic balance adjustments. Accuracy of 0.001° seems possible and will be discussed in the context of geomagnetic mapping.

Meeting Minutes, Wku University Senate

Faculty Senate

Meeting regarding the president's attendance at Faculty Senate meetings, constitution revision, Athletic Committee, Tom Jones symposium, budgets, COSFL, minority recruitment and faculty recognition.

October Agenda, Wku University Senate

Faculty Senate

Agenda for October meeting with resolution endorsing report of the Task Force on Faculty Recognition.

Consolidated Space Test Center Capability To Support Small Satellites, Lt Col David Smith

Small Satellite Conference

No analysis of small satellite programs is complete without thorough consideration of the operational concept that will support them. It is not uncommon today that a space system's lifecycle cost will show that operating costs exceeded development and production costs. This is particularly true for programs that hope to reduce spacecraft expense by transferring, to the ground, as much of the on-board processing requirements as operationally feasible. Facility, hardware, software, maintenance, manning, training, communications, on-orbit operations and launch costs all factor into the total operations spending and must be prudently considered.

A Ground Station For Use With Small Satellites, Ronald Muller, Charles Vermillion

Small Satellite Conference

NASA has plans to initiate a new series of inexpensive, Scout-sized Explorer satellites to be placed in service starting in the early 1990's. Today's computer technology makes it feasible and economical to build such a satellite so that it can be operated from a single, small ground station. This station would be located at the satellite user's facility and it would operate autonomously. Except for launch and support during operational emergencies, no NASA facilities would be required. We show this way of operating will result in a lower cost mission with no performance penalty.

Single-Station Tracking For Orbit Determination Of Small Satellites, Roger Hart

Small Satellite Conference

Available methods of orbit determination and satellite observation are briefly reviewed and evaluated for suitability in tracking small satellites from a single ground station. Radio interferometer and Doppler tracking appear useful and are discussed in further detail. Distinctions in accuracy and application between the two methods are made.

A Satellite Link Analysis Tool For A Portable Ground Station, Capt. William Jackson

Small Satellite Conference

The product of this research effort is a comprehensive and integrated software package for the analysis of digital satellite links. The system is designed to run on the IBM PC, and would be a useful addition to any portable ground station based on a compatible personal computer. The system performs three basic classes of functions: satellite orbital analysis, antenna gain pattern plotting, and link analysis. The first class of functions includes the computation of such quantities as velocity, orbital period, and coverage area for satellites in circular and elliptical orbits. The second class of functions is concerned with plotting the …

The Application Of Vector Quantization To Image Compression For Satellite Imaging Systems, Paul Israelsen, Richard Harris

Small Satellite Conference

Over the past few years it has become more and more common to use satellites for imaging applications. The imaging may be performed in the visual realm using cameras, or may infrared or electro-optical using multi-sensor arrays. One thing that all these imaging techniques have in common is the large amount of data that must be stored and/or transmitted per image. If many images are being gathered over a relatively short time, then storage and power requirements may become too large for small satellite systems.

The Integrated Housekeeping Unit: A Method Of Telemetry, Command And Control For Small Spacecraft, Gordon Hardman

Small Satellite Conference

In a small satellite environment where the total power budget for telemetry command, ranging and all satellite control functions is not to exceed 2 Watts rather focused measures must be taken to consolidate these functions. Since 1975 AMSAT has been developing the concept of the Integrated Housekeeping Unit (IHU) for this purpose. The IHU combines the traditional telemetry encoder and command decoder with a multi-tasking microcomputer so that this single module is capable of handling all spacecraft functions simultaneously. The nature of the orbit planned for the series of spacecraft for which this unit was developed results in a high …

Design Of A Low-Cost Data Communications/R.F. System For Use With Low Earth Orbiting Store And Forward Satellites, Lynn Chidester

Small Satellite Conference

The functional requirements and system overview for a low cost data communications system for small satellite use are presented. Tradeoffs of system parameters will be discussed such as: cost, transmission speed, power consumption, spectrum usage, and system complexity. Link calculations at 137 MHz, with transmission speeds of 9600 BPS, monopole antennas, and a 50kHz bandwidth show that adequate signal margins can be obtained with 2 Watts of R.F. power for most conditions. Use of low cost, amateur or commercial type radio equipment requires only minor modifications, and creates small reliability and performance risks.

Orion: A Small, General Purpose, Low Earth Orbit Satellite Bus Design, A.E. Fuhs, M.R. Mosier

Small Satellite Conference

A low cost general purpose mini-satellite bus has been designed to support a wide variety of small scientific and commercial payloads. The design provides a number of launch options, including the new NASA extended Get-A way-Special (GAS) canister and several small expendable launch vehicles. The satellite is 19 inches in diameter, 35 inches high and weighs approximately 270 lbs. The satellite bus provides telemetry, attitude control, orbital boost/station keeping, electrical power, microprocessor and data storage for up to 50 lbs. of user payload. The satellite has a hydrazine propulsion system, with up to 2600 ft/sec delta-v capability. On-board propulsion reduces …

Mission Design And Operations: Spartan-Halley As A Paradigm For Small Satellites, Alan Stern, J.G. Watzin, N. White

Small Satellite Conference

The SPARTAN reusable spacecraft opened a new arena for innovative scientific and engineering experimentation in low earth orbit. SPARTAN's a free flying, 3-axis inertially stabilized spacecraft which is deployed and retrieved by the Space Shuttle. The spacecraft is unique in that it performs all scientific observations as well as its guidance, navigation, and control functions completely autonomously. This paper will describe the innovative approach that was taken in the design of the SPARTAN guidance and navigation system for a 48-hour observation of Halley's Comet near perihelion passage. Autonomous vehicle navigation techniques that utilized solar sensors, a single star tracker, a …

System Design And Capabilities Of A Current Technology, Low-Cost, Small Satellite, J.R. Stuart, D.L. Taylor

Small Satellite Conference

Ball Aerospace, with its successful background and strong interest in low-cost lightweight satellites, is studying the designs of current technology satellites for a variety of launchers (e.g., STS/GAS, Pershing, Scout, Poseidon, Conestoga, Titan 11, ILV, and Delta II). Ball Aerospace has completed the design of a current technology, multi-mission, low-cost Scout-compatible satellite. This paper summarizes the system design features and capabilities of this Ball Scout Satellite (BSS). The BSS is designed to accommodate a wide range of Earth and celestially oriented missions, both spinning and 3-axis stabilized. The BSS design provides a marked improvement in payload support capabilities (mass, power, …

The Uosat Spacecraft Programme, M. N. Sweeting

Small Satellite Conference

Spacecraft-designed, built and operated by traditional means-have proved extremely costly, thus limiting access to space to large organizations work within enormous budgets. The Amateur Satellite Service, over a period of 20 years, has demonstrated that small spacecraft can be built very inexpensively, and as a low-cost stimulus to technology. The UoSAT Programme at the University of Surrey (UK) has developed highly sophisticated yet inexpensive small satellites through adopting imaginative, cost effective spacecraft engineering techniques. Two UoSAT spacecraft, UoSAT 1 & 2, have been in orbit since 1981 and 1984 respectively supporting active space engineering research, space science and space education …

System Concepts For The Scout Explorer, William Hibbard

Small Satellite Conference

NASA's Explorer program is being expanded to include a series of "Scout-class" science missions. These small spacecraft will be supported by a Standard System, including a spacecraft bus and a transportable ground station. The system concept is being developed in anticipation of an experiment solicitation in 1988. The spacecraft will be a Sun, vertical and star pointer, momentum stabilized, with S-band communications direct to ground stations. The transportable ground stations allow Principal Investigators to assume complete control of the spacecraft. The Standard System is optional to each mission and may be used in part, in total, or not at all.

Inflatables For Lightweight Satellite Application, Geoffrey Williams

Small Satellite Conference

In the 1960's, NASA put considerable effort into inflatable space structures, including Echo I and II, PAGEOS and Explorer IX and XIX. Overall, inflatables in space have been successful and their inherent advantages have been demonstrated. Inflatable space systems invariably require less packaged volume, are lower in weight and cheaper through both development and production phases than competing mechanically erected systems. The meteoroid problem is much less than originally anticipated because large antennas and reflectors require very low inflation pressures; gas lost through leaks can be replaced from a small supply of reserve gas. Inflatables apply themselves extremely we 11 …

The Use Of Graphite/Epoxy Composite Structures In Space Applications, Rudy Lukez

Small Satellite Conference

Graphite/epoxy composite materials are being used increasingly for numerous space applications. Engineers are interested in these materials because of their favorable mechanical characteristic of high strength/high stiffness to weight ratio and potential for zero or near-zero coefficient of thermal expansion. This paper presents an overview of graphite/epoxy composite use for space applications. The historical uses and environmental concerns of graphite/epoxy composites in the low earth orbit are reviewed. Detailed information on the design, fabrication and testing of struts for potential Space Station use is presented as an example of graphite/epoxy material usage for space applications.

Nusat Ii - Manufacturing Design Of Lightweight Satellites, John Boyer Jr.

Small Satellite Conference

The successful flight of NUSAT I during 1985 and 1986 encouraged the Weber State College Center for Aerospace Technology (CAST) to continue developing other small satellites. This paper focuses on the mechanical design and construction of the NUSAT II space frame.

Telescience Vapor Crystal Growth Using Small Satellites, Terrance Thomas, David Yoel

Small Satellite Conference

Small satellites are expected to play an increasingly important role in the flight of space experiments in the post-Challenger era. This paper describes a telescience vapor crystal growth experiment using a small standardized satellite carrier launched into low earth orbit. Scenarios are presented in which crystal growth experiments using a transparent furnace can operate from 8 hours at 900° C up to 48 hours at 125°C. This is followed by an 89 hour period during which the battery is slowly recharged from solar cells mounted on the satellite carrier. Tracking, telemetry, command, and monitoring requirements can be met by utilizing …

Comparison Of Recent Scout Class Spacecraft Subsystem Weights For Future Weight Estimation Purposes, Kevin Heffernan

Small Satellite Conference

The purpose of this paper is to compare the subsystem weights of four recently built Scout class satellites to determine if there are any trends which can be used in future weight predictions. The four satellites whose weights are being compared are: MAGSAT, AMPTE, NOVA III, and Polar BEAR. These four spacecraft are different in many areas and were chosen as such, so as not to bias the data. In order to systematically compare the subsystem weights and extend the results to future spacecraft, a weight accounting system is developed. Thirteen subsystems are baselined. The specific pieces of hardware that …

A Survey Of Recent Apl Spacecraft Power Systems, Gregg Herbert

Small Satellite Conference

During the last 25 years APL has designed and built more than 50 small spacecraft, many being unique designs. The Power Systems of these spacecraft take many forms but almost all use a solar cell array and a Nickel-Cadmium battery. An overview of seven spacecraft power systems is presented. Four of the spacecraft are gravity gradient stabilized in a near-polar Low Earth Orbit (LEO). The remaining three spacecraft are spin stabilized, two with near-equatorial orbits. Both dissipative and nondissipative charge control systems are represented and the solar array configurations, all consisting of deployable panels, are described. Power system performance parameters …

The Small Astronomy Satellite (Sas) Power Systems, Ralph Sullivan

Small Satellite Conference

NASA's Small Astronomy Satellites were designed and developed by The Johns Hopkins University's Applied Physics Laboratory for use in the early 1970's. They were Scout launched, spin stabilized satellites intended for a near equatorial, 550 Km, circular orbit. Since the spacecraft were designed so that their spin axis could be pointed in any direction in inertial space, an omnidirectional solar cell array was required. An additional significant constraint on the solar cell array design was that the effect of atmospheric drag on the spacecraft stabilization had to be minimized. These requirements led to the need for an electronic battery charge …

A Study For Semi-Passive Gravity Gradient Stabilization Of Small Satellites, Ali Siahpush, Andrew Sexton

Small Satellite Conference

This paper gives the results of a dynamical analysis of the Globesat gravity gradient stabilized satellite in a 500 km circular orbit. The linearized equations of motion are developed and the stability of the satellite is investigated. The satellite is equipped with magnetic torquers for the purpose of providing attitude correction torques. These correction torques can be used to effect large changes in orientation and for producing small impulses for damping residual librational motions. The analysis shows that such a satellite can be captured into a gravity gradient stabilized mode, and that residual motions can be damped to small steady …

"Bare Bones" Propulsion For Small, Low Cost Satellites, Richard Daniels

Small Satellite Conference

The radio amateur satellite community pioneered in the design, fabrication and launch of small, low-cost satellites. While these satellites became increasingly more sophisticated, they continued for years as piggyback passengers with no capability for orbital adjustment once released. Beginning with the Phase III spacecraft series an onboard propulsion capability was included permitting significant adjustments to the initial orbit. This paper describes the design of the propulsion modules of three Phase III spacecraft initially using a solid rocket motor and moving to a bi-propellant liquid propulsion system in following spacecraft. While the specific hardware and system design utilized may not be …

Viking And Mailstar: Two Swedish Small Satellite Projects, Sven Grahn

Small Satellite Conference

The VIKING Scientific Satellite launched piggyback on Ariane in February 1986 collected magnetospheric data for 444 days. The project was highly successful and of low cost. The key to low cost and high performance lies in a careful formulation of mission requirements. Costly increases often come from secondary or derived requirements, i.e. requirements which optimize performance or scientific return. To squeeze out a few more per cent of science data may perhaps double the cost. The paper describes examples of how such cost traps were avoided in the VIKING project. MAILSTAR is a low-orbit store-and-forward satellite communications system conceived by …

Army Concept For Space And Lightsat, Ltc Ron Forkenbrock

Small Satellite Conference

This paper explains the Army's role in space both now and in the future, and how space capabilities support joint Air/Land Battle doctrine across the full spectrum of conflict. It concludes with a focus on the Army's requirements for the use of lightsats.

Scout/Crres, Patrick Cudmore

Small Satellite Conference

This paper describes a Scout-launched chemical release satellite that the Goddard Space Flight Center (GSFC) will design, fabricate, integrate, test, and qualify. This will be done using off-the-shelf components assembled to a NASA/GSFC-supplied spacecraft structure as follows: Four chemical release modules from the CRRES satellite (BASD), and Communications, data handling, and power systems from GLOMR (DSI). This satellite will also include flight electronic instrumentation that will measure electric and magnetic fields and particles, and will be furnished by TBD.