Digital Commons Network^™

A Signal Processing Technique For Space Object Identification, Lawrence A. Wan

Space Congress® Proceedings

This paper develops a radar system which is capable of measuring the lateral dimension of satellites* Such information contributes toward the identification of space objects arid assessing their missions. The lateral dimension of a satellite can be inferred from the resolution of the angular separation of scatterers on that object.

Fundamentally, the technique employs doppler data processing in such a manner as to effectively synthesize a large radar antenna* A time invariant angle was formulated from the orbital trajectory and is the basic parameter xvhich is measured to determine the spatial separation of scatterers on the satellite* This is a …

Saturn V System Philosophies, Ludie G. Richard

Space Congress® Proceedings

The Saturn V launch control and checkout system is based on demonstrated advanced techniques. The system employs redundancy, repairability, rigid interface control, and a rugged and reliable central system to meet Saturn performance and reliability goals.

Two computer complexes placed back to back and interconnected through a redundant data link provide automated and remote control functions for the system. These computer complex systems, developed concurrently with the Saturn programs, provide essential functions but are segmented to reduce the amount of equipment that must operate during critical periods.

Display and control capabilities permit the operators to meet all normal and emergency …

The Importance Of Aerospace Contamination Control, Hubert C. Normile

Space Congress® Proceedings

A recent technology "Contamination Control" is described with emphasis on its importance to aerospace missions. A number of incidents occurring at Cape Kennedy are described in which contamination played a part. How contamination may seriously affect an aerospace mission is also brought out. Various types of contamination are described. The importance of Management's role,, carefully selected personnel,, supervision,, training^ quality control, adequate facilities and working conditions are discussed.

Communication System Considerations For Manned Orbiting Laboratory Stations, E. I. Muehldorf

Space Congress® Proceedings

This paper discusses the philosophy of communication systems design for space stations currently under study, such as MORL, LORL and other similar concepts. For the early stations, the communication systems will make use of off-the-shelf equipment. The communication requirements existing for th& different station concepts is summarized. The most important factors for choosing the communication system meeting the requirements are discussed.

A communication system for an early two man laboratory is presented, and its primary features are discussed. Finally the problem of accommodating the different kinds of telemetry data in a composite spectrum is discussed.

Reliability Determination By The Nonparametric Method, Edgar P. Virene

Space Congress® Proceedings

The method presented in this paper is provided for engineers' use in rapidly analyzing test or operational use data when the data has not been identified with any of the commonly used failure frequency distributions, such as the Normal, Exponential, or Weibull distributions. This nonparametric method allows determination of reliability (R), percentage of confidence (C), or test sample size (n) required. That is, any one of the values can be determined by this method if the other two are known, assumed, or stipulated.

Design Requirements For Manned Orbital And Lunar Bases, J. T. Celentano M.D., D. Amorelli

Space Congress® Proceedings

Satisfaction of his physiological needs is the prime requirement for assuring man ! s performance in a short-duration space mission. Many authorities feel that long-duration missions will require essentially only an increase in requirements proportional to the length of the mission, based upon short-term figures. The authors contend, on the other hand, that considerations regarding the most efficient use of man in an actual space environment presume that all of the environmental requirements for human existance have been provided. These needs can be satisfied through appropriate design requirements, established early in the developmental program, so that man can exist and …

Management And The Minuteman, Carl A. Jansen

Space Congress® Proceedings

Since the advent of the "Space Age", the United States has achieved many significant firsts in the field of technology. This is particularly evident in the development of today 1 s advanced weapon systems. The term, weapon system, is defined as an instrument of combat integrated with all it f s associate equipment, support facilities and services. This includes assembly of material, personnel, installations, plans, directives and procedures required to enable the instrument of combat to accomplish it's tactical mission. General Schriever, Commander of the Air Force Systems Command (AFSC) stated at the National Advanced Technology Management Conference held in …

Adaption Of Self-Phasing Antenna Systems To Space Missions, Sinclair Chen, Matthew E. Brady

Space Congress® Proceedings

The ability of the self-phasing antennas to nor only provide high gain but also to minimize the requirement of satellite attitude control has rendered them very attractive for use in satellite communication systems. The potential advantages and versatility afforded by self-phasing antennas are analyzed in this paper with discussions of results obtained for two specific applications.

The paper begins with a description of two types of self-phasing antennas., namely^ the Van Atta array and the so-called phase conjugation array; similarities and differences in operation of the two types of arrays of various geometrical configurations such as planar^ cylindrical^ and spherical^ …

Apollo Exploration Shelter System, Richard E. Rudd, Robert M. Sando

Space Congress® Proceedings

This paper presents two unique personnel shelter systems. When functioning either alone or with MOLAB, they will provide the capability for maintaining 2 or 3 astronauts on the lunar surface for a duration of 30 to 44 Earth days with a stay-time growth potential of 90 days. These shelters offer the United States Lunar Exploration Program the operational flexibility and number of man-days on the Moon required to accomplish a wide range of necessary exploration and scientific missions, including a capability to maintain and repair the LEM, MOLAB, and the shelters themselves. An additional feature of the system is that …

Accelerated Procedure For Determination Of Gas-Off Product From Space Cabin Materials, Paul P. Mader, Gerald V. Colombo

Space Congress® Proceedings

A fast and accurate method for the empirical evaluation of the degassing characteristics of materials and supplies carried aboard a space capsule is described. The proposed procedure utilizes 72-liter flasks as reaction chambers. Materials to be tested were introduced into one group of flasks for a period of 30 to 60 days. The flasks were maintained under temperature, pressure, and lighting conditions expected to prevail within the spacecraft. Parallel experiments were conducted over a 24-hour period at a flask temperature of 120°F obtained by irradiation of the flask with mercury vapor lamps. At regular, predetermined intervals the flask atmospheres -were …

Lunar Surface Navigation For A Roving Vehicle (Molab), M. Streicher

Space Congress® Proceedings

This paper presents an examination of the guidance and navigation requirements for NASA's "MOLAB" vehicle (Mobile Lunar Lab.). The functions and capabilities necessary to guide and navigate a roving vehicle over the area of the lunar surface for exploration and experimental investigations are considered. A mission profile is afforded — providing a general outline of environmental, navigation and guidance, and survey requirements.

The fact that the moon will eventually be explored by man is a foregone conclusion. Aside from the central fact that it exists and can be reached, which in the context of the entire history of the human …

Factors Affecting The Thermal Equilibrium Of A Subject In The Apollo Extra-Vehicular Mobility Unit, Ronald Lang, Robert G. Syversen

Space Congress® Proceedings

The development program for the Space Suit System to be used in Project Apollo is approaching the end of its second year. With the first prototype units delivered and tested, reassessment of the basic input assumptions, conceptual approaches, and system objectives can now be undertaken. System performance test data justified many of the untiled concepts utilised in the first prototype equipment. Nevertheless, the evaluation revealed several problem areas which required more refined technical approaches and, in some cases, extension of current state of the art knowledge.

The pressure suit, the Portable Life Support System, and the accompanying accessory garments used …

Designs To Control Wind-Induced Oscillations Of Launch Vehicles, D. D. Tomlin

Space Congress® Proceedings

During the prelaunch time, launch vehicles will be exposed to prevailing ground winds. When circular cylindrical structures (such as launch vehicles) are exposed to winds, vortices are shed alternately from the sides of the structure which causes alternating lift forces to act upon the sides. Under certain conditions large oscillations can occur depending on the vehicle's structural damping and the characteristics of the wind forces. Wind tunnel investigations of launch vehicles 1,2 indicate that launch vehicles do experience relatively large oscillation amplitudes.

This paper discusses the phenomenon of vortex shedding and techniques of calculating response of cylindrical structures subjected to …

Signature Studies For A Re-Entry System, Murray Gunar, Robert Mennella

Space Congress® Proceedings

The Eastern Test Range (ETR) has recently experienced increasing demands for signature data. Satisfying these demands requires the use of specialized equipment, techniques, and personnel of varied backgrounds. Since this capability has recently been expanded here at the ETR, it is the intent of this paper to present a broad survey of the techniques and equipment being used. Because of the complexity of the subject matter and security requirements it was necessary to avoid greater detail. Much of the information presented here was extracted from unclassified sources and the figures and data that describe the hypothetical test are based on …

Real Time Estimation Of Life-Distribution Parameters, George E. Henry

Space Congress® Proceedings

Highly compressed time schedules, now routinely applied to the development of adyanced military and space systems, generate the need to arrive at management decisions without waiting for completion of detailed data-gathering activity. When a number of like units are placed on life test, it is advantageous to draw tentative conclusions, as soon as possible, about the distribution of time-to-failure. Several techniques are examined whereby preliminary rough estimates can be pulled out, early during -the test. These estimates are then modified in real time as the test continues and additional units fail.

These techniques hinge mostly upon the use of order …

Saturn V Booster - The F-1 Engine, D. E. Aldrich, D. J. Sanchini

Space Congress® Proceedings

On December 20, 196^, NASA announced, "The F-l Rocket Engine, the most powerful being developed by the United States, has completed its flight rating test, and is now ready for cluster firings and actual flight.

The engine that completed FRT consists of a single thrust chamber, injector and dome, a single direct drive turbopump, a single gas generator, two each fuel pump discharge lines and control valves and also lox pump discharge lines and control valves, and a single start valve. The start valve is the only major engine part requiring electrical energy as a control device. Instrumentation to monitor …

Three-Degree-Of-Freedom Simulation Of Gemini Reentry Guidance, Martin Rush, Walter Vodges

Space Congress® Proceedings

The necessity of providing a real-time simulation of controlled reentries of the Gemini vehicle for filtering of tracking data, performance monitoring, and real-time impact prediction has led to the development of a computer program which simulates the Gemini vehicle 1 s performance during computer-controlled reentries. The system characteristics incorporated in the simulation as well as a discussion of some typical Gemini reentry trajectories make up the body of this paper.

Power Generation: A Non-Functional Subsystem, James D. Reams, Curtis Kelly

Space Congress® Proceedings

This paper endeavors to make clear the scope, breadth, diversity, and complexity of the power generation technical area insofar as Air Force interests are concerned. This will be done by presenting the non-functional character of power generation and the non-uniformity of specifying state-of-the-art. There follows an outlining of a means of categorization which encompasses power generation technology, functional subsystems and equipment, systems, and agencies influential upon power generation technology. A general approach to specifying power generation State of Technology will be suggested from the categorization.

Value Control For System Design, Ervin Leshner

Space Congress® Proceedings

Value and cost are created and therefore controlled by the designer. Design decisions made so as to achieve the proper balance of costs and performance will yield the greatest utility value to a system.

Good value may be achieved by developing a cost model and a performance requirements model in detail sufficient to permit trade-offs to be made by the individual designer.

Space Laboratory Mission Simulation And Test In A Closed Ecological System, R. L. Batterton Ph.D., K. H. Houghton M.D., T. C. Secord

Space Congress® Proceedings

The design, development, and management of advance manned space systems wiU be facilitated through the use of mission simulation techniques. These techniques are being used in the Space Cabin Simulator prograia which has been initiated at the Douglas Aircraft Company. The first phase of this program has recently been completed. In this phase, a four man crew accomplished a 30 day mission vhile confined in a double vailed space chamber which duplicates projected space cabin conditions. This mission simulation was quite successful in many respects. Some results of this phase are presented and future phases of the program are discussed.

A Model Reference Adaptive Re-Entry Flight Control System, Andrew P. Sage

Space Congress® Proceedings

The pitch plane equations of motion of a rigid body maneuvering ballistic re-entry vehicle are reviewed. A quasi-linear analysis of these equations is made about a nominal re-entry trajectory. It is demonstrated that in a large number of cases constant gain compensation for the flight control system will not be satisfactory due primarily to variations in dynamic pressure and static margin. A brief review of the adaptive concept is presented. It is shown that a model reference adaptive feedback system which has lift acceleration as the controlled variable and pitch rate as a stabilizing feedback is capable of handling the …

Unified S-Band Data Handling System, Robert S. Siebert

Space Congress® Proceedings

The data handling portion of the Unified S-Band tracking system consists of three readily separable subsystems. These are: a) the Timing System, b) the Antenna Position Programmer, and c) the Tracking Data Processor. Each of these subsystems is briefly described below.

Data Transmission At Optical Frequencies, B. A. Boershig

Space Congress® Proceedings

System analysis of an optical data transmission link and the basic expressions for beam power, received power and signal-to-noise ratio are derived. It is shown that transmission at optical frequencies requires 3-4 orders of magnitude less power than at K band. The effect of background noise, such as sunlit earth, on the signal-to-noise ratio and the improvements obtained by limiting the receiver look-back angle and use of narrow band optical interference filters are considered. In addition, a summary of the design parameters and the problems that were encountered during the development and testing of the Optical Data Transmission System are …

Manned Planetary Exploration Capability Using Nuclear Pulse Propulsion, Paul R. Shipps

Space Congress® Proceedings

This paper discusses the capability of nuclear pulse propulsion in performing manned missions to Mars and other planets using a single-stage vehicle. Recently declassified descriptive data on a 10-meter-diam nuclear pulse propulsion module design (Saturn V compatible) is summarized and a typical complete exploration vehicle employing the module is described. The specific impulse of the propulsion module is 2,500 sec, its dry weight 200,000 Ib.

The mission versatility of this single vehicle design is emphasized. The same propulsion module, and essentially the same overall vehicle design, are shown capable of performing single-stage missions requiring velocity increments ranging from under 40,000 …

Electrical Support Equipment For The Saturn V Launch Vehicle System, R. M. Aden

Space Congress® Proceedings

Electrical support equipment for checkout and launch of the Saturn V vehicle is described. Functional descriptions of the digital computer and the electrical support equipment are presented. Projects that are being developed for future use are discussed briefly.

Impact And Casualty Prediction For Malfunctioning Multi-Stage Vehicles, D. D. Van Winkle, D. L. Mootchnik, V. R. Bourgon

Space Congress® Proceedings

Presented is a rather general explanation of an automated method for determining, by Monte Carlo techniques, the probabilities of impacting populated land masses and causing a casualty when a malfunctioning multi-stage vehicle deviates from its normal instantaneous earth impact pattern. The generation of this data is explained through the use of illustrative material which describes the necessary flow of information and computational operations. The economic advantages of the method discussed are compared, in terms of manpower, computer time, and total elapsed time requirements,with those of a forerunning method used to generate such data.

Application Of The Laser To Electric Propulsion, F. A. Giori, A. S. Gilmour Jr.

Space Congress® Proceedings

Illumination of a metallic surface with focused light from a ruby laser has been shown to produce very high density ion emission, the ionized particles being emitted with substantial initial velocities. Ion currents of several amperes and electron current of hundreds of amperes have been obtained from a surface disc less than 0.020" in diameter. Ion velocities have been measured to be over 4 kilometers per second as emitted, and changed very slowly with changes in laser energy applied to the emitter. Estimates of emitter temperature and plasma density together with electrical measurements of currents and voltages indicate a highly …

Nasa's Meteorological Programs - Beyond The First Five Years, Richard L. Haley

Space Congress® Proceedings

The requirements or objectives for a meteorological satellite program and the application of the data obtained from these satellites to the problem of weather forecasting and meteorological research is related to the existing NASA flight program. The results of the ten meteorological satellites, nine TIROS and one Nimbus launched during the past five years, are summarized. The status of the flight program for the next twelve months is discussed and details are given on the future meteorological program which has been developed to meet the objectives initially outlined.

Included in the presentation are the Weather Bureau funded TIROS Operational Satellite …

Optimizing Attitude Control Systems, J. C. Nicklas, R. Sridhar

Space Congress® Proceedings

This paper discusses a practical approach to attitude control system mechanization. Previous efforts reported in the literature have either resulted in systems too complex to mechanize or have not considered the problem in enough of its aspects to make the work meaningful. The classical control optimization techniques are briefly summarized and a critique of these methods is given. The solutions obtained with the classical techniques are either open loop, which is unsatisfactory from an attitude control standpoint, or they are closed loop. These closed loop solutions in general may require measuring all of the system variables, which may not be …

Digital Data Acquisition System In Saturn V, James E. Rorex, Robert P. Eichelberger

Space Congress® Proceedings

This paper describes the digital data acquisition system (DBAS) and explains its use in the calibration and checkout of the Saturn V space vehicle.

The size and complexity of the Saturn V vehicle necessitates computer controlled checkout. The DDAS combines the functions and hardware normally required for a flight telemetry system into a relatively low-bit-rate, high capacity pulse code modulated (PCM) system. This system may be used in ground or airborne checkout and calibration and as a PCM telemetry system for R&D and operational flight-control data.

The overall design of this system and its relation to the Saturn V automatic …