SPACECRAFT SYSTEMS DEVELOPMENT AND PERFORMANCE
Spacecraft systems development and performance - mercury project
MERCURY PROJECT↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Summary of rendezvous operations
One of the major objectives of the Gemini Program was to develop and to demonstrate techniques for the rendezvous and docking of space vehicles. This objective is of vital importance since rendezvous and docking is mandatory for success in many future manned space-flight programs. For example, lunar orbital rendezvous has been selected as the primary mode for the Apollo lunar-landing mission which requires one rendezvous and two dockings. Other programs requiring rendezvous are planetary missions, manned space stations, and unmanned satellite inspection and repair missions.
structural integrity↗
Ground control and monitoring of rendezvous
This paper discusses the ground control and monitoring function performed in support of the Gemini rendezvous missions. Included are discussions of the support philosophy adopted for Gemini; the resulting influence upon mission design; and comparisons between predicted and actual flight results.
structural integrity↗
Onboard operations for rendezvous
An overall plan for onboard rendezvous operations for the Gemini missions was developed in parallel with the mission plan. The purpose of this plan was to make optimum use of crew time in orbit to maximize the probability of a successful rendezvous. The evolution of the plan began with a preliminary time line of events based upon the known guidance-equipment requirements and upon the estimated crew timing. A preliminary set of flight charts was developed to aid the crew with primary and backup procedures and to establish a backup guidance capability. These charts, which consisted of a few simple graphs and tabulation sheets, enabled the crew to calculate accurate solutions for the terminal maneuvers even with an inoperative guidance-equipment component. As such, the charts significantly contributed to the probability of mission success. Following the development of the charts, an engineering evaluation was conducted on a realistic man-in-the-loop simulation. During this evaluation, the procedures and charts were subjected to the expected equipment errors and trajectory dispersions, and revisions were made as necessary to improve effectiveness. The resulting plan was presented to the flight crew; the charts were evaluated during a period of training on the simulator. The crew spent several weeks training on both the primary procedures and on the various failure modes.
structural integrity↗
Gemini results as related to the Apollo program
The Gemini Program was conceived to provide a space system that could furnish answers to many of the problems in operating manned vehicles in space. It was designed to build upon the experience gained from Project Mercury, and to extend and expand this fund of experience in support of the manned lunar landing program and other future manned space-flight programs. The purpose of this paper is to relate some of the results of the Gemini Program to the Apollo Program, and to discuss some of the contributions which have been made. The objectives of the Gemini Program applicable to Apollo are : (1) long-duration flight, (2) rendezvous and docking, (3) post-docking maneuver capability, (4) controlled reentry and landing, (5) flight- and groundcrew proficiency, and (6) extra vehicular capability. The achievement of these objectives has provided operational experience and confirmed much of the technology which will be utilized in future manned programs. These contributions will be discussed in three major areas : launch and flight operations, flight-crew operations and training, and technological development of subsystems and components. While there is obvious interrelation among the three elements, the grouping affords emphasis and order to the discussion.
structural integrity↗
Analysis of the Artemis I Orion Spacecraft Power System Performance
NASA successfully completed an uncrewed test flight of the Orion spacecraft during the 26-day Artemis I mission in November and December 2022. The Artemis I mission profile included several potentially stressing features for Orion electrical power system (EPS) performance, including eclipse duration, multiple propulsive or navigational maneuvers which constrained positioning of the solar array wings (SAWs), and the proximity and phasing of various events together. All of these features vary significantly with Earth-sun-moon geometry, providing a unique challenge for predicting EPS performance before an exact launch date is known. This presentation will provide a brief mission overview, discuss the different computer models with varying levels of fidelity used to analyze Orion EPS performance, as well as the screening process developed to incorporate EPS performance as a consideration for launch epoch selection. Final preflight model predictions of EPS performance will be compared to in-flight telemetry measurements, and several EPS anomalies observed will be briefly discussed.
Orion↗
Spacecraft Auxiliary Thrust System - Performance-Measuring Techniques
Spacecraft auxiliary thrust system - performance characteristics measuring techniques
PERFORMANCE CHARACTERISTICS↗
Mariner Mars 1964 Project report - Spacecraft performance and analysis
Mariner IV spacecraft system and subsystem performance and analysis
SPACECRAFT PERFORMANCE↗
Gemini Summary Conference
The Gemini Summary Conference was held on February 1 and 2, 1967, at the NASA Manned Spacecraft Center, Houston, Tex. The conference emphasized the highlights of the Gemini Program and especially the flight results of the last five missions. This report contains the 21 technical papers presented at the conference as well as an introduction by George E. Mueller and concluding remarks by George M. Low. The technical papers are divided into five sections: the first describes the rendezvous, docking, and tethered-vehicle operations involving the spacecraft and a target vehicle; the second presents various aspects of extravehicular activity; the third concerns the operational support of the missions ; the fourth cover the experiments conducted during the missions; and the fifth compares the astronaut flight and simulation experiences and relates the Gemini results to the Apollo Program.
structural integrity↗
Role of IAC in large space systems thermal analysis
Computer analysis programs to evaluate critical coupling effects that can significantly influence spacecraft system performance are described. These coupling effects arise from the varied parameters of the spacecraft systems, environments, and forcing functions associated with disciplines such as thermal, structures, and controls. Adverse effects can be expected to significantly impact system design aspects such as structural integrity, controllability, and mission performance. One such needed design analysis capability is a software system that can integrate individual discipline computer codes into a highly user-oriented/interactive-graphics-based analysis capability. The integrated analysis capability (IAC) system can be viewed as: a core framework system which serves as an integrating base whereby users can readily add desired analysis modules and as a self-contained interdisciplinary system analysis capability having a specific set of fully integrated multidisciplinary analysis programs that deal with the coupling of thermal, structures, controls, antenna radiation performance, and instrument optical performance disciplines.
Jones, G. K.↗
Interactions between spacecraft and the charged-particle environment
Spacecraft-environment interactions are defined as the responses of a spacecraft surface to a charged-particle environment. This response can influence spacecraft system performance. Interactions can be divided into two broad categories: spacecraft passive, in which the environment acts on the spacecraft; and spacecraft active, in which the spacecraft causes the interaction. Passive interactions include the spacecraft-charging phenomenon. Active interactions include the relatively new interactions arising from the use of very large spacecraft and space power systems in future missions. To illustrate active interactions, a large power system operating at elevated voltages is considered. Possible interactions are described, available experimental data are reviewed, and the effect on power system performance is estimated.
Stevens, N. J.↗
Lunar Orbiter II - Photographic Mission Summary
Lunar Orbiter II photography of landing sites, and spacecraft systems performance. The second of five Lunar Orbiter spacecraft was successfully launched from Launch Complex 13 at the Air Force Eastern Test Range by an Atlas-Agena launch vehicle at 23:21 GMT on November 6, 1966. Tracking data from the Cape Kennedy and Grand Bahama tracking stations were used to control and guide the launch vehicle during Atlas powered flight. The Agena spacecraft combination was maneuvered into a 100-nautical-mile-altitude Earth orbit by the preset on-board Agena computer. In addition, the Agena computer determined the maneuver 1 and engine-bum period required to inject the spacecraft on the cislunar trajectory 20 minutes after launch. Tracking data from the downrange stations and the Johannesburg, South Africa station were used to monitor the entire boost trajectory.
LUNAR ORBITER↗
Space simulator facilities at the Jet Propulsion Laboratory
Space simulator facility for testing spacecraft systems performance in extreme cold, high vacuum, and intense solar radiation environment
SPACECRAFT PERFORMANCE↗
Influence of charging environments on spacecraft materials and system performance
An overview is presented of potential interactions that can occur on spacecraft operating in space environments. These interactions are discussed in detail. The environment acts on spacecraft in such a way that charging of exterior surfaces occurs. The consequences from this charging then affect system operational performance. Hence, it is the coupling of this exterior charging to system performance that is of concern here. These interactions were first discovered in the spacecraft charging phenomena in which the geomagnetic substorms charged external surfaces to a level that discharges occurred. As a result of the discharge, electronic systems either changed logic state (anomalous switching) or failed. These interactions can occur in all orbits. The type associated with geosynchronous orbits is called passive since the environment provides the charging mechanism. This type can also occur in polar orbits due to auroral charging environments. In low Earth orbits, the thermal plasma alleviates charging environment concerns, but system operations can induce similar effects.
Stevens, N. John↗
Spacecraft Multiple Array Communication System Performance Analysis
The Communication Systems Simulation Laboratory (CSSL) at the NASA Johnson Space Center is tasked to perform spacecraft and ground network communication system simulations, design validation, and performance verification. The CSSL has developed simulation tools that model spacecraft communication systems and the space and ground environment in which the tools operate. In this paper, a spacecraft communication system with multiple arrays is simulated. Multiple array combined technique is used to increase the radio frequency coverage and data rate performance. The technique is to achieve phase coherence among the phased arrays to combine the signals at the targeting receiver constructively. There are many technical challenges in spacecraft integration with a high transmit power communication system. The array combining technique can improve the communication system data rate and coverage performances without increasing the system transmit power requirements. Example simulation results indicate significant performance improvement can be achieved with phase coherence implementation.
Hwu, Shian U.↗
Energy Storage Flywheels on Spacecraft
With advances in carbon composite material, magnetic bearings, microprocessors, and high-speed power switching devices, work has begun on a space qualifiable Energy Momentum Wheel (EMW). An EMW is a device that can be used on a satellite to store energy, like a chemical battery, and manage angular momentum, like a reaction wheel. These combined functions are achieved by the simultaneous and balanced operation of two or more energy storage flywheels. An energy storage flywheel typically consists of a carbon composite rotor driven by a brushless DC motor/generator. Each rotor has a relatively large angular moment of inertia and is suspended on magnetic bearings to minimize energy loss. The use of flywheel batteries on spacecraft will increase system efficiencies (mass and power), while reducing design-production time and life-cycle cost. This paper will present a discussion of flywheel battery design considerations and a simulation of spacecraft system performance utilizing four flywheel batteries to combine energy storage and momentum management for a typical LEO satellite. A proposed set of control laws and an engineering animation will also be presented. Once flight qualified and demonstrated, space flywheel batteries may alter the architecture of most medium and high-powered spacecraft.
Bartlett, Robert O.↗
Solar cell arcing: The role of outgassing and contamination
The effect of outgassing, venting, and thruster firing events on spacecraft system performance has been a long standing issue. Recent laboratory measurements on negatively biased high voltage solar cells at Physical Sciences Inc. (PSI) suggest that some currently designed and certainly future space power systems must address/re-evaluate this issue. Our observations show that exposing these cells to moderate levels (10 exp -3 torr-min) of H2O vapor enhances the arcing frequency, while heating to 85 C to remove water vapor significantly reduces the arc frequency. The interaction of the adhesive used to attach the cover glass to the solar cell with ambient water vapor is the key factor in determining arcing rates. Elimination of adhesive exposed to the environmental plasma reduces the arc frequency more than two orders of magnitude, and eliminates any sensitivity to H2O exposure. The adhesive may also become a source of spacecraft contamination. Macroscopic amounts were observed to blow off some arc events, and (we assume) electrostatically precipitate at other negatively biased locations. Data, analysis, and potential impact for future space platforms are discussed.
Marinelli, W. J.↗
Analytical Assessment of the Reciprocating Feed System
A preliminary analysis tool has been created in Microsoft Excel to determine deliverable payload mass, total system mass, and performance of spacecraft systems using various types of propellant feed systems. These mass estimates are conducted by inserting into the user interface the basic mission parameters (e.g., thrust, burn time, specific impulse, mixture ratio, etc.), system architecture (e.g., propulsion system type and characteristics, propellants, pressurization system type, etc.), and design properties (e.g., material properties, safety factors, etc.). Different propellant feed and pressurization systems are available for comparison in the program. This gives the user the ability to compare conventional pressure fed, reciprocating feed system (RFS), autogenous pressurization thrust augmentation (APTA RFS), and turbopump systems with the deliverable payload, inert mass, and total system mass being the primary comparison metrics. Analyses of several types of missions and spacecraft were conducted and it was found that the RFS offers a performance improvement, especially in terms of delivered payload, over conventional pressure fed systems. Furthermore, it is competitive with a turbopump system at low to moderate chamber pressures, up to approximately 1,500 psi. Various example cases estimating the system mass and deliverable payload of several types of spacecraft are presented that illustrate the potential system performance advantages of the RFS. In addition, a reliability assessment of the RFS was conducted, comparing it to simplified conventional pressure fed and turbopump systems, based on MIL-STD 756B; these results showed that the RFS offers higher reliability, and thus substantially longer periods between system refurbishment, than turbopump systems, and is competitive with conventional pressure fed systems. This is primarily the result of the intrinsic RFS fail-operational capability with three run tanks, since the system can operate with just two run tanks.
Eddleman, David E.↗