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AIAA Space and Astronautics Forum and Exposition, 2018

作者： Badger, Julia M. Frank, Jeremy NASA-Johnson Space Center Robotics and Intelligence for Human Spacecraft Team HoustonTX77058 United States NASA-Ames Research Center Moffett FieldCA94035 United States

ISBN: (数字)9781624105753

ISBN: (纸本)9781624105753

A study was recently conducted that focused on the autonomous functions that would be required for a human spacecraft to be operated without a crew on board for an extended duration in deep space. Though a Martian design reference mission was chosen, the results of this study are more broadly applicable. This paper summarizes key results from the study, including a definition of dormancy, technology gaps, and recommendations on the architecture and design for future exploration spacecraft that are expected to have untended periods. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Lunar Spacecraft Autonomous systems International Space Station Earth environmental control and life support system Robotics Avionics Spacecraft Subsystem Fault Detection and Isolation Space Missions

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Analytical Model for Sparing Policy Analysis and Optimization for Space Habitat Operations

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JOURNAL OF SPACECRAFT AND ROCKETS 2024年第1期61卷 6-15页

作者： Maxwell, Andrew J. Ho, Koki Georgia Inst Technol Daniel Guggenheim Sch Aerosp Engn Atlanta GA 30332 USA

The inclusion of operational sparing policies in early system definition can ensure that spares' allocations can optimally meet desired system reliabilities consistent with the planned maintenance of a crewed vehicle. This approach is critical for long-duration crewed missions where mass allocations are constrained and lack of safe abort contingencies limit options in the event of significant system degradation, especially in the environmental control and life support systems. This paper presents an analytical model for analyzing and optimizing sparing policies as part of an overall evaluation of the probability of sufficiency for a system configuration. The repair transition parameters are varied to change the state visitation probabilities that drive a change in the probability of sufficiency observed for a given mass allocation. These parameters are optimized using a particle swarm optimizer to identify the preferred strategy for a desired allocation mass.

关键词： Exploration Maintainability Analysis Tool Space Habitat environmental control and life support system Sparing Policy Analysis and Optimization

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RELIABILITY AND MAINTAINABILITY ANALYSIS OF A TWO-YEAR MANNED SPACECRAFT MISSION

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JOURNAL OF SPACECRAFT AND ROCKETS 1969年第3期6卷 327-&页

作者： JENNINGS, HA The Boeing Company Seattle Wash.

A mission simulation model was developed to simulate the unscheduled maintenance requirements of the space station. Unscheduled failures were assumed to occur randomly within an assumed exponential distribution about the total system mean time between failure. The mean expected spares usage varied from 95 lb for 90 days to 700 lb for 730 days. The expected impact of the unscheduled maintenance on the mission and crew operations indicates that on 88% of the days there will be no unscheduled maintenance required and on 98% of the days no more than 5 hr will be required. If all the unscheduled maintenance re%quired could beveraged out over the total mission, the mean daily repair time would amount to only 22 min. It is noted that an average of about 158 man-minutes (2. 6 man- hours) per day are required to accomplish the identified scheduled maintenance. 1 ref.

关键词： Interplanetary Mission Orbital Space Station Earth Heat Capacity Mean Time Between Failures Aerodynamic Loads environmental control and life support system Free Molecular Flow Spacecraft system Stagnation Point

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system Exergy: system Integrating Physics of Launch Vehicles and Spacecraft

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JOURNAL OF SPACECRAFT AND ROCKETS 2018年第2期55卷 451-461页

作者： Watson, Michael D. NASA Marshall Space Flight Ctr Syst Engn Off MS EE11 Huntsville AL 35812 USA

system engineering of launch vehicles and spacecraft is a challenging and complex undertaking. There are many diverse systems that must be integrated and balanced to produce an effective design. This involves a multiplicity of individual engineering relationships that are difficult to integrate and even more difficult to define in a best balance. Integration efforts involve many different approaches, from process management to mass balance. But these approaches either do not directly address the launch vehicle or spacecraft performance or require many adjustments to be made to discover a balance. The system integrating physics, derived from the fundamental physics of the system, is the key to identifying a fully integrated system performance measure. Launch vehicles and spacecraft are thermodynamic systems with performance defined by thermodynamic properties. Thus, thermodynamic exergy, which integrates all of the systems thermodynamic properties, provides the system integrating relationships. This provides a basis for determining the most efficient design from among many different configuration options and for guiding the design activities from an integrated system level. This paper explores the current physics relationships used in launch vehicle system design and demonstrates that thermodynamic exergy provides a more explicit and complete approach to system integration.

关键词： Spacecraft Performance Launch Vehicle Configurations Exergy systems Engineering Thermodynamic Properties Propellant Rocket Design Saturn environmental control and life support system Heat Flow

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Characterizing Human Spacecraft Safety and Operability Through a Minimum Functionality Design Methodology

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JOURNAL OF SPACECRAFT AND ROCKETS 2013年第3期50卷 591-602页

作者： Higdon, Kevin P. Klaus, David M. Univ Colorado Boulder CO 80309 USA

A systematic methodology is presented for defining a minimum functionality baseline configuration of a human spacecraft. To estimate a lower bound for the spacecraft mass, a set of essential functions is coupled to single-string subsystems with zero fault tolerance. This minimum functionality baseline is defined to meet the physical requirements needed to transport the crew to the target destination and to ensure that their physiological needs are met, but without margin, dispersions, redundancy, or factor of safety. This constitutes a set of nonnegotiable requirements based on fundamental parameters derived from physics and physiology. By definition, this represents a technically feasible solution, but it results in the highest-risk design. Mass additions beyond the minimum functional configuration are allocated to increased safety or operability through the addition of component redundancy, fault tolerance, factor of safety, additional mission functionality, and improved human system interfaces. This proposed methodology was used to analyze a range of lunar ascent stage spacecraft configurations, and a process was developed to allow systematic estimation of mass for the spacecraft subsystems. The modeled results are verified by comparing them with actual subsystem mass of the Apollo lunar module ascent stage.

关键词： Spacecrafts Spacecraft Configurations Fault Tolerance Spacecraft Launching Factor of Safety Apollo Lunar Module Propellant Mass Fraction Avionics systems environmental control and life support system Reaction control system

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Three-dimensional modeling, estimation, and fault diagnosis of spacecraft air contaminants

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JOURNAL OF SPACECRAFT AND ROCKETS 1998年第4期35卷 565-574页

作者： Narayan, AP Ramirez, WF Univ Colorado Dept Chem Engn Boulder CO 80309 USA

A description is given of the design and implementation of a method to track the presence of air contaminants aboard a spacecraft using an accurate physical model and of a procedure that would raise alarms when certain tolerance levels are exceeded. Because our objective is to monitor the contaminants in real time, we make use of a state estimation procedure that filters measurements from a sensor system and arrives at an optimal estimate of the state of the system. The model essentially consists of a convection-diffusion equation in three dimensions, solved implicitly using the principle of operator splitting, and uses a flowfield obtained by the solution of the Navier-Stokes equations for the cabin geometry, assuming steady-state conditions. A novel implicit Kalman filter has been used for fault detection, a procedure that is an efficient way to track the state of the system and that uses the sparse nature of the state transition matrices.

关键词： Spacecrafts Space Stations Navier Stokes Equations International Space Station Eddy Viscosity Fault Detection and Diagnosis environmental control and life support system Convection Diffusion Equation Ventilation system Kinetic Energy

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Multidisciplinary Design Optimization Approach to Integrated Space Mission Planning and Spacecraft Design

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JOURNAL OF SPACECRAFT AND ROCKETS 2022年第5期59卷 1660-1670页

作者： Isaji, Masafumi Takubo, Yuji Ho, Koki Georgia Inst Technol Daniel Guggenheim Sch Aerosp Engn Atlanta GA 30332 USA

Space mission planning and spacecraft design are tightly coupled and need to be considered together for optimal performance;however, this integrated optimization problem results in a large-scale mixed-integer nonlinear programming (MINLP) problem, which is challenging to solve. In response to this challenge, this paper proposes a new solution approach to this problem based on decomposition-based optimization via augmented Lagrangian coordination. The proposed approach leverages the unique structure of the problem that enables its decomposition into a set of coupled subproblems of different types: a mixed-integer quadratic programming (MIQP) subproblem for mission planning, and one or more nonlinear programming (NLP) subproblem(s) for spacecraft design. Because specialized MIQP or NLP solvers can be applied to each subproblem, the proposed approach can efficiently solve the otherwise intractable integrated MINLP problem. An automatic and effective method to find an initial solution for this iterative approach is also proposed so that the optimization can be performed without a user-defined initial guess. The demonstration case study shows that, compared to the state-of-the-art method, the proposed formulation converges substantially faster and the converged solution is at least the same or better given the same computational time limit.

关键词： Spacecraft Design Lunar Exploration MDO Nonlinear Programming Quadratic Programming Propellant Space Exploration environmental control and life support system Particle Swarm Optimization Space Logistics Optimization

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DRAG OF A SMALL BODY IN WAKE OF LARGE SATELLITE

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JOURNAL OF SPACECRAFT AND ROCKETS 1969年第3期6卷 329-&页

作者： OMAN, RA Grumman Aircraft Engineering Corporation Bethpage N. Y.

To satellite orbital environments, the atmosphere will be sufficiently rarefied for free molecular flow on all vehicles, and the freestream flow will be at a high speed ratio. Under these conditions, there will be a large region of relatively reduced momentum flux resulting from the blockage of freestream molecules by the space station. The opportunity for the smaller vehicle to exploit the local region of low drag is investigated. Molecules reflected or re-emitted from the frontal surface are not considered. It is apparent that substantial drag, and fuel expenditure, reduction is available in a relatively large region of the wake.

关键词： Satellites Drag Reduction Space Stations One Dimensional Flow Mean Time Between Failures Dynamic Pressure environmental control and life support system Influence Coefficients Rayleigh Line Aspect Ratio

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Flexible piloted mars missions using continuous electric propulsion

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JOURNAL OF SPACECRAFT AND ROCKETS 2006年第6期43卷 1231-1238页

作者： Schmidt, Tanja D. Seboldt, Wolfgang Auweter-Kurtz, Monika DLR German Aerosp Ctr Inst Space Simulat D-51147 Cologne Germany Univ Stuttgart Inst Raumfahrtsyst D-70550 Stuttgart Germany

The potential of continuous propulsion systems for future space is outlined and compared to impulsive propulsion (chemical and nuclear-thermal) Although the results are related to piloted Mars missions, some of the stated issues hold true for a broad range of space missions with high-velocity increments, for example, sample return missions. It is demonstrated that for piloted Mars missions the use of impulsive propulsion can lead to very inflexible missions with a long total mission duration, whereas continuous electric propulsion does not only guarantee short total mission durations with moderate masses but also a high degree of flexibility. This can be achieved with a continuous electric propulsion system that has a thrust level of 100 N and a specific impulse of 3000 s, which is not too futuristic for piloted Mars missions in 2030 and beyond.

关键词： Electric Propulsion Interplanetary Mission Propellant Earth Propulsion system Mars Exploration Program Spacecraft Design environmental control and life support system Constellations Low Energy Trajectory

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IMPACT OF WATER INTEGRATION ON SPACE STATION FREEDOM PROPELLANT AVAILABILITY

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JOURNAL OF SPACECRAFT AND ROCKETS 1989年第4期26卷 259-265页

作者： SCHMIDT, GR Booz Alien & Hamilton Inc. Reston Virginia

Water is an important resource on the Freedom Space Station and is essential for life support, laboratory, and general spacecraft operations. Overall distribution is provided by the integrated water system (IWS), which uses water collected from the environmental control and life support system (ECLSS) and Shuttle Orbiter to support extravehicular activity (EVA) and laboratory experiment requirements. Typically, this integrated approach to water handling yields an available excess that can be electrolyzed into gaseous oxygen and hydrogen propellants. In fact, recognition of this potentially "free" resources was the major reason for selecting an electrolysis propulsion system and integrated water distribution for the Freedom Station. This approach also eliminates redundant hardware and reduces operations costs associated with propellant resupply and disposal of waste water. The availability of excess water strongly depends on the operational, design, and performance characteristics of the systems that interface with the IWS. This paper describes the water usage of these systems, identifies the key parameters influencing the overall water balance, and assesses their impact on propellant availability for the propulsion system. © American Institute of Aeronautics and Astronautics, Inc., 1989, All rights reserved.

关键词： Space Station Freedom Propellant environmental control and life support system Extravehicular Activity Propulsion system Shuttle Orbiter Hydrogen Propellant Extravehicular Mobility Unit Fuel Cells Earth

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