Navigator study of electric propulsion for unmanned scientific missions. Constant power mission analysis
Nuclear-electric power generation system requirements for orbiter and flyby missions using Saturn V multistage booster
ELECTRIC PROPULSION↗
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Results for “mission analysis”
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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Mission analysis for earth atmospheric measurements using solar occultation experiments on Shuttle Spacelabs
The maximum geographical coverage of solar occultation experiments for various Shuttle-Spacelab mission concepts is defined and an analysis that includes trade-offs between parameters such as launch time, season, orbital inclination and altitude is presented as well as the mission design data for the Spacelab-3 flight. The effects of orbital ranges from 220 to 600 km on geographical coverage are examined with inclinations up to 97 deg for sun-synchronous orbit. Results show that the widest band of latitude coverage in the tropics and the temperate zones can be achieved with a mid-inclined (i.e., 57 deg) orbit and a mid-morning or late-night launch time.
Harrison, E. F.↗
Mission analysis for a potential Mars Sample Return campaign in the 2020's
The Mars 2020 mission, currently under development by NASA, plans to acquire and cache carefully-selected rock and regolith samples from the surface of Mars for potential future return. NASA and ESA are jointly studying options for returning those samples to Earth with missions launching in the 2020s. This paper demonstrates a method for modeling the various campaign elements, synthesizing coordinated campaign timelines, and assuring trajectory feasibility in the presence of many constraints, and finally optimizing towards mission success. Options for complete sample return campaigns in multiple launch and arrival opportunities are explored and compared.
Huesing, Jakob↗
Mission Analysis, Operations, and Navigation Toolkit Environment (Monte) Version 040
Monte is a software set designed for use in mission design and spacecraft navigation operations. The system can process measurement data, design optimal trajectories and maneuvers, and do orbit determination, all in one application. For the first time, a single software set can be used for mission design and navigation operations. This eliminates problems due to different models and fidelities used in legacy mission design and navigation software. The unique features of Monte 040 include a blowdown thruster model for GRAIL (Gravity Recovery and Interior Laboratory) with associated pressure models, as well as an updated, optimalsearch capability (COSMIC) that facilitated mission design for ARTEMIS. Existing legacy software lacked the capabilities necessary for these two missions. There is also a mean orbital element propagator and an osculating to mean element converter that allows long-term orbital stability analysis for the first time in compiled code. The optimized trajectory search tool COSMIC allows users to place constraints and controls on their searches without any restrictions. Constraints may be user-defined and depend on trajectory information either forward or backwards in time. In addition, a long-term orbit stability analysis tool (morbiter) existed previously as a set of scripts on top of Monte. Monte is becoming the primary tool for navigation operations, a core competency at JPL. The mission design capabilities in Monte are becoming mature enough for use in project proposals as well as post-phase A mission design. Monte has three distinct advantages over existing software. First, it is being developed in a modern paradigm: object- oriented C++ and Python. Second, the software has been developed as a toolkit, which allows users to customize their own applications and allows the development team to implement requirements quickly, efficiently, and with minimal bugs. Finally, the software is managed in accordance with the CMMI (Capability Maturity Model Integration), where it has been ap praised at maturity level 3.
Sunseri, Richard F.↗
Mission analysis data for inclined geosynchronous orbits, part 1
Data needed for preliminary design of inclined geosynchronous missions are provided. The inertial and Earth fixed coordinate systems are described, as well as orbit parameters and elements. The complete family of geosynchronous orbits is discussed. It is shown that circular inclined geosynchronous orbits comprise only one set in this family. The major orbit perturbation and their separate effects on the geosynchronous orbit are discussed. Detailed information on the orbit perturbation of inclined circular geosynchronous orbits is given, with emphasis on time history data of certain orbital elements. Orbit maintenance delta velocity (V) requirements to counteract the major orbit perturbations are determined in order to provide order of magnitude estimates and to show the effects of orbit inclination on delta V. Some of the considerations in mission design for a multisatellite system, such as a halo orbit constellation, are discussed.
Graf, O. F., Jr.↗
Commerce Lab: Mission analysis and payload integration study
The needs of an aggressive commercial microgravity program are identified, space missions are defined, and infrastructural issues are identified and analyzed. A commercial laboratory, commerce lab, is conceived to be one or more an array of carriers which would fly aboard the space shuttle and accommodate microgravity science experiment payloads. Commerce lab is seen as a logical transition between currently planned space shuttle missions and future microgravity missions centered around the space station.
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Mission analysis model requirements for electric propulsion.
Spacecraft electric propulsion parameters and launching vehicle characteristics in low thrust mission simulation, discussing spacecraft path
Barber, T. A.↗
Lunar orbit mission analysis for the improved Delta launch vehicle and AIMP-D SPACECRAFT
Launch window, trajectory shaping, and lunar orbit mission analyses for improved Delta launch vehicle and advanced IMP-D spacecraft
IMP↗
A spacecraft-borne gradiometer mission analysis
Numerical simulations were performed to obtain the orbit- and attitude-determination requirements of a spacecraft-borne gradiometer mission. Results demonstrated that position determination of 300 meters in the along-track and cross-track directions and 50 meters in the radial direction are mission requirements. The optimal orientation of the gradiometer sensing plane is achieved when the spin vector elevation is 0 degrees. The attitude-determination requirements are 5 degrees resolution for spin-vector azimuth and 0.2 degree resolution for spin-vector elevation. When these requirements are met, 3-degree gravity anomalies can be recovered globally with an accuracy of 0.025/mm/sq s (2.5 mgals). The Appendix documents the mathematical procedures for estimating detailed gravity fields from gradiometer data.
Argentiero, P.↗
Mission analysis for coincident measurements of the Upper Atmosphere Research Satellite and Space Shuttle experiments
The launch and orbital characteristics of Space Shuttle missions which will maximize the coincident measurement opportunities between the Atmospheric Laboratory for Applications and Science (ATLAS) and the Upper Atmosphere Research Satellite (UARS) experiments are presented. Updated UARS orbit conditions are used and several ATLAS orbit constraints are incorporated, and the study is expanded to include other classes of instruments on the two satellites. The effects of launch time, altitude, and orbit inclination on the number and latitudinal distribution of coincident measurement opportunities for the UARS and Shuttle experiments are investigated. Large numbers of coincident measurements are possible for UARS and ATLAS limb-viewing experiments, but their distribution is greatly dependent on the inclination of the satellites and initial equatorial crossing times. Results indicate that a great number of coincident measurements may be obtained between limb-scanning devices (300-400) and that observation of the extreme latitudes (70-80 degrees) is obtained with an ATLAS inclination of 57 degrees.
Harrison, Edwin F.↗
Mission analysis flow sequencing optimization
This investigation is an extension of a project dealing with the problem of optimal use of ground resources for future space missions. This problem was formulated as a linear programming problem using an indirect approach. Instead of minimizing the inventory level of needed ground resources, the overlapping periods during which the same types of resources are used by various flights are minimized. The model was built upon the assumption that during the time interval under consideration, the costs of various needed resources remain constant. Under other assumptions concerning costs of resources, the objective function, in general, assumes a non-linear form. In this study, one case where the form of the objective function turns out to be quadratic is considered. Also, disadvantages and limitations of the approach used are briefly discussed.
Scott, M.↗
Mission analysis for earth atmospheric measurements using a Shuttle-Spacelab lidar system
Orbital characteristics and launch conditions of a spaceborne lidar system proposed for a Shuttle Spacelab mission are analyzed. Mission design tradeoffs between instrument fields of view, resolutions, orbit groundtrack repetition parameters (Q), and orbital altitudes are shown. In the multi-experiment application of the Spacelab-lidar system, where scene illumination is the key mission parameter for the performance of the lidar instrument, results indicate that selected daytime or nighttime coverage can be programmed into Spacelab lidar missions by a judicious selection of Shuttle launch time. In addition to controlling the location of nighttime measurements, results indicate that, by the proper selection of Shuttle launch time, the magnitude and variability of solar lighting angles can be optimized to fit the requirements of the Spacelab lidar experiments.
Lawrence, G. F.↗
Orbital operations study. Volume 1: Mission analysis
The final report of the orbital operations study and a summary of the 25 elements in the study inventory are presented. Fourteen interfacing activities are defined. Eleven mission models encompassing all potential interfacing element pairs and interfacing activities are included.
Steinwachs, W. L.↗
An Analytic Approximation to Very High Specific Impulse and Specific Power Interplanetary Space Mission Analysis
A simple, analytic approximation is derived to calculate trip time and performance for propulsion systems of very high specific impulse (50,000 to 200,000 seconds) and very high specific power (10 to 1000 kW/kg) for human interplanetary space missions. The approach assumed field-free space, constant thrust/constant specific power, and near straight line (radial) trajectories between the planets. Closed form, one dimensional equations of motion for two-burn rendezvous and four-burn round trip missions are derived as a function of specific impulse, specific power, and propellant mass ratio. The equations are coupled to an optimizing parameter that maximizes performance and minimizes trip time. Data generated for hypothetical one-way and round trip human missions to Jupiter were found to be within 1% and 6% accuracy of integrated solutions respectively, verifying that for these systems, credible analysis does not require computationally intensive numerical techniques.
Williams, Craig Hamilton↗
Phase 1 of the near term hybrid passenger vehicles development program. Appendix A: Mission analysis and performance specification studies, volume 1
Applicable data was categorized and processed according to vehicle usage and trip parameters with consideration of payload (cargo, people, size) and driving cycles. A mission that maximizes the fuel potential savings for the total 1985 vehicle fleet was selected. Mission requirements that have a bearing on conventional and hybrid vehicle performance and characteristics were identified and formulated and a reference ICE vehicle was selected that meets or exceeds all requirements while maintaining within applicable constraints. Specifications for vehicle performance were established based on mission requirements, mission related vehicle characteristics, and fuel consumption.
Traversi, M.↗
Mission analysis for satellite measurements of stratospheric constituents by solar occultation
Orbital characteristics and launch vehicle requirements for a solar occultation experiment measuring atmospheric constituents, such as aerosols or ozone, during the Nimbus-G and Applications Explorer Missions are analyzed. The experiment to be flown is basically a sun photometer which measures the spectral attenuation of solar radiation by the earth's atmosphere during spacecraft sunrise and sunset, yielding two aerosol and/or ozone stratospheric profiles per orbit. The tangent latitudes and longitudes as well as frequency of these measurements are analyzed for various spacecraft orbits to define maximum geographical coverage capability. Results indicate that a 50 deg inclined orbit for Applications Explorer provides latitude coverage from approximately 70 deg north to 70 deg south every 2-1/2 weeks. A high-moon, sun-synchronous orbit with an inclination of 99 deg for Nimbus-G will provide for coverage of occultation measurements at high latitudes near the polar regions (i.e., 64 to 80 deg north and south). The solar pointing requirements of the experiment in terms of yaw and pitch angles are also defined.
Harrison, E. F.↗
Parameter estimation supplement to the Mission Analysis Evaluation and Space Trajectory Operations program (MAESTRO)
This Parameter Estimation Supplement describes the PEST computer program and gives instructions for its use in determination of lunar gravitation field coefficients. PEST was developed for use in the RAE-B lunar orbiting mission as a means of lunar field recovery. The observations processed by PEST are short-arc osculating orbital elements. These observations are the end product of an orbit determination process obtained with another program. PEST's end product it a set of harmonic coefficients to be used in long-term prediction of the lunar orbit. PEST employs some novel techniques in its estimation process, notably a square batch estimator and linear variational equations in the orbital elements (both osculating and mean) for measurement sensitivities. The program's capabilities are described, and operating instructions and input/output examples are given. PEST utilizes MAESTRO routines for its trajectory propagation. PEST's program structure and subroutines which are not common to MAESTRO are described. Some of the theoretical background information for the estimation process, and a derivation of linear variational equations for the Method 7 elements are included.
Bjorkman, W. S.↗
Space station (modular) mission analysis. Volume 2: Appendix
The experiment requirements summary is prepared for use in manned space flight design studies and provides the basis for sizing space station, shuttle payloads, and experiment modules. Requirements are derived for a space station, and 30-day and 5-day shuttle missions.
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