Cost-effective Missions Research Articles

Leveraging Large Language Models for Tradespace Exploration

This paper proposes a method for leveraging large language models (LLMs) to improve the question-answering capabilities of artificial intelligence (AI) assistants for tradespace exploration. The method operates by querying an information space composed of fused data sources encompassing the tradespace exploration process and responding based on the gathered information. The information retrieval process is modeled as an internal dialog where an LLM-based dialog agent converses with a subquery answering agent. A case study is conducted on a next-generation soil moisture mission (SM-NG), and a generative AI assistant (named Daphne-G) is configured on it. The effect of the dialog agent and the choice of LLM are assessed by comparing the performance of three different system configurations on a validation question set. A second validation effort is conducted, comparing Daphne-G’s responses to those of a baseline template-based AI assistant, Daphne-VA. Results show that the dialog-based system is necessary for answering complex questions requiring multiple documents. Furthermore, results show that Daphne-G can correctly answer all the questions Daphne-VA can answer, while simultaneously being able to answer a greater number of questions than Daphne-VA. The results suggest that LLMs could significantly improve the outcomes of the tradespace exploration process, which may result in better and more cost-effective mission concepts being implemented.

S1920105 ほどよし3-4号機の開発と軌道上運用から得られた実践的な知見とその応用

Since June 2011 to end of March 2014, The University of Tokyo and The Next Generation Space system Technology Research Association had been developing the twin micro-satellite: Hodoyoshi-3 and -4 to demonstrate and establish an innovative system design and a cost-effective development process for mass-production of micro-satellites in the future based on the new concept called "Hodoyoshi" which means reasonably reliable. These two satellites were successfully launched into Sun Synchronous Orbit with an altitude of about 630km on June 19th 2014. So far, we have been getting achievements regarding system performance on-orbit, a lot of mission data, for example, Earth observation images and movies, technical demonstration by new devices, capabilities for new space utilization like space advertisement. In this project, we have been considering and demonstrating, system architecture design methods, integration and test process, on-orbit operation methods including recovery functions from anomaly. This evaluation is undergoing by reviewing operation results from viewpoints of Hodoyoshi concept. This paper descries the Hodoyoshi concept, the major characteristics of the satellites, and the key features and approaches of microsatellite development to realize cost-effective mission.

Design and Implementation of a On-Orbit Service Oriented Dynamic Simulation Platform

The high cost of space missions, long cycle and high risk, simulation technology has been an important way in the research and engineering applications of space technology. A cost-effective space missions in rail services through the Service spacecraft on-orbit servicing, in-orbit replacement to extend the service life of the target spacecraft in the rail supply, to enhance the effectiveness of the spacecraft. In rail service technology involving orbital dynamics, collision dynamics, multibody dynamics, the dynamics knowledge integration application. Therefore requires a comprehensive and efficient simulation platform to support research to expand the application of on-orbit service. In this paper, the open source dynamics engine ODE Open Inventor graphics library and Maltlab numerical simulation software to build a multi-level, in-orbit service simulation platform, play to the advantage of three software can quickly carry out the front end of the rail service, power school simulation, operation, control and results processing.

Investigating Amorphous Metal Composite Architectures as Spacecraft Shielding

AbstractThe threat of micro‐meteoroid and orbital debris (MMOD) collisions with spacecraft and satellites has been increasing with the increasing worldwide use of low earth orbit. Providing low‐areal‐density shielding for the mitigation of these high velocity impacts is essential for ensuring successful and cost effective missions. Here, we report results obtained from hypervelocity impact testing on bulk metallic glass (BMG) matrix composites. Their carbide‐like hardness, low melting temperatures, ultra‐high strength‐to‐weight ratio and the ability to be processed like polymers are material attributes ideally suited for spacecraft shielding, particularly as an outer wall bumper shield.

Small satellites for global coverage: Potential and limits

There is an increasing need for Earth Observation (EO) missions to meet the information requirements in connection with Global Change Studies. Small and cost-effective missions are powerful tools to flexibly react to information requirements with space-borne solutions. Small satellite missions can be conducted relatively quickly and inexpensively by using commercial off-the-shelf-technologies, or they can be enhanced by using advanced technologies. A new class of advanced small satellites, including autonomously operating “intelligent” satellites may be created, opening new fields of application. The increasing number of small satellites and their applications drive developments in the fields of small launchers, small ground station networks, cost-effective data distribution methods, and cost-effective management and quality assurance procedures. There are many advantages of small satellite missions, like more frequent mission opportunities, a faster return of data, larger variety of missions, more rapid expansion of the technical and/or scientific knowledge base, greater involvement of small industry, feasibility by universities and others. This paper deals with general trends in the field of small satellite missions for Earth observation. Special attention is given to the potential of spatial, spectral, and temporal resolution of small satellite based systems. Examples show small satellites offer also the unique possibility to install affordable constellations to provide good daily coverage of the globe and/or allow us to observe dynamic phenomena. The facts and examples given in this paper lead to the conclusion: Small satellites are already powerful tools for monitoring global, regional and local phenomena. In the future, their application spectrum will even broaden based on the ongoing development in many areas of technology and observation techniques.

Venus Express—The first European mission to Venus

Venus Express is the first European mission to planet Venus. The mission aims at a comprehensive investigation of Venus atmosphere and plasma environment and will address some important aspects of the surface physics from orbit. In particular, Venus Express will focus on the structure, composition, and dynamics of the Venus atmosphere, escape processes and interaction of the atmosphere with the solar wind and so to provide answers to the many questions that still remain unanswered in these fields. Venus Express will enable a breakthrough in Venus science after a long period of silence since the period of intense exploration in the 1970s and the 1980s. The payload consists of seven instruments. Five of them were inherited from the Mars Express and Rosetta projects while two instruments were designed and built specifically for Venus Express. The suite of spectrometers and imaging instruments, together with the radio-science experiment, and the plasma package make up an optimised payload well capable of addressing the mission goals to sufficient depth. Several of the instruments will make specific use of the spectral windows at infrared wavelengths in order to study the atmosphere in three dimensions. The spacecraft is based on the Mars Express design with minor modifications mainly needed to cope with the thermal environment around Venus, and so a very cost-effective mission has been realised in an exceptionally short time. The spacecraft was launched on 9 November 2005 from Baikonur, Kazakhstan, by a Russian Soyuz-Fregat launcher and arrived at Venus on 11 April 2006. Venus Express will carry out observations of the planet from a highly elliptic polar orbit with a 24-h period. In 3 Earth years (4 Venus sidereal days) of operations, it will return about 2 Tbit of scientific data. Telecommunications with the Earth is performed by the new ESA ground station in Cebreros, Spain, while a nearly identical ground station in New Norcia, Australia, supports the radio-science investigations.

Trends in cost-effective mission operations

The pressure on achieving cost reductions in Mission Operations has been increasing steadily during the past decade and there is no relaxation in sight for the near future. Therefore, it is necessary to scrutinize mission design and operations concepts for potential in achieving still better cost effectiveness. The present paper presents an assessment of a few concepts that are expected to be promising for further increasing the cost effectiveness of future space mission operations, namely: on-board spacecraft autonomy and on-ground automation, commercial off-the-shelf control systems, multi-mission operation concepts, and hibernation modes. The latter concept is of specific relevance to interplanetary spacecraft with long cruise phases.

Cost-effective mission operations

The present paper identifies and evaluates the various methodologies for performing cost-effective mission operations within the general framework of the ‘Faster, Cheaper, and Better’ paradigm. Emphasis is placed on the mission system engineering process which represents the overall context in which life-cycle costeffectiveness must be measured. The paper analyzes the mission system engineering process in which ground system design and mission operations are performed and illustrates how the characteristics of that environment determine their costs. The most effective cost-saving management and engineering methods with relevance to mission operations will be evaluated. Specific characteristics will be highlighted by reference to APL's interplanetary mission NEAR launched on February 17, 1996.

Low cost approach to Mars Pathfinder

Mars Pathfinder, launching in December '96 and landing in July '97, will demo a low cost delivery system to the surface of Mars. Historically, spacecraft that orbit or land on a distant body carry a large amount of fuel for braking. Mars Pathfinder, thrusting only for navigation, enters directly into the Martian atmosphere, aerobrakes with its aeroshell, deploys a parachute at 10 km above the surface and, within 100 m off the surface, ignites solid rockets for final braking prior to deployment of air bags which cushion touchdown. After landing, petals open to upright the lander, exposing solar panels to the sun. Even though the lander and rover are expected to last longer, the major objectives of Mars Pathfinder, demonstrating EDL (Entry, Descent, Landing) and lander-rover surface operations, will occur within the first few days, at which time panoramic images of the surface will be transmitted and the rover will be deployed to conduct both mobility tests and rock composition measurements. While Mars Pathfinder is primarily an engineering demo, it accomplishes a focused, exciting set of science investigations with a stereo, multi-color lander imager; atmospheric instrumentation, used as a weather station after landing; and the rover with cameras and the APXS (Alpha Proton X-ray Spectrometer). This paper features Mars Pathfinder's approach to innovative and cost effective mission accomplishment, under a development cost cap. Mars Pathfinder is pathfinding a new way of doing business at NASA and JPL for small, low cost, Discovery class missions.

NASA's Discovery Program

NASA's Discovery Program represents an new era in planetary exploration. Discovery's primary goal: to maintain U.S. scientific leadership in planetary research by conducting a series of highly focused, cost effective missions to answer critical questions in solar system science. The Program will stimulate the development of innovative management approaches by encouraging new teaming arrangements among industry, universities and the government. The program encourages the prudent use of new technologies to enable/enhance science return and to reduce life cycle cost, and it supports the transfer of these technologies to the private sector for secondary applications. The Near-Earth Asteroid Rendezvous and Mars Pathfinder missions have been selected as the first two Discovery missions. Both will be launched in 1996. Subsequent, competitively selected missions will be conceived and proposed to NASA by teams of scientists and engineers from industry, academia, and government organizations. This paper summarizes the status of Discovery Program planning.

The NEAR Mission Operations System

Successful completion of the Near Earth Asteroid Rendezvous (NEAR) mission demands not only cost effective spacecraft design and development, but also cost effective mission operations system development and implementation. To control mission operations costs, several steps have been taken. Engineering of the mission operations system is concurrent with engineering of the spacecraft to trade off spacecraft capability with ground system capability. A single integrated system is being developed to support both spacecraft integration and test (I&T) operations and mission operations. Development of this system, which emphasizes the use of Commercial-Off-The-Shelf (COTS) components, is the responsibility of one development team. The mission operations team will be trained by supporting spacecraft I&T operations and will be cross-trained to fill any team position on-orbit. In this paper, status and plans in these areas will be discussed, as well as aspects of the concept of operations that afford cost efficient operations.

Cost-effective mission design for a small solar probe

The Small Solar Probe Mission is designed to characterize the Solar Corona as close as three solar radii above the sun's surface. Until 1992 studies generated concepts with large spacecraft launched on large launch vehicles and requiring nearly a decade to reach their initial perihelion. In 1992 JPL responded to emerging fiscal constraints by proposing a Small Solar Probe. The payload was reduced in scope while yet retaining the primary objectives of this exploratory mission. The mission design uses a Delta launch vehicle and a direct trajectory to Jupiter where a gravity assist places the spacecraft on a polar trajectory about the Sun; This paper describes the mission and the designs derived from it in the context of a cost effective concept. Design choices made are directly related to cost implications.