Technology Mission Research Articles

Water extraction from icy lunar simulants using low power microwave heating

Identifying the best technique for extracting water ice deposits in permanently shadowed regions at the lunar poles will be crucial in determining how successful a long-term or permanent settlement at these locations will be for future scientific and technology missions. This study uses a low-power microwave heating method to extract water from icy lunar simulants. Samples of lunar highland and mare simulants at different water contents (3–15 wt %) were heated using 250 W, 2.45 GHz microwaves. A maximum of 67 ± 5% [2SD] of the water was extracted during heating runs of 25 min. Water was extracted more efficiently from the highland simulant than from the mare simulant. A significant reason for the different efficiency of water extraction in icy lunar simulants was the differing porosity of the samples made from different simulants. Pore space filled with ice leads to a reduced contact area between grains and an increased area of free ice, which causes poor heating performance. The results indicated that differences in chemical composition between the simulants had a negligible effect on water extraction, as the contact area between grains seems to dominate water extraction. This study found that low-power microwave heating is an effective technique for extracting water from cryogenic Icy simulants. It was also found that using a simple input energy principle (Input Energy = Absorbed Power x Heating Time) to estimate the additional heating time was sufficient to overcome inefficient heating due to differing absorbed powers. For undersaturated samples, microwave heating was an efficient heating mechanism, but is less efficient for saturated samples where alternative heating methods may be more efficient at melting free ice before employing microwave heating.

A Set Covering Approach for Selecting Preferred Systems to Support Mission Engineering

We propose a methodology for down-selecting systems to provide required capabilities for a system of systems (SoS). As part of the methodology, we introduce the reliability set covering (RSC) model, which extends the classical set covering optimization model to consider reliability in addition to cost. The proposed methodology embeds the RSC model in a simulation framework that varies factors such as the anticipated duration of the mission, the number of redundant systems of each type available, and the age/condition of each available system. The simulation is guided by a statistical design of experiments, and an analysis of variation is applied to the results. This allows the decision maker to identify scenarios where a significant increase in redundant systems or the use of more expensive systems is required, and “mission critical” systems that are selected in a relatively large number of simulation runs. The process provides the decision maker with cost and mission reliability estimates for each candidate SoS. We demonstrate the practicality of the process for a notional intelligence, surveillance, and reconnaissance mission with three required capabilities and five candidate system types, and randomly generated missions with up to eight required capabilities.

달탐사 아르테미스 1호에 동반된 초소형위성들 임무 소개 및 기술 동향

The Artemis program is a manned lunar exploration plan being pursued by NASA in the United States. It is of great significance that manned lunar exploration has been resumed since Apollo 17. The main partner countries are the European Union (ESA), Japan (JAXA), and Canada (CSA). A total of 22 countries, including Korea, have signed in the Artemis Accords to participate in this program. The first mission of the Artemis program, Artemis 1, is primarily aimed at flight test launch vehicles and spacecraft before full-scale exploration missions. As a secondary mission, 10 nanosatellites mounted on Artemis 1 are deployed and carry out their respective missions. Artemis 1, which is introduced in Korea, consists of only the main mission, and it is very rare to deal with the 10 nanosatellites, making it difficult to understand the scientific and technological mission goals of each nanosatellite. In this paper, the nanosatellite missions of Artemis 1, which have not been introduced in detail in Korea, and the recent trend of nanosatellite development.

The application of applied category theory to quantify mission success

Mission engineering is the quantification of the effects applied by a system of systems to achieve measurable desired results. The execution of the mission is defined by a mission thread; that is the sequence of actions/processes executed by elemental systems. The domain of complex missions has been described as “wicked” because traditional military and space program-based systems engineering practices fail due to a lack of discrete phases, a dependence on context, and the non-uniqueness of a “good-enough” mission thread. Wicked problems also tend to be unstructured (non-hierarchical) with no centralized control and do not lend themselves to linear step-by-step processes. Wicked problems are inherently uncertain leading to the broader issue of trust across a mission knowledge base, and any mission level analyses. Wicked problems are also characterized and challenged by combinatoric complexity. Mission success is primarily driven by the interrelationships between systems and not just by the individual systems themselves. The success of mission engineering will require an iterative approach of modeling, simulation, and analysis resulting in a continuous reduction in uncertainty and refinement in the topology of the mission thread. OODA-based decomposition of mission threads focused on Boyd’s Orient function provides focus on system interrelationships. Trust provides decision-maker confidence in the results that has proved elusive to traditional validation approaches. The approach described in this paper is based upon using applied category theory as a basis for building mission threads, mission models, data stores, and integrating simulation ensembles.

Global Sensitivity Analysis of Earth-Moon Transfer Orbit Parameters Based on Sobol Method

In the process of Earth-Moon transfer orbit, many parameters are involved and the degree of influence varies among the parameters. How to accurately distinguish the influence relationship between different parameters is of great significance to engineering missions. Based on Sobol sequence sampling method and Sobol global sensitivity analysis method, a calculation process of global sensitivity analysis is proposed in this paper for high-fidelity Earth-Moon transfer orbit. A numerical simulation method is used to verify that the Sobol sequence sampling method has better convergence and higher precision than other sampling methods and has better adaptability in global sensitivity analysis. The effects of different state parameters and the combination of different parameters on the perilune parameters of Earth-Moon transfer orbit are given by simulation examples, which verifies the effectiveness and feasibility of the calculation process proposed in this paper. Simulation results show that the radial position and tangential velocity at the trans-lunar injection point are the main sensitivity parameters, and the other parameters have little effect on the results. The sensitivity of the orbital elements at the trans-lunar injection point to the perilune parameters is different and needs to be determined according to the specific parameters. The results of this study can provide important reference for future Earth-Moon transfer orbit design and related engineering missions.

Characterizing integration challenges in mission engineering to form solution strategies

AbstractThis paper presents a systematic approach to characterize integration challenges when implementing mission engineering and discusses some specific techniques to address these issues. With the introduction of mission engineering in the DOD science and technology lexicon, integration assumes a new dimension beyond the system product level. First, the authors offer a more precise definition of integration that focuses on incorporating a new technology or military capability into an existing organization's infrastructure. Using a collection of system integration literature and a set of examples, the authors define major problem areas regarding integration. Analyses of these issues present opportunities to identify specific methods to avoid or mitigate them. The resultant process is a foundation for mission engineering practitioners to plan successful integration of a new system. Acceptance of these procedures in the mission engineering community may lead to inclusion as standard practices in the DOD Mission Engineering Guide.

Performing Information Extraction and Ontology Development for Mission Engineering Applications

The development and evaluation of Mission Engineering Threads (METs) require an understanding of the operational context for which a system-of-systems (SoS) will be employed as well as an assessment that the performance of a complex SoS is effective and safe. The information describing the design and performance parameters of the systems within the SoS is distributed in many different physical locations, and is represented in a variety of formats, both structured and unstructured. Because of this dynamic on the structuring of the data to include differing ontology frameworks, it is necessary to develop a framework and toolset to handle the automated extraction of information from disparate information sources. In addition, this extracted information needs to be categorized properly into defined data types as represented in the specific MET to correctly capture the appropriate context of the mission scenario. Semantic technique solutions will be researched, analysed, and applied as a means to infer new facts from existing facts and data. These techniques are particularly powerful when the amount of data and/or the relationships and constraints among data are too cumbersome and complex for human understanding and reasoning. Using the characteristics of wine as an example, we present our framework to show how it enables rapid and contextually relevant extraction, and represents complex information in a user-friendly format.

Integrating AI Microservices into Hard-Real-Time SoS to Ensure Trustworthiness of Digital Enterprise Using Mission Engineering

Due to the increased complexities and operating speeds of today’s and tomorrow’s system-of-systems (SoS) architectural configurations for digital enterprises, the design of new domain architecture management systems is required. A key element of these new designs will be the incorporation of Artificial Intelligence (AI) microservices to provide dynamically containerized and orchestrated service capabilities within a lightweight interoperability fabric with the ability to operate in hard-real-time environments. Each containerized AI microservice exposes an independent, programmable function, which enables it to be easily reused, evolved, or replaced without compromising interoperability across critical mission essential functions to execute mission threads. In addition, embedded in this design needs to be a trust management layer to enforce reliable messaging and trust amongst the actors. This paper provides a framework for planned research and demonstrates the feasibility of microservices using a representative simple problem to demonstrate the application of the framework. Early positive analysis results using AI microservices within an SoS environment shows that the 500 milli-second (ms) threshold for latency can be met.

What food will we be eating on our journey to Mars?

The aim of this review is to show the possibilities of food production during space travel and to demonstrate the potential of technological solutions that can play a significant role in achieving the goal of colonizing other planets. The paper briefly outlines the conditions of space flight and the associated possible threats that may occur. It is assumed that the basic problem is cosmic radiation, which not only can significantly affect the health of astronauts, but also prevent potential cultivation of plants or animal breeding on board a spacecraft. The solution to this problem proposed here is a shield which provides protection against collisions with high kinetic energy particles, while reducing the speed of corpuscular radiation. Particular attention is given to various biotechnological and bioengineering methods that could be used for food production on board a spacecraft. Technological development in the field of bioprinting or genetic modification of organisms may play a key role in the success of long-distance technological missions. Moreover, organisms such as algae, fungi and insects are indicated as a potential source of energy for future colonizers. In sum, the review covers both the field of engineering and biotechnology, as well as the possibility of checking these technological methods in the test flights.

Trend and Growth Rate Estimation of Principal Crops in Karnataka State in India

The study undertaken to analyse the growth rate performance of area, production, productivity of selected crops in Karnataka from year 1997 to 2019. At state level, it was found that, the productivity of cereals showed positive growth with 1.22 percent. The area under maize increased by 5.30 percent by displacing Jowar, Bajra, minor millets. The rice and maize became stable crops in cultivation due its assured support prices and procurement from government. The production of pulses increased by 4.17 percent. The area under oil seeds showed negative trend with -5.87 percent which may be due to its high cost of production and unremunerative prices where as the commercial crops has recorded positive growth rates of production (2.69 percent) and productivity (2.43 percent) despite of its 0.24 percent area growth. The farmers prioritised sugarcane, cotton because of less labour requirements, good market prices. The Technology mission on oilseeds and Pulses in post 1990’s could be reason for increased production and productivity of pulses.

Mission engineering for the RETALT VTVL launcher

In the last decade, the rapid and successful development of reusable launch systems such as SpaceX’ Falcon 9 demonstrated both the operational feasibility of reusable launchers and their economic viability. The objective of recovering a launcher or a launcher’s booster requires to safely return the launch vehicle from orbital or sub-orbital conditions to a soft landing. To increase the reusability, decrease the turnaround time and reduce costs, a precise touchdown on a pre-defined landing site or on a floating barge on the Ocean is preferred to splashdown in the water, due mainly to the highly detrimental effect of the salted water on the launcher components and equipment. The project RETALT (Retro Propulsion Assisted Landing Technologies) was funded by the EU Horizon 2020 program to study and develop critical technologies for launcher recovery based on retro-propulsion. In this context, and based on in-house experience and tools, DEIMOS Space carried out the mission engineering of the RETALT1 vehicle concept to assess the feasibility of a return mission, from a wide range of Main Engine Cut-Off (MECO) conditions, when the stage is separated from the rest of the launch vehicle, in line with the available propellant budget, and while maintaining the peak entry conditions within acceptable limits. Either a DownRange Landing (DRL) on a drone ship at sea or a Return To Launch Site (RTLS) to land in the proximity of the launch pad is performed based on the velocity and distance at MECO from the launch site. For the landing burn, a safe splashdown approach has been implemented to avoid damaging the ground infrastructure in case of anomalies during the flight. Based on the mission feasibility assessment, the needs for the vehicle recovery have been identified, leading to the definition of preliminary mission requirements at the system and subsystem level. Consequently, the consolidation of the return mission design was possible and optimised trajectories have been defined for the DRL and RTLS scenarios.

Digital Twin-Enabled Decision Support in Mission Engineering and Route Planning

This article presents a Model-Based Systems Engineering (MBSE) methodology for the development of a Digital Twin (DT) for an Unmanned Aerial System (UAS) with the ability to demonstrate route selection capability with a Mission Engineering (ME) focus. It reviews the concept of ME and integrates ME with a MBSE framework for the development of the DT. The methodology is demonstrated through a case study where the UAS is deployed for a Last Mile Delivery (LMD) mission in a military context where adversaries are present, and a route optimization module recommends an optimal route to the user based on a variety of inputs including potential damage or destruction of the UAS by adversary action. The optimization module is based on Multiple Attribute Utility Theory (MAUT) which analyzes predefined criteria which the user assessed would enable the successful conduct of the UAS mission. The article demonstrates that the methodology can execute a ME analysis for route selection to support a user’s decision-making process. The discussion section highlights the key MBSE artifacts and also highlights the benefits of the methodology which standardizes the decision-making process thereby reducing the negative impact of human factors which may deviate from the predefined criteria.

Complete Coverage Path Planning of an Unmanned Surface Vehicle Based on a Complete Coverage Neural Network Algorithm

In practical applications, an unmanned surface vehicle (USV) generally employs a task of complete coverage path planning for exploration in a target area of interest. The biological inspired neural network (BINN) algorithm has been extensively employed in path planning of mobile robots, recently. In this paper, a complete coverage neural network (CCNN) algorithm for the path planning of a USV is proposed for the first time. By simplifying the calculation process of the neural activity, the CCNN algorithm can significantly reduce calculation time. To improve coverage efficiency and make the path more regular, the optimal next position decision formula combined with the covering direction term is established. The CCNN algorithm has increased moving directions of the path in grid maps, which in turn has further reduced turning-angles and makes the path smoother. Besides, an improved A* algorithm that can effectively decrease path turns is presented to escape the deadlock. Simulations are carried out in different environments in this work. The results show that the coverage path generated by the CCNN algorithm has less turning-angle accumulation, deadlocks, and calculation time. In addition, the CCNN algorithm is capable to maintain the covering direction and adapt to complex environments, while effectively escapes deadlocks. It is applicable for USVs to perform multiple engineering missions.

(Invited) Electrolysis at a Distance: Challenges to Autonomous Operation of MOXIE on Mars

Currently on Mars aboard the Perseverance rover, the Mars Oxygen ISRU Experiment (MOXIE) is a prototype of a system that will someday provide many tons of oxygen as the major component of the propellant for a Mars Ascent Vehicle that will return astronauts from the Red Planet.MOXIE (Figure 1) first collects, filters, and compresses the thin Martian air, which consists of 95% CO2 and small amounts of nitrogen and argon at a pressure of <10 mbar, using a custom scroll pump developed by Air Squared, Inc. It then pre-heats the gas to ~800˚C and injects it into a stack of 10 solid oxide electrolysis cells (SOXE) developed by Ceramatec, Inc. (now OxEon Energy). CO2 is thermally and catalytically decomposed according to the reaction CO2 → CO + O2- at the cathode of the electrolysis cells, then the oxygen ions are selectively drawn through the yttriumstabilized zirconia electrolyte where they recombine at the anode into O2 molecules. The transfer of 4 electrons from anode to cathode completes the circuit and provides the motive force for the reaction. The pure oxygen product is characterized, then released through a precision aperture, while CO fuel and unused CO2 are similarly characterized and discharged through an exhaust port.MOXIE expects to produce 6-10 grams of 98% pure O2 per hour, a factor of ~200 less than will eventually be needed on a full-scale system.Planning of MOXIE operations is dominated by the need to maintain safe conditions while at the same time exploring the limits of performance and characterizing the state of the system. As shown in Figure 2, the voltage across the MOXIE cells, the flow rates, and the SOXE temperature need to be carefully balanced to avoid crossing Boudouard boundaries. MOXIE is typically operated in a constant-current mode, introducing uncertainties into the operating voltage. To compound these uncertainties, there are significant voltage drops elsewhere in the system across series resistances that are dominated by the Inconel electrical leads. Determining the variation of performance with SOXE temperature is a one method used to distinguish the resistance across the membrane, which is a strong function of temperature, from those series resistances.Subsequent runs will evaluate operation at different inlet flows and SOXE temperature, and will test alternative control configurations such as voltage-feedback control instead of current-feedback control or cathode pressure feedback control of compressor speed. Development of a “smart” control system is a high priority for future work and will be explored in a laboratory setting during the MOXIE campaign. Acknowledgement: MOXIE is supported by a collaboration between NASA’s Human Exploration and Operations Mission Directorate and the Space Technology Mission Directorate. The Mars 2020 mission is supported by the Science Mission Directorate.

Marinite Li2Ni(SO4)2 as a New Member of the Bisulfate Family of High-Voltage Lithium Battery Cathodes

The authors acknowledge the financial support from the Technology Mission Division (Department of Science and Technology, Government of India) under the Materials for Energy Storage (MES-2018) program (DST/TMD/MES/2K18/207). S.S. and P.K.J. thank the Ministry of Human Resource Development (MHRD) for financial support. P.K.J. thanks Prof. M. Shrivastava and Prof. S. G. Gopalakrishnan for computational resources and scientific discussions, respectively. H.N.A. is grateful to the King Abdullah University of Science and Technology (KAUST) for partial financial support. A.N. and K.J. sincerely acknowledge financial support from the U.S. Department of Energy, Office of Basic Energy Sciences, Grant DE-FG02-03ER46053.

Initial sizing of a roadable personal air vehicle using design of experiments for various engine types

Purpose The purpose of this paper is to analyze and compare the performances of novel roadable personal air vehicle (PAV) concepts that meet established operational requirements with different types of engines. Design/methodology/approach The vehicle configuration was devised considering the dimensions and operational restrictions of the roads, runways and parking lots in South Korea. A folding wing design was adopted for road operations and parking. The propulsion designs considered herein use gasoline, diesel and hybrid architectures for longer-range missions. The sizing point of the roadable PAV that minimizes the wing area was selected, and the rate of climb, ground roll distance, cruise speed and service ceiling requirements were met. For various engine types and mission profiles, the performances of differently sized PAVs were compared with respect to the MTOW, wing area, wing span, thrust-to-weight ratio, wing loading, power-to-weight ratio, brake horsepower and fuel efficiency. Findings Unlike automobiles, the weight penalty of the hybrid system because of the additional electrical components reduced the fuel efficiency considerably. When the four engine types were compared, matching the total engine system weight, the internal combustion (IC) engine PAVs had better fuel efficiency rates than the hybrid powered PAVs. Finally, a gasoline-powered PAV configuration was selected as the final design because it had the lowest MTOW, despite its slightly worse fuel efficiency compared to that of the diesel-powered engine. Research limitations/implications Although an electric aircraft powered only by batteries most capitalizes on the operating cost, noise and emissions benefits of electric propulsion, it also is most hampered by range limitations. Air traffic integration or any safety, and noise issues were not accounted in this study. Practical implications Aircraft sizing is a critical aspect of a system-level study because it is a prerequisite for most design and analysis activities, including those related to the internal layout as well as cost and system effectiveness analyses. The results of this study can be implemented to design a PAV. Social implications This study can contribute to the establishment of innovative PAV concepts that can alleviate today’s transportation problems. Originality/value This study compared the sizing results of PAVs with hybrid engines with those having IC engines.

Food industry and engineering—Quo vadis?

Food industry and engineering—Quo vadis?

Temperature stability of the Taiji-1 satellite in operational orbit

The Taiji-1 satellite is a pioneering space technology mission designed by the Chinese Academy of Science (CAS) to test key technologies required for gravitational wave detection in space. Temperature stability is a critical element because it can couple with the gravitational wave measurement. A dedicated thermal control with a three-level control method was used on the Taiji-1 satellite science module. The simulation analysis shows that the temperature stability control level of its scientific instrument temperature stability can reach ± 1.7 mK. Combined with the in-orbit temperature results, the temperature stability obtained by using the linear smoothing filter and the Kalman filter reached ± 1.1 and ± 0.5 mK, respectively, which were in good concerted with the simulation data, indicating that the thermal control level of Taiji-1satellite science module reached a high precision.

Thinking on large-scale terrestrial ecosystem management and its theoretical fundament and practice.

Ecosystem management at large scales is one of the core solutions to solve current global challenges of environmental and resources problem, mitigate climate change, govern ecosystems and environments regionally and achieve sustainable development. It is also a hotspot in the research and practice of conservation of global natural resources and ecosystems. Based on recalling and synthesizing of several large international actions on ecosystem management in the past two decades, this article rethought the concept of ecosystem management and its application from the perspective of discipline development of ecosystem management, theoretical fundaments and practices. The content included three parts: firstly, we reviewed the development of the scientific concept and practice of ecosystem management, discussed the connotations of the concept and redefined it, and summarized the practice of ecosystem management and its contribution to the development of the discipline. Secondly, we clarified the scientific and technological mission and basic tasks of ecosystem management, organized the discipline system of ecosystem management and its main research fields, summarized fundamental theories and the knowledge system of the science of ecosystem management, and clarified critical steps of ecosystem management actions, basic elements of management plans and management approaches. Finally, we proposed new trends of scientific research and the discipline development of ecosystem management, discussed the important spatial scales and its objects system of the scientific research on ecosystem management, proposed the cutting-edge scientific questions of global ecosystem management, integrative ecology thought and macro ecosystem approach. This review aimed at providing references for the scientific research and discipline deve-lopment of ecosystem management in China.

LICIACube - The Light Italian Cubesat for Imaging of Asteroids In support of the NASA DART mission towards asteroid (65803) Didymos

“LICIACube – the Light Italian Cubesat for Imaging of Asteroids” is managed by the Italian Space Agency (ASI) and will be part of the NASA DART mission, with the aim of i) documenting the DART impact’s effects on the secondary member of the (65803) Didymos binary asteroid system, ii) characterizing the shape of the target, and iii) performing dedicated scientific investigations on it. DART probe will be launched at the end of 2021 and LICIACube will be hosted as piggyback during the interplanetary cruise, then released 10 days before the impact, and autonomously guided along its fly-by trajectory. The LICIACube payload is composed by LEIA, a narrow FoV camera, and LUKE, a wide FoV imager with an RGB Bayer pattern filter, that will collect and transmit to Earth several unique images of the effects of the DART impact on the asteroid, such as the formation and the development of the plume potentially determined by the impact.LICIACube will be the first deep space mission developed and autonomously managed by an Italian team: the design, integration and test of the CubeSat have been assigned by ASI to the aerospace company Argotec, while the LICIACube Ground Segment has a complex architecture based on the Argotec Mission Control Center, antennas of the NASA Deep Space Network and data archiving and processing, managed at the ASI Space Science Data Center. The LICIACube team includes a wide Italian scientific community, involved in the definition of all the aspects of the mission: trajectory design; mission definition (and real-time orbit determination during operations); impact, plume and imaging simulation and modelling, in preparation of a suitable framework for the analysis and interpretation of in-situ data. The major technological mission challenge, i.e. the autonomous targeting and imaging of such a small body during a fast fly-by, to be accomplished with the limited resources of a CubeSat, is affordable thanks to a strong synergy of all the mentioned teams in support of the engineering tasks.