Technology Developments Integrating a Space Network Communications Testbed

NASA is developing plans for innovative and novel approaches to future (unmanned) space exploration missions. Future missions involve sending spacecraft and robots to harsh environments, where resilience is necessary for the survival of the mission. In addition, distances and communication lead times between the spacecraft and Earth necessitate much of the mission operation being autonomous. We have been conducting research on the development of autonomous space exploration missions based on principles from Autonomic Computing (AC), whereby the mission is imbued with self-management capabilities. Such missions will involve several, rather than single, spacecraft, robots or other devices, operating in collaboration. We describe one such concept mission, ANTS (Autonomous Nano-Technology Swarm), which involves a number of sub-missions that are self-similar. Our work in this, and other future missions, has involved the use of techniques from AC for building in self-management, and ultimately self-governance. We have also explored the use of formal methods to gain confidence in the correct behavior of the mission. Since both the physical devices which will be used for exploration, and the software that is essential for their successful deployment, lend themselves to a product-line approach, we have been exploiting techniques from software product-line engineering, in particular Multi-Agent System Product Lines (MAS-PL) and Dynamic Software Product Lines (DSPL).

The article presents an analysis that underscores the importance of constructing a topology for optical networks in free space. This topology is envisaged to connect various space devices, including artificial satellites, nanosatellites, moon walker, Mars probes, and future space equipment that will utilize quantum technologies. These connected devices will facilitate intelligent applications and remote optical control within the realm of space technology. The article introduces a novel optical network topology for space equipment, terrestrial optical terminals, and terrestrial optical-controlled equipment, with due consideration for transit optical communication. Furthermore, a simplified Markov scheme illustrating this proposed topology has been formulated, accompanied by a stability model. This research offers valuable insights into the development of optical networks in space, paving the way for advanced communication and control systems for future space missions and technologies.

In-situ connectability among modules of a space system can provide significantly enhanced flexibility, adaptability, and robustness for space exploration and servicing missions. Connection of modules in extra-terrestrial environment is hence a topic of rising importance in modern orbital or planetary missions. As an example, the increasing number of satellites sent to space have introduced a large set of connections of various type, for transferring mechanical loads, data, electrical power and heat from one module to another. This paper provides a comprehensive review of published work in space robotic connections and presents the different transfer types developed and used to date in robotic applications for orbital and extra-terrestrial planetary missions. The aims of this paper are to present a detailed analysis of the state of the art available technologies, to make an analysis of and comparison among different solutions to common problems, to synthesize and identify future connectability research, and to lay the foundation for future European space robotic connectability effort and work for a complex and growing important future space missions. All types are described in their base characteristics and evaluated for orbital and planetary environments. This analysis shows that despite the large number of connectors developed for each of the four functionalities (mechanical, thermal, data, and electrical power) here considered, the trend is that researchers are integrating more than one functionalizes into a single equipment or device, to reduce costs and improve standardization. The outcomes of this literature review have contributed toward the design of a future multifunctional, standard and scalable interface at the early stage of the Standard Interface for Robotic Manipulation of Payloads in Future Space Missions (SIROM) project, a European Commission funded Horizon 2020 project. SIROM interfaces will be employed by European prime contractors in future extra-terrestrial missions.

Point-of-care diagnostic devices are well-suited, and typically designed, for remote and/or resource-limited environments. The obvious application is for healthcare in the developing world; however, other additional important uses exist, including for security (biothreat agent detection) and human health and research during future manned deep space exploration missions. The objective of this thesis was to develop, and experimentally validate, techniques for improved quantified detection of labels used in lateral flow assays. Limits of detection were characterized for: (a) optical approaches, i.e., unaided eye, mobile electronic device camera images and microscope images with image analysis software developed through this thesis, and (b) a conductance based approach with direct measurement of electrical impedance in the detection region using hardware and software that were developed. Analysis of camera images from mobile electronic devices enables simultaneous detection of many targets on a multiplexed assay. Additionally, a peripheral device was designed which was intended to provide conductimetric analysis capabilities to mobile electronic devices. The detection limit of gold nanoparticles for the unaided eye was determined at a concentration of (3.98 ± 0.40)×10-11 M; mobile electronic device image analysis, microscope image analysis, and the conductance based approach showed improvements by approximately a half to a third, an order of magnitude, and three orders of magnitude, respectively.

With the acceleration of deep space exploration missions such as the moon, mars and asteroids, planetary protection has become an important issue that must be faced. In the near future, astronauts will perform extraterrestrial celestial operations in more distant and complex unknown environments, which may lead to a large increasing in probability and uncertainty of carrying unknown microorganisms after the spacecraft returning to the earth. From the perspective of protecting astronauts and the Earth's biosphere, it is necessary to conduct safe isolation and protection for astronauts returning from the outer space. In this paper, biological isolation and protection technologies at home and abroad are studied. For China’s future manned deep space exploration missions, we carry out a demand analysis, and propose a design scheme of isolation protection platform.

The US ‘vision for space exploration’ articulated at the beginning of 2004 encompasses a broad range of human and robotic space missions, including missions to the Moon, Mars and destinations beyond. It establishes clear goals and objectives, yet sets equally clear budgetary ‘boundaries’ by stating firm priorities, including ‘tough choices’ regarding current major NASA programs. The new vision establishes as policy the goals of pursuing commercial and international collaboration in realizing future space exploration missions. Also, the policy envisions that advances in human and robotic mission technologies will play a key role—both as enabling and as a major public benefit that will result from implementing that vision. In pursuing future international space exploration goals, the exploration of the Moon during the coming decades represents a particularly appealing objective. The Moon provides a unique venue for exploration and discovery—including the science of the Moon (e.g., geological studies), science from the Moon (e.g., astronomical observatories), and science on the Moon (including both basic research, such as biological laboratory science, and applied research and development, such as the use of the Moon as a test bed for later exploration). The Moon may also offer long-term opportunties for utilization—including Earth observing applications and commercial developments. During the coming decade, robotic lunar exploration missions will play a particularly important role, both in their own right and as precursors to later, more ambitious human and robotic exploration and development efforts. The following paper discusses some of the issues and opportunities that may arise in establishing plans for future robotic lunar exploration. Particular emphasis is placed on four specific elements of future robotic infrastructure: Earth–Moon in-space transportation systems; lunar orbiters; lunar descent and landing systems; and systems for long-range transport on the Moon.

Integrated system health management (ISHM) technologies have been developed to address safety, replace time-based maintenance with condition-based maintenance, and to reduce life cycle costs. Traditional space system designs have focused on safety to minimize the risk to crew and to protect the public, astronauts and pilots, the NASA workforce, and high-value equipment and property. Systems have relied on high reliability components to provide the necessary safety margins and avoid operational mission failures. The current vision for future manned and unmanned space missions to the International Space Station, the Moon, Mars, and beyond, will require longer duration missions and will rely on complex assemblages of components. Increased mission duration and complexity increase the probability of operational mission failures that must be mitigated without jeopardizing safety or the objectives of the current or future missions that might reuse critical mission components. ISHM technology will be essential for providing near-real-time assessments of system capability, safety margins, and maintenance and sustainment requirements. The Applied Research Lab has conducted a series of workshops for NASA which focused on defining requirements for integrated system health monitoring and for the integration of health monitoring and control to provide intelligent self situational awareness (ISSA). The results of these workshops indicate that the benefits of ISHM and greater integration between ISHM and control include increased safety and mission assurance, the ability to rapidly respond to system failures, and decreased operator workload. Emerging open system standards such as OSA-EAI provide a framework for integrating system health monitoring with control functionality in spacecraft avionics systems. The purpose of this paper is to describe areas where system health monitoring can impact safety, reliability and sustainment in space applications and present the results of workshops conducted for NASA to identify requirements for the integration of health monitoring and control in future space systems

System flexibility and simplicity must be maximized for future human and robotic missions to Mars and other planets. A network deployed on the surface of another planet must interoperate with a space-based communication link and/or network, as well as the Earth-side networking segment. The operation of the space-based segment should be simple, but should be able to respond to environmental and system variations causing varying degradation of the link quality. An ongoing study into space and regional communication issues is taking place in the Canadian Arctic, at a prime Mars analog research field site. Preliminary results are demonstrating the needs for simplified operation of the space-based component, and a need to respond to ionospheric and tropospheric propagation variations. Such variations require fine control of the space-based segment, but also require network protocols and operational protocols that can maximize the science and other data uplink and downlink capacity of the complete integrated network system at any given moment of time.

Maintenance of human health on long-duration exploration missions is a primary challenge to mission designers. Indeed, human health risks are currently the largest risk contributors to the risks of evacuation or loss of the crew on long-duration International Space Station missions. We describe a quantitative assessment of the relative probabilities of occurrence of the individual risks to human safety and efficiency during space flight to augment qualitative assessments used in this field to date. Quantitative probabilistic risk assessments will allow program managers to focus resources on those human health risks most likely to occur with undesirable consequences. Truly quantitative assessments are common, even expected, in the engineering and actuarial spheres, but that capability is just emerging in some arenas of life sciences research, such as identifying and minimize the hazards to astronauts during future space exploration missions. Our expectation is that these results can be used to inform NASA mission design trade studies in the near future with the objective of preventing the higher among the human health risks. We identify and discuss statistical techniques to provide this risk quantification based on relevant sets of astronaut biomedical data from short and long duration space flights as well as relevant analog populations. We outline critical assumptions made in the calculations and discuss the rationale for these. Our efforts to date have focussed on quantifying the probabilities of medical risks that are qualitatively perceived as relatively high risks of radiation sickness, cardiac dysrhythmias, medically significant renal stone formation due to increased calcium mobilization, decompression sickness as a result of EVA (extravehicular activity), and bone fracture due to loss of bone mineral density. We present these quantitative probabilities in order-of-magnitude comparison format so that relative risk can be gauged. We address the effects of conservative and nonconservative assumptions on the probability results. We discuss the methods necessary to assess mission risks once exploration mission scenarios are characterized. Preliminary efforts have produced results that are commensurate with earlier qualitative estimates of risk probabilities in this and other operational contexts, indicating that our approach may be usefully applied in support of the development of human health and performance standards for long-duration space exploration missions. This approach will also enable mission-specific probabilistic risk assessments for space exploration missions.

Future manned space exploration missions will require collaborative activities with human astronaut and robotic agents. Proposed mission planning and execution architectures rely on reactive task planning, focusing on real-time information sharing between ground personnel, astronauts, and rovers. We present a planning/scheduling strategy that autonomously optimizes initial task plans/schedules over the human-robot team based on specified mission goals, but that also scales computationally to enable reactive replanning based on modifications to mission goals, revised resource utilization profiles, anomalies/emergencies, and astronaut directives. Collaborative exploration task models and search control algorithms are presented and evaluated in terms of computational complexity versus solution optimality. The implemented software was evaluated over teams of simulated and real rovers collaborating with a human companion. These tests demonstrate that the planning tool can reliably trade execution time for solution optimality when required and that the planner/scheduler is able to capably respond to detected anomalies.

Soon after Armstrong`s left foot touched the surface of the moon in July 21, 1969, Mars seemed to be the next target for any future human space explorations [1, 2]. Although during these forty five years, advances in different fields of science like materials, electronics and space resulted in regular presence of satellites, space explorers and even human in space stations but any long travel including mission to the Mars has been limited by space radiation due to its effect on materials, electronics and astronauts [3, 4]. Space radiation can cause degradation in structural materials, introduce noise in electronic system and impose threat to astronauts` health due to biological changes, which could result in diverse diseases like cancer. In order to overcome these challenges, space radiation must be controlled and maintained under the acceptable limits and this can be achieved by using different shielding materials. Although shielding materials used in space structures designs till date are effective in controlling the radiation for short travels, their use for long duration mission may not be adequate, either due to drastically increase in weight or ineffectiveness of the material for long term travel. Therefore, scientific community and the National Aeronautics and Space Administration (NASA) have focused on finding new innovative radiation shielding materials for the future space explorations. This editorial presents an overview of one of such promising materials viz. Boron Nitride Nanotubes as a future space radiation shielding material.

Thank you for all the questions! We are signing off now. Hi, we’re NASA technologists working on space communications systems that allow NASA to connect astronauts to Earth. This can include communications with Mission Control in Houston, with schools for STEM activities and even with social media accounts. Our Space Network provides 24/7/365 communications capabilities with the International Space Station, and with launch vehicles that service the space station. This year, we’re launching a new Tracking and Data Relay Satellite that will expand the capabilities of that network. We’re also working on laser communications for future human spaceflight missions. We are: · Don Cornwell, NASA Advanced Communications and Navigation Projects Lead ·Bob Menrad, NASA Exploration and Space Communications Associate Director ·Todd King, NASA Project Manager for Orion Laser Communications System (LEMNOS) ·Greg Heckler, NASA Deputy Telecommunications Lead for Tracking and Data Relay Satellites Amber Jacobson, NASA Exploration and Space Communications Education and Public Outreach Lead Don’t forget to follow us on Twitter at @NASA_TDRS, @NASALasercomm and @NASASCaN!

The capabilities of maximising standard payload modules’ functionalities for applications such as on-orbit satellite servicing or planetary exploration depend critically on the creation and availability of a standard interface (IF). Standard interface should provide, aside from the necessary mechanical interconnections, electrical power and data connections, as well as thermal transfer between “building block” payload modules. The overall flexibility enabled by such IF will allow endless reconfigurations of payload and other modules for different functional requirements. This can be considered a game changer technology, enabling transformation from the current approach to space missions, deploying single-use system with pre-planned and limited functionalities, to a radically new approach with multi-use, dynamically reconfigurable and multi-functional systems. Hence, SIROM aims to set a new research agenda for future affordable space missions. Within this context, the partners of the SIROM (Standard Interface for Robotic Manipulation of payloads in future space missions) project are developing the first standard IF solution that combines the four required functionalities in an integrated and compact form for future space missions. With a mass lower than 1.5 kg and having an external diameter of 120 mm and a height of 30 mm, this novel interface permits not only mechanical coupling but also electrical, data and thermal connectivity between so called Active Payload Modules (APMs), as well as other modules such as the robotic end-effectors. This multi-functional IF features an androgynous design to allow for replacement and reconfiguration of the individual modules in any combination desired. It consists of the following sub-assemblies: mechanical IF, electrical IF, data IF, thermal IF and IF controller. A clear advantage of SIROM design is that its mechanical IF consists of a latching and guiding systems for misalignment correction, capable of withstanding certain robotic arm positioning inaccuracies: ± 5 mm translation and ± 1.5° rotation in all axes. Regarding the electrical and data IFs, SIROM transfers up to 150 W electrical power and provides a data transfer rate of 100 Mbit/s via SpaceWire, plus command communication with speeds up to 1Mbit/s via CAN bus. The thermal IF provides fluidic ports for flow transfer and has the potential to transfer 2500 W between APMs accordingly provided with the corresponding close-loop heat exchange system. Although not envisaged for SIROM current design, a possible variation could be to use these ports for satellite re-fuelling. Apart from that, SIROM exhibits redundant coupling capabilities: it can match and couple another completely passive SIROM. It is provided with main and redundant connectors for thermal, electrical, data and control flow in case of one of the lines fails. All in all, SIROM will enable long duration missions with no logistic support, refurbishing, maintenance and reconfiguration of satellites, cost efficiency and simplification of the tool exchange in scientific exploration missions. SIROM is designed to be a common building block for European and possibly world future space robotics enabled missions.

The solar sailing spacecraft is one of the promising propulsion systems for the future deep space exploration mission. Japan Aerospace Exploration Agency (JAXA) has been studying the spin solar sail spacecraft which has a squared-shape type solar sail. One of the most significant objective to control the satellite orbit of the spacecraft is to estimate the thrust force induced by the photon, namely to establish the acceleration model before the launch. In a view point to use this model in orbit, the calibration of the acceleration model and evaluation of the dynamics on orbit are also important issue. This paper presents the way to construct the acceleration model of the Solar Radiation Pressure (SRP) on ground, and the calibration and evaluation strategy for this model by using the on-orbit data.

Solar sail is one of the promising propulsion systems for future deep space exploration missions as it does not require any fuel to acquire propulsive force. Although folding method and deployment mechanism of the sail have been intensively developed, attitude control of the solar sail, which is necessary for the orbital control by the solar sail, has not been much studied. This paper discusses the attitude dynamics and the control method of a spinning type solar sail spacecraft. The spinning type solar sail, where the sail equipped around the spacecraft hub is to be deployed and extended by centrifugal force, has no rigid structure supporting its membrane. This type of mechanism has the advantage in its simple and lightweight structure, however, the attitude control is difficult due to the flexibility of the membrane. In this paper, we introduced a mathematical dynamics model including first oscillation mode of the membrane which can handle coupled motion of a rigid spacecraft and a flexible membrane, and analytically developed a controller that can avoid unnecessary oscillatory motion. The performance of the controller was verified by numerical simulations using more precise multi-particle numerical model.