Manned Space Vehicles Research Articles

ELECTRON-BEAM GUN FOR MANUAL ELECTRON-BEAM WELDING IN LUNAR SURFACE CONDITIONS

In recent years, increasing attention in space topics has been paid to the exploration of the Moon. Not the least attention is paid to solving problems related to providing the necessary living conditions for astronauts, with the construction and assembly of a large number of technical devices and structures on site. The operation and development of orbital complexes, as well as the promising tasks of creating structures on the lunar and Martian surfaces, involve the introduction of technologies for the installation and repair of space objects. When working in open space, there are a large number of operations (first of all, repair and restoration or fixation of fragments of large-sized structures), for which it is difficult and impossible to prepare in advance. In addition, there is a possibility of emergencies that require urgent cutting, welding, or soldering technological operations, in which the process and volume of the operation will be determined by the cosmonaut directly on the spot, where he will be able to assess the volume and method of performing the necessary work. Therefore, the creation of modern electron-beam equipment for manual welding, which will contribute to the extension of the life of space objects and sometimes to the preservation of the lives of crews, is necessary. This equipment must be compact and efficiently perform operations on electron beam welding and related technologies under lunar surface conditions. The results of manual electron beam welding experiments carried out in open space indicate that the equipment, which was created earlier, makes it possible to weld stainless steels, titanium and aluminum alloys up to 1.5 mm thick. At the same time, the thickness of the material used in the manufacture of shells of manned space vehicles reaches 4...6 mm, and the length of welding seams can reach several meters. The purpose of this work is to create a new generation of equipment that will solve the problem of welding materials from 4 to 6 mm, which are mainly used in modern aerospace technology.

Projectile fragmentation and debris cloud formation behaviour of wavy plates in hypervelocity impact

Continuously increasing micro meteorite and orbital debris (MMOD) in space poses a threat to any manned or unmanned space vehicle with increasing probability of damaging object impact. To address the sufficient level of protection of space vessels, many Whipple shield configurations has been studied for over half a century. Bumper plate of Whipple shields studied in existing literature are flat surfaced plates. In contrast to earlier studies, this paper investigates the reaction of bumper plates with wavy surfaces against hypervelocity impact by analysing how they contribute to projectile fragmentation, formation of debris cloud, and how they dissipate the impact energy. Aluminium plates with four different surface wave profiles (WPs) were numerically investigated under hypervelocity impact conditions to assess their performance on disintegration of the impacting projectile. Fragmentation patterns of spherical aluminium projectile and debris cloud generated by projectile-wavy plate couples were examined and compared with the equivalents observed in flat-surfaced plate impact. A hybrid Smoothed Particle Hydrodynamics (SPH) combined with finite element modelling (FEM) approach was adopted using ANSYS software to simulate hypervelocity impact phenomenon at 3 km/s. Results of the numerical work carried out in this study revealed the distinctive debris cloud generation that has never been reported before in the existing literature. Furthermore, compared to the flat plate, wavy plates are found to be more effective in decreasing the impact energy.

Combined Effects of Solar Radiation and High Vacuum on the Properties of Graphene/Polysiloxane Nanocomposites in Simulated Space Environment

Polymer–matrix composites (PMCs) filled with graphene nanoplatelets (GNP) are ultralightweight combined with the ability to perform a wide range of functions. These materials are interesting for many applications in space environments, including the monitoring of degradation caused by radiation exposure. Recently, the growing interest in outer space exploration, by both unmanned probes and manned space vehicles, has encouraged research to make great strides to facilitate missions, with one goal being to monitor and limit the impact of highly damaging radiation. With this perspective, we investigate the effects of simulated space conditions on the physico-chemical, morphological, and mechanical properties of elastomeric PMCs made from a polydimethylsiloxane (PDMS) matrix embedding pristine GNP or a hybrid graphene/DNA filler with high sensitivity to ionising radiation. An analysis of the PMC stability, outgassing, and surface modification is reported for samples exposed to solar radiation under high vacuum (HV, 10−6 mbar). The experimental results highlight the mechanical stability of the PMCs with DNA-modified GNP under solar radiation exposure, whereas the surface morphology is highly affected. On the contrary, the surface properties of PMCs with pristine GNP do not vary significantly under simulated space conditions.

Results of the Development of the Research Prototype of the Interactive Electronic Technical Guide for the MSV Simulator.

The paper considers the designation and requirement for the research prototype of the interactive electronic Technical Guide for the simulator of the Manned Space Vehicle (MSV) as well as the results of its development.

Some Issues of Repairing Manned Space Vehicles in Outer Space Using Electron Beam Welding

A new generation of electron beam tool for welding during assembly and repair-restoration works on board of manned space vehicles in open space was demonstrated. The tool includes a small-sized electron beam gun (EBG) with an electron beam power of up to 2.5 kW and a high-voltage power source with a voltage of 10 kV. The design of the electron-optical system of EBG allows using it in both manual as well as in automatic mode applying robotic devices. Applying the manufactured EBG and manipulator, in vacuum chamber the works on simulating the repair of a spacecraft’s section of aluminum 2219 alloy were carried out. The obtained results of studying the structure and mechanical characteristics and also sealing of welds confirmed the high quality of welded joints and a reliability of the technology for repairing a damaged fragment of a spacecraft's body using electron beam welding.

The concept of a long-term service station to increase the life duration of some satellites or to remove space debris

Every year the concentration of space debris is steadily growing, which significantly complicates the conduct of both modern and future space missions using automatic, and especially manned space vehicles. To date, over 18,000 artificial objects and fragments recorded in near-Earth space. Therefore, the issues of cleansing outer space of space debris of various sizes are quite relevant. In this article, the concept of a multirole station is studied. For the successful design of such a station that could serve spacecraft in space and successfully cope with space debris, it is necessary to consider and necessarily take into account in its further work the ballistic aspects of the orbital motion of spacecraft and the logistics of building such a station. This station could be a maintenance hub for satellites or a space debris collector. Because some satellites have very precious instruments onboard, it could be a loose of money to launch a new satellite if the first one is out of service because of a system failure or a lack of fuel. In this perspective, an orbital maintenance hub would enable to fix the failure (batteries replacement, refueling, mechanical maintenance) and to give to the satellites a new life. In this article, we also study the possibility of using such a hub to remove space debris from their orbit and to collect them until they can be deorbiting.

Thermoplastic Polymeric Materials for Spacecraft Applications: Flame Retardant Properties and UV/AtOx Aging Analysis

Space-mission development introduced the problem of human isolation in extreme environments. The integration of architectural concepts such as windows, with their technical implications into human space missions, is necessary especially for long-duration space flights. Such solutions must be subjected to close certification testing in order to establish their compliance with severe space environment conditions. Moreover, projects of long-term missions involve a renewed concern about fire safety in manned space vehicles. The supposed occupancy time of the order of decades, in fact, makes unplanned fire ignition events virtually unavoidable. An experimental test-plan performed to qualify a commercial thermoplastic material for applications as transparent element in spacecraft is reported in the present work. A flame exposure test, as well as ultraviolet radiation and atomic oxygen erosion rate measurements, was carried out on a commercial poly-sulfone material, following ASTM standard procedures. The aim of the research was to develop and put forward flame retardant structures able to withstand the harsh space environment, preventing or mitigating the degradation of their physical and chemical integrity, with particular regard to the visible-light transparency. The results obtained show that the tested poly-sulfone may be considered as a promising material for the claimed application, even if further surface optimization treatments should be conceived in order to gain a full adaptability to the operative constraints.

Technical and mathematical problems of microbiological protection of a manned space vehicle and stations

During longtime space fights and interplanetary missions among numerous outboard risks, the crew faces onboard microbiological intruders as well. There is no way to send biological tests for the analysis to the Earth in such missions, so special onboard system of methods and activities must solve two different problems: sampling different types of bacteria and fungus and perform independent analysis of collected material without professional microbiologist among the crew and any help from the Earth. So we meet an interesting task to create system that would minimize human factor and rely mostly on computing machinery. In order to use pattern recognition method, we need to perform proper tests sampling and prepare them for the machine analysis. Stereoscopy and spectrometry is the only way to achieve our goal. Apart from tests sampling it is necessary to develop modified mathematical model for pattern recognition of bacteria and fungus, which were found during the flight. For that reason we are making mathematical model, describing microbiological samples. Still, we have a lot of work to do but the result of our research could become common use not only in space sector, but also in clinical medicine as well.

Use of cryogenic components of propellants for liquid-propellant rocket engines and in life support systems of manned space vehicles

The cited materials show the use of oxygen, hydrogen, liquefied natural gases (methane) and fluorine as components of the fuel for liquid-propellant rocket engines (LRE). The reasons for the need to use oxygen as an oxidizing agent are indicated. The advantages and disadvantages are disclosed from the point of view of using the listed components as fuel elements for liquid-propellant rocket engines. The issues of ecology when using the considered fuels are reviewed. Shown not only the use of cryogenic components as fuel for LRE, but also in life support systems in manned spacecraft in space research.

The use of inflatable structures for the removal of spacecraft from orbit

Every year the concentration of objects of space debris is steadily growing, which significantly complicates the conduct of both modern and future space missions using automatic, and especially manned space vehicles. To date, over 15,000 artificial objects and fragments larger than 5 cm have been recorded in near-Earth space. Therefore, the issues of cleansing outer space from objects of space debris of various sizes are quite relevant. In this paper, are considered questions use inflatable structures for deorbiting spacecraft, in order to avoid the formation of new space debris. At the end of the work, conclusions are drawn about the effectiveness using of such inflatable structures.

Prospects for using space greenhouses as a part of a suite of crew life support systems of a lunar orbital station, a lunar base and interplanetary transfer vehicles

It is planned to include greenhouses in the suite of regenerative life support systems for crews of manned long-duration space vehicles to improve their habitability. Space greenhouses will provide crew members with green vegetables containing digestible vitamins and dietary fibers, as well as psychophysiological support during long space missions. The paper presents an analytical review of designs of a number of greenhouses in our country and abroad, both existing and under construction that are capable of operating in spaceflight environment. It describes their key design and operational properties, analyses problems standing in the way of developing more productive space greenhouses. It explains the advantages of our country’s conveyor-type space greenhouse with cylindrical planting surface for continuous production of vitamin-rich greens and other vegetables onboard a manned spacecraft. It points out the need to construct our country’s ground prototype for a full-scale space greenhouse to develop the process for growing plants in orbital station, transportation vehicles, in lunar and Martian outposts. Key words: regenerative life support systems, habitat, space greenhouse, cylindrical planting surface.

Government Policies Help Promote Clean Transportation in India: Proton-Exchange Membrane Fuel Cells for Vehicles

The fuel-cell (FC) concept was invented and demonstrated in the early 18th century by Humphrey Davy. The FC itself was developed in 1839 by the chemist William Grove, who conducted a series of experiments with what he called a gas-voltaic battery. The term fuel cell was first used in 1889 by Charles Langer and Ludwig Mond, who researched FCs using coal gas as a fuel. In the early 1960s, the National Aeronautics and Space Administration and its industrial partners conducted experiments on manned space vehicles based on alkaline FCs (AFCs). Later, the international FC made advances in the AFC for the Apollo space mission, which resulted in supporting the requirements of drinking water and electricity for the astronauts.

Suborbital Spaceflight Vehicle Analysis for Single Pilot Operations

Event Abstract Back to Event Suborbital Spaceflight Vehicle Analysis for Single Pilot Operations Scott Glaser1, 2* 1 Flight Research, Inc, Flight Test, United States 2 Drexel University, Biomedical Engineering, United States Commercial suborbital spaceflight vehicles (SSVs) are brining the dream of spaceflight to the common man. The very specific mission of SSVs brings about new questions, different from those of traditional aircraft. One such question is the number of crewmembers required to operate an SSV. If these vehicles can be flown with one pilot, vehicle weight can be reduced or payload can be increased, the number of trained pilots per flight is reduced in addition to other minor factors that will continue to draw down the per flight cost of traveling to space, make it even more accessible to the general public. Modern SSVs are being designed for two pilots. This configuration has been a traditionally accepted path without any controlled study to investigate it. No studies have been conducted yet on the workload required for modern SSV piloting tasks due to the novelty of the industry, nor have similar relevant studies been performed in adjacent disciplines. The FAA’s requirements for jet transports are the most similar to spaceflight vehicles but are generic and at times do not apply. Hence there is a need to determine, quantitatively, if one pilot can operate an SSV. Single pilots have flown similar vehicles in the past such as the X-15 rocket plane and SpaceShipOne, the first manned commercial space vehicle. These vehicles did not carry passengers, however, their trajectories and workload were very similar. SSVs are not available for testing such questions as the vehicles themselves are still in the early stages of development. A dynamic flight simulation capable of high performance human centrifuge, known as a continuous G device (CGD), can be modified with an SSV representative aeromodel and utilized as a surrogate for an actual vehicle. Rating scales for vehicle handling and pilot workload are also established in the aerospace industry. CGD’s have been utilized to mimic in-flight accelerations, however, actual performance against vehicle flight data must be established. Further, a CGD must be demonstrated as a simulator for an SSV specifically. Lastly, the ability of pilots to maintain a launch trajectory with sufficient ratings on known rating scales will answer if one pilot can fly these vehicles. Utilizing these new advances in flight simulator technology, this experiment will study a single pilot’s ability to maintain a spaceflight boost trajectory given a number of vehicle parameters. The resulting data and conclusions will be of value for manufacturers and operators of winged, rocket-powered vehicles. These vehicles will be operable by a single pilot. This will then translate into better efficiency of crews and therefore safer and less expensive vehicles for public passenger space travel. Keywords: Suborbital spaceflight, Pilot workload, Cooper-Harper, Bedford scale, Centrifuge Based Simulator Conference: 2nd International Neuroergonomics Conference, Philadelphia, PA, United States, 27 Jun - 29 Jun, 2018. Presentation Type: Oral Presentation Topic: Neuroergonomics Citation: Glaser S (2019). Suborbital Spaceflight Vehicle Analysis for Single Pilot Operations. Conference Abstract: 2nd International Neuroergonomics Conference. doi: 10.3389/conf.fnhum.2018.227.00052 Copyright: The abstracts in this collection have not been subject to any Frontiers peer review or checks, and are not endorsed by Frontiers. They are made available through the Frontiers publishing platform as a service to conference organizers and presenters. The copyright in the individual abstracts is owned by the author of each abstract or his/her employer unless otherwise stated. Each abstract, as well as the collection of abstracts, are published under a Creative Commons CC-BY 4.0 (attribution) licence (https://creativecommons.org/licenses/by/4.0/) and may thus be reproduced, translated, adapted and be the subject of derivative works provided the authors and Frontiers are attributed. For Frontiers’ terms and conditions please see https://www.frontiersin.org/legal/terms-and-conditions. Received: 13 Apr 2018; Published Online: 27 Sep 2019. * Correspondence: Mr. Scott Glaser, Flight Research, Inc, Flight Test, Mojave, United States, stg37@drexel.edu Login Required This action requires you to be registered with Frontiers and logged in. To register or login click here. Abstract Info Abstract The Authors in Frontiers Scott Glaser Google Scott Glaser Google Scholar Scott Glaser PubMed Scott Glaser Related Article in Frontiers Google Scholar PubMed Abstract Close Back to top Javascript is disabled. Please enable Javascript in your browser settings in order to see all the content on this page.

Inverse simulation system for evaluating handling qualities during rendezvous and docking

The traditional method used for handling qualities assessment of manned space vehicles is too time-consuming to meet the requirements of an increasingly fast design process. In this study, a rendezvous and docking inverse simulation system to assess the handling qualities of spacecraft is proposed using a previously developed model-predictive-control architecture. By considering the fixed discrete force of the thrusters of the system, the inverse model is constructed using the least squares estimation method with a hyper-ellipsoidal restriction, the continuous control outputs of which are subsequently dispersed by pulse width modulation with sensitivity factors introduced. The inputs in every step are deemed constant parameters, and the method could be considered as a general method for solving nominal, redundant, and insufficient inverse problems. The rendezvous and docking inverse simulation is applied to a nine-degrees-of-freedom platform, and a novel handling qualities evaluation scheme is established according to the operation precision and astronauts' workload. Finally, different nominal trajectories are scored by the inverse simulation and an established evaluation scheme. The scores can offer theoretical guidance for astronaut training and more complex operation missions.

Перспективный интерфейс «человек—машина» для управления пилотируемым космическим аппаратом на базе планшетных компьютеров

Перспективный интерфейс «человек—машина» для управления пилотируемым космическим аппаратом на базе планшетных компьютеров

RF Field Build-Up inside a Manned Space Vehicle Using Novel Ray-Tracing Algorithm

The radio-frequency (RF) field mapping and its analysis inside a space vehicle cabin, although of immense importance, represent a complex problem due to their inherent concavity. Further hybrid surface modeling required for such concave enclosures leads to ray proliferation, thereby making the problem computationally intractable. In this paper, space vehicle is modeled as a double-curvatured general paraboloid of revolution (GPOR) frustum, whose aft section is matched to an end-capped right circular cylinder. A 3D ray-tracing package is developed which involves a uniform ray-launching scheme, an intelligent scheme for ray bunching, and an adaptive reception algorithm for obtaining ray-path details inside the concave space vehicle. Due to nonavailability of image method for concave curvatured surfaces, the proposed ray-tracing method is validated with respect to the RF field build-up inside a closed lossy cuboid using image method. The RF field build-up within the space vehicle is determined using the details of ray paths and the material parameters. The results for RF field build-up inside a metal-backed dielectric space vehicle are compared with those of highly metallic one for parallel and perpendicular polarizations. The convergence of RF field within the vehicle is analyzed with respect to the propagation time and the number of bounces a ray undergoes before reaching the receiving point.

Aerodynamic Analysis of a Manned Space Vehicle for Missions to Mars

The paper deals with the aerodynamic analysis of a manned braking system entering the Mars atmosphere with the aim to support planetary entry system design studies. The exploration vehicle is an axisymmetric blunt body close to the Apollo capsule. Several fully three‐dimensional computational fluid dynamics analyses have been performed to address the capsule aerodynamic performance. To this end, a wide range of flow conditions including reacting and nonreacting flow, different angles of attack, and Mach numbers have been investigated and compared. Moreover, nonequilibrium effects on the flow field around the entry vehicle have also been investigated. Results show that real‐gas effects, for all the angles of attack considered, increase both the aerodynamic drag and pitching moment whereas the lift is only slighted affected. Finally, results comparisons highlight that experimental and CFD aerodynamic findings available for the Apollo capsule in air adequately represent the static coefficients of the capsule in the Mars atmosphere.

S1904-2-4 有人宇宙船の大気突入誘導技術(大気突入・減速技術(2),社会変革を技術で廻す機械工学)

S1904-2-4 有人宇宙船の大気突入誘導技術(大気突入・減速技術(2),社会変革を技術で廻す機械工学)

S1904-2-5 有人宇宙船の緩降下、着陸技術(大気突入・減速技術(2),社会変革を技術で廻す機械工学)

S1904-2-5 有人宇宙船の緩降下、着陸技術(大気突入・減速技術(2),社会変革を技術で廻す機械工学)

NASA contract for charged particle spectrometer for manned space vehicle

NASA contract for charged particle spectrometer for manned space vehicle