Academic literature on the topic 'Space craft engineering'
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Journal articles on the topic "Space craft engineering"
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Cowen, Ron. "Tryst in Space: Craft, Asteroid Rendezvous." Science News 157, no. 8 (February 19, 2000): 118. http://dx.doi.org/10.2307/4012201.
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Jordan, James F. "Navigation of Spacecraft on Deep Space Missions." Journal of Navigation 40, no. 1 (January 1987): 19–29. http://dx.doi.org/10.1017/s0373463300000266.
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Spacecraft which are sent on deep space missions to the planets must be accurately navigated in order to achieve the correct flight path. Navigation analysts use precise measurements and large computational software systems to determine a spacecraft's position throughout the mission and compute the velocity corrections for its guidance through space. When the spacecraft is launched into deep space on its voyage, it is impossible to know with great precision where it is headed. Imperfections in both the launch vehicle's terminal velocity and the uncertainty in the knowledge of the parameters which will affect the spacecraft trajectory contribute to errors in the predictions of the total flight path. Continuous navigation of the spacecraft achieves an ever-evolving prediction of its orbit from the reduction of radiometric and astrometric observations of the craft. Control of the spacecraft is achieved by computing and signalling to the craft a series of propulsive, velocity correction commands, which manoeuvre the craft to its desired course.
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Bruno, Claudio, Antonella Ingenito, and Domenico Simone. "Mars One-Year Mission Craft." Aerospace 10, no. 7 (June 30, 2023): 610. http://dx.doi.org/10.3390/aerospace10070610.
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A human Mars mission is more challenging to astronauts than the Apollo mission because of travel time, life support requirements, and the space environment. Although plans for Mars exploration by NASA and SpaceX based on conventional rockets have been presented, there are considerations that suggest alternatives for the mid- or long-term. The purpose of this paper is to outline a fast mission enabled by advanced (nuclear) propulsion and by internationally shared technology. Whether the destination is the Mars surface or Phobos, for a chemical powered spacecraft, the round trip takes about 990 days, including a 480-day surface stay, compared to only 370 days, including a 41-day surface stay, for the nuclear-powered spacecraft assumed here. Since nuclear propulsion can provide higher speed than chemical, the radiation dose can be drastically reduced. The logistics of such a mission involve one or more cargo craft that must precede the astronauts. Ballistic entry into Mars’ atmosphere depends on accurate knowledge of its features, to date poorly known, that may result in uncertainty in landing coordinates. For a single vehicle, this is not critical, but for a human crew ballistic landing kilometers away from cargo is unacceptable: walking for anything but the shortest distance cannot be afforded with current space suits. In this context, the concept of a modest L/D maneuvering cargo glider based on the past Russian “Kliper” is recommended and developed to ensure landing within a hundred meters of each spacecraft. The crewed lander vehicle is based on the high L/D, inherently stable USAF FDL-7C/D hypersonic glider experience. In a similar approach, an exploration vehicle powered by in situ manufactured CO2 and silane is described that can explore the Martian surface much faster and efficiently than with rovers or rocket-powered ‘hoppers’.
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KOBAYASHI, Akihide. "Surface Finishing in Thermal Control of Space Craft." Journal of the Surface Finishing Society of Japan 66, no. 6 (2015): 256–58. http://dx.doi.org/10.4139/sfj.66.256.
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Divya N.M, Jhanavi M, Nithin Kumar S, Shalmali S.Mankikar, Dr. Sindhu Sree M, Dr. Pavithra G, and Dr. T.C.Manjunath. "A study on weather forecasting by using nano-space craft." international journal of engineering technology and management sciences 7, no. 3 (2023): 464–67. http://dx.doi.org/10.46647/ijetms.2023.v07i03.62.
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In this paper, the study on weather forecasting by using nano space craft is presented. In the past two decades, a silent revolution has taken place in the space domain, leading to what today is known as “New Space.” We have passed from a selected group of countries, space agencies, and big industries building, launching, and operating satellites and other spacecrafts, of a scenario in which many universities and research institutes can do it. The key of this was the definition of the “CubeSat” standard, back to 1999. In 2013, it all took off on the commercial Earth Observation sector with the first launches from two companies that are now running 100+ CubeSat constellations for optical imaging or weather prediction, with very low revisit times. Today, the same revolution is taking place in the fields of Telecommunications, and Astronomical Scientific missions. In this chapter, the evolution of the space sector is briefly revised until the arrival of the CubeSats. Then, the CubeSat intrinsic limitations are discussed as they are key to understand the development and current situation of the CubeSat sector. NASA and ESA strategies are also presented. The chapter concludes with a summary of the technology roadmap to enable the next generation of CubeSat-based missions, including satellite constellations or federations, formation flying, synthetic apertures… The work done & presented in this paper is the result of the mini-project work that has been done by the first sem engineering students of the college and as such there is little novelty in it and the references are being taken from various sources from the internet, the paper is being written by the students to test their writing skills in the starting of their engineering career and also to test the presentation skills during their mini-project presentation. The work done & presented in this paper is the report of the assignment / alternate assessment tool as a part and parcel of the academic assignment of the first year subject on nanotechnology & IoT.
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Stapleford, Thomas A. "Engineering the “Statistical Control of Business”." History of Political Economy 52, S1 (December 1, 2020): 59–84. http://dx.doi.org/10.1215/00182702-8717924.
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Malcolm Rorty is best known to historians of economics as the primary organizer and founder of the National Bureau of Economic Research. This article situates Rorty’s interest in economics against the backdrop of his early career in telephone engineering at American Telephone & Telegraph. I argue that distinct structural features of telephone engineering in general, and AT&T in particular, created overlaps between the practices of engineering and economics, and also opened space for Rorty to craft a broader vision for the “statistical control of business” through quantitatively informed management.
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Sinha, Apoorva, Vandana Sehgal, and Shriyak Singh. "Association of Bastar Tribal Art & Craft in Interiors." International Journal for Research in Applied Science and Engineering Technology 11, no. 4 (April 30, 2023): 3695–703. http://dx.doi.org/10.22214/ijraset.2023.51074.
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Abstract: The dominant fragment of India, the central belt and the central-eastern states are the most important part of India where the tribal communities live. The tribal people are deeply rooted in India and have developed their own techniques and characteristics from various sources. Various tribal arts are increasingly recognized as distinct art forms with distinct aesthetic beauty. All the artistic factors that give an artistic formation a distinctive individuality, such as composition, line, color, texture, and rhythm, are examined in this study to evaluate the emerging trends of tribal art in interior design. Art allows people to express their personality and their beliefs. A tribe harbors an environment for generating new ideas for work and life whilst also fostering a sense of community which is vital for a healthy productive life. Tribal Art encourages dialogue and inspires our imaginations. Art improves the quality of our lives and our living spaces. It adds warmth and texture to your space. Thus, Tribal Art lets us think about new ideas, explore and experience new perspectives in life. It helps us take a moment away from our busy lives to connect with new community also. The research is based on secondary data collection through case studies and information collected by government departments based on different research papers respectively. Finally, it is concluded that these tribal art products are astonishing and due to this reason, it makes an interior space more enticing and aesthetic. By promoting the handicraft of Bastar, we are not only revealing the hidden talents of the artisans to the world but also strengthening the Indian culture by escalating it in the global scenario
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Cowen, Ron. "Stormy weather in space: Craft take panoramic view of solar eruptions." Science News 171, no. 9 (September 30, 2009): 133. http://dx.doi.org/10.1002/scin.2007.5591710906.
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Mahdi Sajedi, Sayyed, Parviz Ghadimi, Mohammad Sheikholeslami, and Mohammad A. Ghassemi. "Experimental and numerical analyses of wedge effects on the rooster tail and porpoising phenomenon of a high-speed planing craft in calm water." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 233, no. 13 (March 6, 2019): 4637–52. http://dx.doi.org/10.1177/0954406219833722.
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This paper presents experimental and numerical investigation of stability and rooster tail of a mono-hull high-speed planing craft with a constant deadrise angle. Initially, a one-fifth scale model was tested in a towing tank, which showed porpoising phenomenon at 8 m/s (equal to the speed of sailing). Subsequently, two wedges of 5 and 10 mm heights, based on the boundary layer calculations, were mounted on the aft section of the planing hull. These wedges were shown to increase the lift at the aft section. These experiments were carried out at different speeds up to 10 m/s in calm water. The experimental results indicated that the installed wedges reduced the trim, drag, and the elapsed time for reaching the hump peak, and also eliminated the porpoising condition. All these test cases were also numerically simulated using Star CCM+ software. The free surface was modeled using the volume of fluid scheme in three-dimensional space. The examined planing craft had two degrees of freedom, and overset mesh technique was used for space discretization. The obtained numerical results were compared with experimental data and good agreement was displayed in the presented comparisons. Ultimately, the effect of the wedge on the rooster tail behind the planing craft was studied. The results of this investigation showed that by decreasing the trim at a constant speed, the height of the generated wake profile (rooster tail) behind the craft decreases, albeit its length increases.
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D’Amato, Egidio, Immacolata Notaro, Vincenzo Piscopo, and Antonio Scamardella. "Hydrodynamic Design of Fixed Hydrofoils for Planing Craft." Journal of Marine Science and Engineering 11, no. 2 (January 18, 2023): 246. http://dx.doi.org/10.3390/jmse11020246.
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The employment of fixed hydrofoils on existing planing craft is becoming a widely investigated topic, thanks to the opportunity of reducing the total drag forces and the consumptions of main engines, with a positive impact also in terms of air pollutant emissions in the atmosphere. The design of fixed hydrofoils for planing craft is investigated after developing the wing hydrodynamic model, capable of capturing the main forces acting on the craft longitudinal plane. An iterative procedure is developed to solve the nonlinear equilibrium equations and detect the minimum thrust configuration of the fixed hydrofoils at the cruise speed. The new iterative procedure allows investigating the entire design space of fixed hydrofoils and detecting the best configuration for both new and existing craft, with a positive impact in terms of time effort amount and design efficiency. A simplified seakeeping model is also developed to evaluate the impact of fixed hydrofoils on the craft hydrodynamics in a seaway. The USV01 planing craft is assumed as reference for the case study. The wing optimization procedure is employed and the seakeeping analysis in the foil-borne mode is subsequently performed by a set of dedicated codes developed in Matlab. The obtained results are discussed and some suggestions for the reliable design of fixed hydrofoils are provided.
Dissertations / Theses on the topic "Space craft engineering"
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Tiwari, Pyare Mohan. "Spacecraft attitude control using advanced sliding mode control techniques." Thesis, IIT Delhi, 2016. http://eprint.iitd.ac.in:80//handle/2074/8189.
Full textBooks on the topic "Space craft engineering"
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Deep Space Craft An Overview Of Interplanetary Flight. Springer, 2009.
Find full textBook chapters on the topic "Space craft engineering"
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Crouch, Dora P. "Architectural Expression of Public and Private Water Supply at Morgantina, Corinth, Athens, and Delos." In Water Management in Ancient Greek Cities. Oxford University Press, 1993. http://dx.doi.org/10.1093/oso/9780195072808.003.0034.
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Water in ancient Greek cities can be considered under several rubrics— aesthetic enrichment of urban spaces, ornamentation of enclosed precincts, nuisance or danger in the form of flood or excessive storm runoff, domestic amenity, public ritual and spectacle, to name a few. This chapter focuses on public fountains, which were both amenity and necessity, contrasting them with the more humble domestic arrangements of the same cities. The appearance, function, and location of fountains cannot be understood as merely visual matters, even though the form and ornamentation of fountains made significant architectural and aesthetic contributions to the cityscape. Rather, understanding the local geology and climate and the principles of hydraulic engineering makes possible a new and clearer understanding of this architectural type. The technological and geological basis of water supply is of equal weight in urban development with the formal presentation of water as an urban amenity. Water management in ancient Greek cities expressed in its physical forms both the simplicity and the sophistication of their hydraulic technology. The physical arrangements were expressed in the same vocabulary of the Greek orders and decorative details that were used for other buildings and fittings, and in the same range of local and imported materials. Placement of the water system elements not only facilitated their use but also indicated the high value placed on water and on its use. The dangers of too much water or not enough were not only solved by Greek technological tradition but also expressed in the physical forms given to the individual parts and to the water system as a whole. Each of the water elements I have studied is simple, fulfilling its function economically, yet each is sophisticated enough that modern day practice is just beginning to catch up with these crafty ancients. For instance, having both the flowing water of fountains and wells, and the stored rainwater of cisterns, meant that the water supply of a Greek city was diversified for greater safety in time of war or shortage, and for ecological soundness. In the late twentieth century we are just beginning to understand the utility of redundancy.
Conference papers on the topic "Space craft engineering"
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Das, K. Krishna, and V. S. Aakash Simsshti. "Hyper-thrusted luminal space-craft application of beam expanders." In 2014 2nd International Conference on Current Trends in Engineering and Technology (ICCTET). IEEE, 2014. http://dx.doi.org/10.1109/icctet.2014.6966306.
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Yoshida, Yutaka, Yuji Honma, Tadashi Narabayashi, and Yoichiro Shimazu. "Study for the Space Craft for Interplanetary Cruise: (3) Examination of the Thermal Efficiency." In 16th International Conference on Nuclear Engineering. ASMEDC, 2008. http://dx.doi.org/10.1115/icone16-48491.
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In order to explore the deep space, such as Mars, Jupiter, Saturn, etc in the future, a spacecraft that will be driven by nuclear power should be developed [1]. At present, satellites or space probes have been using mainly electric source of chemical battery, fuel battery, solar battery, and RI battery. However, considering highly developed and extensive space exploration in the future, it is obvious that larger electric power is required over the long term space travel more than several years. Additionally, the solar battery used in space will be fundamentally impossible to use in planetary exploration father away form Mars because sunlight is attenuated. Therefore, lager electric power source must be installed in the space craft. In this study, we consider about co-generation system for heat and electricity using nuclear power. We think that the nuclear power is appropriate for using in deep space because of a long time operation without refueling and possibility in downsizing due to higher power density. We selected the fast reactor system of about 18 MWth compared with other type of reactors, such as PWR and high temperature gas reactor [2]. With regard to a power generation system, we examined about efficiency of Stirling engine compared with a gas-turbine engine. Theoretical efficiency of Stirling engine [3] is much higher than that of gas-turbine engine. Therefore, we selected Stirling engine and we have started the model test of a Stirling engine. Total power generation at International Space Station (ISS) that has been built since 1998 is about 110kWe. We estimated that about 5times as much electricity as that of ISS is enough to explore or develop the space. In that case, 2.5MWe will be generated by the system, number of crews will be about 10 and 2MW will be used to electric propulsion.
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Nakaya, Koji, Shuhei Nishimaki, Osamu Mori, and Jun’Ichiro Kawaguchi. "Dynamics of Large Membrane for Solar Sail-Craft." In ASME 2007 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/detc2007-35919.
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This paper discusses dynamics of large membrane for achieving spinning solar sail-craft proposed by the Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA). For comprehending the dynamics, firstly, two types of grand-scale experiments were conducted. One was an ice rink experiment. The other was a balloon experiment. In the both experiments, we succeeded in deploying 10m and 20m diameter membrane and observing the motion. Secondly, we constructed a numerical model using a multi-particle method, and numerical simulations were conducted. We drew a comparison between results of experiments and numerical simulations. The effectively of the multi-particle model was then indicated in this paper.
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Goode, T. "Machinery Space Fire Fighting – Modern Alternatives." In 14th International Naval Engineering Conference and Exhibition. IMarEST, 2018. http://dx.doi.org/10.24868/issn.2515-818x.2018.025.
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Machinery spaces in the majority of Royal Navy (RN) vessels use carbon dioxide (CO2) as the primary fire suppressant. While CO2 is very effective for firefighting, particularly in machinery space application, it is harmful to life in the concentrations required for effective fire suppression; exposure to concentrations greater than 15% can cause death within sixty seconds. The use of CO2 and similar fire suppressant systems in machinery spaces presents a risk due to the potential exposure of personnel. This may occur in a fire scenario where personnel are unable to escape the affected compartment, if there is a leak in the system, or due to accidental discharge. These risks are typically mitigated through physical means and procedural controls. However, in the hierarchy of safety controls the primary means should always be the elimination of the hazard. Babcock Energy and Marine undertook a study for the United Kingdom Ministry of Defence (MoD) into alternative methods of firefighting on Royal Navy minor warship machinery spaces with the safety of personnel considered a key requirement. The study identified five alternatives to CO2 available on the market. One particular aerosol fire suppression system was found to be superior to the others for application in small craft. This system is not toxic, non-ozone depleting and leaves almost no residue after application to the affected space, enabling re-entry (provided that the space has been ventilated to remove the products of combustion). The study concluded that traditional methods of fire suppression should be reconsidered across all small craft due to the health and safety issues associated with CO2 and the availability of improved alternatives. This paper considers the use of traditional firefighting systems on naval vessels in light of 21st century health and safety regulations. An assessment of current fire extinguishing agents is presented followed by a case study to determine the most appropriate solution for a minor warship concept with a particular aerosol system being justified as the preferred option. The paper also considers if the same conclusions would be reached for major warships or if the difference in scale results in an alternative solution.
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Smith, Warren F., Ahmad F. Mohamad Ayob, and Tapabrata Ray. "The Design of High Speed Planing Craft Using an Optimization Framework." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-85844.
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High speed planing craft as a unique vessel type play key commercial roles in niche passenger ferrying and high value cargo transport. In addition, they are used to support several critical maritime activities such as coastal surveillance, reconnaissance, and life-saving operations and many recreational pursuits. Formal optimization frameworks, despite their significant use across a range of domains, have rarely been proposed and developed to deal with the design challenges of high speed planing craft. Highlighted in this paper is an optimization framework drawing on both domain dependent and domain independent elements for the conceptual and preliminary design of high speed planing craft. A summary of the principal components of the optimization framework are presented, followed by several case study examples. The solvers developed and employed are classified as being population based, evolutionary and stochastic in nature. These characteristics are well suited to design space exploration in all engineering and decision making contexts. Within the case studies presented, the sample key performance indicators include calm water resistance, resistance in waves, seakeeping and manoeuvring. The concept of scenario-based hydrodynamic design optimization is introduced using an example of a small rescue craft operating in a predefined sea-state. Finally, a multi-objective optimization case study considering total resistance, steady turning diameter and vertical impact acceleration is presented to demonstrate the capability to explore trade-offs while at the same time providing an understanding of the design intent of a basis ship. This work has significant purpose and relevance in both ab-initio and reverse engineering contexts. It also has natural extensions in both depth of analysis and breadth of application.
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Wang, Lei, Zong-quan Deng, Hao-di Wang, and Hong-hao Yue. "Analysis of Hybrid Programming Simulation Based on the Variable Stiffness Ring With Expanding Loop SMA Actuator." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-71246.
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In the development of space craft design index, the requirements of hypersonic space craft control accuracy has been increasingly rigorous. Thin-walled structure is often employed in hypersonic craft to reduce the weight of the load and to save the room. During the flight of the craft, temperature field is produced along the surface and the dynamic properties of the craft structure are obviously changed. The decreasing elastic modulus of the structure material and the appearance of thermal stress lead to the decrease of integral rigidity and stability of the structure, then the thermal flutter appears and control difficulties increase. Shape Memory Alloy (SMA) has the advantages of the considerable driving force in the compact volume and the simple driving method. By the combination of actuator structure design and stiffness control, the smart structure is able to make active control to the thermal stiffness variation. In this paper, the apex high-temperature area is equivalent to a ring structure. Finite difference method is employed firstly to transform the governing partial differential equation into discrete finite difference equations. Then the elastic modulus change, thermal stress and tension along the circumference are considered comprehensively to propose the calculation formulas of equivalent young’s modulus. The discrete dynamic matrix model is obtained containing the control terms of SMA. To solve the big-matrix calculation and multiple iterated large data problem, hybrid program is developed with C++ and MATLAB. Finite element software is employed to make optimization analysis to design an expanding loop actuator containing SMA as driving source, variable thickness loops of spring steel as expanding units, and universal-ball pre-loading units. On the basis of that, the thermal stiffness variation active control system with smart structure is developed based on expanding loop SMA actuator. After the analysis of examples, the variation law of the needed SMA driving force is obtained. The distribution position and quantity of the driving source is optimized. This research provides reference for the Theoretical Analysis and Simulation of structure stiffness active control and adaptive control of the aircraft employing smart material. The research results have guiding significance for the smart structure design of hypersonic aircraft in the future.
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Komerath, Narayanan. "Rocket-Augmented Two Stage Runway Based Space Access Architecture." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-70253.
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A runway-based space access system concept based on two stages to orbit is further refined. Routine access to Space with large payloads is essential for Space infrastructure projects such as solar power stations. The aim is to develop a reference architecture to enable cost estimation for a large reusable fleet. Prior work established that a 25000 kg payload could be delivered to low earth orbit starting with takeoff from a runway using a vehicle with the parameters of today’s large airliners. Hydrogen-fueled high-bypass turbofans provide efficient subsonic climb while oxygen is liquefied and stored. The second stage is launched at transonic speed at 18 kilometers altitude, followed by aerodynamic flight with ramjet, SCRAMjet and then rocket propulsion to orbit. A new feature is a brief rocket burn to fill the transonic ramjet performance gap, followed by ramjet-powered supersonic acceleration and climb. Beyond 60 km, SCRAMJET acceleration reaches the von Karman limit of 100km at Mach 8, beyond which rocket propulsion takes the craft to orbit. A refined initial mass estimation process allows the design to close swiftly, showing that payload capacity can be increased in future iterations with the same carrier aircraft parameters.
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Dignan, M., G. Schudel, M. Sutterlin, and D. Kewley. "An Autonomous System for the Active Control of Noise on a High Speed Patrol Craft." In ASME 1996 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/imece1996-0502.
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Abstract An autonomous active noise control system has been developed to reduce low frequency noise in the aft berthing space of a high speed patrol craft. The system controls both high amplitude propeller blade-rate harmonic noise, as well as broadband noise caused by propeller cavitation and machinery. A local control strategy using an adaptive feedback algorithm provides a quiet zone at the head of each bunk. One system, containing a loudspeaker, microphones, and control electronics, is mounted at the head end of each bunk. The only external connection to the system is a power cable. Noise reductions of up to 20 dB at tones and 8, 15, and 5 dB in the 31, 63, and 125 Hz octave bands respectively have been measured at the head position of the bunks. Overall A-weighted level reductions of up to 6 dB have also been measured.
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Ruggiero, Eric J., Garret T. Bonnema, and Daniel J. Inman. "Application of SISO and MIMO Modal Analysis Techniques on a Membrane Mirror Satellite." In ASME 2003 International Mechanical Engineering Congress and Exposition. ASMEDC, 2003. http://dx.doi.org/10.1115/imece2003-41710.
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The future of space satellite technology lies in the development of ultra-large, ultra-lightweight space structures orders of magnitude greater in size than current satellite technology. Such large craft will increase current communication and imaging capabilities from orbit. To get ultra-large structures in space, they will have to be stored within the Space Shuttle cargo bay and then inflated on-orbit. However, the highly flexible and pressurized nature of these ultra-large spacecraft poses several daunting vibration and control problems. Disturbances (i.e. on-orbit maneuvering, guidance and attitude control, and the harsh environment of space) wreck havoc with the on-orbit stability, pointing accuracy, and surface resolution capability of the inflated satellite. However, recent advances in integrated smart material systems promise to provide solutions to these problems. Recent research into the use of Macro-Fiber Composite (MFC®) devices integrated into the dynamic measurement and vibration control of inflated structures has had promising results. These piezoelectric-based devices possess a superior electromechanical coupling coefficient making them superb sensors and actuators in dynamic analysis applications. Initially, research was performed on an inflated torus using single-input, single-output (SISO) testing techniques. Since then, steps have been taken to outline a new, multiple-input, multiple-output (MIMO) testing technique for these ultralarge structures. Based on the matrix formulation and postprocessing techniques recently developed, the current work applies these results to an inflated torus with bonded membrane mirror to extract modal parameters, such as the damped natural frequencies, associated damping, and mode shapes within the frequency bandwidth of interest for these structures (5 – 200 Hz). MIMO modal testing techniques are ideal for large, inflated structure applications. The nature of the structure requires the use of multiple sensors and actuators for worthwhile dynamic analysis and control. Therefore, in the future, the results of this work will form the premise for an autonomous, self-contained system that can both identify the vibratory characteristics of an ultra-large, inflated space craft and apply an appropriate control algorithm to suppress any unwanted vibration—all while on-orbit.
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Yu, Xiaochuan, and Jeffrey Falzarano. "Motion Response Control of the DWSC Spar Based on State-Space Model." In ASME 2012 31st International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/omae2012-84258.
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In 2007, the Office of Naval Research (ONR) started a technology development program called STLVAST (Small to Large Vessel At-Sea Transfer), in order to develop ‘enabling capabilities’ in the realm of logistic transfer (i.e. stores, equipment, vehicles) between a large transport vessel and a smaller T-craft ship, using a Deep Water Stable Crane (DWSC) spar between them. In this paper, the equation of motions of the single DWSC spar is initially expressed as the standard state-space model. Then the ODE solver of Matlab is directly employed to obtain the motion responses at each time step. Two levels of approximation of hydrodynamic coefficients are considered in this study. One is the Constant Coefficient Method (CCM), and the other one is the Impulse Response Function (IRF) method, with fluid memory effects considered. WAMIT software is used to calculate the hydrodynamic coefficients, including the added mass, radiation damping, IRF, the first order and second order waves loads transfer functions, etc. The motion response control is achieved by assuming the thrusters can provide the optimal feedback force derived from Linear Quadratic Regulator (LQR) method.