Researcher:
Kara, Ozan

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PhD Student

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Ozan

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Kara

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Kara, Ozan

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2014 - 202015

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    Understanding regression rate characteristics of CO2 as an oxidizer compound in paraffin based hybrid rocket motors
    (International Astronautical Federation, IAF, 2020) N/A; Department of Mechanical Engineering; Kara, Ozan; Karabeyoğlu, Mustafa Arif; PhD Student; Faculty Member; Department of Mechanical Engineering; Graduate School of Sciences and Engineering; College of Engineering; N/A; 114595
    CO2 is considered as a major combustion product in nature. However, CO2 can only burn with metallic powders due to high reactivity levels of metals compared to carbon. Therefore, Metal/CO2 combustion mechanism can be a potential propellant candidate for Mars Ascent Vehicles. In-situ CO2 can be used in Mars atmosphere reduces required Earth-based propellant mass. Propellant combination in this hybrid rocket motor consist of paraffin wax based solid fuel including metallic aluminium and magnesium. CO2 is mixed with N2O in various percentages by mass as the motor oxidizer. The goal of this research is to understand the maximum CO2 percentage by mass can be ignited with selected propellant combination (classical hybrid rocket motor). Maximum CO2 is achieved as 75% in oxidizer mixture by using 60% Magnesium 40% Paraffin solid fuel. Oxidizer flow rate at 75% CO2 is obtained as 60 g/s. Aluminum based solid fuels has maximum CO2 percentage of 50%. Magnesium provides better ignition characteristics with CO2. Therefore, the ignition boundary in mass flow rate vs. CO2 percentage is presented for both Al and Mg fuels. Regression rate characteristics does not change with the addition of CO2 in nitrous. Combustion efficiency of Mg based experiments are higher than Al and above 90%. Ignition results indicate that CO2 percentage can be increased with changing internal ballistics of hybrid motor. Paraffin/Metal/CO2 propellant combination can be a potential candidate for Mars Ascent Vehicles.
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    Main circumstances for next generation workforce: how do young professionals enter and grow into the-aero-space sector?
    (International Astronautical Federation, 2015) Park, Ji Hyun; Burgett, Taylor; Yamashiro, Ryoma; Weber-Steinhaus, Luise; Ukaegbu, Kingsley; Kara, Ozan; PhD Student; Graduate School of Sciences and Engineering; N/A
    The private sector has incremental responsibilities to foster innovations in the space sector. New responsibilities require well-educated, disposed and representative young people for the space sector. Therefore, entering and growing into the sector is one of the crucial issues which all young professionals are always facing. We discussed this significant concern at the IAC2014, IPMC Young Professional Workshop, in Toronto, Canada. Possible career paths, circumstances, advantages and challenges working for academia, industry and government were main topics for our discussion. Briefly, academia ensures intellectual freedom since YPs can be part of designing concepts, making computations and system engineering trainings. The private sector bridges over between academia and government for YPs. Working in the government provides an advantages involving hands-on work with the new technologies. Our main discussion approaches were constituted in two perspective; individual and common aspects. Due to our personal experiences we came up discussion points such as (1) circumstances before/after becoming YP, (2) importance of K12 education, (3) overview of German space industry: activities of Airbus, DLR and ESA and (4) workforce supply/demand analysis by the instance of the JAXA. In addition, common aspects included (1) political and sociological issues, (2) lack of corporations in developing countries, (3) boss-YP relations and (4) career paths transition from student to become an YP. Personal aspects presented that a great way for teaching K-12 students relevant skills is to have university students and young professionals helping the in classrooms. Overview of Germany showed that international activities pave the way students to become YPs. Furthermore, language courses, space engineering courses and diverse engineering courses in the Airbus are pertinent examples for YPs to grow into the sector. Due to the workforce supply/demand analysis, while the supply for workforce increases, the demand doesn't change. That makes it difficult for the students to get a job in space sector. Common aspects brought to an end that in the less development countries, sociological conditions and internal policies generally create lack of private industry and restrict improvement of next generation workforce. Young professionals whose bosses are interactive, social, and trustable, sympathizer feel more comfortable during the working periods. Finally, project-based undergraduate education skills have positive effects on students to become YPs.
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    Future mars mission demonstrationwith gamification and socioeconomictraits: nextgenerationworkforce development and self-knowledge management
    (American Institute of Aeronautics and Astronautics Inc, AIAA, 2015) N/A; N/A; Kara, Ozan; PhD Student; Graduate School of Sciences and Engineering; N/A
    This research enhance proper gamification scenerios for future Mars missions. Scenarios include mars atmosphere and surface design, cubesat Mars orbiter, micro flying robot demonstration, in-situ research support, human health risk reduction, digital 3D printing and hands-on rover experiments. The scheduled Mars mission concepts consisting of gamification allow the first uncrewed orbital return with Orion around 2024. The forecasted crewed mission can be realized in early 2030. The next generation workforce development for Mars exploration is presented from 2014 IPMC Young Professional workshop “entering and growing into the space sector” group findings, 2014 OECD Space report and NASA APPEL studies. The workshop findings compare young professional development in academia, industry and government. In addition, findings are classified under student, K12 education, boss relations, sociological conditions and global workforce demand data. OECD report show total space economy is $256B US dollars in 2013. NASA APPEL and CKO has new knowledge map for NASA to unite people and systems in sustainable and effective way. The groundwork of the young professional development and impacts of gamification are comprehended by self-knowledge management and decision making. Finally, reflections of space missions such as Orion, Rosetta and New Horizons inspire public society and have different impacts in countries.
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    Small satellite architecture optimization: electric propulsion moon imaging mission
    (American Institute of Aeronautics and Astronautics Inc, AIAA, 2015) N/A; Department of Mechanical Engineering; Karabeyoğlu, Mustafa Arif; Kara, Ozan; Faculty Member; Master Student; Department of Mechanical Engineering; College of Engineering; Graduate School of Sciences and Engineering; 114595; N/A
    This study underlies small satellite architecture optimization by using existing electric propulsion systems for the Moon missions. The estimated objective is panoramic imaging of the Moon accompanied with future in-situ applications. Edelbaum’s low thrust trajectory transfer with optimal control theory is used to calculate the required ΔV. During the journey, 1.5h eclipse duration effects the solar array design. The optimized xenon propellant density and pressure are 1350 kgm3 and 8.3 MPa within 300K. Two types of optimization process revealed based on hexagonal SC architecture. The iterative method with LEO departured ion thruster has 23 mN with minimum 213 kg total mass. Corresponding SC volume is 0.70 m3, propellant mass is 64 kg. This scenario cost $108.5M and takes 980 days. Same thruster level for GEO departure case takes 880 days with 58 kg xenon gas. The total cost reduces $2.5M. For HALL engine design, LEO departure case needs 0.8 m3, 247 kg SC including 82 kg xenon. 77 mN thrust operates 208 days towards the Moon that ends up with $121M total cost. If the SC to be launched from GEO, flight time reduces 45 days by consuming 65 kg propellant. Total SC mass, volume and power values are 230 kg, 0.71 m3 and 1351W which cost $115M. Results are compared with previous Moon or electric propulsion missions such as SMART-1, LADEE, Clementine and Hayabusa. For future applications of small satellites, innovative concepts are envisioned for in-space, Earth-independent exploration and space education. 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. .
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    Knowledge management infrastructure: Nasa's mars mission with gamification technique & self-knowledge management intangible outcomes for young professionals
    (International Astronautical Federation, 2015) Kara, Ozan; PhD Student; Graduate School of Sciences and Engineering; N/A
    Exploration of the Mars is the preferential topic by space community. Especially NASA is willing to accomplish both robotic and manned Mars missions within 2020s. Before the human spaceflight, the demonstration of a practicable knowledge management infrastructure prevents possible mission failures. In conjunction with the incremental responsibilities, the private sector requires well qualified young people to collaborate and support agencies and governments for future Mars missions. Therefore, the pa-per objectives to create a knowledge management (KM) approach by analysing (1) collaboration among universities, agencies and private sector and (2) young professional workforce development to support requirements of future Mars missions. In the meantime, the knowledge management approach and young professional development particularly focuses on the self-knowledge management. The self-knowledge management associates issues in the social and personality psychologies such as unconscious, introspection, accuracy, bias, experimental methods. The following objective of the paper is the integration of intangible outcomes of the self-knowledge management into the applicable knowledge management approach for NASA's Mars Mission. The KM approach is constituted by following resources; (1) IPMC Young Professional Workshops, (2) NASA's APPEL documents and Masters with Masters Programs (3) literature review about training and education and (4) Self-knowledge management studies. Results of the self-knowledge management are related outcomes such as motives and biases, decision making, un-conscious though and relationship outcomes. The literature review denotes challenges of current trends in training and development such as mobile learning, social learning and leadership development. IPMC YP workshops show practical applications of project management and system engineering from various organizations. Due to the recent studies of NASA, the potential KM approach involves gamification techniques and constructive scenarios for the Mars missions including technical and organizational issues. Gamification technique uses simulations to train young professionals by using previous mission failures. In addition, simulations allow hands-on experience for scientists and engineers visualize Mars within possible defailments.
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    IAC-15- B4.8.7 comprehensive study of small satellite moon missions: architecture design, electric propulsion system optimization and cost analysis
    (International Astronautical Federation, 2015) Kılıç, Çağrı; Kara, Ozan; PhD Student; Graduate School of Sciences and Engineering; N/A
    This study underlies small satellite architecture optimization by using existing electric propulsion systems for the Moon missions. The estimated objective is imaging of the Moon accompanied with future in-situ applications. Edelbaum's low thrust trajectory transfer with optimal control theory is used to calculate the required AV. During the joumey, 1.5h eclipse duration effects the solar array design. The optimized xenon propeliant density and pressure are 1350 kg m3 and 8.3 MPa within 300K. Two types of optimization process revealed based on hexagonal SC architecture. The iterative method with LEO departured ion thruster has 23 mN with minimum 213 kg total mass. Corresponding SC volume is 0.70 m3, propeliant mass is 64 kg. This scenario cost 108.5M and takes 980 days. Same thruster level for GEO departure case takes 880 days with 58 kg xenon gas.The total cost reduces S2.5M. For HALL engine design, LEO departure case needs 0.8 m3, 247 kg SC including 82 kg xenon. 77 mN thrust operates 208 days towards the Moon that ends up with 121M total cost. If the SC to be launched from GEO, flight time reduces 45 days by consuming 65 kg propeliant. Total SC mass, volume and power values are 230 kg, 0.71 m3 and 1351W which cost 115M. Results are compared with previous Moon or electric propulsion missions such as SMART-1, LADEE, Clementine and Hayabusa. For future applications of small satellites, innovative concepts are envisioned for in-space, Earth-independent exploration and space education.
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    Findings from IAC 2013 Young Professional Workshop: tools and project organization methodologies that can be implemented into the space sector from other industries
    (International Astronautical Federation (IAF), 2014) Stube, Kevin; Wood, Danielle; Svoboda, Jan; Li, Rui; Fuse, Tetsuhito; Kukhta, Andrii; N/A; Kara, Ozan; PhD Student; Graduate School of Sciences and Engineering; N/A
    Applied technologies in space sector are performing complicated and challenging projects in comparison other industries. This complexity in the space sector requires new alternatives for business management and project development. Therefore, management strategies in an organization directly affect the project achievements. Project applications, improvement of economic earnings, relations among people in an organization, mentorships, motivation factors and international activities are other significant issues which are really crucial for space sector. To discuss these important issues, we were one of five groups at International Astronautical Congress, Young Professional Workshop in Beijing, 20th September 2013. Our relevant group topic was "What tools and project organization methodologies have been and can be implemented into the space sector from other industries and the YPs' experience (e.g. software, automotive)?". As a group we have met several times prior to the workshop. Many ideas are emerged in consequence of meetings. Pre-meeting report helped us to prepare individual materials as members thru the workshop. These different reflections were: (1) agile software and engineering issues, (2) process improvement techniques and learning from manufacturing by multiple copies of the same space platform, (3) social activities of organizations for the internal motivation, (4) TRL improvement, (5) project management and system engineering certification the examples from NASA APPEL and Aerospace Corporation, (6) technology transfer among sectors just as military-space and biology-space, (7) Experience assessment of JAXA, (8) software tools that are being used across industries. During the workshop, we simplified these findings and made the final presentation. In addition, preliminary survey questions are listed and determined after the workshop. Finally, common grounds in our final report are summarized as (1) Software development tools, (2) Process improvement techniques, (3) Project management, system engineering education and certification, (4) Company organization structures and (5) Social Activities to improve sector interest. In the final report, group recommendations are given for the each topic and presented to the IAF YP Committee.
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    Testing N2O/CO2 oxidizer mixtures with paraffin based μaluminum fuels for Mars Ascent Vehicles
    (American Institute of Aeronautics and Astronautics Inc, AIAA, 2019) Karakaş, Hakkı; Department of Mechanical Engineering; N/A; Karabeyoğlu, Mustafa Arif; Kara, Ozan; Faculty Member; PhD Student; Department of Mechanical Engineering; College of Engineering; Graduate School of Sciences and Engineering; 114595; N/A
    The objective of this research is to perform experimental test of a hybrid rocket motor by using N2O/CO2 mixture as the oxidizer and paraffin wax as fuel with the addition of metallic powders such as micron size aluminum and magnesium. The impact of 3-micron size aluminum on key performance parameters such as specific impulse (Isp), regression rate (r), and combustion efficiency (ηcomb) has been studied experimentally using a lab scale hybrid motor with 70 mm grain length and 30 mm outer grain diameter. Thermochemical performance of the various propellants studied in this paper are evaluated using NASA’s Chemical Equilibrium Analysis (CEA) software. Numerous tests are performed with N2 O/CO2 mixtures as the oxidizer. CO2 as a saturated liquid is mixed with liquid N2 O between 8 to 30% by mass in order to measure the motor performance characteristics such as average regression rate, r and combustion efficiency, ηcomb. Experiments were performed in the blowdown mode using the self-pressurizing capability of the mixed oxidizer around 45-50 bar. Chamber pressure of the hybrid motor was in the 15-30 bar range. Successful ignition and motor operation of the mixed oxidizer is achieved all the way up to 22% CO2 in the mixture. Initial conclusion from this study indicate that mixing CO2 with N2 O is a viable method of burning CO2 in a practical rocket system for Mars missions.
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    IAC-15-B4.8 emerging small satellite operations in Turkey: interplanetary mission infrastructure and benefits in the space sector
    (International Astronautical Federation, 2015) Kılıç, Çağrı; Kara, Ozan; PhD Student; Graduate School of Sciences and Engineering; N/A
    Next step to keep pace with the rapidly developing area of space technology. The results and benefits of this case study may serve to the developing space awareness and space plans of Turkey. This paper presents the emerging subsystem technologies that are planning to be used for interplanetary small satellite missions. In addition to create an interplanetary mission infrastructure, proposed small satellite Moon mission case requires more than S100M including launch, operation and development costs. Therefore Turkey should create a concrete roadmap including international collaborations to accomplish the Moon missions. Organizational challenges, educational benefits and outcomes for the space sector are also discussed. In addition, collaboration among universities, government and the private sector is a crucial point which impress (1) project based university education, (2) social media, (3) press and information activities such as TV programs and news, (4) long-Term internship opportunities, (5) relations between students and young professionals, (6) leadership and knowledge management, and (7) public outreach activities to foster space in the society.,Turkey is in the stage of developing, producing and operating communication satellites, Earth observation satellites and scientific CubeSat itself. The space road map of Turkey describes that a variety of spacecraft systems shall be tested for upcoming space events. Moreover, Turkey intends to have own launch systems in the future. Most of the developed subsystems are ready to flight, but some of them may be scalable for small satellites. In order to estimate the needs of satisfied future missions and show the benefits of small satellites, an interplanetary mission would be the ,.
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    Communication architecture and international policy recommendations enabling the development of global cubesat space networks
    (International Astronautical Federation, 2015) Brunner, Melanie; Birkeland, Roger; Schor, Dario; Yaǧlıoǧlu, Burak; Smith, Thomas; Hornig, Andreas; Kara, Ozan; PhD Student; Graduate School of Sciences and Engineering; N/A
    Emerging technologies of CubeSat communication and navigation systems enable new approaches such as larger bandwidths, spectrum and security decrement and high speed communications. In order to create a vantage point, young professionals and students from the four corners of the earth had performed a comprehensive study at the 2014 Space Generation Congress in Toronto, Canada under "CubeSat Swarms Communication Networks and Policy Challenges" working group. While potential possibilities are endless for the structure of Cubesat networks, decisions made amongst the group were based on existing technologies and guidelines. Therefore, the working group discussed (1) short and long term technical challenges (2) policy requirements, (3) radio communication bandwidth limitations, (4) data collection and transmission regulations and (5) the standardization of the CubeSat communication system. Technical challenges for small satellite missions involve limitations of link budgets, the size of the déployable high gain antennas, optical and laser communication and the restriction of the link budget due to the interferences. In addition, policy issues have immaturities for frequency allocation and registration complimenting the short lifespan of CubeSats. The standardization of mission operations enables a space communication network architecture that of which is similar to the internet, incorporated into CubeSat Swarms. The group suggests a CubeSat network system architecture including inter-swarm and intra-swarm constellations, optical and laser communications and delay-tolerant networks (DTN). The proposed CubeSat communication network also consists of inter-swarm constellation communications along with intra-swarm constellations sustained through four different basic data links, a mother-daughter satellite framework, and net-neutrality throughout the network. In the meantime, policy regulation recommendations allow global communication by reducing data downlink time. Governments, as well as service providers, treat all data used online the same regardless of its origins, platform, and users. The standardization of the CubeSat network system was formed by operator expectations for high downlink speeds, equal priority for data transfers, and streamlined registrations. The simplified registration process for CubeSat-Swarms is more efficient by establishing new baseline legal framework, rules, and standards. This would help all users and operators in this sector, including entrepreneurs, licensing bodies, and end-users. Saving time for everyone while achieving maximum efficiency, utilization of the time and results are the end result of proposed system architecture by the working group.