Students for the Exploration and Development of Space. San José State University Chapter Sponsor Information

Transcription

1 Students for the Exploration and Development of Space San José State University Chapter Sponsor Information

2 Table of Contents What is SEDS... 1 SEDS at SJSU... 1 Active Projects and Competitions... University Student Rocketry Competition... FAR-Mars Hyperion Rocket FAR-Mars Mission Parameters... 3 FAR-Mars Safety Requirements... 3 Hyperion Preliminary Technical Specifications... Airframe... Combustion Chamber... Tanks and Plumbing... Nozzle Sponsorship... Sponsor benefits... Sponsor packages Testimonials... 8 Contact Us... 9

3 What is SEDS Students for the Exploration and Development of Space (SEDS) is a 501(c)3 non-profit organization that empowers young people to participate and make an impact in space exploration. SEDS was founded as a chapter-based organization in 1980 at MIT by Peter Diamandis, at Princeton by Scott Scharfman, and at Yale by Richard Sorkin. The largest student-run space organization in the world, SEDS consists of an international community of high school, undergraduate, and graduate students from a diverse range of educational backgrounds. SEDS has established chapters throughout the world in over two dozen countries. SEDS at SJSU Building on the success of Leon-1 and other past projects, SEDS at SJSU s primary focus has progressed to the complete development of a liquid bipropellant rocket. Upon its completion, this rocket, named Hyperion, will be launched in the national FAR-Mars competition in Doing so will signify the first time such an endeavor has been attempted in SJSU s history. In addition to academic and technical projects, SEDS at SJSU continues to invest significant time in community outreach, sharing our passion for rocketry at such events as the 2016 Plasma Sciences Expo, the 2017 Silicon Valley Comic Con, and the 2017 An Evening With NASA event hosted by the Alum Rock School District. SEDS at San José State University (SJSU) was founded in 2014 by Simon Sørensen to promote interest in space and rocketry-related projects among students in the university s Charles W. Davidson College of Engineering. Since then, SEDS at SJSU has provided SJSU students with a variety of opportunities and projects with which to expand their academic and technical backgrounds. These opportunities include designing, building, and launching rockets at multiple solid rocket competitions, participating in outreach events, and conducting liquid propulsion research. In 2015, Leon-1, SJSU s first 3D-printed liquid bipropellant regeneratively-cooled rocket engine, was developed. Designed to be propelled by liquid methane and liquid oxygen, Leon-1 s primary objective was to serve as a proof of concept for application in future Mars return missions. A prototype 3D-printed model was created by SEDS at SJSU, with a static hydro test fire being successfully completed in

4 Active Projects and Competitions University Student Rocketry Competition Coordinated by SEDS-USA, the 2017 University Student Rocketry Competition (USRC) calls upon SEDS chapters across the United States to design, build, and fly a multi-stage solid rocket with a maximum impulse of 640 newton-seconds (N*s) to as high of an altitude as possible. Chapters must submit timely updates, reports, and technical drawings in order to qualify. Team scoring is based on the overall design and manufacturing process of the rocket, as well as its flight performance. The winner will be announced at the SpaceVision 2017 conference November 16-18, As of July 2017, the rocket is under construction. We intend to launch in September 2017 at a yet to be determined site in the San Joaquin Valley. Design Specifications Diameter: 2 1/4 inches Height: /8 inches Loaded mass: 3.3 pounds Stages: 3 Recovery: Black powder parachute deployment per stage Estimated apogee: 7,000 feet Estimated maximum speed: Mach 0.70 FAR-Mars Hyperion Rocket Jointly organized and sponsored by Friends of Amateur Rocketry Inc. (FAR) and the Mars Society, the FAR-Mars competition will award up to $100,000 in engineering-based scholarship funds to the university of the team that can design, build, and launch a liquid methalox-powered rocket to a specified altitude of 45,000 feet. The organizers of FAR-Mars see the competition as an opportunity to spark the interest of university students in advancing the development of the technologies necessary for a successful manned mission to Mars. For SEDS at SJSU to successfully design, build, and launch a methalox-powered rocket from the ground up would not only be an extraordinary milestone for SJSU, but would be an extraordinary accomplishment for the advancement of university rocketry as a whole. Upon the project s completion, our members will have gained substantial knowledge of and experience with the construction and operation of each individual system in a liquid-powered rocket, plus a multitude of other aspects associated with rocketry-based projects, including logistics, organization, and testing. This project will lay the groundwork for future SEDS at SJSU members (and for the aerospace department at SJSU as a whole) to advance toward achieving even more ambitious goals in the future. The contest launch window is from May 5, 2018 through May 13, The rocket of each university team will be launched from the FAR Site launch complex, located north of Edwards Air Force Base in southern California. SEDS at SJSU is currently in the design phase of Hyperion and is seeking funding and manufacturing opportunities to advance into the construction phase. 2

5 FAR-Mars Mission Parameters In order to qualify for the FAR-Mars competition, the following design parameters must be met. The rocket must: 1. Have a total-impulse of less than or equal to 9,208 lb-sec. 2. Utilize a bipropellant engine only (no solid rocket motors). 3. Utilize a dual-deployed parachute recovery, with a drogue parachute being deployed at apogee and a main parachute being deployed below 1,000 feet. 4. Be passively guided, have fixed fins, and launch from a fixed launch rail. 5. Achieve an apogee of exactly 45,000 feet MSL, reaching at least 30,000 feet but not exceeding 50,000 feet. 6. Be successfully recovered with minimal damage to both the rocket and the payload. 7. Carry a 2.2-lb payload that will monitor the rocket s altitude at apogee. FAR-Mars Safety Requirements The following safety requirements must also be met: 1. Propellant and pressurant tanks must be proof tested to 1.5 of operating pressure. 2. The relief valves on the tanks must be rated at 1.25 of operating pressure. 3. Propellants must be filled and drained from the bottom of the rocket. 4. The rocket must be equipped with remote controlled vent valves for the propellant and pressurant tanks, utilizing an electrical, pneumatic, or hydraulic system. 5. The rocket must posses the ability to be depressurized independent of the launch controller, if it is computer controlled. 6. Remote electronic pressure instrumentation for tank pressures must be equipped, such as pressure transducers and telemetry or data acquisition. 7. The rocket must utilize electromechanical or pneumatic release or lift-off pressure umbilicals. 8. Lift-off pull and release of umbilicals must be utilized for remote vents and pressure instrumentation. 9. An electrical ignition with key lock-out on the pad and with the same key lock-out at the main launch controller must be equipped. 3

6 Hyperion Preliminary Technical Specifications Airframe The body tube of the airframe will consist of an internal structure of ribs. These ribs will form the shape of a cage and provide mounting points for internal hardware. When compared to a purely monocoque construction, ribs will provide superior load-bearing capabilities. The cage will be attached to the body tube using rivets; rivets will provide additional drag, which raises the center of pressure and ensures vehicle stability. Preliminary calculations show the empty mass of the body to be 416,506 grams, with the center of gravity (cg) located at 144 inches and the center of pressure (cp) located at 171 inches from the nose. Computational fluid dynamics simulations (CFD) of the airframe are still needed to determine the drag coefficient and pressure distribution over the entire rocket. A preliminary breakdown of each subsystem of the airframe is provided below: Body tube 25.4 cm outer diameter 5.5 m tube height 6061-T6 aluminum body Alodine coating for corrosion resistance Nose cone 25.4 cm maximum outer diameter 50 cm length x1/2 power series Combustion Chamber The architecture for the injection of the cryogenic liquid oxygen and liquid methane will be of the movable pintle type. This injector scheme is known to be extremely stable and is capable of deep throttling; this is achieved by actuating the pintle, which varies the area in which the fuel is allowed to enter the chamber. The injector will be of the oxidizer centered type. This was chosen to reduce the amount of failure modes associated with lean conditions in which combustion instabilities can potentially damage the combustion chamber. With this architecture, the fuel and oxidizer are sent through concentric fuel distribution manifolds and are then routed into the combustion chamber. This injector is composed of four different layers which integrate into each other to form the propellant passages and the distribution manifold. All of these are then bolted together. Concentric brass sealing rings are utilized as an additional sealing surface, as to reduce the potential for catastrophic failure. These four separate layers are designed to be fabricated out of T6061 aluminum using conventional milling processes. The total cost of the injector will vary depending on the manufacturing process and the materials used, both of which are currently being investigated. The cost of 3D printing the injector is additionally being evaluated. Fins 4-fin configuration Clipped delta or tapered design Fins will be modeled as a symmetric airfoil to reduce drag, and will be 3D printed 4

7 Tanks and Plumbing The tank and plumbing assembly represent the majority of the internal structure of the rocket. In addition to the various connections, including valves, pressure regulators, and fuel lines, the assembly itself can be broken down into four main component. These include: A cryogenic oxygen pressure vessel A cryogenic methane pressure vessel A gaseous helium pressure vessel Separation/support frames between each pressure vessel, which house the various pressure sensing/regulating equipment and fuel intake ports The cryogenic pressure vessels are currently designed to be constructed from aluminum and are intended to operate at 500 psi with a safety factor of 1.5. Currently, the plumbing of the system is designed to operate with a ¾ inch inner diameter in order to achieve a minimum mass flow to the nozzle of 2 kg/s. Due to the highly specialized nature of the system, an effective cost estimate will not be achievable until a manufacturer of custom equipment has been decided upon. Nozzle A conical nozzle will be manufactured from stainless steel 310S due, in part, to its high melting point and machinability. Metal spinning is currently being investigated to achieve the desired nozzle contour as spinning requires far less raw material than does conventional milling. A combination of film and radiative cooling are being considered to cool the nozzle and combustion chamber. Thrust and Mass Flow Rates Chamber pressure 300 psi Chamber thrust 5 kn Specific impulse (opt) 275 s Total mass flow rate 1.83 kg/s Oxidizer mass flow rate 1.37 kg/s Fuel mass flow rate 0.46 kg/s Thrust Chamber Geometry with Parabolic Nozzle Dc mm Lc mm Dt mm Le mm De mm Ae/At 6.94 Ac/At 5 Divergence efficiency Drag efficiency Thrust coefficient

8 Sponsorship Sponsor Benefits The members of SEDS at SJSU have continued to push the limits of what is possible, building upon the knowledge and experience gained by each preceding year since our founding. Our ambitions are constrained only by our knowledge and resources, both of which we strive to expand every day. Your contributions to SEDS at SJSU will go directly toward the development of our Hyperion bipropellant rocket being built for the FAR-Mars competition. Upon its completion, this project will stand as the testbed for future versions of better and more-ambitious rockets to be developed by future engineering students. It will be up to them to achieve our ultimate long-term goal of developing the first university-designed orbital CubeSat launch vehicle. However, none of this can be achieved without your help. By sponsoring SEDS at SJSU, you will enable our members to gain hands-on experience in designing, building, and flying a rocket with nearly all essential systems of a space-capable rocket. Additional benefits of sponsorship include: Tax deductible contributions (we are a 501(c)3 non-profit) Visibility of your company to a wide audience Association of your company with supporting higher education Gaining access to students who will soon be prospective employees We thank you for considering our request. All sponsors are welcome to visit us at the SJSU aerospace engineering department to witness the work of your contributions first-hand. 6

9 Sponsor Packages Mercury - up to $500 Your company name/logo on seds-sjsu.org sponsor page and ground support equipment (GSE) Venus - $501-$1,000 Mercury package benefits plus Small logo on rocket Earth - $1,001-$2,000 Venus package benefits plus Upgrade to large company name/logo on seds-sjsu.org sponsor page and small logo on main page Upgrade to medium logo on GSE Upgrade to two small logos on rocket Mars - $2,001-$5,000 Earth package benefits plus Upgrade to medium logo on seds-sjsu.org main page Upgrade to large logo on GSE and medium logo on rocket Jupiter - More than $5,000 Mars package benefits plus Upgrade to large logo on seds-sjsu.org sponsor page and main page Upgrade to large logo on GSE and rocket 7

10 Testimonials A huge part of encouraging investments in science and technology is reaching out and empowering prospective scientists and engineering students. We are proud to count the Students for the Exploration and Development of Space (SEDS) as one of our allies in the fight for space. William Pomerantz Vice President of Special Projects Virgin Galactic Chris Lewicki President and Chief of Engineering Planetary Resources The SEDS movement played a big part in my early life and I encourage any student to get involved in that for sure. I have always been a fan of SEDS and the things the students are trying to accomplish. Ben Brockert CEO Able Space CO. 8

11 Contact Us More Information seds-sjsu.org facebook.com/sedssjsu engineering.sjsu.edu seds.org friendsofamateurrocketry.org/launch_contest.html 9