- The document describes the intern's work testing and integrating sounding rocket payloads at Orbital Sciences Corporation under NASA's Sounding Rocket Operations Contract.
- Key tasks included aiding the testing of payloads through procedures like vibration, bend, and balance testing to ensure durability and mission success.
- The intern also helped design hardware components and gained an understanding of manufacturing processes.
- Overall the internship met the goals of learning about payload integration timelines and systems, and developing mechanical engineering skills.
NAUTILUS-X Future in Space Operations (FISO) Group PresentationA. Rocketeer
Nautilus-X: A presentation at the Future In Space Operations teleconference on Jan 26th 2011, given by Mark Holderman and Edward Henderson of NASA JSC.
Presentation by Dale Thomas (Constellation Program Deputy Manager, NASA) at the Von Braun Memorial Symposium in Huntsville, Alabama, 21 October 2008.
<a href="http://astronautical.org/vonbraun/vonbraun-2008/session2">http://astronautical.org/vonbraun/vonbraun-2008/session2</a>
Experimental study of magnus effect over an aircraft wingeSAT Journals
Abstract We present this paper as an experimental study of employing Magnus Effect in an aircraft wing. The scope and interest of study of Magnus Effect and its application in Aerospace Engineering is widely increasing all over the world to make use of the Magnus Force for enhanced Lift by Drag Ratio. Most of the trials weren't successful due to the heavy Drag Force produced by large cylinders, even though sufficient Lift Force was generated. The main stereotypical apprehension of Magnus Effect is that it could be applied only over symmetrical bodies like a spinning ball(sphere), or a cylinder or a disc. We suggest an idea to be applied differently by maintaining a constant circumferential speed over an airfoil profile. We propose to initiate the project work by considering a symmetrical airfoil and study it’s aerodynamic characteristics and make an attempt in extending it's performing envelope by implementing Magnus Effect. Our intention is to provide the constant circumferential speed over the airfoil skin is by compositing a treadmill like motion contributed by a series of rollers fastened over a chain track and driven by a stepper motor. The Rollers coupled Treadmill spins in a clockwise direction, when air passes over the upper surface of the airfoil, it will be pushed down, due to the energy provided by the treadmill motion imparted to the airflow. This apparently make the air below the airfoil denser and eventually leading to a pressure rise in the lower surface of the airfoil. Consequently, the supplemented acceleration of airflow over the upper surface of the airflow results in a greater pressure difference between both the surfaces of airfoil. Thus we are generating surplus Lift Force and minimize Drag Force by implementing Magnus Effect over the aircraft wing. We term this entire approach as Flo-Lapse. Our Pilot Studies and predictions make it seem that this idea will wide open many avenues for production of augmented Lift/Drag Ratio, wielding of shorter wingspan, probability of initiating a Vertical Take-Off for Unmanned Aerial Vehicles, or production of Lift at Zero Airspeed. A probable condition of the Cruise phase of a flight profile, where in the aircraft is at maximum speed, the incoming airstream can be used to reverse the Flo-Lapse approach and serve the purpose of an energy solution. We suggest that optimising the circumferential speed, we can have better L/D Ratios and delay early stalling of wing. KeyWords:Magnus effect, Treadmill motion, Flo-Lapse, Aerodynamics, L/D ratio & Aircraft wing
NAUTILUS-X Future in Space Operations (FISO) Group PresentationA. Rocketeer
Nautilus-X: A presentation at the Future In Space Operations teleconference on Jan 26th 2011, given by Mark Holderman and Edward Henderson of NASA JSC.
Presentation by Dale Thomas (Constellation Program Deputy Manager, NASA) at the Von Braun Memorial Symposium in Huntsville, Alabama, 21 October 2008.
<a href="http://astronautical.org/vonbraun/vonbraun-2008/session2">http://astronautical.org/vonbraun/vonbraun-2008/session2</a>
Experimental study of magnus effect over an aircraft wingeSAT Journals
Abstract We present this paper as an experimental study of employing Magnus Effect in an aircraft wing. The scope and interest of study of Magnus Effect and its application in Aerospace Engineering is widely increasing all over the world to make use of the Magnus Force for enhanced Lift by Drag Ratio. Most of the trials weren't successful due to the heavy Drag Force produced by large cylinders, even though sufficient Lift Force was generated. The main stereotypical apprehension of Magnus Effect is that it could be applied only over symmetrical bodies like a spinning ball(sphere), or a cylinder or a disc. We suggest an idea to be applied differently by maintaining a constant circumferential speed over an airfoil profile. We propose to initiate the project work by considering a symmetrical airfoil and study it’s aerodynamic characteristics and make an attempt in extending it's performing envelope by implementing Magnus Effect. Our intention is to provide the constant circumferential speed over the airfoil skin is by compositing a treadmill like motion contributed by a series of rollers fastened over a chain track and driven by a stepper motor. The Rollers coupled Treadmill spins in a clockwise direction, when air passes over the upper surface of the airfoil, it will be pushed down, due to the energy provided by the treadmill motion imparted to the airflow. This apparently make the air below the airfoil denser and eventually leading to a pressure rise in the lower surface of the airfoil. Consequently, the supplemented acceleration of airflow over the upper surface of the airflow results in a greater pressure difference between both the surfaces of airfoil. Thus we are generating surplus Lift Force and minimize Drag Force by implementing Magnus Effect over the aircraft wing. We term this entire approach as Flo-Lapse. Our Pilot Studies and predictions make it seem that this idea will wide open many avenues for production of augmented Lift/Drag Ratio, wielding of shorter wingspan, probability of initiating a Vertical Take-Off for Unmanned Aerial Vehicles, or production of Lift at Zero Airspeed. A probable condition of the Cruise phase of a flight profile, where in the aircraft is at maximum speed, the incoming airstream can be used to reverse the Flo-Lapse approach and serve the purpose of an energy solution. We suggest that optimising the circumferential speed, we can have better L/D Ratios and delay early stalling of wing. KeyWords:Magnus effect, Treadmill motion, Flo-Lapse, Aerodynamics, L/D ratio & Aircraft wing
ASSESSMENT OF AIRFRAME OVERLOADS OF AEROBATIC AIRCRAFTIAEME Publication
The paper presents the results of studies of statistical patterns of scattering of
overloads of aerobatic aircraft. The main parameters are the magnitude and repetition of
vertical overloads at the center of gravity for the two loading groups of the aerobatic
aircraft. Based on a statistical analysis of the values of equivalent vertical overloads for
each of the groups, correlation ratios were obtained for equivalent vertical overloads and
their repetition depending on the flight duration of the aircraft. The resulting solutions
allow us to predict the levels of damage occurring to the structure of a particular aircraft
for the total flight duration. Specific examples of comparative calculations of the
equivalent flying hours, as well as integral and differential repetition of aircraft in
formation and lead aircraft are considered.
М.Г.Гоман, А.В.Храмцовский, М.Шапиро «Разработка моделей аэродинамики и моделирование динамики самолета на больших углах атаки», доклад на международной конференции «Тренажерные технологии и обучение», прошедей в ЦАГИ, г.Жуковский, 24-25 мая 2001 г.
M.Goman, A.Khramtsovsky and M.Shapiro "Aerodynamics Modeling and Dynamics Simulation at High Angles of Attack", presentation at the International conference on Simulation Technology & Training held at TsAGI, Zhukovsky (Russia), on 24 May 2001.
ASSESSMENT OF AIRFRAME OVERLOADS OF AEROBATIC AIRCRAFTIAEME Publication
The paper presents the results of studies of statistical patterns of scattering of
overloads of aerobatic aircraft. The main parameters are the magnitude and repetition of
vertical overloads at the center of gravity for the two loading groups of the aerobatic
aircraft. Based on a statistical analysis of the values of equivalent vertical overloads for
each of the groups, correlation ratios were obtained for equivalent vertical overloads and
their repetition depending on the flight duration of the aircraft. The resulting solutions
allow us to predict the levels of damage occurring to the structure of a particular aircraft
for the total flight duration. Specific examples of comparative calculations of the
equivalent flying hours, as well as integral and differential repetition of aircraft in
formation and lead aircraft are considered.
М.Г.Гоман, А.В.Храмцовский, М.Шапиро «Разработка моделей аэродинамики и моделирование динамики самолета на больших углах атаки», доклад на международной конференции «Тренажерные технологии и обучение», прошедей в ЦАГИ, г.Жуковский, 24-25 мая 2001 г.
M.Goman, A.Khramtsovsky and M.Shapiro "Aerodynamics Modeling and Dynamics Simulation at High Angles of Attack", presentation at the International conference on Simulation Technology & Training held at TsAGI, Zhukovsky (Russia), on 24 May 2001.
Aerospace structure and engineering unitsVera414786
Aerospace structure and engineering units encompass disciplines vital to aircraft and spacecraft design, ensuring structural integrity, performance, and safety. These units specialize in materials science, aerodynamics, propulsion, and systems engineering. Engineers collaborate to create lightweight yet robust structures capable of withstanding extreme environments, while optimizing fuel efficiency and maneuverability. Their innovations drive advancements in aviation and space exploration.
Presentation delivered by Dr. Ron Sega, Director of Graduate Programs in Systems Engineering at Colorado State University, to INCOSE Colorado Front Range Chapter on Nov 21, 2013 and Dec 10, 2013.
Abstract:
A brief history of the evolution of systems engineering will be presented; reviewing its origins in the aerospace industry to the current applicability of systems engineering principles to contemporary, complex areas such as energy systems. Previous practical case-study experience in the civil space and government defense sectors will be outlined to provide a backdrop for the current systems engineering educational activities at Colorado State University where they are applying the systems engineering approach to various complex systems through graduate degree program offerings and increased research activities. A customer-driven Master of Engineering (M.E.) in Systems Engineering program and a Certificate of Completion program in Systems Engineering from the Fort Collins campus began in the Fall of 2008.
Eit norsk romfartseventyr
Fortelle bakgrunnen og historien til selskapet og gründeren, kvifor og korleis det blei stifta. Litt om utviklinga til selskapet, teamet bak og om produkta det jobbes med. Fortelja om korleis dei har jobba so langt, korleis det er under endring, kva dei gjer vidare no, kven dei samarbeider med. Vil fortelja om partnerselskap med Rocketstar LLC frå New York som utvikler rakettmotorer.
Kristoffer Liland er direktør for Ripple Aerospace AS, han er gründer av selskapet og har ledet selskapet frå si byrjing i januar 2014 til i dag. Iløpet av denne tida har han samla eit team på 14 menneske som har hjulpet frivillig å byggja eit selskap i ein industri utanom det vanlege. Kristoffer fullfører for augeblikket mastergrad i innovasjon og kunnskapsutvikling.
Long duration, lighter than air, stratospheric airships might offer a unique and compelling platform for a wide range of Earth science and astrophysics. There is also great commercial opportunity in stratospheric, stationary platforms that can remain aloft for months or even years at a time. A 2013 Keck Institute for Space Studies (KISS) series of workshops (http://kiss.caltech.edu/programs.html#airships) brought together a number of scientists and aerospace industry professionals to discuss this potential. The report from that study (http://kiss.caltech.edu/papers/airships/papers/airships.pdf) identified the need for a graduated approach to developing the necessary technology and recommended a funded challenge as one way to meet this need. The NASA Centennial Challenge office funded development of the Airships-20-20-20 Challenge, but NASA ultimately decided not to pursue the Challenge. I will describe the science enabled by airships and the proposed Challenge.
This short Course provides to University Aerospace Engineering students with a Panoramic Instruction on the Project Management (PM), System Engineering (SE) and Integrated Logistic Support (ILS) Processes which are Fundamental to the Success of Aerospace Projects together with some hints for Professional Development in these Fields.
The Cource also introduces the PM, SE and ILS Basic Activities, Organizational Aspects, Main Processes, Methods, and Procedures.
1. Orbital Sciences Corporation (OSC) – Rensselaer Polytechnic Institute (RPI) – Cooperative Education Work Report
Rensselaer Polytechnic Institute i 2/9/2015
Cooperative Education Project Work Report
Rensselaer Polytechnic Institute
Testing and Integration of Sounding Rocket Payloads Overview
Duration: 11AUG14 – 19DEC14
Ray Parker1
Rensselaer Polytechnic Institute, Bachelor of Science, Chemical Engineering
Orbital Sciences Corporation, Wallops Flight Facility, Virginia 23337
Mentors: Robert Marshall2
, Philip Cathell3
1
Testing and Environmental Engineering Co-op, Chemical Engineering, Rensselaer Polytechnic Institute.
2
Testing and Environmental Engineering Lab Supervisor.
3
Mechanical Engineering Lead, Mechanical Engineering, Virginia Tech, Old Dominion University.
2. Orbital Sciences Corporation (OSC) – Rensselaer Polytechnic Institute (RPI) – Cooperative Education Work Report
Rensselaer Polytechnic Institute Page 1 12/10/2014
I. Overview
Orbital Sciences Corporation (Orbital ATK) is an industry leader in small and medium class space and rocket
systems. Orbital also supports human space flight by supplying commercial cargo resupply services for the
International Space Station using our new Antares® rocket and Cygnus™ cargo logistics spacecraft. In addition,
Orbital provides full service engineering, production and technical services for NASA, DoD, commercial and
academic space programs. Orbital also holds various commercial contracts, such as the NASA’s Commercial
Resupply Services (CRS) Contract and NASA’s Sounding Rocket Operations Contract (NSROC II).
In 2010, Orbital Sciences Corporation was selected by the National Aeronautics and Space Administration
(NASA) as the prime contractor role for the NASA Sounding Rocket Operations Contract II (NSROC II) program.
Under the NSROC II program, which is primarily centered at the NASA/GSFC, Wallops Flight Facility in Virginia,
Orbital’s Technical Services Division (TSD) is responsible for planning, coordinating, and carrying out sounding
rocket missions from locations in the U.S. and around the world. In addition, Orbital TSD is working with NASA to
develop and implement advanced sounding rocket capabilities to be used on the program. Sounding rockets are
smaller-sized launch vehicles that conduct suborbital missions for high-altitude scientific and atmospheric research.
Co-op Abstract. Under direct supervision by a senior testing and environmental technician or engineer,
perform specific engineering tasks of an analysis or test nature in a specialized engineering fields. Will
work to test and integrate sounding rocket payloads and various components and systems of spaceflight
sounding rocket technologies. Will collaborate with the Mechanical Engineering Department in the
Technical Services Division to help design and model hardware for future testing or integration. Apply
theoretical knowledge and engineering techniques to the solution of analytical engineering problems.
A. Key Deliverables at Project Completion:
1. Develop understandings of sounding rocket integration and testing timelines.
2. Aid in the design and modeling of multiple hardware components for the Mechanical Engineering
Department and develop an understanding of hardware manufacturing and assembly.
3. Develop a broad understanding of sounding rocket payload systems and suggestion modifications
and troubleshoot problems.
B. Key Learning:
1. Sounding rocket integration and testing timeline development.
2. Gain understanding of hardware and components that make up sounding rockets.
3. Understand manufacturing process and mechanical integration limitation.
The majority of sounding rocket flight hardware that is used at Wallops Flight Facility is tested in the Testing and
Environmental (T&E) Laboratory, run by Orbital Sciences. The lab consists of machinery and electrical devices that
are used to balance, vibrate, deploy, and bend test all sounding rocket payloads, and can also perform magnetic
calibration, and mass property analytics. The T&E Laboratory is a subsidiary of the Mechanical Engineering
Department which is overlooked by the Engineering Directorate underneath NSROC II Operations Management.
All sounding rocket payloads consist of scientific instruments or telescope, as directed by NASA. Each year
applications are sent out to academic institutions across the globe, of whom submit proposals with certain specialized
experiments designed to study sub-orbital space and high-atmospheric environments. Accepted proposals are then laid
out into the launch manifest. Launch can be achieved in as little as six months from design conception. Different
rocket payloads are split into different group classes with each payload being assigned a mechanical technician,
electrical technician, power engineering, electrical engineer, mechanical engineer, altitude control systems (ACS)
engineer and mission manager. This team takes the entire payload from the design stage to the final launch.
Scientific instrumentation and telescopes are the two main payloads launched by sounding rockets. Since sounding
rockets are much more simple than traditional medium-class orbital launch vehicles, they have a very quick turnaround
time (sometimes less than a month), much less expensive (sometimes as low as a million dollars), and allows for
repeatability of experiments and launches. When NASA puts a telescope (such as the Hubble Space Telescope, The
Great Observatories, etc.) into orbit, they require calibration and setting adjustments before they can begin taking
observations. In order to do this, NASA uses sounding rockets with identical lenses to put it into space momentarily,
allowing them to fine tune the settings of the satellite telescopes.
3. Orbital Sciences Corporation (OSC) – Rensselaer Polytechnic Institute (RPI) – Cooperative Education Work Report
Rensselaer Polytechnic Institute Page 2 12/10/2014
Most payloads consists of sub-payloads, stowaway booms and ampules that take sensitive measurements in high
atmospheric or space environments. These payloads are released by the launch vehicle at certain altitudes or variable
timing and are shot off by rockets, deployed by springs or pyrotechnics, or extended off the main body of the payload.
As an intern, some tasks and responsibilities that were required were to help in critical lift operations of various
flight hardware, including payloads/payload sections, palettes, vacuum chambers, various experiments and other
machinery. Additionally, torqueing joints and bolts, troubleshooting various problems within mechanical and
electrical systems, and helping to design and model various hardware components in Solidworks was done. The largest
responsibility expected of interns was aiding in the moving and testing of 10+ customized sounding rocket payloads,
through various test articles outlined below.
Sounding Rocket Flight Qualification Testing Concepts
Static and Dynamic Balance Testing
• During launch and takeoff, the launch vehicle spins in a counter-clockwise direction at a frequency between
two to five hertz, in order to maintain balance stability and directional accuracy during launch. Payloads must
be balanced beforehand in order for ACS and flight dynamic guidance to be maintained and ensure flight
mission assurance. Payload is place on a spin table with lead weights added on to pre-determined planes.
Sine and Random Vibration Testing
• In order to ensure payload durability during flight, the payload and components of the payload, need to be
tested beforehand on vibration machines. The payload is plugged into ground support equipment and then
vibrated with sine or random profiles. If no mechanical systems fail and ground support reads steadily and
reliably, the payload passes. Tests are usually over-simulated and natural frequencies may affect testing.
Bend Testing
• During flight, the payload is subjected to multiple high intensity bending moments, friction, compression and
tension forces. In order to ensure durability and mission assurance, V-Band joints are measured for
compliance. Testing consists of setting up dial indicators and bending by pushing and pulling via pneumatic
piston and measured by a load cell.
Mass Property Measurements Testing
• In order for ACS to perform properly, and flight performance predictions to be accurate, several mass
property measurements are needed, including pitch, roll and center of gravity of the payload. In order to do
so, each component and flight/launch configuration are needed to be measured for the Flight Performance
Department to ensure mission assurance during flight, as well as for ACS engineering. Each configuration of
the rocket is placed on a floating table with bearings that measure forces and moments for each configuration.
Operational Spin and Deployment Testing
• During or near apogee, the payload’s scientific objective usually occurs, which involves deployment of sub-
payloads/doors, science booms, nosecones and other devices. In order to ensure flight performance, testing
is done to ensure that pyrotechnics fire, releasing mechanisms without fail.
Magnetic Calibration Testing
• When the payload is guided to the correct trajectory or scientific instruments are determined by the Earth’s
magnetic field, the magnetometer of the payload must be calibrated using a specialized structure in order to
null out all other magnetic materials of the payload.
Ogive Recovery System Assembly
The O-give Recovery System
Assembly (ORSA), which includes a
parachute, is housed in the nosecone.
Experiments/Instruments
Provided by the researcher,
often from a University or
Government agency, to
collect data on the target
Attitude Control Systems (ACS)
Small jets expel gas to rotate the
payload in the desired direction. All
three axes, pitch, yaw and roll are
controlled.
Telemetry System
The TM transmits science
and vehicle data to a ground
station.
S19 Boost Guidance System
Most telescope payloads are launched
from sites with land impact areas and
are recoverable.
Aft Transition Section
The aft transition section is
used to mate two sections of
different diameters.
Table 1. Description of the main components of Sounding Rockets.
Figure 1. Model of a Black Brant IX Sounding Rocket
4. Orbital Sciences Corporation (OSC) – Rensselaer Polytechnic Institute (RPI) – Cooperative Education Work Report
Rensselaer Polytechnic Institute Page 3 12/10/2014
Centrifugal Testing
• Electronics and other payload components are tested using a medium size centrifuge. The centrifuge spins
for various RPMs for certain time intervals while the component is monitored to ensure flight durability.
Corona Testing
• Corona testing is done to verify transmitters and other electronics do not experience electrical arcing, or
coronal events, when they pass through the coronal region, typically 80,000 to 120,000 feet.
The goal for the duration of this co-op rotation was to help integrate and test sounding rockets and other various
types of space hardware in a safe and effective manner. Other objectives include helping the Mechanical Engineering
Department with various CAD and modeling projects.
II. Evaluation
In comparison to the job description and my expectations at OSC, I was pleased. I expected to be able to;
Develop understandings of sounding rocket integration and testing timelines.
Aid in the design and modeling of hardware components for the Mechanical Engineering Department.
Develop an understanding of hardware manufacturing and assembly.
Develop a broad understanding of sounding rocket payload systems.
Sounding rocket integration and testing timeline development.
All of my goals have been met, besides being a contributor to a publication while on co-op; this may happen later
on. My mentor and all of the staff at Orbital and other contracting companies and organizations were very friendly
and accepting. I did not have many problems with people there. In addition to this, my colleagues that I share
laboratory and testing space with, have been very helpful in answering my questions and helping me to understand
certain rules and concepts. They have all given me suggestions on how to do things differently to improve my skills
as well as given me conceptual advice on what could be done more effectively while running tests and other concepts
in the Testing and Environmental Engineering Lab.
T&E Engineering Section Concepts
• Knowledgeable w/ various tools/machines
• Construction and basic ME fundamentals
• Vibration, Bend, and Balance test analysis
• Critical Lift Operations experience
• Fixture Installation
Software
• Solidworks 2014
• Adept for Solidworks
Mechanical Engineering Concepts
• Solidworks Modeling skills
• Solidworks Drawings and drafting
• Work document compilation
• Data mining for launch log book
Miscellaneous Concepts
• Electrical Engineering walk down
• Altitude Control System walk down
• Machine Shop walk down
No patents or honors/rewards were received. Various presentations may represent my work in the
future. Hardware will be in outer space though! Rensselaer’s Co-op Program has been very insightful
and has been a great learning experience. I am thankful for the opportunity to be able to go on co-op.
My only comment to make the co-op program better would be to have the monthly emails sent out on
time at the beginning of the month. I cannot think of
anything different.
Overall, my experience at Orbital Sciences
Corporation and NASA has been very interesting and
useful to my future. I have never thought that I would
be able to have a clear understanding of rockets or
launch vehicles work, or the basic process behind how
they are made and integrated. In addition to gaining an
understanding of the process, I’ve been able to help
accomplish important objectives with my colleagues
including successfully sending a couple of the rockets
that I worked on into space.Figure 2. Conde 52.001
after Deployment Testing Figure 3. Mechanical Technician and T&E Intern
unscrewing a Radax joint on Collins 46.009.