Conference Session

Topics Related to Assessments and Outcomes

Collection

2007 Annual Conference & Exposition

Authors

James Helbling, Embry-Riddle Aeronautical University; David Lanning, Embry-Riddle Aeronautical University; Ron Madler, Embry-Riddle Aeronautical University; Darin Marriott, Embry-Riddle Aeronautical University; Karl Siebold, Embry-Riddle Aeronautical University

Tagged Divisions

Aerospace

dedicated for use by students involved with undergraduate researchprojects. The building’s floor plan is shown in Figure 1, below. Figure 1: AXFAB Building Floor Plan Page 12.826.4As shown in this figure, all laboratories are located only steps away from the fabrication suite toallow students easy access to the tools necessary to produce the subject of their experiments.Also shown in the figure is the 3600 square foot Service Yard adjacent to the Machine Shop andStructures Lab. This outdoor area allows for storage of equipment and material and facilitatesthe importation of large items to those locations.Three photographs of

Conference Session

Topics Related to Assessments and Outcomes

Collection

2007 Annual Conference & Exposition

Authors

Robert Frederick, Mechanical and Aeropace Engineering; Rebekah Frederick, Homewood Academy for Girls

Tagged Divisions

Aerospace

University of Alabama in Huntsville (UAH)1 and Ecole Superieuredes Techniques Aeronautiques et de Construction (ESTACA) a college in France.2 Theobjective of the course is to integrate the technical skills learned at the undergraduate level in adesign project. The actual project is a “nesting” of several classes. The core students come fromthe senior-level Aerospace and Mechanical Engineering design classes. The students aregrouped into multi-disciplinary teams that also can include electrical, computer, or industrialengineers and English students.3 Each team member has a designated technical/support role onthe team. This allowed individual members to understand their responsibilities, receive trainingin their area, and gain focused access to

Conference Session

Undergraduate Spacecraft Design I

Collection

2007 Annual Conference & Exposition

Authors

Thomas Liu, University of Michigan; Christopher Deline, University of Michigan; Rafael Ramos, University of Michigan; Steven Sandoval, University of Michigan; Ashley Smetana, University of Michigan; Yang Li, University of Michigan; Richard Redick, University of Michigan; Julie Bellerose, University of Michigan; Peter Washabaugh, University of Michigan; Bogdan Oaida, University of Michigan; Brian Gilchrist, University of Michigan; Nilton Renno, University of Michigan

Tagged Divisions

Aerospace

address the challenges facinga student-run lab. Case studies of projects are also used to highlight important lessons learnedover the years.1 What is S3FL?Since 1998, the Student Space Systems Fabrication Laboratory (S3FL) at the University ofMichigan’s College of Engineering has combined a formal design process with student creativityand spontaneity to train and provide students with opportunities for research in space systemsdesign and development.1 Each year, S3FL involves over a hundred undergraduate and graduatestudents in realistic and intensive design-build-test activities ranging from balloon payloads tomicrogravity experiments to nanosatellites. By participating in the end-to-end development ofcomplete space systems, students acquire

Conference Session

Undergraduate Spacecraft Design I

Collection

2007 Annual Conference & Exposition

Authors

Ashley Smetana, University of Michigan; Suzanne Lessack, University of Michigan; Thomas Liu, University of Michigan; Rebecca Wind, University of Michigan; William Woelk, University of Michigan; Theresa Biehle, University of Michigan; Laura Dionisio, Loyola Marymount University; Rafael Ramos, University of Michigan; Nathaniel Gallaher, University of Michigan; Katie Thorne, Michigan Technological University; Brian Gilchrist, University of Michigan; Peter Washabaugh, University of Michigan

Tagged Divisions

Aerospace

sensor technologies. The main purposeof TSATT is to develop a way to decrease the risk normally incurred while testing these sensortechnologies and algorithms in flight as well as to develop ground observation capabilities ofclose-flying spacecraft. The design of TSATT consists of two end masses – connected by a tetherdeveloped by Tethers Unlimited, Inc. – that are initially joined together. Upon separation, theend masses are free to move apart from each other as the tether is deployed up to 1 km.Deployment initiates the beginning of data collection from the two end masses. Once a set timeis reached, the tether begins to retract, and data is collected as the two end masses are pulledtogether.Since separation is a possible point of failure on the

Conference Session

Undergraduate Spacecraft Design I

Collection

2007 Annual Conference & Exposition

Authors

Michael McGrath, University of Colorado at Boulder

Tagged Divisions

Aerospace

AC 2007-1340: EVOLUTION OF A CLASS IN SPACECRAFT DESIGN:EXPERIENCES GAINED OVER A DECADE OF TEACHINGMichael McGrath, University of Colorado at Boulder Page 12.703.1© American Society for Engineering Education, 2007 1/25/2007 4:25:00 PMEvolution of a Class in Spacecraft Design: Experiences Gained over a Decadeof TeachingAbstract.Spacecraft Design at the University of Colorado at Boulder is a project-based approach to thedesign of an unmanned spacecraft mission, focused at the senior and graduate level. Teams ofstudents produce a Concept Study Document and series of oral presentations for a hypotheticalNASA

Conference Session

Teaching Topics in Aircraft Manufacturing

Collection

2007 Annual Conference & Exposition

Authors

Ronald Sterkenburg, Purdue University; Sergey Dubikovsky, Purdue University

Tagged Divisions

Aerospace

new skillset to design and manufacture an aluminum alloy formed wing rib using CNC equipment andconventional sheet metal equipment. The wing rib was chosen as a project because on modernaircraft these parts are modeled and CNC machined (Figure 1). For this project students designeda basic wing shape using commercial available software based on assigned parameters like grossweight, cruise speed, and stall speed. Students will select an airfoil for a small piston poweredUltra Light aircraft with a maximum gross weight of 500 pounds, cruise speed of 150 mph, and astall speed of 50 mph. Page 12.978.3There are plenty of commercial off the shelf

Conference Session

Topics Related to Assessments and Outcomes

Collection

2007 Annual Conference & Exposition

Authors

Mark Maughmer, Pennsylvania State University; Kathy Schmidt, University of Texas-Austin

Tagged Divisions

Aerospace

demoralized since many seemto have some difficulty with the seemingly simple task of basic sketching. If thefeedback, however, is all positive then it is not helpful and the students do notreceive explicit guidance on how to improve. While the exercises can certainlyvary a great deal and accomplish the same results, a typical set is outlined below.Exercise 1: Sketching an AirfoilDifferent types of airfoil are briefly described and sketched. These include aclassical NACA (NACA 4415, for example) four-digit section, a laminar flowairfoil (NACA 63-415, Wortmann FX 67-150, etc.), a supercritical airfoil(Whitcomb), and a thin supersonic section (NACA 66-009). The steps are thendescribed as to how, for example, the laminar-flow airfoil is sketched

Conference Session

Undergraduate Aerospace Design – General Topics

Collection

2007 Annual Conference & Exposition

Authors

Karl Siebold, Embry-Riddle Aeronautical University; James Helbling, Embry-Riddle Aeronautical University; Darin Marriott, Embry-Riddle Aeronautical University; Mischa Kim, Embry-Riddle Aeronautical University

Tagged Divisions

Aerospace

/Project Lifecycle /1/. Since the curriculum leads into the Page 12.575.2capstone design sequence, a schematic displaying the different project phases with its corresponding classes is shown in the following table /Table 1/. It is clear that credit hour constraints make it difficult to take all in depth classes before the actual design sequence starts. The simulation concept understanding and simulation building process is shown in the last row. FORMULATIONPhases Pre-Phase A Phase A Phase B Advanced Studies Preliminary Analysis

Conference Session

Teaching Topics in Aircraft Manufacturing

Collection

2007 Annual Conference & Exposition

Authors

Swami Karunamoorthy, St. Louis University; H. Mallikarjuna, St. Louis University

Tagged Divisions

Aerospace

some students have very good grasp of these principles,majority of the class have trouble in application of these concepts. The computation oftransfer functions in analytical form requires the knowledge of partial fractions andLaplace Transforms. Manual computation of transfer functions is rather laborious foreven some simple systems. MATLAB software can be easily used for this purpose and itis efficient in applying Laplace Transform in order to find the transfer function.Rules for Modeling 1. Degrees of Freedom: (a) Every degree of freedom [Xi] is associated with a mass [Mi]; (b) A degree of freedom without a real mass is associated with a virtual mass of zero magnitude (or zero-mass). 2. Stiffness Matrix: (a) Diagonal elements

Conference Session

Undergraduate Spacecraft Design II

Collection

2007 Annual Conference & Exposition

Authors

Lawrence Boyer, St. Louis University; Krishnaswamy Ravindra, St. Louis University; John George, St. Louis University; Kyle Mitchell, St. Louis University

Tagged Divisions

Aerospace

an opportunity to the students to use the fundamental knowledge theyhave gained in mathematics and physics in their freshman year. At Parks College the projectsassigned may include the design, build and test of a glider for a specified set of constraints, or theassembly and test of a model rocket (Figure 1) for a specified set of constraints. In this paper, thedetails of the model rocket project are provided. The constraint is that the payload mass must bedetermined such that the rocket altitude is 100 feet. This allows the test firing of the rocket in arelatively small area such as a baseball field. Wadding Figure 1 Diagram of a typical model rocketIt is noted that model

Conference Session

Undergraduate Aerospace Design – General Topics

Collection

2007 Annual Conference & Exposition

Authors

Daniel Biezad, California Polytechnic State University; Joon Kim, Lockheed Aircraft Co

Tagged Divisions

Aerospace

Education Annual Conference * Exposition Copyright © 2005, American Society for Engineering Education they relate to flight, and a systems view of planning, task scheduling, documentation, and testing. Students completing this course will be able to: (1) explain fundamental manufacturing and fabrication techniques used for aircraft made of metal or of composites; (2) implement the types of fabrication processes used by industry and by small aircraft builders; (3) document their own progress using established procedures; (4) demonstrate expertise in reading aircraft plans and construction diagrams, especially as the systems of the aircraft come together; (5) analyze how modifications and errors impact fabrication time and cost

Conference Session

Undergraduate Spacecraft Design II

Collection

2007 Annual Conference & Exposition

Authors

Robert Brown, U.S. Air Force Academy; Lynnane George, U.S. Air Force Academy

Tagged Divisions

Aerospace

ascenario, which allows them to visually verify the result of their calculations (See Figure 1 and2). The goal of these labs is not to teach the students to become STK experts, but merely toallow them to visually see orbits and ground tracks, thus giving them a better understanding ofmore difficult concepts introduced in class. Page 12.509.6 1. Select Propagate 2. Set the Trip time to the first value calculated in 1.e of Mission Planning Figure 1: Sample

Conference Session

Undergraduate Aerospace Design – General Topics

Collection

2007 Annual Conference & Exposition

Authors

M. Christopher Cotting, Virginia Tech; Leigh McCue, Virginia Tech; Wayne Durham, Virginia Tech

Tagged Divisions

Aerospace

retired its A-6E’s and replaced them with F/A-18’s. The transfer was made possible withthe help and support of research sponsors at Naval Air Systems Command Headquarters and atthe Manned Flight Simulator branch of the Naval Air Warfare Center, Patuxent River, Maryland.A diagram of the simulation system can be found in Figure 1. The left (pilot’s) seat of the trainercockpit represents the cockpit of a A-6E Intruder. The right seat has been modified toaccommodate either an instructor or a flight test engineer with a computer driven CRT that canbe custom configured with instrumentation as desired. The simulation computer has beenconverted to a SGI Origin 2000 computer. This allows the simulation of many different aircraftmodels, from a Cessna 152

Conference Session

Undergraduate Spacecraft Design II

Collection

2007 Annual Conference & Exposition

Authors

Charles Bittle, University of North Texas; Mitty Plummer, University of North Texas

Tagged Divisions

Aerospace

launch of themissile. An iterative solution is developed to calculate each time and eccentric anomaly for eachnew azimuth and elevation on the trajectory. The trajectory of the missile as seen by theobservation site is plotted.TrajectoryFrom a military point of view, a ballistic missile has the sole objective of carrying an explosivewarhead from the launch point to the impact point or target. Both points are on the trajectoryplane and surface of the Earth. A typical trajectory of a ballistic missile is shown in Figure 1.The trajectory is divided into powered, ballistic, and re-entry flights. During powered flight, themissile goes from a static position to dynamic flight and is propelled beyond the appreciableatmosphere. A propulsion system

Conference Session

Undergraduate Aerospace Design – General Topics

Collection

2007 Annual Conference & Exposition

Authors

Charles Eastlake, Embry-Riddle Aeronautical University; Magdy Attia, Embry-Riddle Aeronautical University

Tagged Divisions

Aerospace

, and peer evaluation of each individual’s productive participationin the project), report format and drawing format. The SOW is supplemented by 16 Worddocuments, each of which defines a deliverable task in greater detail. The 16 tasks are:Task 1 – Conceptual design, by each individual studentTask 2 – Oral presentation of individual conceptual designsTask 3 – Second iteration of the conceptual design selected by each design teamTask 4 – Wing designTask 5 – Fuselage layoutTask 6 – Engine installation and propeller noiseTask 7 – Landing gear layoutTask 8 – Structural conceptTask 9 – Weight and balanceTask 10 – Stability and controlTask 11 – Inboard profile drawingTask 12 – Drag and performance

Conference Session

Teaching Topics in Aircraft Manufacturing

Collection

2007 Annual Conference & Exposition

Authors

Sergey Dubikovsky, Purdue University; Ronald Sterkenburg, Purdue University

Tagged Divisions

Aerospace

the highly technical positions in modernmanufacturing6. Figure 1: Testing of structural riveted joints on tension.The third component of the course is testing. As was mentioned before, students test severalstructural riveted joints on tension, and hardness testing of several samples of aluminum strips isperformed to learn about the effects of heat treatment. "Dog bones" samples are relatively simpleto make, but the effects of the property changes of aluminum alloy after heat treatment is not soeasy to explain. Students learn about different types of heat treatment, but most importantly, they Page 12.1166.4also discover

Conference Session

Undergraduate Spacecraft Design II

Collection

2007 Annual Conference & Exposition

Authors

David Miller, University of Oklahoma; Yunjun Xu, University of Oklahoma

Tagged Divisions

Aerospace

Page 12.1468.3 Figure 1: Preliminary Design of Science Roverinspect the lower stage of the LEM (Lunar Excursion Module) and perform ananalysis of the aging the materials of the LEM had experienced. The class createda preliminary design of a rover to travel from the SLS landing site a short distanceto an Apollo landing site and perform a materials survey. (see Figure 1).The only Apollo site that was formally with regards to materials and surface finishis Apollo 17. For those reasons, Apollo 17 is the primary site for the SLS explo-ration. This selection had the additional advantage that Lunakhod 2 is less than150km almost due North of this site. The class decided that a secondary sprintrover (see Figure 2) should be created to