скачать Appendix A Homework Problems/Classroom Exercises
These homework problems/classroom exercises are designed to complement the problems at the end of each chapter. The problems at the end of the chapters can be posed as verbal questions to the students, providing an indication that the students were listening to the lecture. The following homework problems/classroom exercises are designed provide a more indepth learning reinforcement. Points associated with each homework problem/classroom exercise indicate the degree of difficulty, as a consideration in assigning the student’s grade for the problem.
(20 points). Chapter I (Introduction/Key Drivers in the Design Process). Compare measures of merit for the following alternative concepts to destroy threat ballistic missiles during their boost phase: Spacebased interceptors Spacebased lasers Airborne laser Airlaunched interceptors Shiplaunched interceptors Groundlaunched interceptors
(10 points). Chapter I (Introduction/Key Drivers in the Design Process). Develop a stateoftheart comparison of tactical missile characteristics with the current stateoftheart (SOTA) of UCAVs. Show examples where missiles are driving technology. Also show examples where the missile is not driving technology.
(10 points). Chapter I (Introduction/Key Drivers in the Design Process). For the examples shown of airlaunched and surfacelaunched missiles, which have been applied to more than one mission?
(20 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). Based on the example, calculate radar seeker detection range and 3dB beam width for a target cross section s = 1 m^{2}, mmW transmitter frequency f = 35 x 10^{9} Hz, transmitted power P_{t} = 100 W, and antenna diameter d = 4 in.
(20 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). Based on the example, calculate imaging IR seeker detection range and instantaneous field of view for rainfall at 4 mm/hr and optics diameter d_{o} = 2 in.
(10 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). Based on the example, calculate the first mode body bending frequency for a missile weight of 367 lb.
(10 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). In the bodyflare example, what is the required diameter of the flare to provide neutral stability at launch?
(20 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). What are the strengths and weaknesses of the China SD10/PL12 tail planform?
(10 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). Calculate the rocket baseline wing normal force coefficient (C_{N})_{Wing} at Mach 1.1, d = 13 deg, a = 9 deg.
(40 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). Calculate C_{D0}, C_{N}, and C_{m} for the ramjet baseline at Mach 2.5 endofcruise and Mach 4.0 endofcruise. Compare with the aerodynamic data of Chapter VII. Why is it difficult to accurately predict (or even obtain accurate data) for C_{m}?
(20 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). What are the dynamic pressures at cruise (L/D)_{max} for a circular cross section missile and an a/b = 2 lifting body cross section missile if the weight W = 500 lb, cross sectional reference area S_{Ref} = 0.5 ft^{2}, lengthtodiameter ratio l/d = 10, and zerolift drag coefficient C_{D0} = 0.2?
(20 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). Calculate hinge moment for the ramjet baseline at the initiation of a pitchover dive. Flight conditions are Mach 4.0, h = 80k ft altitude, endofcruise, d_{e} = 30 deg control deflection, and a = a_{max} angle of attack.
(20 points). Chapter II (Aerodynamic Considerations in Tactical Missile Design). Using the approach of the text example, calculate the required tail area of the rocket baseline to provide neutral static stability at launch.
(20 points). Chapter III (Propulsion Considerations in Tactical Missile Design). Using the approach of the text example, compare compressor exit temperature at Mach number M = 3, altitude h = sea level with the Mach 2, h = 60k ft compressor temperature result of the text example.
(20 points). Chapter III (Propulsion Considerations in Tactical Missile Design). For the turbojet text example (T_{4} = 3000 R, A_{0} = 114 in^{2}, RJ5 fuel, M = 2, h = 60k ft) show the impact on maximum ideal thrust and specific impulse of +/ 10% uncertainty in specific heat ratio.
(30 points). Chapter III (Propulsion Considerations in Tactical Missile Design). For an ideal turbojet, calculate thrust, specific impulse, equivalence ratio, and nozzle exit area for the following conditions/assumptions: liquid hydrocarbon fuel, free stream Mach number = 2, angle of attack = 0 deg, altitude = 60k ft, compressor pressure ratio for maximum thrust, turbine maximum temperature = 2000 R, and inlet capture area = 114 in^{2}. Compare with the text example.
(20 points). Chapter III (Propulsion Considerations in Tactical Missile Design). Using the approach of the text example of a centrifugal compressor, what is the rotation rate if the impeller tip Mach number M_{ImpellerTip} = 1.2?
(20 points). Chapter III (Propulsion Considerations in Tactical Missile Design). For an axial compressor stage with a pressure coefficient c_{p} = 0.6 and rotor entrance local Mach number M_{entrance} = 1.4, what is stage pressure ratio p_{exit}/p_{entrannce}?
(10 points). Chapter III (Propulsion Considerations in Tactical Missile Design). For an assumed axial compressor single stage pressure ratio p_{exit}/p_{entrannce }= 2, what is the overall compressor pressure ratio p_{3}/p_{2 }of a fourstage compressor?
(20 points). Chapter III (Propulsion Considerations in Tactical Missile Design). For an assumed turbine entrance temperature T_{4} = 4000R, compare the thrust T and specific impulse I_{SP} with the example in the text (T_{4} = 3000R).
(20 points). Chapter III (Propulsion Considerations in Tactical Missile Design). At what combustion temperature does dissociation of water become a significant contributor to real gas effects?
(30 points). Chapter III (Propulsion Considerations in Tactical Missile Design). Calculate the thrust, specific impulse, equivalence ratio, and nozzle exit area of an ideal ramjet for the following conditions/assumptions: liquid hydrocarbon fuel, free stream Mach number = 2.5, angle of attack = 0 deg, altitude = 60k ft, ramjet combustor maximum temperature 4000 R, and inlet capture area = 114 in^{2}. Compare with the ramjet baseline data of Chapter VII.
(40 points). Chapter III (Propulsion Considerations in Tactical Missile Design). The corrected specific impulse of a ramjet is a function of the individual efficiencies of the combustor, nozzle, and inlet. Assuming that the driving parameter for the efficiencies is the total pressure recovery, derive an expression for correcting theoretical specific impulse.
(100+ points). Chapter III (Propulsion Considerations in Tactical Missile Design). Derive the onedimensional equations for thrust and specific impulse for an ideal scramjet. Calculate thrust, specific impulse, combustor area, and nozzle exit area for the following conditions/assumptions: hydrocarbon fuel, free stream Mach number = 6.5, angle of attack = 0 deg, altitude = 100k ft, Mach 3 initial combustion, thermal choking limit, combustor maximum temperature = 4000 R, and inlet capture area = 114 in^{2}. How is a scramjet similar to a ramjet? How is it different?
(10 points). Chapter III (Propulsion Considerations in Tactical Missile Design). In the example, what is the inlet start Mach number if the inlet throat area A_{IT} = 0.4 ft^{2}? Is there a problem in having a large area for the inlet throat?
(30 points). Chapter III (Propulsion Considerations in Tactical Missile Design). Calculate the total pressure ratios entering the combustor for the ramjet baseline cruising at Mach 2.5, sea level and at Mach 4.0, 80k ft. The inlet is a mixed compression type with a total of four compressions prior to the normal shock, consisting of 1) the shock wave on the conical nose, followed by 2) the shock wave on the ramp leading to the cowl, followed by 3) the shock wave on the cowl, and finally 4) a series of nearly isentropic internal contraction shock waves leading to a normal shock. Compare with the maximum available total pressure ratio from four optimum compressions.
(100+ points). Chapter III (Propulsion Considerations in Tactical Missile Design). Derive the onedimensional equations for thrust and specific impulse for an ideal ducted rocket. Calculate thrust, specific impulse, equivalence ratio, inlet throat area, and diffuser exit area for the following conditions/assumptions: 40% boron fuel, 8% aluminum fuel, 27% binder fuel, 25% ammonium perchlorate oxidizer, free stream Mach number = 4, angle of attack = 0 deg, altitude = 80k ft, gas generator pressure = 1000 psi, combustor maximum temperature = 4000 R, combustor area = 287 in^{2}, and inlet capture area = 114 in^{2}.
(10 points). Chapter III (Propulsion Considerations in Tactical Missile Design). Compute the turbojet specific impulse I_{SP} of a 40% JP10/60% boron carbide slurry fuel that has a heating value H_{f} = 23,820 BTU/lbm. Compare with the text example (RJ5 fuel with H_{f} = 14,525 BTU/lbm).
(20 points). Chapter III (Propulsion Considerations in Tactical Missile Design). Calculate the rocket baseline thrust at altitudes of sea level, 20k ft, and 50k ft. Compare results with Chapter VII.
(20 points). Chapter III (Propulsion Considerations in Tactical Missile Design). If the rocket baseline throat area were reduced by 50%, with the propellant, burn area, and nozzle expansion ratio the same, what would be the resulting boost/sustain chamber pressure, thrust, specific impulse, and propellant weight flow rate?
(30 points). Chapter III (Propulsion Considerations in Tactical Missile Design). Assume a propellant burn rate exponent n = 0.9. Also assume the same nominal propellant burn rate r_{pc=1000 psi}, propellant characteristic velocity c*, propellant density r, nozzle geometry, and thrust profile as the rocket baseline. Calculate the chamber pressures and burn areas for boost/sustain. Compare with the rocket baseline chamber pressures and burn areas.
(20 points). Chapter IV (Weight Considerations in Tactical Missile Design). The baseline rocket propellant grain is a slotted tube with a propellant volumetric efficiency of 90%. For the same volume of the motor case, what is the boost propellant weight and endofboost velocity for a grain with a propellant volumetric efficiency of 80%?
(20 points). Chapter IV (Weight Considerations in Tactical Missile Design). A typical strategic ballistic missile motor has a much larger propellant fraction than a typical tactical ballistic missile, resulting in longer range. Assume a strategic ballistic missile has a typical inert subsystems weight fraction of 0.1 of the propellant weight. Also assume a payload weight of 1000 lb. Neglecting drag and the curvature of the earth, calculate the maximum range of a threestage 100,000 lb missile with specific impulse of I_{SP} = 250 s (Minutemantype solid propellant). As a comparison, calculate the maximum range of a twostage 100,000 lb missile with specific impulse of I_{SP} = 300 s (Titantype liquid propellant). Discuss the tradeoff of the number of stages vs type of propellant/specific impulse.
(20 points). Chapter IV (Weight Considerations in Tactical Missile Design). Calculate the centerofgravity and pitch/yaw momentofinertia of the rocket baseline if the propellant density were increased by 50%, assuming the same weights for subsystems (e.g., motor case) in Chapter VII. Compare with the data in Chapter VII.
(30 points). Chapter IV (Weight Considerations in Tactical Missile Design). Based on an average heat transfer coefficient, estimate the rocket baseline airframe temperature at the end of the flight trajectory example of Chapter 7.1 (Mach 0.8 launch at 20k ft altitude, 3.26 s boost, 10.86 s sustain, 9.85 s coast).
(30 points). Chapter IV (Weight Considerations in Tactical Missile Design). Calculate the ramjet baseline radome internal wall temperature and surface wall temperature after 10 s flight at Mach 3, sea level.
(30 points). Chapter IV (Weight Considerations in Tactical Missile Design). Estimate the ramjet baseline internal insulation required thickness to maintain warhead temperature less than 160° F for 10 m time of flight at Mach 4/80k ft.
(40 points). Chapter IV (Weight Considerations in Tactical Missile Design). For the ramjet baseline, compare the weight of an aluminum airframe with external microquartz insulation to that of the baseline uninsulated titanium airframe.
(30 points). Chapter IV (Weight Considerations in Tactical Missile Design). Using the baseline ramjet inlet geometry and material data of Chapter VII, estimate the required inlet thickness and the required inlet weight based on an inlet start at Mach 2.5, sea level altitude. Compare with the inlet weight of Chapter VII.
(20 points). Chapter IV (Weight Considerations in Tactical Missile Design). Calculate motor case weight for the rocket baseline if the case were titanium, with a forward dome ellipse ratio of 3 and a cylindrical cross section aftbody. Compare with the example calculation for a steel motor case and the data in Chapter VII.
(20 points). Chapter IV (Weight Considerations in Tactical Missile Design). Calculate required tail thickness and the resulting weight of the rocket baseline tail surfaces. Assume a flight condition of Mach 2, altitude = 20k ft, motor burnout, angle of attack = 9.4 deg, and an ultimate stress factor of safety = 1.5. Compare result with the data of Chapter VII.
(20 points). Chapter IV (Weight Considerations in Tactical Missile Design). Calculate radome weight for the rocket baseline if the radome were silicon nitride with an optimum transmission thickness. Compare with the example calculation for a pyroceram radome and the data in Chapter VII.
(20 points). Chapter IV (Weight Considerations in Tactical Missile Design). Calculate the required thickness and the resulting weight of the rocket baseline radome to withstand the load from Mach 2, 20k ft altitude, and angle of attack = 9.4 deg for an ultimate stress factor of safety = 1.5. Compare with the Chapter IV example of optimum transmission thickness and the data of Chapter VII.
(10 points). Chapter IV (Weight Considerations in Tactical Missile Design). Calculate actuation system weight for the rocket baseline if the actuators were electromechanical. Compare with the text example calculation and the data in Chapter VII.
(10 points). Chapter V (Flight Performance Considerations in Tactical Missile Design). Using the Breguet range equation, calculate the Mach 2.5, sea level cruise range of the ramjet baseline, using data from Chapter VII. Compare with the range in Chapter VII.
(10 points). Chapter V (Flight Performance Considerations in Tactical Missile Design). Calculate the steady state rate of climb and the climb flight path angle for the ramjet baseline at Mach 2.5, sea level, maximum thrust. Use data from Chapter VII.
(20 points). Chapter V (Flight Performance Considerations in Tactical Missile Design). Calculate turn radius and turn rate of the ramjet baseline for horizontal and pitchover turns at Mach 4, h = 80k ft altitude, end of cruise, angle of attack a = 15 deg. Use data from Chapter VII.
(20 points). Chapter V (Flight Performance Considerations in Tactical Missile Design). Calculate the velocity and range of the rocket baseline after 10 s of coast at a flight path angle of +30 deg for an initial velocity of 2151 ft/s and an initial altitude of 20k ft.
(20 points). Chapter V (Flight Performance Considerations in Tactical Missile Design). Calculate booster burnout Mach number and ramjet acceleration capability following booster burnout at sea level for the ramjet baseline. Compare with the performance data of Chapter VII.
(10 points). Chapter V (Flight Performance Considerations in Tactical Missile Design). Assuming a nonaccelerating target at Mach 0.8, h = 20k ft altitude, and 30 deg aspect, what is the required missile lead angle for a constant bearing Mach 3 flyout at h = 20k ft?
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). For fog cover of 20 m height over the target, what is the required lookdown angle to achieve less than 5 dB attenuation of a passive IR seeker?
(20 points). Chapter VI (Measures of Merit and Launch Platform Integration). Compare the performance of an MWIR seeker vs an LWIR seeker using the data of the text example, but with a target temperature of 500 K.
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). Assume a missile with a velocity V = 300 m/s, strapdown seeker with a field of view = 20 deg, and seeker detection range R_{D} = 1 km. Assume that an offboard sensor (e.g., UAV) provides the missile with a target location error TLE = 10 m. Assume the target has a velocity V_{T} = 10 m/s, laterally to the flight path of the missile. If the update time from the offboard sensor is equal to the target latency time (i.e., t_{Update} = t_{Latency}), what is the required update time from the offboard sensor?
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). For the text example rocket baseline warhead, what is the blast overpressure Dp at a distance from the center of explosion of r = 5 ft and an altitude h = sea level?
(20 points). Chapter VI (Measures of Merit and Launch Platform Integration). Calculate the maximum miss distance requirement of a 5 lb warhead with C/M = 1 to achieve a lethality of 0.5 for a typical air target vulnerability (overpressure Dp = 330 psi, fragments impact energy = 130k ftlb/ft^{2}).
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). Assume a revised rocket baseline warhead that has reduced collateral damage, with a warhead metal case mass M_{m} = 0.4 slug. For a warhead charge mass M_{c} = 1.207 slug, what is the total kinetic energy KE of the warhead?
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). Compare the text example of penetration through concrete with the penetration of the same penetrator through granite of density r = 0.0897 lb/in^{3} and ultimate strength s = 20,000 psi.
(30 points). Chapter VI (Measures of Merit and Launch Platform Integration). Assume a missile defense interceptor has a time constant of t = 0.05 s, an effective navigation ratio of N’ = 4, and the target glint noise bandwidth is B = 2 Hz. What is the miss distance from glint for the imaging IR seeker example in Chapter II?
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). In the text example for survivability through high altitude flight and low radar cross section (RCS), if the flight altitude h = 80k ft, what is the required RCS to avoid detection by a threat radar that has a transmitted power P_{t} = 10^{6} W and a wavelength l = 0.01 m?
(20 points). Chapter VI (Measures of Merit and Launch Platform Integration). Calculate the frontal RCS of the rocket baseline.
(20 points). Chapter VI (Measures of Merit and Launch Platform Integration). Using data from the example in the text, calculate the frontal radiant intensity of the ramjet baseline for long duration flight at Mach 2.5/sea level.
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). Using data from the example in the text, calculate the frontal IR detection range if the if the radiant intensity is reduced by 50%.
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). Using data from the text example for reduced frontal RCS, calculate detection range and exposure time for +/ 4 dB, 1 uncertainty in RCS.
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). Assuming a reliability of 98%, what is the missile circular error probable (CEP) that is required to provide a 95% probability of kill for a warhead lethal radius of 5 ft?
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). Calculate a typical system reliability of a missile that combines the autopilot, navigation sensors and computer as a single subsystem and has no seeker. Compare with the text example.
(10 points). Chapter VI (Measures of Merit and Launch Platform Integration). For a seven year development program of a 300 lb missile with a learning curve of 0.7, calculate the following for a total buy of 10,000 missiles: development cost total production cost average unit production cost unit production cost of missile number 10,000
(20 points). Chapter VI (Measures of Merit and Launch Platform Integration). Using the rocket baseline motor example of the text, what is the inner surface temperature of the motor if the initial temperature is 70 deg F and it is subjected to an ambient temperature of – 60 deg F for 1 h?
(20 points). Chapter VI (Measures of Merit and Launch Platform Integration). Using the rocket baseline motor example of the text, what is the maximum temperature of a titanium motor case?
(10 points). Chapter VII (Sizing Examples). What are the visual detection and recognition ranges of a small UCAV target that has a presented area A_{P} = 10 ft^{2} and a contrast C_{T} = 0.1?
(30 points). Chapter VII (Sizing Examples). Compare the rocket motor baseline motor case (see Chapter VII) with a higher strength motor case made of 4130 heat treated steel with an ultimate tensile strength of 250,000 psi. Discuss design considerations such as brittleness, fracture sensitivity, material cost, motor case manufacturing cost (e.g., machining, welding), required case thickness, and required case weight. Is a higher strength 4130 motor case a good idea?
(60 points). Chapter VII (Sizing Examples). Using the rocket baseline airtoair standoff range example, compare the results based on the 1DOF analytical equations of motion of Chapter V with results from a numerical solution of the time marching equations of motion.
(30 points). Chapter VII (Sizing Examples). For the rocket baseline, what is the required wing area for 40 g maneuverability at Mach 3, burnout, and 20k ft altitude?
(30 points). Chapter VII (Sizing Examples). Conduct a Design of Experiment (DOE) to define the wind tunnel model configuration alternatives for the harmonized rocket baseline. Specify the nose, body, wing, and tail geometry options for a light weight/small miss distance missile.
(40 points). Chapter VII (Sizing Examples). For the ramjet baseline, compare the inlet mass flow rate at Mach 2.5, sea level altitude with the mass flow rate at Mach 4.0, 80k ft altitude.
(10 points). Chapter VII (Sizing Examples). Based on the ramjet baseline data in Chapter VII and the Breguet range equation, calculate the cruise range for Mach 4/80k ft altitude. Assume that all of the fuel is available for cruise.
(80 points). Chapter VII (Sizing Examples). Size an extended range ramjet that has 30% greater range than the ramjet baseline. Assume launch at Mach 0.8/sea level with cruise at Mach 2.3/sea level. Size the design by extending the missile length while maintaining constant missile diameter and static margin. Compare the new body length, tail area, launch weight, and the individual weights of fuel, fuel tank, boost propellant, booster case, and tails with the ramjet baseline.
(20 points). Chapter VII (Sizing Examples). Calculate the frontal radar cross section RCS of the turbojet baseline.
(30 points). Chapter VII (Sizing Examples). Calculate the Mach M = 0.4 zerolift drag coefficient C_{D0, }normal force coefficient C_{N}, and lifttodrag ratio L/D of the turbojet baseline. Compare with the data of Chapter VII.
(40 points). Chapter VII (Sizing Examples). From the Request for Proposal given in Appendix B, develop a House of Quality Customer Requirements/Most Important Requirements (MIRs) and an Importance Rating of the MIRs. Expand the rows and columns of the House of Quality. Give rationale for your selections and values.
(20 points). Chapter VII (Sizing Examples). For the soda straw rocket baseline, specify a tail geometry and area that provides neutral static stability.
(30 points). Chapter VII (Sizing Examples). For the soda straw rocket baseline, what is the zerolift drag coefficient C_{D0 }if we assume a laminar boundary layer?
(80 points). Chapter VII (Sizing Examples). Design, build, and fly a soda straw rocket that is optimized for maximum range at an assumed launch condition of 30 psi launch pressure. The rocket design must be compatible with a launch platform constraint of a “Super Jumbo” straw launcher of 0.25 in diameter and 6 in available launch length. You may base your rocket on the materials provided in class, or you may use your own materials as long as you satisfy the launch straw constraint (0.25 in diameter, 6 in available length). Provide the following information for your design: Geometric, weight, centerofgravity, aerodynamic, and thrusttime characteristics and the rationale for their values. Dimensioned drawing Velocity during boost as a function of time and distance. Postboost flight trajectory height and horizontal range as a function of time. Effect of +/ 10% (1s) prediction uncertainty of the drag coefficient on horizontal range. Effect of +/ 10 ft/s (1s) horizontal head/tail wind velocity on horizontal range. Comparison of predicted range with flight test
(10 points). Chapter VII (Sizing Examples). For the soda straw rocket house of quality of the text example, what is relative ranking of engineering design parameters if the customer emphasis is changed to 70% emphasis on light weight/30% emphasis on long range?
(40 points). Chapter VIII (Development Process). For the ASALM PTV flight envelope boundaries, what are the values of the booster transition thrust – drag, high dynamic pressure, high aero heating, high L/D cruise, and low dynamic pressure.
(20 points). Chapter VIII (Development Process). For the ramjet baseline, compute the Mach number when thrust equals drag at an altitude h = 40k ft if the equivalence ratio f = 1. Compare with the ASALM PTV flight test result.
(20 points). Chapter VIII (Development Process). Give an example of the typical sequence of events for flight trajectory modeling development of a typical tactical missile system.
(20 points). Chapter VIII (Development Process). Give an example of the typical sequence of events for propulsion system development of a typical tactical missile system.
(20 points). Chapter VIII (Development Process). Give an example of the typical sequence of events for structure development of a typical tactical missile system.
(30 points). Chapter VIII (Development Process). Show a history of the events in stateoftheart SOTA advancement in the reduction in weight of synthetic aperture radar (SAR).
(30 points). Chapter VIII (Development Process). Show a history of the events in stateoftheart SOTA advancement in the size of missile infrared seeker focal plane array.
(30 points). Chapter VIII (Development Process). Show a history of the events in stateoftheart SOTA advancements in energy per weight and power per weight of missile power supply.
(60 points). Appendix B. Develop a technology roadmap for the Request for Proposal given in Appendix B.
(60 points). CD Design Case Studies. Select one of the design case study presentations from the CD included with the textbook and conduct a review of the design case study. Provide a scoring/evaluation of the presentation, including rationale. The review should address the areas of technical content (35% weighting), organization and presentation (20% weighting), originality (20% weighting), and practical application and feasibility (25% weighting).
Appendix B Example of Request for Proposal

 Fax 123 456 7890  ^ Team Missile Design Competition MultiMission Cruise Missile (MMCM) Design and Analysis Study Sponsored by the Missile Systems Technical Committee (MSTC) Revised October 15, 2003 Table of Contents INTRODUCTION ^ SCORING/EVALUATION AWARD ADDITIONAL INFORMATION AND CLARRIFICATIONS
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