Massachusetts Institute of Technology Department of Aeronautics and Astronautics Cambridge, MA 02139 16.03/16.04 Unified Engineering III, IV Spring 2004 Problem Set 11 Name: Due Date: 4/27/04 Time Spent (min) CP13-14 P5 P6 P7 S13 Study Time Announcements: Q5S will be on Friday, April 23.C13-14 The problems in this problem set cover lectures C13 and C14 1. a. Define a robust algorithm to carry out integer division using repeated subtraction. Your algorithm accepts two integers and returns the quotient and the remainder. Hint: What are the preconditions and postconditions of your algorithm? b. Implement your algorithm as an Ada95 program, using exception handling to provide robustness. Turn in a hard copy of your algorithm and code listing, and an electronic copy of your code. 2. a. What is the cyclomatic complexity of the code fragment shown below? loop exit when Flag := True; if A < 100 and B > 200 then if A > 50 then Sum := Sum +2; else Sum := Sum +1; end if; else if B < 300 then Sum:= Sum -1; else Sum := Sum -2; end if; end if; end loop; Hint: Draw the control flow graph b. What is the minimum number of test cases needed to test the fragment of code shown below? Justify your answer. if A < 100 and B > 200 then if A > 50 then Sum := Sum +2; else Sum := Sum +1; end if; else if B < 300 then Sum:= Sum -1; else Sum := Sum -2; end if;end if;Unified Engineering Spring Term 2004 Problem P5. (Propulsion) (L.O. D) For a future high performance military fighter, with a wing loading (W/S) of 3500 N/m2, does it require does it require a higher ratio of thrust to weight to i) Perform a steady, constant altitude, constant speed 5g combat turn at M=0.9, or ii) Accelerate from M=0.5 to M=2 in 20 seconds? (Note, for a 5g turn the load factor, n=5, is the acceleration perpendicular to the wing. For n=1, L=W.) Assume all the maneuvers occur at an altitude of 11km where the pressure is 22.6 kPa, the temperature is 217 K, the density is 0.34 kg/m3, and the speed of sound is 295 m/s. Assume the coefficient of lift takes the form WhereCURRENTFUTURE0.050.040.030.020.010.25 0.5 0.75 1 1.251.51.7520CDOCURRENTFUTURE0.050.040.030.020.010.25 0.5 0.75 1 1.251.51.7520KFlight Mach numberUnified Engineering Spring Term 2004 Problem P6. (Propulsion) (L.O. E) Evaluate the performance of a single stage sounding rocket to be used for atmospheric research. You are given the following design parameters: Combustion chamber temperature = 4000 K Combustion chamber pressure = 5 MPa Nozzle throat area = 0.0006 m2 Nozzle exit area = 0.01 m2 Propellant mass = 35 kg Total mass at takeoff = 50 kg Gas constant = 300 J/kg-K Ratio of specific heats = 1.35 a) What are the Isp and take-off thrust for this rocket? b) Assuming the rocket is launched vertically, and neglecting drag, how high will it go?[Note: To solve this problem you will have to use relationships from thermodynamics (steady flow energy equation) and fluid mechanics (compressible flow relations). These can all be found in the Unified Propulsion notes (Chapters V and VI). Most of the relations are written in terms of the exit Mach number, Me. To find this you will have to try several values of Me in the relationship for A*/Ae until the equation gives you the same ratio as given in the problem statement.]Unified Engineering Spring Term 2004 Problem P7. (Propulsion) (L.O. F) For this problem, consider the design of a turbojet engine for a supersonic aircraft. Assume the engine uses conventional hydrocarbon fuels (h = 42.8 MJ/kg and that γ = 1.4 and cp = 1000 J/(kg-K). There are two important material temperature limits for gas turbine engines. The first is the temperature at the inlet to the turbine (TT4) which may range as high as 2000K. The second is the temperature at the exit of the compressor (TT3) which is typically limited to less than 1000K. [The turbine can be run in conditions well above the melting temperature of the metal because air from the exit of the compressor is used to "cool" the turbine. This air is pumped through the turbine blades and forced out small holes in the surface forming a protective film (see picture below from Rolls-Royce, The Jet Engine). Due to their very small size, it is much harder to cool the compressor blades, so no active cooling is currently used.] Reproduced with the kind permission of Rolls-Royce plc. Copyright Rolls-Royce plc 1986. Used with permission.a) For a turbojet engine with a compressor pressure ratio of 25, and a turbine inlet temperature of 1800K, under what flight conditions (Mach number) would the compressor inlet temperature limit be exceeded? Consider performance at sea-level (Tatm=300K) and at 10km (Tatm = 216K) b) At a constant flight Mach number of 1.2, how much do the thermal and propulsive efficiency change between altitudes of sea-level and 10km? Explain this behavior. c) If you were forced to reduce the turbine inlet temperature to 1400K because the turbine durability group was having difficulty designing the blades to withstand temperatures of 1800K, how would it impact the performance of the vehicle (consider M=1.2 and 10km only)?Unified Engineering II Spring 2004 Problem S13 (Signals and Systems) In class, you learned about a smoother, with transfer function 2 G1(s) = −a (s − a)(s + a) The smoother is an example of a low-pass filter, which means that it tends to attenuate high-frequency sine waves, but “pass” low-frequency sine waves. Unfortunately, the smoother is non-causal, which means that it can’t be implemented in real time. A similar causal low-pass filter is 2aG2(s) = (s + a)2 In this problem, you will compare these two low-pass filters, to see how they affect sinusoidal inputs. Consider an input signal u(t) = cos ωt 1. Find the transfer function, G1(jω), as a function of frequency, ω. 2. Since the transfer function is complex, it can b e represented as G1(jω) = A1(ω)ejφ1(ω) where the amplitude of the transfer function is A1(ω), and the phase of the trasnfer function is φ1(ω). Find A1(ω) and φ1(ω). 3. Find the transfer function, G2(jω), as a function of frequency, ω, as well as A2(ω) and φ2(ω). 4. For the input u(t) above, show that the output of the system G1 is y1(t) = A1(ω) cos(ωt + φ1(ω)) and do likewise for system G2. 5. A1 and A2 determine how much the magnitude of the
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