assignment2 - Space Flight Dynamics and Propulsion Systems...

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Space Flight Dynamics and Propulsion Systems MECH 6251/498D Department of Mechanical and Industrial Engineering Concordia University Assignment #2 Basic Space Flight Dynamics Due: Tuesday, October 26, 2010 Instructions: Answer all questions; ensure your homework assignment is completed properly. Please clearly write down your name and student ID. List all necessary assumptions and the models you used. Show all calculations and units. Textbook: G.P. Sutton, O. Biblarz, Rocket Propulsion Elements, 7 th edition, Wiley Interscience. Problem 1: For a satellite cruising in a circular orbit at an altitude of 500 km, determine the period of revolution, the flight speed, and the energy expended to bring a unit mass into this orbit. Problem 2: Determine the payload for a single-stage vehicle in Example 4-3. Compare it with the two-stage vehicle. Problem 3: Use the data given in Example 4-3, except that the payload is fixed at 250 kg and the Δ u is not given but has to be determined for both cases, namely equal-sized stages and stages of equal mass ratio. What can be concluded from these results and the results in the example? Problem 4: An airplane that is flying horizontally at a 7000 m altitude, at a speed of 700 km/hr over flat country, releases an unguided missile with four small tail fins for flight stability. Determine the impact location (relative to the release point as projected onto the earth surface), the impact angle, and the time from release to target. Assume that the drag causes an average of about 8% reduction in flight velocities. Problem 5: A two stage rocket has equal effective exhaust velocities C 1 = C 2 = 4000 m/s and structural coefficient ε 1 = 2 = 0.2 for each stage. The Δ V required to reach the desired orbit is 11,000 m/s. Assume no drag or gravitational losses. a) How much of the initial mass is payload? b) Show how the payload ratio varies with the number of stages.
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Problem 6: Consider a two-stage launch vehicle delivering a 15,000-kg payload (satellite) to low earth orbit. The vehicle has the following characteristics: Stage 1: I sp = 275s ζ = 0.95 Stage 2: I sp = 460s ζ = 0.88 After a thorough mission budget analysis that includes necessary Δ v to compensate gravity and drag losses, it is determined that the total budget needed equals 13,215 m/s. Determine the
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This note was uploaded on 12/12/2010 for the course MECH 351 taught by Professor Chekhov during the Fall '10 term at Concordia Canada.

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assignment2 - Space Flight Dynamics and Propulsion Systems...

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