PFR - Aerospace Engineering Sciences Senior Design Projects ...

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Project Final Report – CUDBF April 30 th , 2009 ASEN 4028: Aerospace Senior Projects 7.0 Project Feasibility and Risk Assessment Author: Eric Hall Co-Author: Dan Colwell 7.1 Project Feasibility 7.1.1 Weight Budget and Feasibility The estimated weight of the aircraft was determined from the sum of the weights of all the systems components. From the combination of the system weights stated earlier, the estimated maximum takeoff weight of the aircraft is approximately 15 pounds. This weight reasonably satisfies the aircraft maximum weight requirement (0.PRJ.5). This weight estimation can be further validated by comparison to similar aircraft. A database of aircraft from the 2007-2008 DBF competition shows an average payload weight to empty aircraft weight ratio (W PL /W E ) of 1.27. The 2008-2009 competition payload weight of 8.33 pounds determines the aircraft should have an empty weight of approximately 6.54 pounds. This estimate also satisfies 0.PRJ.5. 7.1.2 Cost Feasibility In order to guarantee the project’s material costs are less than the project’s budget, a base estimate of the prices of each component was collected. The estimated budget for construction and travel can be observed in Section 14.4. The estimated budget for the project is $12,130. Based on the funding provided by the Aerospace Engineering Sciences Department ($4,000), the Engineering Excellence Fund ($2,000), and Lockheed Martin ($10,000), the budget for constructing the aircraft is feasible even with a 25% margin. 7.1.3 Aerodynamic Feasibility Based on the design to specifications, the aircraft was sized to a takeoff distance of 90 feet with a 10 ft margin, 40 ft/sec stall speed, 100 ft/sec cruise speed and 2g maneuver at 80 ft/sec. The performance sizing plot is shown in Figure 30. Performance sizing was checked with Dr. Gerren, a team advisor [10] . 52
Project Final Report – CUDBF April 30 th , 2009 ASEN 4028: Aerospace Senior Projects Figure 30: Performance Constraint Plot From the performance sizing, the design area that meets all requirements was determined. In the plot shown, the shaded area indicates the optimal design area. The equations used to determine the weight to power ratio as a function of stall speed, takeoff distance, cruise speed and maneuver are shown in Equation 9, Equation 10, and Equation 11 respectively: = 1 2 Equation 9: Weight-to-Power Ratio for Stall Speed In Equation 9, is the ambient density, is the maximum lift coefficient and V stall is the stall speed. = ∙ ∙ ∙ ∙ 1.44 ∙ Equation 10: Weight-to-Power ratio for takeoff. In the performance sizing equation for takeoff distance, is the takeoff distance, is the density, is the maximum lift coefficient, is the landing speed, is the acceleration due to gravity and is the wing loading. 53
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