Emphasis Heading 1 Heading 2 Heading 3 REGRESSIONI Solid Propellant Rocket Engine Simple Linear Regression Exercise Name: The Space Transportation Program Office has tasked you with estimating production costs for a new solid propellant rocket engine to be used of the International Launch Vehicle (ILV). Prior to collecting historical data, meetings with propulsion engineers were held. The results of the identification phase were encouraging. The experts agree that the primary driver of solid propellant rocket engine production costs is Power. For propulsion systems, Power can be measured in several ways, such as Average Thrust. Burn Time and Propellant Weight. During the specification phase, the experts all agreed that as power, burn time, and propellant weight increased, cost would also increase Data on twelve analogous rocket engines were gathered. The cost data is normalized to the cost at unit 100 in FY985. The historical database is as follows: Rocket Engines Average Thrust Engine Cost (Unit 100) Burn Time (sec) Propellant Weight 1 2 3 4 5 6 7 9. 739150510.35 6 , 836 2320 11.55 11.280 46,780 16.80 9 6.334 2. 465 2 1.52 58, 5939. 432 14.93 44, 389 24,345 17. 432 911,234 16, 290 35. 606 999.999 33. 735 3 1. 80 6 9 32510 33.450 43.10 1 ,344,350 4.500 45.60 1 ,481,090 14,657 50.60 1.536,800 67.555 52.40, 1003 2340 2536 6556 3,348 .504 ,451 ,986 8 9 10 11 12 307 9,400 9120 Tasks: Develop the "best" model/prediction possible, given the database provided. Document the process used and the decisions made along the way. 4. Using the preferred"CER, estimate the cost at unit 100 for the solid rocket motor that will be employed on the new International Launch Vehicle (ILV). Following are the specifications for the IL V rocket motor: Average Thrust - 71,544 lbs Burn Time - 48.5 sec Propellant Weight -9,290 lbs Emphasis Heading 1 Heading 2 Heading 3 REGRESSIONI Solid Propellant Rocket Engine Simple Linear Regression Exercise Name: The Space Transportation Program Office has tasked you with estimating production costs for a new solid propellant rocket engine to be used of the International Launch Vehicle (ILV). Prior to collecting historical data, meetings with propulsion engineers were held. The results of the identification phase were encouraging. The experts agree that the primary driver of solid propellant rocket engine production costs is Power. For propulsion systems, Power can be measured in several ways, such as Average Thrust. Burn Time and Propellant Weight. During the specification phase, the experts all agreed that as power, burn time, and propellant weight increased, cost would also increase Data on twelve analogous rocket engines were gathered. The cost data is normalized to the cost at unit 100 in FY985. The historical database is as follows: Rocket Engines Average Thrust Engine Cost (Unit 100) Burn Time (sec) Propellant Weight 1 2 3 4 5 6 7 9. 739150510.35 6 , 836 2320 11.55 11.280 46,780 16.80 9 6.334 2. 465 2 1.52 58, 5939. 432 14.93 44, 389 24,345 17. 432 911,234 16, 290 35. 606 999.999 33. 735 3 1. 80 6 9 32510 33.450 43.10 1 ,344,350 4.500 45.60 1 ,481,090 14,657 50.60 1.536,800 67.555 52.40, 1003 2340 2536 6556 3,348 .504 ,451 ,986 8 9 10 11 12 307 9,400 9120 Tasks: Develop the "best" model/prediction possible, given the database provided. Document the process used and the decisions made along the way. 4. Using the preferred"CER, estimate the cost at unit 100 for the solid rocket motor that will be employed on the new International Launch Vehicle (ILV). Following are the specifications for the IL V rocket motor: Average Thrust - 71,544 lbs Burn Time - 48.5 sec Propellant Weight -9,290 lbs