AAE 450 Spring 2008

Nicole WilcoxMarch 20th, 2008

PropulsionEngine Performance

Characteristics Breakdown Propellant and Pressurant Final

Slides

Propulsion

AAE 450 Spring 2008

Engine Performance Characteristics

 Isp,vac

(s)Isp,SL

(s)

ChamberPressure

(Mpa)O/F

RatioC*

(m/s)Exit

Mach # Ae/At

Stage 1 352.3 337.6 2.1 6.0 1752.0 4.4 60

Stages 2,3 309.3 292.1 6.0 1.0 1480.0 4.1 60

Propulsion

AAE 450 Spring 2008

Propellant and Pressurant Cost Propellant

– Stage 1 - Hydrogen Peroxide and HTPB

– Stage 2,3 - AP/HTPB/Al

Pressurant– Nitrogen– 12 MPa– 1st Stage Only

Propulsion

Vehicle StagePropellantMass (kg)

PropellantCost ($)

PressurantMass (kg)

PressurantCost ($)

200 g

1 1462.0 $14,650 59.0 $29.50

2 566.6 $2,833 - -

3 37.3 $187 - -

Total 2065.9 $17,670 59.0 $29.50

1 kg

1 947.9 $9,500 38.2 $19.10

2 336.9 $1,685 - -

3 45.1 $226 - -

Total 1330.0 $11,410 38.2 $19.10

5 kg

1 4122.2 $41,320 166.3 $83.15

2 1009.2 $5,046 - -

3 38.4 $192 - -

Total 5169.8 $46,560 166.3 $83.15

AAE 450 Spring 2008

References Heister, Stephen D. Humble, R. W., Henry, G. N., Larson, W. J., Space Propulsion Analysis and

Design, McGraw-Hill, New York, NY, 1995. Javorsek, D., and Longuski, J.M., “Velocity Pointing Errors Associated with

Spinning Thrusting Spacecraft,” Journal of Spacecraft and Rockets, Vol. 37, No. 3, 2000, pp. 359-360.

Klaurans, B. “The Vanguard Satellite Launching Vehicle,” The Martin Company. No. 11022, April 1964.

Knauber, R.N., “Thrust Misalignments of Fixed-Nozzle Solid Rocket Motors,” Journal of Spacecraft and Rockets, Vol. 33, No. 6, 1996, pp. 794-799.

Sutton, George P., Biblarz, Oscar “Solid Propellants,” Rocket Propulsion Elements, 7th ed., Wiley, New York, 2001.

Ventura, M., “The Lowest Cost Rocket Propulsion System,” General Kinetics Inc, Huntington Beach, CA, Jul. 2006.

Tsohas, John.

Propulsion