1. AIT-JAR-10/04
Bi-prop Thruster Test
Compilation of data taken during 2
second burn at Site 300 10/12/04

2. AIT-JAR-10/04
Peroxide/RP-1 Bi-prop Thruster
Copper Thrust Chamber and Fuel Injector

3. AIT-JAR-10/04
Bi-prop Thruster Continued
Catalyst Bed, Fuel Injector, Copper Chamber

4. AIT-JAR-10/04
2 Second Burn

5. AIT-JAR-10/04
Data Plots:
Pressure Data: 1000 psi Output
Propellant Flows:
Ox = 330g/s
Fuel = 52g/s
6.4:1 Ratio
Load Cell Output
200lbf

6. AIT-JAR-10/04
Rocket Engine Fundamentals for Bi-Prop Burn:
Isp - The specific impulse of a rocket propellant is a rough measure of how fast the propellant is
ejected out of the back of the rocket. Propellants are 90% H2O2 + RP-1 at 6.7:1 ratio.
Isp Theoretical = 260s
Efficiency = 94%
C*
- considered to be indicative of the combustion efficiency. It is a measure of exhaust velocity.
C*
Theoretical is a function of the products of combustion, pressures, and temperatures.
R = Universal Gas Constant = 8314J/kmol-K, J = kgm/s
Tc = 2700K

7. AIT-JAR-10/04
m = mass of combustion products = 21.4g/mol
k = Cp/Cv = 1.18
Efficiency = 96.6%
C*
th = 5327ft/s (computer simulation)
Efficiency = 95%
General Kinetics Results = 97%

8. AIT-JAR-10/04
Run using June 1988 Version of PEP,
Case 1 of 1 28 Oct 2004 at 7:50:36.26 am
CODE WEIGHT D-H DENS COMPOSITION
513 HYDROGEN PEROXIDE (90 PC) 1000.000 -1439 0.05010 642H 586O
854 RP-1 150.000 -1340 0.02890 2H 1C
THE PROPELLANT DENSITY IS 0.04572 LB/CU-IN OR 1.2657 GM/CC
THE TOTAL PROPELLANT WEIGHT IS 1150.0000 GRAMS
NUMBER OF GRAM ATOMS OF EACH ELEMENT PRESENT IN INGREDIENTS
85.439133 H 10.693663 C 58.464737 O
****************************CHAMBER RESULTS FOLLOW *****************************
T(K) T(F) P(ATM) P(PSI) ENTHALPY ENTROPY CP/CV GAS RT/V
2712. 4422. 25.51 375.00 -1640.00 3379.60 1.1845 53.884 0.473
SPECIFIC HEAT (MOLAR) OF GAS AND TOTAL= 12.754 12.755
NUMBER MOLS GAS AND CONDENSED= 53.8843 0.0000
39.65253 H2O 7.33630 CO2 3.35695 CO 2.72049 H2
0.54981 HO 0.14258 H 0.10695 O2 0.01804 O
3.79E-04 HO2 2.38E-05 CHO
THE MOLECULAR WEIGHT OF THE MIXTURE IS 21.342

9. AIT-JAR-10/04
****************************EXHAUST RESULTS FOLLOW *****************************
T(K) T(F) P(ATM) P(PSI) ENTHALPY ENTROPY CP/CV GAS RT/V
1569. 2365. 0.68 10.00 -2457.60 3379.60 1.2093 53.413 0.013
SPECIFIC HEAT (MOLAR) OF GAS AND TOTAL= 11.483 11.483
NUMBER MOLS GAS AND CONDENSED= 53.4134 0.0000
39.24401 H2O 8.52701 CO2 3.47494 H2 2.16625 CO
6.43E-04 H 2.66E-04 HO
THE MOLECULAR WEIGHT OF THE MIXTURE IS 21.530
**********PERFORMANCE: FROZEN ON FIRST LINE, SHIFTING ON SECOND LINE**********
IMPULSE IS EX T* P* C* ISP* OPT-EX D-ISP A*M EX-T
245.6 1.1980 2468. 14.41 5186.4 5.72 310.8 0.42996 1490.
248.8 1.1660 2511. 14.57 5244.8 202.1 5.83 314.8 0.43480 1569.

10. AIT-JAR-10/04
Shock Diamonds (Mach Disk)
Nozzle Exit Pressure Below Sea Level
AIT Bi-Prop Run @ 200lbf
Shuttle Main Engine@.5Mlbf