AIT-JAR-10/04

Bi-prop Thruster Test

Compilation of data taken during 2 second burn at Site 300 10/12/04

AIT-JAR-10/04

Peroxide/RP-1 Bi-prop Thruster

Copper Thrust Chamber and Fuel Injector

AIT-JAR-10/04

Bi-prop Thruster Continued

Catalyst Bed, Fuel Injector, Copper Chamber

AIT-JAR-10/04

2 Second Burn

AIT-JAR-10/04

Data Plots:

Pressure Data: 1000 psi Output

Propellant Flows:Ox = 330g/sFuel = 52g/s6.4:1 Ratio

Load Cell Output200lbf

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.

sslb

lbf

slbm

lbfThrustI

m

sp244

/82.

200

)/(

)(

Isp Theoretical = 260s Efficiency = 94% C* - considered to be indicative of the combustion efficiency. It is a measure of exhaust velocity.

sftsmskg

smkgm

m

PAC chamberthroat /5038/1535

/4.

//1048.200025. 262

*

C* Theoretical is a function of the products of combustion, pressures, and temperatures.

1

1

2

1*

k

k

ck

mk

RTC

R = Universal Gas Constant = 8314J/kmol-K, J = kgm/s Tc = 2700K

AIT-JAR-10/04

m = mass of combustion products = 21.4g/mol k = Cp/Cv = 1.18

sftsmkmolkg

KkmolK

skgm

CK

k

/5211/15882

118.1

18.1/4.21

2700/

8314*

1

1

Efficiency = 96.6% C*

th = 5327ft/s (computer simulation) Efficiency = 95% General Kinetics Results = 97%

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

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.

AIT-JAR-10/04

Shock Diamonds (Mach Disk)Nozzle Exit Pressure Below Sea Level

AIT Bi-Prop Run @ 200lbf

Shuttle Main Engine@.5Mlbf