Aero 4442
Transatmospheric Propulsion
March 5, 2015
!
Since n<1, this indicates that the factor !>1 and thus the combustion pressure is
more sensitive to changes in Ti then is the burning surface recession rate. As

P=mV ; P = momentum
F=
d
( P)
dt
I sp =
F=
F
ma
g
d
dm
dV
( P)= V +m
=mV
+ ma g
dt
dt
dt
I = F dt =mave V veh = m
V dt ; I=impulse
I = V m
dt= V M ; If V is constant
V veh =
I
veh
M
m a=F=
G m1 m2
R2
u r
r = r
R3
=G(m1 +m2) GM
g=
R2
p
1+ cos
=Eccentr

Aero 4442
Transatmospheric Propulsion
March 5, 2015
1
>1 and thus the combustion
1n
pressure is more sensitive to changes in T i then is the burning surface recession rate.
As n approaches 0, the combustion pressure sensitivity decreases and n approaches

Aero 4442
Transatmospheric Propulsion
March 31, 2015
Even at speeds below M=1, Small shocks can start forming due to local flow
acceleration around the vehicle.
As the sound barrier is breached, the entire vehicle creates a bow shock,
which will be at nea

Aero 4442
Transatmospheric Propulsion
March 24, 2015
Equations 88a to 88c can be expressed in matrix form to more easily find the
1 , 2 , 3 , i , ln m , ln T
solution vector [
such that [A]cfw_x=[y]:
T
T =cfw_ x
Given a set of initial conditions this sy

Aero 4442
Transatmospheric Propulsion
March 19, 2015
Thus for most fuels/oxidizers in use, Eq 81 is a set of n a=4 equations, each
represents the conservation of H,0,C and N as the various species change during the
combustion process. Taking the derivativ

Aero 4442
Transatmospheric Propulsion
March 10, 2015
In all these cases, once the fuel and oxidizer are introduced into the combustion
chamber, the task becomes one of atomizing the liquids (creating very fine droplets
of liquid) followed by vaporization

Aero 4442
Transatmospheric Propulsion
March 3, 2015
Most grain patterns are designed to produce a neutral burn and keep combustion
pressure constant to within +/- 15% over some portion of the burn time. Since the
complete process from ignition to shut dow

Aero 4442
Transatmospheric Propulsion
March 12, 2015
Recalling the momentum equation, if we apply it to a small control volume
within our nozzle but allow for 2 distinct phases (i.e. ms, vs, and mg, v g where
s = solid and g=gas)
A
u d
u
d
F= dt u dv