# (19 Dec 1994)

Let us assume that we have a Liquid Air Cycle Engine (LACE) where the fuel is provided by the rocket and the oxidiser is from surrounding air. To simplify our derivation we assume that the rocket is frictionless (except for engine drag). For a normal rocket which carries its own fuel and oxidiser we have from Newton's third law that

```
dv(t)                  F
a(t) = ----- = ------------------------------------
dt     m_c + m_s + m_f + m_o - (r_f + r_o)t

```

where

a(t) = acceleration varying with time (m/s^2) v(t) = the speed varying with time (m/s) F = engine thrust (N) m_c = cargo mass (kg) m_s = structure mass (kg) m_f = fuel mass (kg) m_o = oxidiser mass (kg) r_f = fuel rate (kg/s) r_o = oxidiser rate (kg/s)

We have T = m_f/r_f = m_o/r_o is the firing duration of the rocket. Integrating and letting t = T we have the standard rocket equation

```

F        (m_c + m_s + m_f + m_o)
v(T) = --------- ln (---------------------)
r_f + r_o    (      m_c + m_s      )

= v_e ln (1 + (m_f + m_o)/(m_c + m_s))

```

where

```
v_e = F/(r_f + r_o) = effective exhaust speed of the engine (m/s)

```

For a LACE m_o is not carried aboard and must be accelerated to the speed of the rocket. This induces an effective drag on the vehicle equal to v(t)r_o. We derive this from the fact that the effective thrust of a rocket equation is that obtained by accelerating the propellant mass continuously entering the engine up to some exhaust speed v_e (the energy being obtained from the combustion of a fuel and an oxidiser). It does not matter how the mass was accelerated. Only the final speed is important. Conversely, to bring the oxidiser up to the same speed of the rocket before entering the combustion chambers requires a force equal to v(t)r_o. The acceleration equation then becomes

```
dv(t)   v_e(r_f + r_o) - v(t) r_o
----- = -------------------------
dt      m_c + m_s + m_f - r_f t

```

For a positive acceleration we must have

```
v_e(r_f + r_o) - v(t) r_o > 0

```

or

```
v(t) < v_e (1 + r_f/r_o)

```

The upper speed obtained by a LACE only powered vehicle is therefore fixed. For hydrogen/oxygen propellants v_e = 4000 m/s (the space shuttle main engine has v_e = 3543 m/s at sea level and 4441 m/s in a vacuum). Air has only about 25% oxygen by mass (a rough guess since I could only find out that 21% of air by volume is oxygen and oxygen is denser than nitrogen which makes up most of the rest of air). This means that the combustion energy is distributed over about four times the mass resulting in an exhaust speed of about half (since exhaust energy is proportional to v_e^2). Thus v_e = 2000 m/s. Now to make up for the fact that nearly 75% of air is nitrogen with a mass 14/(16+2) = 7/9 times smaller than water we have v_e = 4000 / sqrt(1+3x7/9) = 2190 m/s. So lets say v_e = 2200 m/s.

For the SKYLON LACE engine 2/3 of the hydrogen is used to cool the incoming air and is then dumped overboard. A normal hydrogen/oxygen engine has a mixture ratio of O/F = 6:1. For LACE we have (1+3x14/16)x6:(1+2) = 7.25:1. Thus the maximum speed that we can expect for a hydrogen powered vehicle starting from rest is about 2500 m/s which is far short of the orbital speed of about 8000 m/s (and that's ignoring gravity and air drag losses).

We can solve the LACE differential equation (I used the Laplace transform) and get (assuming starting at rest)

```
r_o/r_f
[    (   m_c + m_s   )       ]
v(T) = v_e (1 + r_f/r_o) [1 - (---------------)       ]
[    (m_c + m_s + m_f)       ]

```

This is the LACE Rocket Equation (probably discovered yonks ago, but what the heck, it was fun deriving it). For the LACE the air powered portion of the flight has

```
m_c + m_s = 224 t
m_c + m_s + m_f = 262 t

```

Thus v(T) = 1700 m/s. The quoted final speed for SKYLON was 1657 m/s. Ways to increase the performance of the LACE is to not cool the air so that the thermal energy can be used in the rocket engine. In fact the SKYLON SABRE engine does not liquify the air which increases the performance of the system. SKYLON then uses normal rocket powered flight to reach orbit. We have

```
m_c = 10 t
m_s = 45.7 t
m_f + m_o = 168.3 t

```

Using the rocket equation and v_e = 4400 m/s we have v(T) = 6123 m/s. SKYLON receives an initial rocket powered boost requiring 13 t of propellant. This gives an initial v(T) of 169 m/s assuming v_e = 3500 m/s. The total deltaV is thus about 8000 m/s. Hmm, might be a bit low, but then again SKYLON does take off horizontally which should save on gravity losses (since it follows the Earth's velocity vector, unlike a rocket which takes off perpendicular to the velocity vector).

In case you're wondering, this is the LACE equation if you start with an initial speed of v_i

```
r_o/r_f
(   m_c + m_s   )
v(T) = v_e(1 + r_f/r_o) + (v_i - v_e(1 + r_f/r_o)) (---------------)
(m_c + m_s + m_f)
```

Food for thought. How do you handle SCRAM (supersonic combustion RAM) jets? The air is decelerated to some supersonic value (say v_s) and combustion takes place. The drag is now (v-v_s)r_o. Now I can imagine incoming oxygen molecules smashing into the hydrogen molecules with an almighty whack. The air velocity vector has been partially converted to thermal energy. You should be able to get this energy back again in the engine exhaust (with a suitable expansion nozzle) plus the energy of combusting hydrogen with oxygen. As you can imagine the drag increases with speed and so the thrust must increase with it. This is the reverse of rocket engines where you usually decrease the thrust the faster you go. A SCRAM powered vehicle would have three different types of operation: zero to the supersonic speed where the SCRAM kicks in (using a LACE engine?), supersonic to as fast as you can go, and then a normal rocket engine to put you into orbit. Plus the fact that a SCRAM engine has such a big mouth (and a matching rear end) that you have to design your vehicle around it.

```Steven S. Pietrobon,  Australian Space Centre for Signal Processing
Signal Processing Research Institute, University of South Australia
The Levels, SA 5095, Australia.     steven@spri.levels.unisa.edu.au
```