Mass ratio
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In aerospace engineering, mass ratio is a measure of the efficiency of a rocket. It describes how much more massive the vehicle is with propellant than without; that is, it is the ratio of the rocket's wet mass (vehicle plus contents plus propellant) to its dry mass (vehicle plus contents). A more efficient rocket design requires less propellant to achieve a given goal, and would therefore have a lower mass ratio.
The mass ratio is a useful quantity for back-of-the-envelope rocketry calculations: it is an easy number to derive from either Δv numbers or from rocket and propellant mass numbers, and therefore serves as a handy bridge between the two. It is also a useful number to give an impression of the size of a rocket: while two rockets with mass fractions of, say, 92% and 95% may appear similar, the corresponding mass ratios of 12.5 and 20 clearly indicate that the latter system requires much more propellant.
Typical multistage rockets have mass ratios in the range from 8 to 20. The Space Shuttle, for example, has a mass ratio around 16.
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[edit] Derivation
The definition arises naturally from the Tsiolkovsky rocket equation:
where
-
- Δv is the desired change in the rocket's velocity
- ve is the effective exhaust velocity (see specific impulse)
- m0 is the initial mass (rocket plus contents plus propellant)
- m1 is the final mass (rocket plus contents)
This equation can be rewritten in the following equivalent form:
The fraction on the left-hand side of this equation is the rocket's mass ratio by definition.
This equation indicates that a Δv of n times the exhaust velocity requires a mass ratio of en. For instance, for a vehicle to achieve a Δv of 2.5 times its exhaust velocity would require a mass ratio of e2.5 (approximately 12.2). One could say that a "velocity ratio" of n requires a mass ratio of en.
[edit] Examples
| Vehicle | Takeoff Mass | Final Mass | Mass ratio | Mass fraction |
|---|---|---|---|---|
| Ariane 5 (vehicle + payload) | 746,000 kg [1] | 2,700 kg + 16,000 kg[1] | 39.9 | 0.975 |
| Titan 23G first stage | 258,000 lb (117,020 kg) | 10,500 lb (4,760 kg) | 24.6 | 0.959 |
| Saturn V | 3,038,500 kg[2] | 13,300 kg + 118,000 kg[2] | 23.1 | 0.957 |
| Space Shuttle (vehicle + payload) | 2,040,000 kg | 104,000 kg + 28,800 kg | 15.4 | 0.935 |
| Saturn 1B (stage only) | 448,648 kg[3] | 41,594 kg[3] | 10.7 | 0.907 |
| V2 | 12.8 ton (13000 kg) | 3.85 | 0.74 [4] | |
| X-15 | 34,000 lb (15,420 kg) | 14,600 lb (6,620 kg) | 2.3 | 0.57[5] |
| Concorde | 400,000 lb [5] | 2 | 0.5[5] | |
| 747 | 800,000 lb[5] | 2 | 0.5[5] |
[edit] References
Zubrin, Robert (1999). Entering Space: Creating a Spacefaring Civilization. Tarcher/Putnam. ISBN 0-87477-975-8.
