Pogo oscillation is a potentially dangerous type of self-excited combustion oscillation in liquid fuel rocket engines. This oscillation results in variations of thrust from the engines, causing variations of acceleration on the rocket's structure, giving variations in fuel pressure and flow rate. Pogo places stress on the frame of the vehicle which can be severe. Although the term is frequently written POGO, it is not an acronym, but in fact a reference to the bouncing of a pogo stick.
In general, pogo oscillation occurs when a surge in engine pressure increases back pressure against the fuel coming into the engine, reducing engine pressure, causing more fuel to come in and increasing engine pressure again. Flexing of fuel pipes can also induce fluctuations in fuel pressure. If the cycle happens to match a resonance frequency of the rocket then dangerous oscillations can occur through positive feedback, which can, in extreme cases, tear the vehicle apart.
Another situation in which pogo oscillation will occur is when the engine is moving upward with fluctuating speed. Owing to inertia, if the speed of the vehicle suddenly increases, the fuel inside the fuel tank tends to 'fall behind' and is forced into the turbopump, a situation somewhat similar to the slosh of liquid inside a tanker. This creates excess pressure to the turbopump and causes unintended excessive fuel to be delivered. This in turn creates excessive thrust and causes the vehicle to accelerate which leads to further increase in turbopump pressure and an unintended increase in fuel delivery. This can set up a vicious circle, and can result in structural failure in the vehicle.
The most famous pogo oscillation was in the Saturn V first stage, S-IC, caused by the cruciform thrust structure. This structure was an "X" of two I-beams, with an engine on the end of each beam and the center engine at the intersection of the beams. The center of the cruciform was unsupported, so the central F-1 engine caused the structure to bend upwards. The pogo oscillation occurred when this structure sprang back, lengthening the center engine's fuel line bellow (which was mounted down the center of the cruciform), temporarily reducing the fuel flow and thus reducing thrust. At the other end of the oscillation, the fuel line was compressed, increasing fuel flow. This caused a sinusoidal thrust oscillation during the first stage ascent.
If the oscillation is left unchecked, failures can result. One case occurred in the middle J-2 engine of the second stage, S-II, of the Apollo 13 lunar mission. Fortunately in this case the engine shut down before the oscillations could cause damage to the vehicle. Later events in this mission overshadowed the pogo problem. Pogo was also the cause of some of the serious problems experienced by the unmanned Apollo 6 test flight in 1968. One of the Soviet Union's N1-L3 rocket test flights suffered pogo oscillations in the first stage on November 23, 1972. The launch vehicle reached initial engine cutoff, but exploded 107 seconds after liftoff and disintegrated. There are other cases during unmanned launches in the 50s and 60s where the pogo effect caused catastrophic launch failures.
However, modern vibration analysis methods can account for the pogo oscillation to ensure that it is far away from the vehicle's resonant frequencies. Suppression methods include damping mechanisms or bellows in propellant lines. The Space Shuttle Main Engines each had a damper in the LOX line, but not in the hydrogen fuel line.
- Apollo 13 Pogo Oscillation, Tom Irvine, Vibrationdata Newsletter, October 2008, pp. 2-6, retrieved on 18-06-2009.
- The Perils of Pogo
- Launch Vehicle Design: Configurations and Structures, Princeton University, retrieved on 18-06-2009.
- Fenwick, Jim (Spring 1992). "PWR Engineering — Threshold Journal: Pogo". Threshold (Pratt & Whitney Rocketdyne). Retrieved 2009-09-11.
- NASA Experience with Pogo in Human Spaceflight Vehicles, retrieved 26-06-2012.
- "Die russische Mondrakete N-1 (in German)".