Rockets separate from the launch pad and supporting structures very early in flight. It seems like they should tip over once that happens.

  • Why don't they tip over ?

  • Is it due to a well designed center of gravity or do they somehow achieve aerodynamic stabilization ?


Nowadays, rockets use a Gimbaled Thrust System. The rocket nozzles are gimbaled (An appliance that allows an object such as a ship's compass, to remain horizontal even as its support tips) so they can vector the thrust to direct the rocket. In a gimbaled thrust system, the exhaust nozzle of the rocket can be swivelled from side to side. As the nozzle is moved, the direction of the thrust is changed relative to the center of gravity of the rocket.

Early rockets had Vernier Thrusters which uses small rocket engines on either sides, to control the attitude (vs altitude) of a rocket. Nowadays, they are common in most satellites.

In this Image, The middle rocket shows the normal flight configuration in which the direction of thrust is along the center line of the rocket and through the center of gravity of the rocket. On the left one, the nozzle has been deflected to the left and the thrust line is now inclined to the center line at a gimbal angle $a$. As the thrust no longer passes through the center of gravity, a torque is generated about the center of gravity and the nose of the rocket turns to the left. If the nozzle is gimbaled back along the center line, the rocket will move to the left. On the right one, the nozzle has been deflected to the right and the nose is moved to the right.

Thrust vectoring Wikipedia says,

In spacecraft propulsion, rocket engines are generally mounted on a pair of gimbals to allow a single engine to vector thrust about both the pitch and yaw axes; or sometimes just one axis is provided per engine. To control roll, twin engines with differential pitch or yaw control signals are used to provide torque about the vehicle's roll axis.

The right & left gimbaling is necessary to direct the rocket to its original path, thereby maintaining its stability... This link gives a good explanation regarding the stability of rockets. This essay is also good, but it's somewhat big...

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    $\begingroup$ Another possible source of confusion is the misconception that gravity will pull a rocket over, due to thinking it is "supported" against gravity by the engines at its base. Gravity (apart from very weak tidal forces) acts on the rocket as a whole, not applying any torque. en.wikipedia.org/wiki/Pendulum_rocket_fallacy $\endgroup$ – Christopher James Huff Dec 30 '12 at 5:23
  • $\begingroup$ Very early rockets used air vanes and graphite jet vanes. $\endgroup$ – Deer Hunter Aug 5 '13 at 9:05
  • $\begingroup$ I think the question doesnt ask about the rocket in flight but the rocket before launch, just before take off. $\endgroup$ – karthikeyan Jun 8 '14 at 7:57
  • $\begingroup$ @karthikeyan: The author has accepted the answer, which implies that he's convinced ;-) $\endgroup$ – Waffle's Crazy Peanut Jun 14 '14 at 13:34
  • $\begingroup$ So that's what those little squirters on the side of the early Atlas were! I'd always assumed that all rockets had some kind of vectored thrust, since the V2 had this and implemented it with graphite vanes in the exhaust. $\endgroup$ – Selene Routley Feb 8 '17 at 0:44

More fundamental than the gimballed thrust system or verniers is the relationship between the "center of gravity" and "center of pressure" on a rocket (or any kind of projectile (e.g., bullet).

For the rocket to fly nose-forward and not flip around, the center of gravity must be ahead of the center of pressure. In building small amateur or model rockets, the guideline is always that the CG should be at least 1 body diameter ahead of the CP.

The center of gravity is the point where the mass components of the rocket "act" with respect to the ground (i.e., you can treat the CG as a point representing "the rocket" when calculating the opposing force of gravity pulling the rocket downward). The center of pressure is the point where aerodynamic forces on the rocket body, nose, and any fins sum together and "act".

rocket stability

In the above answer about gimballed thrust, for example, the gimbals are actually acting to force the CP back under the CG when the nose tilts. Fins (e.g., on missiles or model rockets) act in the same way to keep the CP under the CG.

So individual technologies for doing that may vary, but the underlying principle here is the CG/CP relationship. Hope that helps.


  • $\begingroup$ That's fine for model rockets, but orbital launchers rapidly leave the atmosphere. CP is only relevant for the first minute or so of launch...and isn't relevant at all for launches from airless bodies. The answer is simply that they're actively stabilized, against both aerodynamic forces when present and any other small imbalances and misalignments in thrust. For an extreme example, a recent Falcon 9 launch lost one engine on the way up, along with an aerodynamic cover for the engine, but the guidance system was able to compensate. $\endgroup$ – Christopher James Huff Dec 30 '12 at 5:16
  • $\begingroup$ In buoyancy problems, the CP is necessarily under the CG, but those don't lead to unstable solutions. Instead, the CP moves to the side as the vessel tilts, and the question of stability is whether it moves horizontally further or less than the CG. In the case of a rocket, it's plainly obvious that the CP moves if the rocket tilts. The literal question of stability is if the CG-CP line rotates opposite the orientation of the rocket. $\endgroup$ – Alan Rominger Feb 19 '13 at 15:56

There are a couple of things at work here.

First - the rotational inertia of the rocket is quite large. That means that if it were to "fall over", it would do so very slowly

Second - it only "falls over" if there ia a torque applied. While it is standing on the launchpad, the center of gravity is between the support points so it doesn't fall; once it's launched, there are three forces at work:

  1. Gravity - acting on the center of mass, it cannot provide torque
  2. Thrust - if the trust is pointed along the axis of the rocket, it provides no torque; but if you can "aim" slightly off to the side (using gimbaled thrust as explained by Waffle) you can cause the rocket to "tip"
  3. Air flow - for rockets with small fins, this tends to be a stabilizing torque, especially as the rocket goes faster. Of course at higher altitudes this matters less

One thing to note - because the torque in (2) is relatively small (small angle ... displacement of line of work relative to center of mass will be small), any "tipping" will happen quite slowly, and the control mechanism has time to respond. This is comparable to the problem of balancing a broom on your hand vs a match stick. The larger size of the broom gives you much more time to react to small angular displacements. In fact, you can consider the system to be not unlike an inverted pendulum for which the typical time constant will be proportional to $\sqrt\frac{\ell}{g}$. So if you can balance a broom that is 1 m tall, it will be 10x easier to balance a rocket that is 100 m (the approximate size of the Saturn V) tall (in terms of time for the control system to react).

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    $\begingroup$ The last point illustrates every other answer very well. One of the things I do at my daughter's school is to show the children (about grade 3 or up) a video of the hold-down pins releasing on launch and prompt the children to think about why the rocket needs to be held down in the first place. We end up pretending to be guidance systems by balancing broom handles: the children jump at the chance offered by "who wants to pretend to be a rocket guidance computer"? Your point would be a good one to make (without the equations of course) alongside this exercise. $\endgroup$ – Selene Routley Feb 8 '17 at 0:39
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    $\begingroup$ @WetSavannaAnimalakaRodVance I love the idea of making the third graders in "rocket guidance control systems"! $\endgroup$ – Floris Feb 8 '17 at 1:19

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