The transpiration cooling control system of surface thermal protection for bodies of revolution at hypersonic is studied. Not only the critical transpiration quantity equaling to plane case is obtained, but also another smaller second critical transpiration quantity is found. When the transpiration quantity is between of this two critical transpiration quantities, the ablation will appear on the shield surface, but the ablation will stop automatically, and a remainder thickness of shield will be kept at last. Numerical simulation is accomplished and yields all kinds of charactdstic curves. Three methods of ablation control for shield surface are discussed:the controls are for surface temperature, for ablation quantity and for ablation beginning time, the rules for selecting control variable are given.