upper free surface of the fluid with a low pressure manifold and vented from ports at the base of the fairing for example in the case of the chambercore architecture 5 psi pressure is adequate to vent 60 vertical feet of chambercore in less than 10 seconds the venting prevents significant reduction of payload mass that would result if the aerated media were carried to fairing separation at the edge of the sensible atmosphere 45 000 to 100 000 m for most fairings thin adhesive membranes of aluminum sheeting or plastic film would temporarily plug vents at the base of the fairing these membranes could be ruptured at a controlled altitude by electrically heated wires mechanical actuators transient pressure overloads or similar mechanisms typical delay times for initiation of venting depend on launch vehicle size and acceleration from the surface of the earth but would typically range from a few seconds for small launch vehicles to a few tens of seconds for the largest launch vehicles fig1 shows a typical payload fairing with the cylindrical chambercore section 1 being the part that contains the gas fluid mixture the other sandwich panel sections 2 and a small part of the launch vehicle 3 fig2 a is a cross section of the fairing showing the air delivery system 20 a detailed view of the air delivery system 20 is shown in fig2 b comprised of an air tank 4 a pressure regulator 5 and an electronic controller 6 fig3 a and fig3 b is another view of the air delivery system 20 showing the high pressure air supply line 7 used to expel the fluid at altitude and the low pressure air supply line 8 for supplying the bubbles both draw from the same.