Aroll programortilt maneuver is an aerodynamic maneuver that alters the attitude of a vertically launched space launch vehicle. The maneuver is used to place the spacecraft on a proper heading toward its intended orbit. It often consists of a partial rotation around the vehicle's vertical axis ("roll") followed by tilting the vehicle ("pitch") to follow the proper gravity turn and/or to improve aerodynamics.
A roll program is completed shortly after the vehicle clears the tower. In the case of a crewed mission, a crew member (usually the commander) reports the roll to the mission control center which is then acknowledged by the capsule communicator.[1]
The Saturn V's roll program was initiated shortly after launch and was handled by the first stage. It was open-loop: the commands were pre-programmed to occur at a specific time after lift-off, and no closed loop control was used. This made the program simpler to design at the expense of not being able to correct for unforeseen conditions such as high winds. The rocket simply initiated its roll program at the appropriate time after launch, and rolled until an adequate amount of time had passed to ensure that the desired roll angle was achieved.[2]
Roll on the Saturn V was initiated by tilting the engines simultaneously using the roll and pitch servos, which served to initiate a rolling torque on the vehicle.[3]
During the launch of a Space Shuttle, the roll program was simultaneously accompanied by a pitch maneuver and yaw maneuver.[4]
The roll program occurred during a Shuttle launch for the following reasons:
To place the shuttle in a heads down position
Increasing the mass that can be carried into orbit (this was actually the initial reason - a 20% payload increase due to more efficient aerodynamics and moment balancing between the boosters and main engines)[5]
Orienting the shuttle more parallel toward the ground with the nose to the east
The RAGMOP computer program (Northrop) in 1971–72 discovered a ~20% payload increase by rolling upside down. It went from ~40,000 lb to ~48,000 lb to a 150 NM equatorial orbit without violating any constraints (max Q, 3 G limit, etc.). So the incentive to roll was initially for the payload increase by minimizing drag losses and moment balancing losses by keeping the main engine thrust vectors more parallel to the SRBs.[5]
^Gunderson, Robert; Hardy, Gordon (1966). Piloted Guidance and Control of the Saturn V Launch Vehicle. Peaceful Uses of Automation in Outer Space. Springer. pp. 33–50.
^Haeurssurmann, Walter (1970). Description and Performance of the Saturn Launch Vehicle's Navigation, Guidance, and Control System. 3rd International IFAC Conference on Automatic Control in Space, Toulouse. Toulouse: Elsevier. pp. 275–312.
