Abstract: Systems and methods for determining bi-propellant volume and adjusting a mixture ratio are discussed herein. A controller can calculate an adjusted mixture ratio and command the rocket engine to implement the adjusted mixture ratio by opening or closing valves of the propellant tanks, which changes the volumetric flow rates of each of the propellants. The adjusted mixture ratio can be calculated by an algorithm based on sensed or calculated data associated with each propellant. The adjusted mixture ratio can be used to evenly deplete the propellants to reduce the amount of each propellant remaining after a mission and to improve propellant use, which allows for an increase in a non-propellant payload.

Abstract: Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.

Abstract: Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.