Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Abstract

Landing heavier payloads with pinpoint precision on the surface of Mars is a known challenge for future missions to Mars. Supersonic retropropulsion has been proposed as a means to deliver higher-mass payloads to the surface, traditionally with the sole intent of deceleration. By adding range control capability during the supersonic retropropulsion maneuver by means of thrust vectoring, it has been found that a substantial amount of propellant can be saved in a precision landing scenario when compared with traditional architectures. Decreasing the propellant mass necessary for the mission increases the amount of payload mass that can be brought to the surface. Propellant mass savings greater than 30% are possible if thrust vectoring is unconstrained during the supersonic phase of flight. Propellant mass fraction is found to be sensitive to the divert direction and also the altitude and flight-path angle at ignition, favoring low altitudes and shallow flight-path angles. Decreased nozzle cant angles and aerodynamic drag preservation have also been found to reduce propellant usage.= reference area, m 2 s = range, m T∕W = thrust-to-weight ratio, referenced to Mars surface gravity V = velocity, m∕s β = ballistic coefficient, kg∕m 2 ΔV = change in velocity, m∕s = flight-path angle, defined as positive above the horizon,°θ = off-velocity thrust angle,°∞ = freestream conditions

Simulation and analysis of drag for inflatable aerodynamic decelerator

“…In recent years, SpaceX has realized the recycling of the first stage through the retro-propulsion and attitude control technology of the launch vehicle, which effectively reduces the launch cost and the launch cycle and promotes the development of the reusable launch vehicle (RLV). But a certain amount of propellant is reserved for the reentry process, which results in the loss of carrier capability [2]. In this situation, the inflatable aerodynamic decelerator (IAD) is noticed gradually due to its small size, foldable, and lightweight [3].…”

Advancing Supersonic Retropropulsion Using Mars-Relevant Flight Data: An Overview

“…SRP can also be utilized as additional control authority for precision landing. 17 Computational fluid dynamics tools have been shown capable of capturing major flowfield features, including unsteadiness, albeit at considerable computational expense. [13][14] Recent computational and experimental efforts have demonstrated that, in Mars relevant conditions, thrust requirements are sufficiently high to render the aerodynamic axial force contribution negligible.…”