Smart Divert: A New Mars Robotic Entry, Descent, and Landing Architecture

Grant, Michael J.; Steinfeldt, Bradley A.; Braun, Robert D.; Barton, Gregg H.

doi:10.2514/1.47030

Cited by 17 publications

(8 citation statements)

References 11 publications

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“…The equations of motion are integrated with a constant-timestep fourth-order Runge-Kutta integration scheme in a planet-centered inertial frame. Versions of the simulation software have been validated and used in previous design studies [16].…”

Section: A Numerical Simulationmentioning

confidence: 99%

Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Mandalia

Braun

2015

Journal of Spacecraft and Rockets

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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

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Section: A Numerical Simulationmentioning

confidence: 99%

Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Mandalia

Braun

2015

Journal of Spacecraft and Rockets

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“…Versions of this simulation have been validated and used in previous design studies. 10 A simulated flight computer allows for the operation of navigation, guidance, and control at different rates. The simulation ends when the vehicle lands at the target altitude, initially set at 0 km.…”

Section: A Numerical Simulationmentioning

confidence: 99%

Supersonic Propulsive Divert Maneuvers for Future Robotic and Human Mars Missions

Mandalia

Braun

2014

AIAA Atmospheric Flight Mechanics Conference

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“…Generally, scientifically interesting landing sites are not flat and contain many landing hazards including significant variation in terrain elevation, craters and rocks [7]. The touchdown spot of previous missions could only be pre-specified to lie within an uncertainty ellipse with a semi-major axis of several kilometers, ranging from 200 to 300 km in the cases of the Pathfinder and Viking landers, and to 80 km in the case of Mars Exploration Rovers.…”

Section: Introductionmentioning

confidence: 99%

Use of Modern Digital Software to Model the Motion Dynamics of Spacecraft during Landing

Koryanov

Heras

2020

ITM Web Conf.

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Landing systems for future space missions in Earth and Mars require trustable technologies capable of achieving their aim in the most accurate way possible. For this purpose, systems should go through rigorous dynamic simulations run by precise and efficient software. This study aims to approximately determine the dynamic motion of a landing vehicle using the modern digital software of Universal Mechanism and MATLAB. Universal Mechanism applies the classic mechanics theory on a model based on the geometry of the spacecraft, taking into account the environmental conditions that affect its motion and the properties of the ground to resist its impact [1]. The forces implied in the vehicle phase of descent are also included in MATLAB code to calculate the landing area of the vehicle according to its re-entry velocity [2-4]. Studies were conducted for different initial conditions and approaches to the surface. As a result, the values of the arising overloads and forces acting on the descent vehicle were obtained [1]. The data provided by the simulations conclude the safest landing options that should be taken into account for the success of future missions.

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Smart Divert: A New Mars Robotic Entry, Descent, and Landing Architecture

Cited by 17 publications

References 11 publications

Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Supersonic Propulsive Divert Maneuvers for Future Robotic and Human Mars Missions

Use of Modern Digital Software to Model the Motion Dynamics of Spacecraft during Landing

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