Human Mars lander design for NASA's evolvable mars campaign

Polsgrove, Tara; Chapman, John S.; Sutherlin, Steve; Taylor, Brian D.; Robertson, Ed; Studak, Bill; Vitalpur, Sharada; Fabisinski, Leo; Lee, Allan Y.; Collins, Tim; Cianciolo, Alicia Dwyer; Samareh, Jamshid A.; Rakow, Glenn

doi:10.1109/aero.2016.7500778

Cited by 22 publications

(9 citation statements)

References 7 publications

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“…First, the simulation parameters and initial values need to be given. The probe configuration is similar to the human Mars lander mentioned in Reference [20]; however, the separation device for an inflatable aerodynamic decelerator is added, and the Mars descent module (MDM) is removed, so the total mass was reduced to 45 metric tons. The parameters are shown in Table 1.…”

Section: Simulation Condition Andmentioning

confidence: 99%

Analytical Predictive Guidance Algorithm Based on Single Ballistic Coefficient Switching for Mars Aerocapture

Peng

et al. 2019

International Journal of Aerospace Engineering

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Aerocapture can significantly reduce the velocity increment required for a planetary orbital mission and reduce the amount of propellant needed. And it may be one of the key technologies necessary for large-scale space exploration missions in the future. In this paper, the analytical solution of aerocapture based on the piecewise variable ballistic coefficient is studied around the exploration of Mars. An aerocapture analytical predictive guidance algorithm for single ballistic coefficient switching is proposed. The terminal velocity after the ballistic coefficient switching can be obtained by analytical calculation in real time. The adaptive control of the switching time of the ballistic coefficient is realized. The simulation results show that the guidance algorithm is accurate and robust, which can effectively overcome the influence of atmospheric density error, aerodynamic parameter error, and initial state uncertainty.

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Section: Simulation Condition Andmentioning

confidence: 99%

Analytical Predictive Guidance Algorithm Based on Single Ballistic Coefficient Switching for Mars Aerocapture

Peng

et al. 2019

International Journal of Aerospace Engineering

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“…The six degree-of-freedom (DoF) simulation is built using the Program to Optimize Simulated Trajectories -II (POST2) software 4 . In this simulation, the PDV model is based on a human Mars mission architecture outlined by NASA's evolvable Mars campaign 5,6 . The PDV initial mass is 46.4 mt (of which 9.5 mt is fuel) and utilizes eight fixed engines with a maximum thrust of 100 kN per engine for deceleration 5,6 .…”

Section: Trajectory Simulationmentioning

confidence: 99%

Adaptive Control Allocation for Powered Descent Vehicles

Green

Lindberg

2018

2018 Space Flight Mechanics Meeting

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The following work details a study into real-time failure adaptive control allocation method for powered descent vehicle systems. The motivation for this work is to enable future human and robotic missions utilizing a powered descent system to tolerate engine failures in flight without the loss of crew or assets. This study is conducted using a six degree-of-freedom trajectory simulation of a PDV experiencing either a loss of thrust or an engine stuck full on failure scenario. Sequential least squares in the frequency domain is used on-board to process inertial measurement unit (IMU) data and generate an estimate of the PDV plant model, which is then fed to the guidance and control system. Data used by the sequential least squares method is generated from an in-flight maneuver. The work herein focuses on determining a maneuver that is least impactful to the PDV trajectory and enables a suitable plant model estimate. A 1.5 s long maneuver with an amplitude of 5% throttle is determined to provide suitable data for the sequential least squares method to estimate a plant model. A PDV implementing this method can adapt to a single engine failure and continue to reach its touchdown conditions.

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“…Developing system analysis capability requires a significant initial effort. The results will help identify critical drivers and high payoff technologies (Samareh et al, 2014;Polsgrove et al, 2016) through system sensitivity analysis. Two approaches that are relevant to space applications are discussed next: gear ratio and a simple rocket equation that are useful in providing the big picture, and integrated systems analysis for more detailed systems level assessment.…”

Section: Systems Analysismentioning

confidence: 99%

“…The system must be designed to survive both aerocapture and EDL. The hypersonic inflatable aerodynamic decelerator (HIAD) is one of the several candidates that NASA is considering (Polsgrove et al, 2016). The current system consists of two separate HIADs with mass of 4-5 t for each aeroshell.…”

Section: Integrated Systems Analysismentioning

confidence: 99%

Systems analysis of carbon nanotubes: opportunities and challenges for space applications

Samareh

Siochi

2017

Nanotechnology

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Recent availability of carbon nanotubes (CNTs) in quantities and formats amenable to producing macroscale components invites consideration of these materials in space applications where their attractive properties can enable the realization of bold concepts for affordable space exploration. The challenge is to identify relevant systems and quantify the benefits at the systems level. Before significant investment or adoption of CNTs for large aerospace systems can be justified, there must be a plausible path to attain the perceived systems level benefits. This challenging step requires a close collaboration among experts on CNTs and aerospace system communities. This paper provides an overview of a few relevant potential CNTs applications for space systems and the gap that must be overcome for deployment of CNTs. It also provides a simple engineering-level systems analysis approach to quantify the benefits of using CNTs over state of the art material solutions.

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Human Mars lander design for NASA's evolvable mars campaign

Cited by 22 publications

References 7 publications

Analytical Predictive Guidance Algorithm Based on Single Ballistic Coefficient Switching for Mars Aerocapture

Analytical Predictive Guidance Algorithm Based on Single Ballistic Coefficient Switching for Mars Aerocapture

Adaptive Control Allocation for Powered Descent Vehicles

Systems analysis of carbon nanotubes: opportunities and challenges for space applications

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