Angle of Attack Modulation for Mars Entry Terminal State Optimization

Lafleur, Jarret M.; Cerimele, Christopher J.

doi:10.2514/6.2009-5611

Cited by 13 publications

(4 citation statements)

References 3 publications

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“…Angle-of-attack modulation has also been investigated for Mars entry [16] and shown feasible for aerocapture missions [17]. Direct force control is yet another control mode for entry vehicles, which uses active flaps to create moments and controls the angle-of-attack and side slip angles [18].…”

Section: Vehicle Designsmentioning

confidence: 99%

Aerocapture, Aerobraking, and Entry for Robotic and Human Mars Missions

Lu¹

2020

Mars Exploration - A Step Forward

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This chapter provides an overview of the aeroassist technologies and performances for Mars missions. We review the current state-of-the-art aeroassist technologies for Mars explorations, including aerocapture, aerobraking, and entry. Then we present a parametric analysis considering key design parameters such as interplanetary trajectory and vehicle design parameters (lift-to-drag ratio, ballistic coefficient, peak g-load, peak heat rate, and total heat load) for aerocapture, aerobraking, and entry. A new perspective on a rapid aerobraking concept will be provided. The analysis will include first-order estimates for thermal loading, thermal protection systems material selection, and vehicle design. Results and discussion focus on both robotic missions and human missions as landed assets and orbiters.

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Section: Vehicle Designsmentioning

confidence: 99%

Aerocapture, Aerobraking, and Entry for Robotic and Human Mars Missions

Lu¹

2020

Mars Exploration - A Step Forward

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“…The ellipsled aerobrake configuration may hold merit for design payloads with a volume requirement exceeding that of manned GEO satellite servicing, overall resulting in increased vehicle size and relaxed aeroheating constraint. The aeroshell definition and subsequent performance and mass estimates are based on the COBRA Ellipsled series of vehicle publications (16,17) .…”

Section: Vehicle Concept Descriptionmentioning

confidence: 99%

Orbital transfer vehicle (OTV) system sizing study for manned GEO satellite servicing

et al. 2016

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In an effort to quantify the feasibility of candidate space architectures for astronauts servicing Geosynchronous Earth Orbit (GEO) satellites, a conceptual assessment of architectureconcept and operations-technology combinations has been performed. The focus has been the development of a system with the capability to transfer payload to and from geostationary orbit. Two primary concepts of operations have been selected: (a) Direct insertion/re-entry (Concept of Operations 1 -CONOP 1); (b) Launch to low-earth orbit at Kennedy Space Center inclination angle with an orbital transfer to/from geostationary orbit (Concept of Operations 2 -CONOP 2). The study concludes that a capsule and de-orbit propulsion module system sized for the geostationary satellite servicing mission is feasible for a direct insertion/re-entry concept of operation CONOP 1. Vehicles sized for CONOP 2 show overall total mass savings when utilising the aero-assisted orbital transfer vehicle de-orbit propulsion module options compared to the pure propulsive baseline cases. Overall, the consideration of technical, operational and cost factors determine if either the aero-assisted orbital transfer vehicle concepts or the re-usable/expendable ascent/de-orbit propulsion modules is the preferred option.

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“…A lower ballistic coefficient vehicle decelerates higher in the atmosphere, providing additional timeline and altitude margin necessary for heavier payloads. 6 According to the EDL-SA, some type of IAD implementation is an anticipated necessary component to be able to land larger payloads on the Mars surface. 4 This investigation assesses the candidacy of three blunt, asymmetric HIAD families proposed for Mars entry by evaluating inherent aerodynamic characteristics for each configuration and making comparisons to a symmetric counterpart.…”

Section: Objectivementioning

confidence: 99%

Asymmetrically Stacked Tori Hypersonic Inflatable Aerodynamic Decelerator Design Study for Mars Entry

Harper

Braun

2014

AIAA Atmospheric Flight Mechanics Conference

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The Mars missions envisioned in the future require payload mass in excess of the current capable limit for entry vehicle technology. Deployable Hypersonic Inflatable Aerodynamic Decelerators offer one solution to successfully carry out the beginning of an entry architecture as payload mass increases. The majority of the research that has been conducted on these structures only focuses on axisymmetric geometries. In this investigation, aerodynamic performance and stability is examined for three proposed asymmetric families that can generate non-zero lift-to-drag ratios at 0° angle of attack. Advantages of an asymmetric lifting Hypersonic Inflatable Aerodynamic Decelerator include a larger entry corridor, reduced peak heating, larger range, and improved landing accuracy. In particular, there is potential to increase drag performance and reduce ballistic coefficient to mitigate entry, descent, and landing concerns. Blunt, asymmetric Hypersonic Inflatable Aerodynamic Decelerator designs considered are assembled from stacked tori configurations with a base diameter of 20 m and the capability to interface with a 10 m diameter rigid center body. The configurations considered are capable of producing hypersonic lift-to-drag ratios between ~0.6 and ~0.1 for angles of attack ranging from-30° to 20°. A 40 (t) entry mass, approximate mass of large robotic or human scale mission, is assumed resulting in ballistic coefficients from ~78 kg/m 2 to ~113 kg/m 2. From the analyses conducted thus far, encouraging results project asymmetric Hypersonic Inflatable Aerodynamic Decelerators as conceivable candidates for future large scale Mars missions.

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Angle of Attack Modulation for Mars Entry Terminal State Optimization

Cited by 13 publications

References 3 publications

Aerocapture, Aerobraking, and Entry for Robotic and Human Mars Missions

Aerocapture, Aerobraking, and Entry for Robotic and Human Mars Missions

Orbital transfer vehicle (OTV) system sizing study for manned GEO satellite servicing

Asymmetrically Stacked Tori Hypersonic Inflatable Aerodynamic Decelerator Design Study for Mars Entry

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