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EDL – Lessons Learned and Recommendations

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EDL – Lessons Learned and Recommendations ."#!(*"# 0 1(%"##" !)"#!(*"#* 0 1"!#"("#"#(-$" ."!##("""*#!#$*#( "" !#!#0 1%"#"! /!##"*!###"#" #"#!$#!##!("""-"!"##&!%%!%&# $!!# %"##"*!%#'##(#!"##"#!$$# /25-!&""$!)# %"##!""*&""#!$#$! !$# $##"##%#(# ! "#"-! *#"!,021 ""# !"$!+031 !" )!%+041 #!( !"!# #$!"+051 # #$! !%#-" $##"!#""#$#$! %"##"#!#(- IPPW Enabled International Collaborations in EDL – Lessons Learned and Recommendations: Ethiraj Venkatapathy1, Chief Technologist, Entry Systems and Technology Division, NASA ARC, 2 Ali Gülhan , Department Head, Supersonic and Hypersonic Technologies Department, DLR, Cologne, and Michelle Munk3, Principal Technologist, EDL, Space Technology Mission Directorate, NASA. 1 NASA Ames Research Center, Moffett Field, CA [email protected]. 2 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), German Aerospace Center, [email protected] 3 NASA Langley Research Center, Hampron, VA. [email protected] Abstract of the Proposed Talk: One of the goals of IPPW has been to bring about international collaboration. Establishing collaboration, especially in the area of EDL, can present numerous frustrating challenges. IPPW presents opportunities to present advances in various technology areas. It allows for opportunity for general discussion. Evaluating collaboration potential requires open dialogue as to the needs of the parties and what critical capabilities each party possesses. Understanding opportunities for collaboration as well as the rules and regulations that govern collaboration are essential. The authors of this proposed talk have explored and established collaboration in multiple areas of interest to IPPW community. The authors will present examples that illustrate the motivations for the partnership, our common goals, and the unique capabilities of each party. The first example involves earth entry of a large asteroid and break-up. NASA Ames is leading an effort for the agency to assess and estimate the threat posed by large asteroids under the Asteroid Threat Assessment Project (ATAP). Asteroids of size ranging from 10 m to 50 m, much larger, heavier and higher velocity than typical spacecrafts, can cause significant damage as a result of break-up in the atmosphere and sending shock waves towards the ground. Depending on the compositional characteristics of the asteroid and size, typically less than ~5% of the asteroid original mass reaches the surface as a result of break-up and spreading. The spreading of the broken material is postulated to deliver energy to the atmosphere in the form of strong shock wave that travels towards earth. This is akin to sonic boom created by supersonic aircrafts but the strength of the shockwave is much more devastating. NASA and DLR have partnered together to understand the physics behind this phenomenon and have been conducting experiments and computations for over a year. The study of the asteroid entry and break-up problem is also relevant to spacecraft break-up, such as large satellites, during their demise. They are also relevant for designing entry systems for mission assurance during separation of heat-shield and back-shell prior to the deployment of parachute along with science payload. The second example involves planetary entry into planets across solar system. The entry system design requires a better understanding of the aero-thermodynamic characteristics of the flow during entry in different atmospheres on the heatshield and more importantly on the back-shell. In the past, opportunities to instrument flight articles have been neglected due to many reasons. Strong advocacy by the EDL community in the US led to NASA leadership instituting requirements for Engineering Science Investigation (ESI). A direct result of this was instrumented MSL heatshield and now the instrumented aeroshell of Mars 2020. ESA instrument the Mars EDM backshell with COMARS+ sensors. Though the landing of the lander Schiaparelli was not successful, COMARS+ sensor returned data during entry and descent. NASA’s New Frontier proposals, due at the end of April, 2017, requires proposers to respond to the ESI requirements and encourages cost-effective sensors to be part of the proposal. The New Frontiers is a perfect opportunity for international partnership. NASA Ames is working in partnership with DLR and New Frontiers-4 proposal teams in evaluating the viability of the COMARS+ sensor for a host of destinations. This is a first step in the competitive proposal process. Successful selection of a mission that can utilize COMARS+ sensors is necessary and in order to have successful mission implementation has many challenges that need to be tackled. The third example involves Mars. Dust storms at Mars is a well observed phenomenon and yet, the effect of dust, especially high altitude dust that has the potential to cause significant damage to entry heat-shield is poorly understood. Modeling of the heat-shield performance and risk under dusty environment requires not only the characteristics of the dust and also the response of the specific heat-shield material including system aspects such as seams and gaps. NASA’s human missions to Mars will involve entry system that could be an order of magnitude larger and may involve materials that are more susceptible to dust and if robustness is a requirement, then understanding and accounting for dust effects become very important. NASA’s robotic science missions to Mars use very light weight ablative systems such as SLA or PICA. The response of these systems to dust are poor at best. DLR has developed specialized arc jet test facility and test methodology to study dust erosion. A potential for collaboration is currently being explored to develop fundamental understanding of the dust erosion and validate models with data from DLR facility. In this talk, in addition to presenting the goals and technical problem dimensions, focus will be on what makes an international collaboration feasible and acceptable. We will also show how successful collaboration can bring about greater understanding that benefits the community at large. AMBIENT MAGNETIC ENERGY HARVESTING AS AN ASSISTING POWER SOURCE A. Aguilar1, T. Larson2 and A. Davies3 1Student, University of Idaho, 709 S Deakin St, Moscow, ID 83844, [email protected], 2Student, University of Idaho, 709 S Deakin St, Moscow, ID 83844 [email protected], 3Student, University of Idaho, 709 S Deakin St, Moscow, ID 83844, da- [email protected]. Introduction: The purpose of this project is to inves- tigate the viability of an ambient magnetic energy har- vesting and conversion system as an assisting power source applied to CubeSat and SmallSat technology. As CubeSats and SmallSats become increasingly popu- lar for space exploration and usage as probes beyond Earth, alternative power sources should be investigated in order to keep the costs and weight of these satellites down, while still equipping them with sufficient in- strumentation and measurement technology. The am- bient magnetic energy harvesting and conversion sys- tem would carry less mass than battery packs and func- tion in environments where solar energy is not viable such as beneath the clouds of Venus, or in the outer solar system. While this technology is not meant to be a primary source of power, it will be useful for provid- ing additional power during peak load times as well as charging on-board lithium ion batteries. For a magnetic field, a loop antenna is analogous to an electric dipole in an electric field [1]. Since magnet- ic fields are more prevalent in space environments and will likely be present in future CubeSat and SmallSat outer planet exploration, a multi-turn loop antenna was chosen for harvesting and conversion analysis. Using a receiving antenna and impedance matching network, planetary magnetic fields incident upon the antenna, assumed to be traveling through the magnetic field over space and time, result in voltage and current in accordance with Faraday’s Law and that can be uti- lized and transferred to an electrical load. In no load conditions, the antenna has an induced voltage of 1.324 uV, and can transfer 1.306 pW under impedance matched conditions. References: [1] C. A. Balanis (2016) Antenna Theory Analysis and Design INTERPLANETARY NAVIGATION MISSION SUPPORT SYSTEM. M. Feher*1, T. Renteria*1,J. Rodriguez* 1, P. Wu*1, P. Papadopoulos**1, 1RE: Department of Aerospace Engineering San Jose State University, 1 Washington Square, San Jose, CA 95192. The current publication presents a potential solution to deep space interplanetary positioning challenges. Introduction: The design of the interplanetary The future of the SNS is the development of navigation mission support system is expanding the Earth’s SNC. The advantage of Earth’s SNC comes capacity for high accuracy research missions in orbits from creating a more robust infrastructure for high beyond Medium Earth Orbit (MEO). Current satellite accuracy travel within the Earth's sphere of influence. positioning systems are generally in MEO, sending Future SNC’s will be expanded into a network of time and position data towards the Earth. These SNC’s that will support missions that travel to any primarily service ground and Low Earth Orbit (LEO) planetary body within the solar system and further into systems. Current satellite systems that operate beyond deep space. MEO are reliant on trajectory prediction models, radio signal delay and inertia measuring units (IMU) to approximate their position and velocity vector. The work conducted on the Solar Navigation
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