The EDS, a self-bootstrap large scale industry in deep space
指数深空，一种大尺度空间工业自举建设方法
Abstract
包含学术研究类文章摘要的四要素：研究目的、方法、结果、结论；综述类的文章，应涵盖该领域的主要成果和研究进展，提出作者的观点和见解，指出这一主题继续研究的方向......(8.5 Pt宋体)
建议关键词为4-8个，从大领域、小领域、研究方法、研究对象、使用数据、主要结果、热点检索词等方面精选关键词(8.5 Pt宋体)
参考文献(References)
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Structure mass of space system is a critical limitation for the launch to orbit and takes a significant part of large equipment. The further investigation includes on-orbit assembly, in-situ resource utilization of fuels and build materials etc. However, relatively sustainable exponential expansion of the industry is needed to get large scale space industries. We propose the concept of Exponential Deep Space (EDS) here to enable exponential scaling of industry in deep space to achieve the goal above.
空间系统的结构质量在发射入轨过程中是个非常严格的限制，同时也是大型设备总质量中非常重要的一部分，探索中的工作包括在轨组装，燃料与建造材料的原位资源利用等。然而，可持续的指数增长是构建大尺度空间工业很重要的部分。为了达到以上目标本文提出了指数深空（Exponential Deep Space, EDS）的概念以获得深空工业的指数增长能力。
A systematic method of utilizing solar energy for smelting and fabrication in metallic Near Earth Asteroid (NEA) is proposed in this paper. Solar collector enables in situ melting and forming for structural materials. After that, we utilize a space robot arm system to replicate the solar collector and other key structures include the robot arms itself to enable exponential growth of deep space industries. A reasonable payload has been planned to meet the requirement of the launch system for the initial base package. The key challenge has been analyzed including positioning/attitude of the solar collector, metallurgy problem under micro-gravity/vacuum environment, and the failure rate influences of the autonomous system. Series of evidence of the existence of metallic NEA have been proposed, including the requirement of the properties of the target NEA.
本文介绍了利用太阳能对金属类近地小行星进行熔融与生产的方法体系并进行了基础的评估与理论计算。太阳能收集阵列对金属类小行星本体进行原位加热熔融，这一部分得到了相应的热仿真模型的数据支持。获得了熔融的加热金属后几种结构成型方法进行了评估。之后，我们使用空间机械臂系统复制太阳能收集阵以及包括机械臂本体的其他关键结构以获得空间工业的指数增长。接下来本文计划了适合初始基地包发射运载的质量分配，并对例如太阳能收集阵姿轨控、微重力与真空环境下的冶金问题、自动化系统的失效率等一系列挑战进行了分析。本文还介绍了一系列金属类近地小行星存在性的证据，以及目标近地小行星的一些基本特性需求。
Several potential applications have been evaluated in the 5th section of the paper. Finally, we estimated the sustainable throughput with rational supplements from the earth industry and potential further developments have been discussed.
文章的第五部分评估了一系列潜在的应用。最后，我们估计了在地球工业提供适度补给下上述指数深空可持续的生产规模，以及在这一基础下进一步的展望。
1. Background
2. The method
3. Challenge of engineering
3.1. Solar collector
3.2. Metallurgy and shaping
构件理论强度以加压舱需求为例，晶胞vs冷却速度
3.3. Autonomous system
4. Does metallic NEA exist?
4.1. Evidence
4.1.1. Radar observations
4.1.2. Crate of Greenland
4.1.3. Statistic survey of available crate
4.2. Requirement
4.2.1. Component content
4.2.2. Orbit
4.2.3. Spin
5. Applications
5.1. Solar Power Satellites (SPS)
5.2. Cabin section
5.3. Large scale radio telescope
5.4. Interplanetary transfer vehicle
6. Further developments and conclusion
6.1. Propellant harvest from C/S-type
6.2. Mass driver, Interplanetary launch system (
6.3. Space city (
6.4. The scale (7. conclusion
autonomous breakdown (comparing with lunar1982 etc historically, ImageNet/warcraft etc, should be a awarded challenge contest
- sensing
- recognization
- movement planning
- online monitoring
- hierarchical planning/optimization
analysis of failure rate
- hardware tri redundant
- software double tri redundant
Reference
MARS GAS STATION: TRANSITION FROM INDEPENDENT MISSIONS OF PROPELLANT PRODUCTION HARDWARE TO EXTRATERRESTRIAL “GAS STATIONS” SUPPORTING REUSABLE LANDERS
The most recent comprehensive mission architecture for human missions to Mars is the NASA Design Reference Architecture V5 (DRA5), which includes in-situ production of liquid oxygen (LOX) from atmospheric methane as a critical mission factor in drastically reducing the mass of oxygen required to be sent to Mars. The atmosphere-only fuel production option is selected, since prospecting and extracting water on Mars was deemed too risky. However, if this problem can be solved, much lower energy processes to produce LOX while at the same time producing methane fuel can be achieved.
This study examined several candidate technologies for methane production on Mars, evaluating the processing requirements, and calculating the energy costs of methane production and storage on the surface. The technology candidates included solid oxide electrolysis (SOXE) to produce LOX only, and several others to produce LOX/methane: Sabatier/electrolysis, Sabatier/SOXE processing, and electrochemical production using ionic liquid cells. In addition to the production energy costs, liquification of the output products as well as energy costs of storage were also calculated.
The study used the detailed designs from the Mars DRA5, augmented with more recent conceptual design specifications of Mars landers from the Evolvable Mars Campaign (EMC). The EMC design has 3 Mars Descent Modules (MDM)s and one Mars Ascent Vehicle (MAV) per human mission. In the EMC design, the propellant production unit fills the MAV tanks for the return to Mars orbit. Using this design envelope, the study calculated the energy increase required to convert from LOX-only, to methane and LOX production, as well as the energy requirements of using the landed mission assets over time to create a Mars gas station infrastructure to provide fuel for the next generation of reusable vehicles. Each human mission would land a power supply, a production plant, and enough storage tanks for its own return flight. However, if these systems continue to produce fuel after the initial mission period, storing the new production in unused landed tanks in the MDMs, then an additional 30t of fuel can be produced per synodic period, per set of landed hardware. After three missions to the same location using this disposable hardware, there would be enough propellant production and storage capability at this Mars base to fully fuel a reusable transport system.
Keywords: (Mars, ISRU, propellant, methane, Sabatier, SOXE)
WHAT’S INSIDE A RUBBLE PILE ASTEROID? DISCUS - ATOMOGRAPHIC TWIN RADAR CUBESAT TO FIND OUT
A large fraction of asteroids with diameter d > 240 m are suspected to be loose piles of rocks
and boulders bound together mainly by gravity and only weak cohesion. Still to date the size
and distribution of voids and monolithic fragments inside these "rubble-piles" are not known.
To perform a full tomographic interior reconstruction a bistatic CubeSat configuration has
been investigated by Tampere University of Technology (TUT), Radar Systemtechnik GmbH
(RST) and the Max Planck Institute for Solar System Research (MPS). The concept is based
on two 6U CubeSats, both carrying an identical 1U sized stepped frequency radar. As stepped
frequency radars can be built compact, require less power and generate less data volume
compared to other radar applications they are well-suited for small satellite platforms. In 2017
the Concurrent Design Facility of ESA/ESTEC conducted two studies relevant for DISCUS. In
the Small Planetary Probes (SPP) study DISCUS served as a reference payload for a piggyback
mission to a Near-Earth Asteroid (NEA) or even a Main Belt Asteroid (MBA). The M-ARGO
study investigated a stand-alone mission to a NEA, with a DISCUS sized instrument. Based
on the spacecraft design of SPP and M-ARGO we could prove the instrument requirements
as feasible and evaluate our science case from the orbits and mission duration that have been
identified by these studies. Using inversion methods developed for medical tomography the
data would allow to reconstruct the large scale interior structure of a small body. Simulations
have shown that the measurement principle and the inversion method are robust enough to
allow full reconstruction of the interior even if the orbits do not cover the entire surface of
the asteroid. The measurement results of the mission will help to gain a better understanding
of asteroids and the formation mechanisms of the solar system. In addition, the findings
will increase the predictability of asteroid impact consequences on Earth and improve future
concepts of asteroid deflection.
Introduction
space industry in need
aim, self bootstrap large scale of industry in space
Background
the isru Survey, state of arts now, [1982Lunar, Donald Rapp, Project RAMA] etc.
limitation, capacity in need of IBP, human/autonomous
exponential [Dyson, .., etc]
Method
ExponentialDeepSpace/exponentialdeepspace.github.io#2 (comment)
metal asteroid
mirror/solar pumped laser [Vasile], simulation
加来道雄与nasa some one火星加热规划
mech/magnatics [magnatic float, etc]
zone melting []
powder/thin rolling/cold source []
foil/steel mirror []
robotics [MadeInSpace, orbitRTK, RepSat]
ExponentialDeepSpace/exponentialdeepspace.github.io#7
http://exponentialdeepspace.org/eds-calc/
Plan
plan of IBP [Apollo, 1982Lunar, etc]
scale of exponential
Challenges
in search of M-type
fix position of mirror array
failure rate
Conclusion
the feasibility of eds
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