The startup’s next step is launching two fully operational satellites this year, with an ambition to build in-orbit computing.

This Hyderabad Startup is Building India’s First AI Lab in Orbit

A Russian spacecraft launched higher than most satellites has long had the Pentagon worried — and it apparently has a space nuke on it.

US Military Alarmed by Russian Nuclear Weapon Platform in Orbit

Space Banana SpaceX's latest test flight of its Starship spacecraft carried a highly unusual payload into orbit: a single banana. Footage showed the interior of the behemoth rocket being adorned with one, lonely piece of fruit. It also conveniently puts the size of the spacecraft to scale.

Starship Shoots Into Orbit With Single Banana in Cargo Hold

"X-37B missions have continuously advanced our nation's space capabilities by testing new technologies that reduce risk and inform our future space architectures," said program director for Boeing's Experimental Systems Group Holly Murphy in the video.

Boeing's Military Space Plane Just Slammed on the Brakes in Orbit

Some of the world's leading space experts are warning that the current space junk crisis surrounding our planet is soon to reach a head.

A Massive Space Junk Disaster in Orbit Is Inevitable Now, Scientists Warn

Orbit

orbit

Table of Links Abstract and 1. Introduction Clock in Orbit
2.1 Coordinate Time
2.2 Local Frame for the Moon


Clock Rate Differences Between Earth and Moon


Clocks at Earth-Moon Lagrance Points
4.1 Clock at Lagrange point L1
4.2. Clock at Lagrange point L2
4.3. Clock at Lagrange point L4 or L5


Conclusions Appendix 1: Fermi Coordinates with Origin at the Center of the Moon Appendix 2: Construction of Freely Falling Center of Mass Frame Appendix 3: Equations of Motion of Earth and Moon Appendix 4: Comparing Results in Rotating and Non-Rotating Coordinate Systems Acknowledgments and References 5. CONCLUSION We presented a model based on Keplerian orbits for establishing coordinate time on the Moon and rates of clocks at Lagrange points in cislunar space. We have used values for Keplerian orbit parameters that can be looked up; the only parameters that fit were the times of periapsis passage. The main numerical results obtained using our approach are given in Table II. We assumed a fixed eccentricity and fixed value for the semi-major axis for the Moon’s orbit around the Earth, as the present-day values for these parameters are very slowly varying [13]. Authors:
(1) Neil Ashby, National Institute of Standards and Technology, Boulder, CO 80305 (Neil.Ashby@Colorado.Edu);
(2) Bijunath R. Patla, National Institute of Standards and Technology, Boulder, CO 80305 (bijunath.patla@nist.gov). This paper is available on arxiv under CC0 1.0 license. Table of Links Abstract and 1. Introduction Abstract and 1. Introduction Clock in Orbit
2.1 Coordinate Time
2.2 Local Frame for the Moon Clock Rate Differences Between Earth and Moon Clocks at Earth-Moon Lagrance Points
4.1 Clock at Lagrange point L1
4.2. Clock at Lagrange point L2
4.3. Clock at Lagrange point L4 or L5 Conclusions Clock in Orbit 2.1 Coordinate Time 2.2 Local Frame for the Moon Clock in Orbit Clock in Orbit 2.1 Coordinate Time 2.1 Coordinate Time 2.2 Local Frame for the Moon 2.2 Local Frame for the Moon Clock Rate Differences Between Earth and Moon Clock Rate Differences Between Earth and Moon Clock Rate Differences Between Earth and Moon Clocks at Earth-Moon Lagrance Points 4.1 Clock at Lagrange point L1 4.2. Clock at Lagrange point L2 4.3. Clock at Lagrange point L4 or L5 Clocks at Earth-Moon Lagrance Points 4.1 Clock at Lagrange point L1 4.1 Clock at Lagrange point L1 4.2. Clock at Lagrange point L2 4.2. Clock at Lagrange point L2 4.3. Clock at Lagrange point L4 or L5 4.3. Clock at Lagrange point L4 or L5 Conclusions Conclusions Conclusions Appendix 1: Fermi Coordinates with Origin at the Center of the Moon Appendix 1: Fermi Coordinates with Origin at the Center of the Moon Appendix 2: Construction of Freely Falling Center of Mass Frame Appendix 2: Construction of Freely Falling Center of Mass Frame Appendix 3: Equations of Motion of Earth and Moon Appendix 3: Equations of Motion of Earth and Moon Appendix 4: Comparing Results in Rotating and Non-Rotating Coordinate Systems Appendix 4: Comparing Results in Rotating and Non-Rotating Coordinate Systems Acknowledgments and References Acknowledgments and References 5. CONCLUSION We presented a model based on Keplerian orbits for establishing coordinate time on the Moon and rates of clocks at Lagrange points in cislunar space. We have used values for Keplerian orbit parameters that can be looked up; the only parameters that fit were the times of periapsis passage. The main numerical results obtained using our approach are given in Table II. We assumed a fixed eccentricity and fixed value for the semi-major axis for the Moon’s orbit around the Earth, as the present-day values for these parameters are very slowly varying [13]. Authors: (1) Neil Ashby, National Institute of Standards and Technology, Boulder, CO 80305 (Neil.Ashby@Colorado.Edu); (2) Bijunath R. Patla, National Institute of Standards and Technology, Boulder, CO 80305 (bijunath.patla@nist.gov). Authors: Authors: (1) Neil Ashby, National Institute of Standards and Technology, Boulder, CO 80305 ( Neil.Ashby@Colorado.Edu ); Neil.Ashby@Colorado.Edu (2) Bijunath R. Patla, National Institute of Standards and Technology, Boulder, CO 80305 ( bijunath.patla@nist.gov ). bijunath.patla@nist.gov This paper is available on arxiv under CC0 1.0 license. This paper is available on arxiv under CC0 1.0 license. available on arxiv available on arxiv

How Keplerian Orbits Help Define Time on the Moon

(1) Samir Chitnavis, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK & Digital Environment Research Institute, Queen Mary University of London, Empire House, Whitechapel E1 1HH, UK;
(2) Thomas J. Haworth, Astronomy Unit, Queen Mary University of London, Mile End Road, London E1 4NS, UK;
(3) Edward Gillen, Astronomy Unit, Queen Mary University of London, Mile End Road, London E1 4NS, UK;
(4) Conrad W. Mullineaux, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK;
(5) Christopher D. P. Duffy, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK & Digital Environment Research Institute, Queen Mary University of London, Empire House, Whitechapel E1 1HH, UK (Email: c.duffy@qmul.ac.uk). Table of Links Abstract and Introduction
2 Methodology
2.1 Local spectral irradiance as a function of stellar temperature
2.2 Thermodynamic model of an oxygenic light-harvesting system
2.3 Lattice model of an oxygenic light-harvesting system
3 Results
3.1 Orbital distances and incident spectral fluxes
3.2 Thermodynamic antenna model: Increasing antenna size in limited PAR
3.3 Lattice antenna model: Increasing the size of a “flat” antenna in limited PAR
3.4 Lattice antenna model: Improving antenna efficiency with an energetic ’funnel’
4 Discussion
Acknowledgements, Author Contribution Statement, Authors disclosure statement and References 3 Results 3.1 Orbital distances and incident spectral fluxes This paper is available on arxiv under CC 4.0 license. (1) Samir Chitnavis, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK & Digital Environment Research Institute, Queen Mary University of London, Empire House, Whitechapel E1 1HH, UK; (2) Thomas J. Haworth, Astronomy Unit, Queen Mary University of London, Mile End Road, London E1 4NS, UK; (3) Edward Gillen, Astronomy Unit, Queen Mary University of London, Mile End Road, London E1 4NS, UK; (4) Conrad W. Mullineaux, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK; (5) Christopher D. P. Duffy, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK & Digital Environment Research Institute, Queen Mary University of London, Empire House, Whitechapel E1 1HH, UK (Email: c.duffy@qmul.ac.uk). (1) Samir Chitnavis, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK & Digital Environment Research Institute, Queen Mary University of London, Empire House, Whitechapel E1 1HH, UK; (2) Thomas J. Haworth, Astronomy Unit, Queen Mary University of London, Mile End Road, London E1 4NS, UK; (3) Edward Gillen, Astronomy Unit, Queen Mary University of London, Mile End Road, London E1 4NS, UK; (4) Conrad W. Mullineaux, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK; (5) Christopher D. P. Duffy, School of Biological and Behavioural Sciences, Queen Mary University of London, Mile End, London E1 4NS, UK & Digital Environment Research Institute, Queen Mary University of London, Empire House, Whitechapel E1 1HH, UK (Email: c.duffy@qmul.ac.uk). Table of Links Abstract and Introduction 2 Methodology 2.1 Local spectral irradiance as a function of stellar temperature 2.2 Thermodynamic model of an oxygenic light-harvesting system 2.3 Lattice model of an oxygenic light-harvesting system 3 Results 3.1 Orbital distances and incident spectral fluxes 3.2 Thermodynamic antenna model: Increasing antenna size in limited PAR 3.3 Lattice antenna model: Increasing the size of a “flat” antenna in limited PAR 3.4 Lattice antenna model: Improving antenna efficiency with an energetic ’funnel’ 4 Discussion Acknowledgements, Author Contribution Statement, Authors disclosure statement and References Abstract and Introduction Abstract and Introduction 2 Methodology 2.1 Local spectral irradiance as a function of stellar temperature 2.1 Local spectral irradiance as a function of stellar temperature 2.2 Thermodynamic model of an oxygenic light-harvesting system 2.2 Thermodynamic model of an oxygenic light-harvesting system 2.3 Lattice model of an oxygenic light-harvesting system 2.3 Lattice model of an oxygenic light-harvesting system 3 Results 3.1 Orbital distances and incident spectral fluxes 3.1 Orbital distances and incident spectral fluxes 3.2 Thermodynamic antenna model: Increasing antenna size in limited PAR 3.2 Thermodynamic antenna model: Increasing antenna size in limited PAR 3.3 Lattice antenna model: Increasing the size of a “flat” antenna in limited PAR 3.3 Lattice antenna model: Increasing the size of a “flat” antenna in limited PAR 3.4 Lattice antenna model: Improving antenna efficiency with an energetic ’funnel’ 3.4 Lattice antenna model: Improving antenna efficiency with an energetic ’funnel’ 4 Discussion 4 Discussion Acknowledgements, Author Contribution Statement, Authors disclosure statement and References Acknowledgements, Author Contribution Statement, Authors disclosure statement and References 3 Results 3.1 Orbital distances and incident spectral fluxes This paper is available on arxiv under CC 4.0 license. This paper is available on arxiv under CC 4.0 license. available on arxiv

Thermodynamic Limits Around M-dwarf Stars: Orbital Distances and Incident Spectral Fluxes

Authors:
(1) Agustin Moreno;
(2) Francesco Ruscelli. Table of Links Abstract
Introduction
Preliminaries
The B-signature
GIT sequence: low dimensions
GIT sequence: arbitrary dimension
Appendix A. Stability, the Krein–Moser theorem, and refinements and References Abstract We address the general problem of studying linear stability and bifurcations of periodic orbits for Hamiltonian systems of arbitrary degrees of freedom. We study the topology of the GIT sequence introduced by the first author and Urs frauenfelder in [FM], in arbitrary dimension. In particular, we note that the combinatorics encoding the linear stability of periodic orbits is governed by a quotient of the associahedron. Our approach gives a topological/combinatorial proof of the classical Krein–Moser theorem, and refines it for the case of symmetric orbits. This paper is available on arxiv under CC BY-NC-SA 4.0 DEED license. Authors: (1) Agustin Moreno; (2) Francesco Ruscelli. Authors: Authors: (1) Agustin Moreno; (2) Francesco Ruscelli. Table of Links Abstract Introduction Preliminaries The B-signature GIT sequence: low dimensions GIT sequence: arbitrary dimension Appendix A. Stability, the Krein–Moser theorem, and refinements and References Abstract Abstract Introduction Introduction Preliminaries Preliminaries The B-signature The B-signature GIT sequence: low dimensions GIT sequence: low dimensions GIT sequence: arbitrary dimension GIT sequence: arbitrary dimension Appendix A. Stability, the Krein–Moser theorem, and refinements and References Appendix A. Stability, the Krein–Moser theorem, and refinements and References Abstract We address the general problem of studying linear stability and bifurcations of periodic orbits for Hamiltonian systems of arbitrary degrees of freedom. We study the topology of the GIT sequence introduced by the first author and Urs frauenfelder in [FM], in arbitrary dimension. In particular, we note that the combinatorics encoding the linear stability of periodic orbits is governed by a quotient of the associahedron. Our approach gives a topological/combinatorial proof of the classical Krein–Moser theorem, and refines it for the case of symmetric orbits. This paper is available on arxiv under CC BY-NC-SA 4.0 DEED license. This paper is available on arxiv under CC BY-NC-SA 4.0 DEED license. available on arxiv

Addressing the General Problem of Studying Linear Stability and Bifurcations of Periodic Orbits

রৈখিক স্থিতিশীলতা এবং পর্যায়ক্রমিক কক্ষপথের বিভাজন অধ্যয়নের সাধারণ সমস্যা সমাধান করা

Behandlung des allgemeinen Problems der Untersuchung linearer Stabilität und Bifurkationen periodischer Bahnen

Abordar el problema general del estudio de la estabilidad lineal y las bifurcaciones de órbitas periódicas

Aborder le problème général de l'étude de la stabilité linéaire et des bifurcations des orbites périodiques

आवर्त कक्षाओं के रैखिक स्थायित्व और द्विभाजन के अध्ययन की सामान्य समस्या का समाधान

周期軌道の線形安定性と分岐を研究する一般的な問題への取り組み

선형 안정성과 주기 궤도 분기 연구의 일반적인 문제 해결

Resolvendo o problema geral do estudo da estabilidade linear e bifurcações de órbitas periódicas

К общей проблеме исследования линейной устойчивости и бифуркаций периодических орбит

Periyodik Yörüngelerin Doğrusal Kararlılığı ve Çatallanmalarının İncelenmesine İlişkin Genel Sorunun Ele Alınması

Giải quyết vấn đề chung của việc nghiên cứu sự ổn định tuyến tính và sự phân nhánh của quỹ đạo định kỳ

解决研究周期轨道的线性稳定性和分岔的一般问题

This paper is available on arxiv under CC 4.0 license.
Authors:
(1) Z. Jennings, Astrophysics Group, Keele University, Staffordshire, ST5 5BG, UK (E-mail: z.jennings@keele.ac.uk);
(2) J. Southworth, Astrophysics Group, Keele University, Staffordshire, ST5 5BG, UK;
(3) K. Pavlovski, Department of Physics, Faculty of Science, University of Zagreb, 10000 Zagreb, Croatia;
(4) T. Van Reeth, Institute of Astronomy, KU Leuven, Celestijnenlaan 200D, B-3001 Leuven, Belgium. Table of Links Abstract and Intro
Observation
Orbital Ephemeris
Radial Velocity Analysis
Spectral Analysis
Analysis of the Light Curve
Physical Properties
Asteroseismic Analysis
Discussion
Conclusion, Data Availability, Acknowledgments, and References
Appendix A: Ephemeris Determination
Appendix B: Iteratively Prewhitened Frequencies
Appendix C: Detected Tidally Perturbed Pulsations 3 ORBITAL EPHEMERIS We also fitted for the linear coefficients u of the quadratic limb darkening (LD) law while quadratic terms were taken from Claret & Bloemen (2011) and Claret (2017) for the Kepler and TESS bands, respectively; we used the estimated atmospheric parameters reported in the KIC to choose the appropriate values for the quadratic coefficients. We performed fits to the WASP light curve but the lower quality of this data compared to the Kepler and TESS light curves means that including these results in the calculation of the overall preliminary eclipse model would lead to less well determined parameters. Thus, we simply include the epochs of primary minimum estimated from the WASP light curves as additional observational constraints on T0 in the preliminary fits to the Kepler and TESS light curves. The adopted values for the light curve parameters from this preliminary analysis were taken as the weighted averages of the results from the fits to the individual Kepler quarters and TESS sectors, where the reciprocal of the squared errors from the covriance matrix were used as weights. These values are given in Table A1, and Fig. 2 shows the fit to the Kepler Quarter 0 light curve; high-frequency variability due to pulsations of the δ Scuti type is clearly visible at all orbital phases in the residuals shown in the lower panel, with amplitudes of around ±0.2 mmag. There seems to be a trend in the O-C diagram compared with the linear ephemeris, with data points corresponding to TESS observations (>1000 cycles) all appearing above the red line. Thus, we also attempted to fit for a quadratic ephemeris, which is represented by the blue dashed line in Fig. 3. However, the corresponding quadratic term was a similar size to its errorbar. We therefore decided to stick with the linear ephemeris which was measured to be: This paper is available on arxiv under CC 4.0 license. Authors: (1) Z. Jennings, Astrophysics Group, Keele University, Staffordshire, ST5 5BG, UK (E-mail: z.jennings@keele.ac.uk); (2) J. Southworth, Astrophysics Group, Keele University, Staffordshire, ST5 5BG, UK; (3) K. Pavlovski, Department of Physics, Faculty of Science, University of Zagreb, 10000 Zagreb, Croatia; (4) T. Van Reeth, Institute of Astronomy, KU Leuven, Celestijnenlaan 200D, B-3001 Leuven, Belgium. This paper is available on arxiv under CC 4.0 license. Authors: Authors: (1) Z. Jennings, Astrophysics Group, Keele University, Staffordshire, ST5 5BG, UK (E-mail: z.jennings@keele.ac.uk); (2) J. Southworth, Astrophysics Group, Keele University, Staffordshire, ST5 5BG, UK; (3) K. Pavlovski, Department of Physics, Faculty of Science, University of Zagreb, 10000 Zagreb, Croatia; (4) T. Van Reeth, Institute of Astronomy, KU Leuven, Celestijnenlaan 200D, B-3001 Leuven, Belgium. Table of Links Abstract and Intro Observation Orbital Ephemeris Radial Velocity Analysis Spectral Analysis Analysis of the Light Curve Physical Properties Asteroseismic Analysis Discussion Conclusion, Data Availability, Acknowledgments, and References Appendix A: Ephemeris Determination Appendix B: Iteratively Prewhitened Frequencies Appendix C: Detected Tidally Perturbed Pulsations Abstract and Intro Abstract and Intro Observation Observation Orbital Ephemeris Orbital Ephemeris Radial Velocity Analysis Radial Velocity Analysis Spectral Analysis Spectral Analysis Analysis of the Light Curve Analysis of the Light Curve Physical Properties Physical Properties Asteroseismic Analysis Asteroseismic Analysis Discussion Discussion Conclusion, Data Availability, Acknowledgments, and References Conclusion, Data Availability, Acknowledgments, and References Appendix A: Ephemeris Determination Appendix A: Ephemeris Determination Appendix B: Iteratively Prewhitened Frequencies Appendix B: Iteratively Prewhitened Frequencies Appendix C: Detected Tidally Perturbed Pulsations Appendix C: Detected Tidally Perturbed Pulsations 3 ORBITAL EPHEMERIS We also fitted for the linear coefficients u of the quadratic limb darkening (LD) law while quadratic terms were taken from Claret & Bloemen (2011) and Claret (2017) for the Kepler and TESS bands, respectively; we used the estimated atmospheric parameters reported in the KIC to choose the appropriate values for the quadratic coefficients. We performed fits to the WASP light curve but the lower quality of this data compared to the Kepler and TESS light curves means that including these results in the calculation of the overall preliminary eclipse model would lead to less well determined parameters. Thus, we simply include the epochs of primary minimum estimated from the WASP light curves as additional observational constraints on T0 in the preliminary fits to the Kepler and TESS light curves. The adopted values for the light curve parameters from this preliminary analysis were taken as the weighted averages of the results from the fits to the individual Kepler quarters and TESS sectors, where the reciprocal of the squared errors from the covriance matrix were used as weights. These values are given in Table A1, and Fig. 2 shows the fit to the Kepler Quarter 0 light curve; high-frequency variability due to pulsations of the δ Scuti type is clearly visible at all orbital phases in the residuals shown in the lower panel, with amplitudes of around ±0.2 mmag. There seems to be a trend in the O-C diagram compared with the linear ephemeris, with data points corresponding to TESS observations (>1000 cycles) all appearing above the red line. Thus, we also attempted to fit for a quadratic ephemeris, which is represented by the blue dashed line in Fig. 3. However, the corresponding quadratic term was a similar size to its errorbar. We therefore decided to stick with the linear ephemeris which was measured to be:

Physical Properties of the Eclipsing Binary KIC 9851944: Orbital Ephemeris

the revolutionary Web3 gaming platform, prepares to streak out of beta with a slew of ground-breaking initiatives that will redefine the way blockchain games are developed. LONDON, United Kingdom, March 28th, 2024/Chainwire/--Metacade, CEO, Russell Bennett, forecasts a series of landmark announcements across Q2 and Q3, 2024. Commencing with the appointment of an advisory board. Jamie King, Dan Hibell, Elly Bradbury, and Anders Christiansen combine premium Web2-Web3 commercial nous to spearhead Metacade’s expansion across Talent, Product, Utility, and Engagement. As blockchain games gear up to embrace one billion players, Metacade will mobilize advancements in game development. Fostering stronger bonds between games and experienced Web3 players, through immersive tournaments designed to improve gameplay. During beta, Metacade experienced high demand for this innovative approach. "Over 60 partners joined the Metacade ecosystem in a few months. It’s evidence that games and gamers seek deeper connection," notes newly appointed advisor Jamie King, co-founder of Rockstar Games. "Metacade's commitment to transform tournaments into a multi-asset environment adds substantial value, offering hyper utility for holders and gamers alike. It’s a big vision, focused beyond a single cycle and I’m looking forward to guiding it."Proflic angel investor and Web 3 guild expert, Dan Hibell adds, “For Web3 gaming to reach mainstream adoption we have to address accessibility and usability. Gamers don’t want to pay outrageous prices for an item or wait for a node validator to process a transaction before getting their seasonal cosmetic item. Metacade exists to help builders improve these Web3 issues, the infrastructure use case is needed industry-wide.” Metacade’s test-play tournament model is already proving successful, attracting a fast-growing community of seasoned Web3 gamers chasing rewards for early-stage feedback. “Community is the most under-valued business asset,” says former Director, Columbia Tristar and seasoned Web3 marketing advisor, Elly Bradbury. “Die-hard communities are built on value add experiences, where belonging is about believing. Metacade has invested in all the right early-stage community layers, building a super fan OG culture showing all the hallmarks of explosive brand growth.” Next stage platform developments draw on partner insights. “Metacade is already booming,” said Bennett. “We have a thriving partner ecosystem with shared values. It’s clear our best shot at backing winners is to innovate frictionless blockchain infrastructure so that our partners can do what they do best; create and innovate.” To meet this expansion, Metacade’s team will be strategically shaped by leading Web3 recruiter and business development expert, Anders Christiansen. With a proven track record, Christiansen has facilitated 100+ c-suite placements across the industry through his previous business Priority Crypto. “Metacade’s novel business plan will depend on forward-thinking people with multi-disciplined experience. I’m excited to bring those leading minds to Metacade.” About METACADE: is a seamless Web3 Gaming platform connecting developers and players through plug-and-play community initiatives. Providing an unfair advantage through early access, dev-player collaborations, and financial rewards. Metacade Contact Elly Bradbury Metacade marketing@metacade.co This story was distributed as a release by Chainwire under HackerNoon’s Business Blogging Program. Learn more about the program here.

Rockstar Co-Founder And All-star Line Up Join Advisory Board To Take Metacade Into Post-Beta Orbit

রকস্টার সহ-প্রতিষ্ঠাতা এবং অল-স্টার লাইন আপ মেটাকেড পোস্ট-বিটা অরবিটে নিয়ে যাওয়ার জন্য উপদেষ্টা বোর্ডে যোগদান করেন

Rockstar-Mitbegründer und All-Star-Besetzung treten dem Beirat bei, um Metacade in die Post-Beta-Umlaufbahn zu bringen

El cofundador de Rockstar y el equipo de estrellas se unen al consejo asesor para llevar Metacade a la órbita post-beta

Le co-fondateur de Rockstar et son line-up All-Star rejoignent le conseil consultatif pour amener Metacade sur l'orbite post-bêta

रॉकस्टार के सह-संस्थापक और ऑल-स्टार लाइन अप मेटाकेड को पोस्ट-बीटा कक्षा में ले जाने के लिए सलाहकार बोर्ड में शामिल हुए

ロックスターの共同創設者とオールスター陣が諮問委員会に参加し、メタケードをベータ後の軌道に乗せる

Rockstar 공동 창업자와 올스타 라인업이 자문위원회에 합류하여 메타케이드를 베타 이후 궤도로 끌어올립니다.

O cofundador da Rockstar e a formação de estrelas unem-se ao conselho consultivo para levar o Metacade à órbita pós-beta

Соучредитель Rockstar и звездный состав присоединились к консультативному совету, чтобы вывести Metacade на орбиту пост-бета-тестирования

Rockstar Kurucu Ortağı ve All-Star Dizilişi, Metacade'i Beta Sonrası Yörüngeye Taşımak İçin Danışma Kuruluna Katıldı

Người đồng sáng lập Rockstar và dàn sao toàn năng tham gia Ban cố vấn để đưa Metacade vào quỹ đạo hậu Beta

Rockstar 联合创始人和全明星阵容加入顾问委员会，推动 Metacade 进入后 Beta 轨道

Orbiter Finance, a pioneering force in the blockchain industry, is making headlines with the introduction of Vizing, an innovative zero-knowledge proof (ZK)-powered Ethereum layer 2 (L2) network. Orbiter Finance has captured the attention of over 3 million users with its cross-chain bridge, facilitating asset swaps across various Layer-2 networks. Strategic Support from Esteemed Backers Building on the momentum gained from its successful 2022 seed round, which attracted investments from distinguished backers like Tiger Global Management and Matrixport, Orbiter Finance now secures strategic support from OKX Ventures. This endorsement underscores the growing confidence in Orbiter Finance's vision and technological capabilities. A ZK Proof Powerhouse Heralds the END GAME for Scaling Vizing leverages Orbiter Finance's expertise in zero-knowledge proof technology to address Ethereum's scalability challenges while enhancing security. With its deep understanding of ZK-powered solutions, Orbiter Finance is poised to usher in a new era of efficiency and reliability for Ethereum users. Expanding Reach with Orbiter Vizing Orbiter Finance is set to diversify its portfolio by introducing Orbiter Vizing, a groundbreaking zero-knowledge proof powered "meta-layer." This innovative addition aims to provide users with enhanced capabilities and streamline their experience within the Ethereum ecosystem. By incorporating Orbiter Vizing into its suite of solutions, Orbiter Finance is poised to further elevate its status in the blockchain space and offer users unparalleled access to advanced technologies. An "Omni-connection" Future Envisioned Central to is the concept of an "omni-connection" future. With Vizing, Orbiter Finance seeks to simplify the process of transferring assets and data across all Layer-2 networks, providing users with a seamless experience. By offering a unified interface, Vizing unlocks new opportunities for collaboration and innovation within the Ethereum ecosystem. Orbiter Finance's mission Orbiter Releases Token Launch Plans: Anticipating a significant milestone, Orbiter Finance has announced plans for a token launch in 2024. The tokenomics and distribution strategy will be gradually unveiled throughout the year, offering users a comprehensive ecosystem that goes beyond Orbiter Bridge and Vizing. This token will play a vital role in governance, incentivization, and value transfer within the Orbiter Finance ecosystem. Orbiter Finance's introduction of Vizing marks a significant step forward in Ethereum's evolution. , Orbiter Finance is well-positioned to lead the charge towards a more scalable and interconnected blockchain infrastructure. As Orbiter Finance continues to unveil its plans for Vizing, the future of decentralized finance looks increasingly promising. Stay tuned for more updates as Orbiter Finance reshapes the landscape of blockchain technology. With OKX Ventures' backing This story was distributed as a release by ZEX MEDIA under HackerNoon’s Brand As An Author Program. Learn more about the program . here

Orbiter Finance Unveils Vizing: A Game-Changing ZK-Powered Ethereum Layer 2 Network

অরবিটার ফাইন্যান্স ভাইজিং উন্মোচন করেছে: একটি গেম-চেঞ্জিং ZK-চালিত ইথেরিয়াম লেয়ার 2 নেটওয়ার্ক

Orbiter Finance stellt Vizing vor: Ein bahnbrechendes ZK-basiertes Ethereum Layer 2-Netzwerk

Orbiter Finance presenta Vizing: una innovadora red Ethereum Layer 2 impulsada por ZK

Orbiter Finance dévoile Vizing : un réseau Ethereum Layer 2 révolutionnaire alimenté par ZK

ऑर्बिटर फाइनेंस ने विज़िंग का अनावरण किया: एक गेम-चेंजिंग ZK-पावर्ड एथेरियम लेयर 2 नेटवर्क

Orbiter Finance が Vizing を発表: 革新的な ZK 搭載イーサリアム レイヤ 2 ネットワーク

Orbiter Finance, Vizing 공개: 판도를 바꾸는 ZK 기반 Ethereum 레이어 2 네트워크

Orbiter Finance revela Vizing: uma rede Ethereum Layer 2 revolucionária alimentada por ZK

Orbiter Finance представляет Vizing: революционную сеть Ethereum Layer 2 на базе ZK

Orbiter Finance, Vizing'i Tanıtıyor: Oyunun Kurallarını Değiştiren ZK Destekli Ethereum Katman 2 Ağı

Orbiter Finance tiết lộ Vizing: Mạng Ethereum lớp 2 được hỗ trợ bởi ZK có thể thay đổi trò chơi

Orbiter Finance 推出 Vizing：改变游戏规则、由 ZK 驱动的以太坊第 2 层网络

You can jump to any section of y The National Cislunar Science & Technology Strateg here. Objective 3: Extend U.S. space situational awareness capabilities into Cislunar space SSA is essential to safe and successful spacecraft operations in all orbits, including in Cislunar space. SSA data, for example, help satellite operators avoid collisions with other satellites or debris, support rendezvous and proximity operations, and enable the identification of anomalous, irresponsible, or potentially dangerous spacecraft operations and space weather phenomena of significance. Expanded SSA capabilities will also provide benefits to, and benefit from, future missions to detect and warn of incoming potentially hazardous asteroids. The U.S. government will aim to understand the long-term effects of growing human activities on the Cislunar environment, and to preserve a safe and sustainable environment in Cislunar space—such as limiting debris in Lunar orbit. The following sub-objectives will advance this objective: Though there are designs for preliminary program architectures, a comprehensive framework for the SSA R&D needs for Cislunar space remains undeveloped. The United States will support R&D to advance technology useful for Cislunar SSA, including improved monitoring methods and better understanding of Cislunar orbit families and spacecraft dynamics. In pursuing this work, the United States will leverage work undertaken across the Federal government, the private sector, and relevant standards developing organizations. The United States should pursue cooperation with all entities operating in Cislunar space to identify and track emerging requirements, and make recommendations for SSA and transparency improvements. Evaluate SSA needs, priorities, and existing gaps for extending current SSA capabilities into Cislunar space. The United States should advance Cislunar SSA by initially identifying an architecture that optimizes terrestrial, Lunar-based, and space-based sensors, then leveraging existing ground-based sensors and developing new ground-based sensors as needed. Existing sensors should be investigated to determine if upgrades and/or modification to sensor software and hardware can improve detection of objects in Cislunar space. The U.S. government will support demonstrations of new, cost-effective terrestrial sensing capabilities optimized for Cislunar space, as well as continue developing and testing cost-effective space-based sensors for Cislunar SSA. These in-space tests should leverage orbits available in Cislunar space that can potentially enhance SSA capabilities. U.S. government organizations will leverage partnerships with the private sector to reduce the cost of Cislunar SSA capabilities. Develop or improve current ground-based sensors, and demonstrate cost-effective space-based and Lunar surface sensors, as needed. The scale and geometry of Cislunar space makes global networks of diverse sensors valuable to robust SSA, highlighting the value of international and private sector collaboration. The United States will pursue Cislunar SSA sharing with international collaborators, private sector actors, and academic institutions operating in Cislunar space. This could include joint research and development efforts, joint efforts on standards, and other areas. Due to the global importance of Cislunar SSA, the U.S. government will explore opportunities to increase the volume and speed of science and avoid duplication while coordinating critical overall efforts. Increase cooperation and data-exchanges with other users of Cislunar space. Data formatting and standards between the U.S. government and private and international space missions will need to be coordinated to ensure compatibility. The U.S. government will develop and maintain an integrated catalog of Cislunar objects, both natural and human-made, utilizing data from all available sources and in collaboration with private entities. The catalog should include human-made objects on the Lunar surface. The catalog should also include information about objects that can aid in assuring compatible coexistence with spacecraft and scientific investigations, including those from the Shielded Zone of the Moon. If possible, satellite operators should periodically provide their planned maneuvers and trajectories to the catalog. Develop an integrated Cislunar object catalog. Consistent with national policy, including Space Policy Directive-3, the U.S. government will continue to share SSA information and provide basic spaceflight safety services to all space operators. A civilian open data platform will be used to leverage Cislunar SSA data and services provided from a variety of government, commercial, academic, and international sources. Additional discovery and characterization of potentially hazardous objects may leverage the International Astronomical Union’s (IAU) Minor Planet Center, the longstanding U.S. contribution via NASA’s Office of Planetary Defense. Develop procedures for publicly sharing Cislunar space situational awareness data, as well as navigation and spaceflight safety support in Cislunar space. This content was initially published on in November 2022. whitehouse.gov This content has been broken-up into bite sized sections each with unique headlines and AI-generated lead images in line with the provisions of Creative Commons 3.0.

Guardians of the Galaxy: U.S. Ambitions to Expand Space Awareness Beyond Earth's Orbit

গ্যালাক্সির অভিভাবক: পৃথিবীর কক্ষপথের বাইরে মহাকাশ সচেতনতা প্রসারিত করার জন্য মার্কিন উচ্চাকাঙ্ক্ষা

Guardians of the Galaxy: Ambitionen der USA, das Weltraumbewusstsein über die Erdumlaufbahn hinaus zu erweitern

Guardianes de la Galaxia: Ambiciones de Estados Unidos para expandir la conciencia espacial más allá de la órbita terrestre

Gardiens de la Galaxie : les ambitions américaines d'étendre la sensibilisation à l'espace au-delà de l'orbite terrestre

गैलेक्सी के संरक्षक: पृथ्वी की कक्षा से परे अंतरिक्ष जागरूकता का विस्तार करने की अमेरिकी महत्वाकांक्षाएँ

ガーディアンズ・オブ・ギャラクシー：地球の軌道を超えて宇宙への意識を拡大するという米国の野心

가디언즈 오브 갤럭시: 지구 궤도 너머로 우주 인식을 확장하려는 미국의 야망

Guardiões da Galáxia: ambições dos EUA para expandir a consciência espacial além da órbita da Terra

Стражи Галактики: амбиции США по расширению космической осведомленности за пределами земной орбиты

Galaksinin Koruyucuları: ABD'nin Uzay Bilincini Dünya Yörüngesinin Ötesine Genişletme Hırsları

Những người bảo vệ thiên hà: Tham vọng của Hoa Kỳ nhằm mở rộng nhận thức về không gian ngoài quỹ đạo Trái đất

银河护卫队：美国将太空意识扩展到地球轨道之外的野心

The purpose of my project is to build a system for tracking satellites in orbit. The system will position directional antennas and make it possible to communicate with the satellites. The project requires stepper motors with high torque. Supplies a planetary gearbox stepper motor gerar ratio 100:1 a large bearing a hexagonal piece a 12 mm steel drive shaft extension a rigid flange coupling motor guide 3d printed pieces a few circuits based around the Trinamic Motor Control TMC2041 IC a motion sensor through hole slip rings Step 1: The Installation of the Motor The installation of the motor was somewhat complicated. It included designing a center Pilon inside the enclosure to seat the motor. Then, manufacturing of a metal plate to bolt the motor to the pilon. Next, a large bearing was bolted to the top of the frame and the rotor was then bolted to the bearing. The top of the drive shaft was fitted with a hexagonal piece that mated with the bottom of the rotor. The rotor was then electrically coupled to the lower unit via slip ring. In addition to these components, I made a 12 mm steel drive shaft extension and used it with a bore brass shaft coupler from. The purpose of this device is to couple the motor shaft to the extension shaft. The Slip ring was then added onto the extension shaft. Finally, a rigid flange coupling motor guide was placed on top of the extension shaft, this made it possible for me to fit the hexagonal-shaped drive piece onto the top of the shaft and couple the motor to the rotor. This final piece was 3d printed because of its unique shape and enabled me to drive the rotor. Unfortunately, the plastic is not very strong and the result is the rotor has about 5 degrees of wiggle back and forth. However, this is a difficult problem to solve. I am hoping to fix this problem in the newer model that I plan on building. In addition, I hope by selecting the high precision planetary gearbox motor will give me less wiggle on the motor than the economy planetary gearbox I used on the previous model. Step 2: Drive the Motor To drive the motor I have designed and assembled a few circuits based around the Trinamic Motor Control TMC2041 IC. This integrated chip simplifies the driving of stepper motors, making it possible to drive up to two motors from a single chip. This IC boasts a remarkable 1/256 micro stepping resolution. This also gives the unit a remarkable step resolution that can be calculated as the steps per degree of the motor (1.8 degrees/57 gear ratio) then divide this quantity by the microstep resolution of 256. The resulting step resolution of the current project is then 0.000150 degrees of 150 millionths of a degree. This extremely fine resolution gives rise to very smooth motor accelerations and further enhances the utility of your motors. Step 3: Measure Accelerations and Read Direction Unfortunately, the current circuit does not allow for use of the rotary encoder built into the motor. As a result, the device uses a motion sensor attached to the rotor to measure accelerations and read direction. Although it would be very useful to me to have an encoder, I can not free up enough GPIO pins to read all of the pins of the encoder. With the new motor, which has 1:100 gear ratio the new design will achieve a 70 millionths of a degree resolution. This will be yet another improvement that will lead to smoother motor motion and more accurate performance. Wrapping Up The purpose of my project is to build a system for tracking satellites in orbit. The system will position directional antennas and make it possible to communicate with the satellites. The project requires stepper motors with high torque.

DIY Tutorial: Building a System to Track and Communicate with Satellites in Orbit

Donald Trump demanded NASA land humans on the moon in 2024 and increased funding for the agency. But the deadline kept shifting to the right. Now even 2027 is in question - industry experts doubt Axiom's ability to create a spacesuit for lunar conditions. Donald Trump demanded NASA In parallel, Elon Musk said, “We will fly straight to Mars, the Moon is a distraction.” The billionaire's critics suggested that he was having trouble with the landing module and wanted to get out of the lunar project while saving face. And then the media also investigated that the new leadership of NASA plans to abandon the SLS rocket and the Orion spacecraft. That is, except for Musk, who gave up on the Moon, the agency will simply have no other carrier capable of delivering people to Earth's satellite. From the outside, the Artemis III lunar program looks like poorly managed chaos. Does this mean that landing on the moon won't happen in the next few years? Artemis III lunar program The photo below shows an astronaut on the moon during the Artemis III mission. The picture is not just an artist's fantasy - it shows the scope of ambition of the planners of the new mission. The spacesuits of the times of the first flights to Selene did not allow anything like this: it was unreal to bend legs at 90 degrees and stand in them, astronauts moved barely bending their legs, and sometimes even jumped. Now, mankind knows much more about the Moon and, in theory, should be capable of new achievements there. Including the exploration of the Moon's south pole, which is rich in ice and permafrost, and providing astronauts with fundamentally new technical means. Let's imagine that we have been invited to lead a long and complex project, the intricacies of which are sometimes not fully understood by the developers. After all, they were once called in to correct the faults of those who came before them. This is the situation with the project “Artemis III” - the return of astronauts to the moon in 2027 or later. The current solutions to the project seem like a dead end. But what went wrong, and how might events unfold? Artemis problems before Trump The Constellation project was launched in 2005 with the goal of “returning to the Moon no later than 2020”. 15 years seemed to be a sufficient period at the time: the previous lunar project in 1961-1969 was half as long. And this on “grandfather hardware” and software. Constellation project Then, twenty years ago, NASA expected to fly to the Moon, land, and return completely independently, as under von Braun, giving contractors the general technical appearance of the product and controlling the way they build it. There are four key components in the lunar programs: Super-heavy launch vehicle
Spacecraft
Landing module
Spacesuit Super-heavy launch vehicle Spacecraft Landing module Spacesuit It would seem that success is inevitable. After all, the program planners initially reported that in order to save time and money as much as possible, they use the engines left over from the Space Shuttle program. After four years, it became clear: overruns on the development are so great that without a sharp increase in the total costs of the program, it is unrealizable. It was canceled, but NASA did not give up and rebranded the super-heavy rocket for the moon “Ares” in SLS. The ship Orion was not renamed. There was a minimum of changes in the project, and the lunar landing module Altair was postponed until better times. “Best times” for a return to the Moon developed during Trump's first term: in 2018, he finally sanctioned the Artemis program for this purpose. But by the early 2020s, it became clear that finishing all four components of the lunar program in-house was utopian for the agency. The finalization of SLS and Orion rockets was already in the second decade, and the final was not seen. NASA has not succeeded in developing a spacesuit at all. It was risky to start a module under such conditions. developing a spacesuit Then, the agency decided to get rid of criticism for punctures in the development and make it a future target of private developers. The lunar landing module was entrusted to SpaceX - in fact, it turned out to be a Starship with landing legs. Two private companies were hired to make spacesuits: Collins and Axiom. The extravehicular spacesuits have not worked out so well so far. Collins simply withdrew from development, saying that it is too complex a task. And Axiom, even at public shows, demonstrated the models being created without life support systems. In addition, at one of the latest shows, people saw a clone of a prototype NASA spacesuit from 2019, but with colored design inserts from Prada. By the way, there will almost certainly be no large inserts in the real lunar landing for technical reasons. As if spacesuits weren't enough! The situation has been simultaneously exacerbated by both Musk and his political opponents. Seth Abramson, for example, thinks the latter has lost his mind. By the way, he calls himself “Ilon Musk's biographer,” although the existing biography was actually created by Walter Isaacson. Anyway, on January 7, Abramson suggested that the Biden administration break all contracts with Ilon and begin prosecution. Except that without contracts with Musk, not only Artemis, but even the banal return of American astronauts from the ISS is difficult. In fact, we are talking about a proposal to deprive America of manned spaceflight. Seth Abramson Walter Isaacson The owner of SpaceX isn't letting things get boring either. As I wrote above, earlier this year, he stated, "We're going to fly straight to Mars. The moon is a distraction." The media, as usual, presented it as hype as possible: say, the most important person in the American space program does not want to fly to the Moon. Then there were “witnesses to the conspiracy”: SpaceX is not doing well with the lunar module, for which NASA paid the company $2.89 billion. Here he is trying to find an excuse not to follow the contracts! he stated In fact, Musk wrote these words in response to a question from another space enthusiast. The latter asked if Starship going to Mars should be refueled with lunar oxygen. The question, at first glance, is reasonable: 69% of the fuel mass of such a ship is oxygen. Answering, the head of SpaceX meant that refueling on the Moon in the conditions of reusable carriers does not make economic sense. It is easier to deliver oxygen from Earth than to build a mini-city on Selene for O2 extraction. question from another space enthusiast Let it be a hype, but still, “Artemis III” by 2025 has accumulated quite serious problems: the Orion heat shield returned after the orbit of the Moon was cracked. That is, another test flight of the ship is needed. But there is no money for it: the Artemis project has generated such an expensive rocket (SLS) that one of its launches with the ship costs $4.1 billion. $4.1 billion The head of SpaceX summarized all this: "The architecture of Artemis is extremely inefficient. This is a program to increase employment, not to achieve results. Something fundamentally new is needed." head of SpaceX summarized all this Let us return to the place of the invited project manager and ask ourselves a question: What would we suggest to ourselves? Already Solved Controls One often hears: Why does Artemis even need a lunar module and ship separately? We are already seeing the seventh Starship test flight. Yes, there are flaws, but it is obvious that by 2027, it will be flying regularly. There are also unlikely to be problems with the life support system, as SpaceX has already made one for Dragon ships. Why not take astronauts to the Moon, land them directly on Starship HLS, and then return to Earth on it? This approach to project management can be tentatively called “new broom”. Often, a new manager wants to radically change everything, to sweep away unnecessary crutches left by his predecessors. And then “make everything normal and fast”. In practice, this approach is not applicable. First, for a launch from Earth on a ship without a very large statistics of accident-free flights, it is desirable to have an emergency rescue system. Technically, this is a set of small engines to separate the ship from the rocket if it malfunctions. And, of course, a parachute system for atmospheric braking. Starship doesn't and won't have all of that. Otherwise, the ship would have to be radically redesigned, which takes a lot of time. And the developer doesn't want to, noting that airliners don't have parachutes. And Elon Musk is going to make an airliner for space (a mass and cheap carrier), not a simple experimental airplane with a parachute. Then, there is a temptation to take another ready-made piece of space technology - the manned SpaceX Dragon. Launch astronauts into orbit on it, dock it with Starship, and then launch it to the Moon for a human landing mission. This would solve the problem with the escape system: the Dragon has one. But for all the appeal of this option, it is quite difficult to implement. Existing versions of Starship simply don't have enough fuel to fly back to Earth from the Moon after the astronauts lift off. Unlike a ship like Orion, Starship is very massive. Of course, it is possible to refuel Starship in near-lunar orbit and then return it to our planet. But that would require many additional Starship tanker flights. To send one fuel tanker to the Moon, it would have to be refueled in Earth's orbit. What if, during landing or takeoff, a Starship tanker damages the launch equipment at one site, say, Starbase in Texas? That would clearly block the next flights from there. The wait for refueling could get longer. And what if another tanker damages the launch spot at the second launch pad for the Starship being built in Florida as well? Will astronauts wait months in orbit, enjoying the magnificent views? Casey Handmer's Option Physicist Casey Handmer, who used to work with NASA, offered a different solution four years ago. Yes, for a full-fledged Starship with a 100-ton payload, a return from the Moon is realistic only after complex refueling in low lunar orbit. But what if the ship's payload is reduced on the first flight? offered a different solution Handmer calculated that with 25 tons of payload, 12 refuelings in low-Earth orbit would allow the ship to fly to the Moon and return. Refueling in higher orbits is theoretically possible. It would give Starship the ability to deliver 200+ tons of payload to the Moon and then return the crew and tons of lunar soil. But there just isn't enough room inside the ship for 200 tons of cargo. Unless you want to mount an Olympic swimming pool inside and launch whales into it, the physicist notes. If anyone doubts the scientist's calculations, it is not difficult to check them yourself. Delta-V, the energy budget for reaching certain points of the Solar System (simply put, by how much the ship's speed should be changed), is well known. First, note that all calculations on this indicator for Starship are given after the launch into low-Earth orbit. In any case, refueling will take place there - the tanks will be full, and the delta-V countdown should be started again. To get from low Earth orbit (200 km) to geo-transition orbit (from about 200 km at perigee to 36,000 km at apogee), you need a delta of 2.44 km/s. To go to the Moon from this orbit would require 0.68 km/s of additional velocity. To reach a low lunar orbit (100 km above the Moon) - another 0.82 km/s. Landing on the Moon is already more difficult: there is no atmosphere here, against which we can extinguish the speed. So we will spend 1.72 km/s delta-V for braking on landing and another 1.72 km/s for takeoff a few days later. Another 0.82 km/s is needed to send it to Earth. That is, the total delta-V (after reaching low-Earth orbit, where refueling will take place) is about 8.2 km/s in total. That is quite capable for Starship with those parameters of the engines (380 seconds of impulse in vacuum), which are planned by SpaceX. Will 25 tons be enough for everyone? 25 tons for three astronauts may look like a severe limitation. After all, not only do they and their in-ship and out-of-ship spacesuits have to be stuffed into that load somehow, but also the equipment for traveling on the Moon. Without lunomobiles, traveling in the lunar shadow at -190 and below is no easy walk. It's worth remembering here that the mass of Apollo-era lunar modules is an unhelpful load. Namely, the total mass was only a dozen and a half tons. Sure, on the way to the Moon, the astronauts used the air, water, and food of the command module, which didn't fit into those 15 tons. But their total mass didn't even reach a ton. So maybe the astronauts in 2027 will have to shrink - but they certainly won't have to sleep sitting up like their 1960s counterparts. I don't think we should sympathize with astronauts about the tightness just yet. Musk, who employs his own style of project management, has heavily revised the final look of his brainchild over the past three years. Starship V3 should already have a payload of 200 tons, not 100 as Handmer had calculated. At the same time, the fuel mass is 2,300 tons. That is, full refueling in orbit will require about the same 12 tanker flights as before. Counting with the same dry mass proportions, we get a payload of more than 25 tons. we get a payload What in Handmer's calculations looks problematic? He thinks it's rational to land Starship HLS directly on Earth with people inside. This is questionable for two reasons. First, then it needs heat shielding like a regular Starship, and landing legs like its extraterrestrial version - there is no Mechazilla on the Moon yet. And that would reduce its payload on the Moon. Secondly, landing with astronauts can be done only after several tests without humans. The spacecraft is new. There is no experience of its operation yet. And if Starship cargo flights will soon be in abundance, we will not be able to say that about landings of manned versions. Besides, if we first send one Starship to the Moon with cargo but without the task of taking off again, it will have a “surplus” delta-V of at least 2.54 km/s. That means it will be able to deliver literally hundreds of tons of equipment to the Earth's satellite. It is possible to place not only lunomobiles but also mini-drilling machines, which are very useful for studying the south pole of the Moon. Let's summarize: the most realistic scenario for rebuilding the lunar program under the new administration is Handmer's version. Only slightly modified, in which people will get on board the Starship in Earth orbit with pre-launched Dragon. And it would return them to Earth after returning from the Moon. Such a launch will throw out of the flight program two launches of Orion on SLS: the first to test the updated heat shield and the second with people on board. In total, it saves $9 billion. What the real players are planning There have been leaks in the US press that seem to say that Handmer's option has already been adopted. In December 2024, renowned journalist Eric Berger presented data from his sources in the industry: the new NASA leadership is planning to abandon Orion and SLS. Technically, this is only possible if the new head of NASA, Jared Isaacman, commander of the first private space crew in history, plans to rely solely on SpaceX technology to fly to the moon. After all, no one else has any other rockets and ships of this class. Of course, Bill Nelson, head of NASA, tried to deny that leak. He gave an interview to the same Eric Berger and stated that Trump would not risk scrapping Orion and SLS. So as not to lose the race to the Chinese and definitely have time to see astronauts on the moon before the end of his term. Bill Nelson gave an interview But I will remind you that NASA astronauts did not just affectionately nickname Bill “Ballast” Nelson. The nickname has a basis: The politician is not very well versed in space issues. For example, he stated that one side of the moon is dark all the time. Of course, that's better than if he thought it was flat. But his overall level of understanding of the Artemis issues is still hard to call excessively high. nickname Bill “Ballast” Nelson he stated The position of Nelson and other politicians whose careers have been associated with SLS and Orion is understandable. They don't like the prospect of curtailing “job growth programs.” They've spent a lot of effort to maintain them and have associated their name with their success. Except neither Trump nor Musk are involved - and a Handmer-esque shakeup of the lunar program could very well become a reality. That's not to say there's an easy ride ahead for astronauts on their way to the moon. The issue of spacesuits is not yet closed. If we do not radically accelerate, then by 2027, there may be no working “iron”. The Starship trials are another non-obvious story. On the one hand, they are progressing rapidly. On the other hand, it is a reusable system. You need more flights to be sure of its reliability than with a disposable one. Personally, I expect more than a dozen Starship launches this year and a few dozen in 2026. And next year, there will mostly be not so many test flights as satellite-oriented. Perhaps this is the most reliable link of the American lunar program of the XXI century. Therefore, the decision to bet on it and get off the stagecoach such expensive passengers, such as Orion and SLS, looks really logical.

Trump Wants Astronauts On the Moon But Musk Has Other Plans

Space Technology Could Be Big if We Can Overcome the Technological Hurdles

Stories, News & Mentions about ORBIT

Categories

Trending Topics

Stories, News & Mentions about ORBIT

Orbit’s Stories on HackerNoon

Orbit's News & Mentions

Categories

Trending Topics