The document proposes a reusable lunar lander concept that would reduce costs by reusing the lander for crew rotations rather than abandoning it after each mission. Key elements include a propellant transfer module to provide fuel for lunar orbit insertion and resupply, and deployable lunar outpost modules that can be transported and stored in the lander. The initial flight would use the lander to perform lunar orbit insertion and deploy the first outpost module. Subsequent flights would use the propellant transfer module for orbit insertion while transporting additional outpost modules. The document provides details on the proposed lander design including mass estimates and equipment.
Compensation of time-varying clock-offset in a LBL navigationjournalBEEI
This paper presents compensation of the clock-offset in a long baseline (LBL)navigation. It departs from the existing literature mainly in dealing with a time-varyingclock-offset, i.e. the clock-rate drifts over the time. Specifically, the clock-offsetdynamics are introduced to the ToFs as an autoregressive filter.Subsequently,interactions among the now biased ToFs and the kinematics of an autonomousunderwater vehicle (AUV)–the navigation subject–are represented in a state-spaceform. Implementing the so-called graphic approach, minimum sensor requirementfor this system’s observability is then explicated. Finally, a standard discrete Kalmanfilter is deployed as the state estimator. By simulation, it is demonstrated that theestimator manages to compensate the offset and to provide localization with less than1 m accuracy.
This presentation is intended to compare the manual and computerized calculation. This software can be customized for any fuel carrying barge requiring LIST and TRIM correction. It can also be usable to manage the fuel storage system in any Tank Firm.
This software is designed for Marine Bunker Surveyors to minimize time in bunker quantification following API-MPMS guidelines. It also contains some other conversion tools which are really important to calculate the fuel characteristics like Shell CCAI, BP CII, Net and Gross Specific Energy, Injection, Temperature based on measured viscosity, density conversion tools and much more.
Compensation of time-varying clock-offset in a LBL navigationjournalBEEI
This paper presents compensation of the clock-offset in a long baseline (LBL)navigation. It departs from the existing literature mainly in dealing with a time-varyingclock-offset, i.e. the clock-rate drifts over the time. Specifically, the clock-offsetdynamics are introduced to the ToFs as an autoregressive filter.Subsequently,interactions among the now biased ToFs and the kinematics of an autonomousunderwater vehicle (AUV)–the navigation subject–are represented in a state-spaceform. Implementing the so-called graphic approach, minimum sensor requirementfor this system’s observability is then explicated. Finally, a standard discrete Kalmanfilter is deployed as the state estimator. By simulation, it is demonstrated that theestimator manages to compensate the offset and to provide localization with less than1 m accuracy.
This presentation is intended to compare the manual and computerized calculation. This software can be customized for any fuel carrying barge requiring LIST and TRIM correction. It can also be usable to manage the fuel storage system in any Tank Firm.
This software is designed for Marine Bunker Surveyors to minimize time in bunker quantification following API-MPMS guidelines. It also contains some other conversion tools which are really important to calculate the fuel characteristics like Shell CCAI, BP CII, Net and Gross Specific Energy, Injection, Temperature based on measured viscosity, density conversion tools and much more.
An Offshore supply vessel is a multi-task vessel and has to be designed for many different purposes. This is contrary to most other ships used worldwide. In general, the geographical location where the offshore activity takes place is an important indicator of the choice of supply vessel.
Factors like weather conditions, the amount of equipment needed and the distance from the shore
are important for what properties the vessel should have. The deep-water oilfield market is
becoming more important as the conventional oilfield market in shallow water cannot meet the
energy requirements from the consuming market. The Offshore Supply Vessels (hereafter it is
called OSVs) market is becoming booming and the demand for OSVs has never reached the extent
like today in previous periods.
In this project an offshore supply vessel will be designed according to ABS Rules.
An Offshore supply vessel is a multi-task vessel and has to be designed for many different purposes. This is contrary to most other ships used worldwide. In general, the geographical location where the offshore activity takes place is an important indicator of the choice of supply vessel.
Factors like weather conditions, the amount of equipment needed and the distance from the shore
are important for what properties the vessel should have. The deep-water oilfield market is
becoming more important as the conventional oilfield market in shallow water cannot meet the
energy requirements from the consuming market. The Offshore Supply Vessels (hereafter it is
called OSVs) market is becoming booming and the demand for OSVs has never reached the extent
like today in previous periods.
In this project an offshore supply vessel will be designed according to ABS Rules.
CargoSurveyor: toolbox for marine cargo surveyorsRon Mooring
CargoSurveyor is the ultimate iOS app for marine cargo surveyors. It contains a complete set of tools to carry out full cargo surveys on board oil / chemical tankers and bunker surveys. It contains all you need to produce smart accurate ullage reports, bunker reports, transfer records, VEF reports, letters of protest and much more. See also mooringmarineconsultancy.wordpress.com.
Download it on iTunes: http://bit.ly/1A6X1Wy
The Centurion Orbit Transfer Vehicle (OTV) was part of our Aerospace Engineering Senior Design project at the University of Illinois at Urbana-Champaign. It is equipped with the latest technologies, including a nuclear thermal propulsion system. The structure weighs 89,000 kg and is capable of transporting cargo to Lagrange points L1 or L2.
Instead of abandoning the Lunar Lander after ascent each flight reuse for crew change out.
Requires several development components.
Propellant Transfer Module
Provides Delta V to CEV for LOI since LSAM is no longer part of TLI stack
Provides Delta V to resupply Lander for descent and ascent
Provides Consumables to CEV and Lander
Lunar outpost modules that can be stowed in Lander
Based off Single Stage, Dual Hab design
concept #2 Lunar Surface Access Module Study, RFT0020.05JSC
Fighter jet design and performance calculations by using the case studies.Mani5436
1.Fighter jet theoretical calculations by using previous calculations.
2. Case study of the fighter jet
3. Configuration selection of the fighter jet
4. Aircraft Performance
Mini project Jet Engine Powered LocomotiveGagan Nir
Turbo Jet Engine Powered Locomotive MIT World Peace University, Pune B.Tech Third Mechanical Engineering Year Mini Project Presentation (First Review). Less Pollution, Jet Fuel vs Conventional Fuel, Better Mileage. Future Locomotive. New Designed Locomotive. Use Of Honda Jet Engine in more efficient way. Future Railways
Similar to the celebrity tours that happen at JSC this would be a one day tour of facilities, talking with individuals but also helping educate the attendees on what it takes to operate a space station, build a spacecraft, make a Journey to Mars etc. The workshop briefings would focus on the design considerations, operational concepts and stories from astronauts about their experiences living on the station or flying these missions. The briefings cover the topics from a perspective that will help the attendees go beyond the usual factoids but delve into areas that would help the writer craft a better story, an animator/cgi artist design the scene more lifelike or an actor realize the character more three dimensionally.
Prototype Development of an Integrated Mars Atmosphere and Soil Processing Sy...Michael Interbartolo
NASA multicenter effort to design and build an integrated system for processing representative Martian Atmosphere and Soil. Presented at the Earth & Space 2012 conference in Pasadena CA.
Epistemic Interaction - tuning interfaces to provide information for AI supportAlan Dix
Paper presented at SYNERGY workshop at AVI 2024, Genoa, Italy. 3rd June 2024
https://alandix.com/academic/papers/synergy2024-epistemic/
As machine learning integrates deeper into human-computer interactions, the concept of epistemic interaction emerges, aiming to refine these interactions to enhance system adaptability. This approach encourages minor, intentional adjustments in user behaviour to enrich the data available for system learning. This paper introduces epistemic interaction within the context of human-system communication, illustrating how deliberate interaction design can improve system understanding and adaptation. Through concrete examples, we demonstrate the potential of epistemic interaction to significantly advance human-computer interaction by leveraging intuitive human communication strategies to inform system design and functionality, offering a novel pathway for enriching user-system engagements.
Key Trends Shaping the Future of Infrastructure.pdfCheryl Hung
Keynote at DIGIT West Expo, Glasgow on 29 May 2024.
Cheryl Hung, ochery.com
Sr Director, Infrastructure Ecosystem, Arm.
The key trends across hardware, cloud and open-source; exploring how these areas are likely to mature and develop over the short and long-term, and then considering how organisations can position themselves to adapt and thrive.
Software Delivery At the Speed of AI: Inflectra Invests In AI-Powered QualityInflectra
In this insightful webinar, Inflectra explores how artificial intelligence (AI) is transforming software development and testing. Discover how AI-powered tools are revolutionizing every stage of the software development lifecycle (SDLC), from design and prototyping to testing, deployment, and monitoring.
Learn about:
• The Future of Testing: How AI is shifting testing towards verification, analysis, and higher-level skills, while reducing repetitive tasks.
• Test Automation: How AI-powered test case generation, optimization, and self-healing tests are making testing more efficient and effective.
• Visual Testing: Explore the emerging capabilities of AI in visual testing and how it's set to revolutionize UI verification.
• Inflectra's AI Solutions: See demonstrations of Inflectra's cutting-edge AI tools like the ChatGPT plugin and Azure Open AI platform, designed to streamline your testing process.
Whether you're a developer, tester, or QA professional, this webinar will give you valuable insights into how AI is shaping the future of software delivery.
The Art of the Pitch: WordPress Relationships and SalesLaura Byrne
Clients don’t know what they don’t know. What web solutions are right for them? How does WordPress come into the picture? How do you make sure you understand scope and timeline? What do you do if sometime changes?
All these questions and more will be explored as we talk about matching clients’ needs with what your agency offers without pulling teeth or pulling your hair out. Practical tips, and strategies for successful relationship building that leads to closing the deal.
GDG Cloud Southlake #33: Boule & Rebala: Effective AppSec in SDLC using Deplo...James Anderson
Effective Application Security in Software Delivery lifecycle using Deployment Firewall and DBOM
The modern software delivery process (or the CI/CD process) includes many tools, distributed teams, open-source code, and cloud platforms. Constant focus on speed to release software to market, along with the traditional slow and manual security checks has caused gaps in continuous security as an important piece in the software supply chain. Today organizations feel more susceptible to external and internal cyber threats due to the vast attack surface in their applications supply chain and the lack of end-to-end governance and risk management.
The software team must secure its software delivery process to avoid vulnerability and security breaches. This needs to be achieved with existing tool chains and without extensive rework of the delivery processes. This talk will present strategies and techniques for providing visibility into the true risk of the existing vulnerabilities, preventing the introduction of security issues in the software, resolving vulnerabilities in production environments quickly, and capturing the deployment bill of materials (DBOM).
Speakers:
Bob Boule
Robert Boule is a technology enthusiast with PASSION for technology and making things work along with a knack for helping others understand how things work. He comes with around 20 years of solution engineering experience in application security, software continuous delivery, and SaaS platforms. He is known for his dynamic presentations in CI/CD and application security integrated in software delivery lifecycle.
Gopinath Rebala
Gopinath Rebala is the CTO of OpsMx, where he has overall responsibility for the machine learning and data processing architectures for Secure Software Delivery. Gopi also has a strong connection with our customers, leading design and architecture for strategic implementations. Gopi is a frequent speaker and well-known leader in continuous delivery and integrating security into software delivery.
DevOps and Testing slides at DASA ConnectKari Kakkonen
My and Rik Marselis slides at 30.5.2024 DASA Connect conference. We discuss about what is testing, then what is agile testing and finally what is Testing in DevOps. Finally we had lovely workshop with the participants trying to find out different ways to think about quality and testing in different parts of the DevOps infinity loop.
State of ICS and IoT Cyber Threat Landscape Report 2024 previewPrayukth K V
The IoT and OT threat landscape report has been prepared by the Threat Research Team at Sectrio using data from Sectrio, cyber threat intelligence farming facilities spread across over 85 cities around the world. In addition, Sectrio also runs AI-based advanced threat and payload engagement facilities that serve as sinks to attract and engage sophisticated threat actors, and newer malware including new variants and latent threats that are at an earlier stage of development.
The latest edition of the OT/ICS and IoT security Threat Landscape Report 2024 also covers:
State of global ICS asset and network exposure
Sectoral targets and attacks as well as the cost of ransom
Global APT activity, AI usage, actor and tactic profiles, and implications
Rise in volumes of AI-powered cyberattacks
Major cyber events in 2024
Malware and malicious payload trends
Cyberattack types and targets
Vulnerability exploit attempts on CVEs
Attacks on counties – USA
Expansion of bot farms – how, where, and why
In-depth analysis of the cyber threat landscape across North America, South America, Europe, APAC, and the Middle East
Why are attacks on smart factories rising?
Cyber risk predictions
Axis of attacks – Europe
Systemic attacks in the Middle East
Download the full report from here:
https://sectrio.com/resources/ot-threat-landscape-reports/sectrio-releases-ot-ics-and-iot-security-threat-landscape-report-2024/
Neuro-symbolic is not enough, we need neuro-*semantic*Frank van Harmelen
Neuro-symbolic (NeSy) AI is on the rise. However, simply machine learning on just any symbolic structure is not sufficient to really harvest the gains of NeSy. These will only be gained when the symbolic structures have an actual semantics. I give an operational definition of semantics as “predictable inference”.
All of this illustrated with link prediction over knowledge graphs, but the argument is general.
JMeter webinar - integration with InfluxDB and GrafanaRTTS
Watch this recorded webinar about real-time monitoring of application performance. See how to integrate Apache JMeter, the open-source leader in performance testing, with InfluxDB, the open-source time-series database, and Grafana, the open-source analytics and visualization application.
In this webinar, we will review the benefits of leveraging InfluxDB and Grafana when executing load tests and demonstrate how these tools are used to visualize performance metrics.
Length: 30 minutes
Session Overview
-------------------------------------------
During this webinar, we will cover the following topics while demonstrating the integrations of JMeter, InfluxDB and Grafana:
- What out-of-the-box solutions are available for real-time monitoring JMeter tests?
- What are the benefits of integrating InfluxDB and Grafana into the load testing stack?
- Which features are provided by Grafana?
- Demonstration of InfluxDB and Grafana using a practice web application
To view the webinar recording, go to:
https://www.rttsweb.com/jmeter-integration-webinar
Transcript: Selling digital books in 2024: Insights from industry leaders - T...BookNet Canada
The publishing industry has been selling digital audiobooks and ebooks for over a decade and has found its groove. What’s changed? What has stayed the same? Where do we go from here? Join a group of leading sales peers from across the industry for a conversation about the lessons learned since the popularization of digital books, best practices, digital book supply chain management, and more.
Link to video recording: https://bnctechforum.ca/sessions/selling-digital-books-in-2024-insights-from-industry-leaders/
Presented by BookNet Canada on May 28, 2024, with support from the Department of Canadian Heritage.
Search and Society: Reimagining Information Access for Radical FuturesBhaskar Mitra
The field of Information retrieval (IR) is currently undergoing a transformative shift, at least partly due to the emerging applications of generative AI to information access. In this talk, we will deliberate on the sociotechnical implications of generative AI for information access. We will argue that there is both a critical necessity and an exciting opportunity for the IR community to re-center our research agendas on societal needs while dismantling the artificial separation between the work on fairness, accountability, transparency, and ethics in IR and the rest of IR research. Instead of adopting a reactionary strategy of trying to mitigate potential social harms from emerging technologies, the community should aim to proactively set the research agenda for the kinds of systems we should build inspired by diverse explicitly stated sociotechnical imaginaries. The sociotechnical imaginaries that underpin the design and development of information access technologies needs to be explicitly articulated, and we need to develop theories of change in context of these diverse perspectives. Our guiding future imaginaries must be informed by other academic fields, such as democratic theory and critical theory, and should be co-developed with social science scholars, legal scholars, civil rights and social justice activists, and artists, among others.
2. Agenda
• Introduction
• Mass Allocations and Equipment List
• Lander Schematics
• Flight One and Two Sequence
• Lunar Outpost Assembly Sequence and
Crew Rotation
• Conclusion
4. Concept
• Instead of abandoning the Lunar Lander after
ascent each flight reuse for crew change out.
• Requires several development components.
– Propellant Transfer Module
• Provides Delta V to CEV for LOI since LSAM is no longer
part of TLI stack
• Provides Delta V to resupply Lander for descent and ascent
• Provides Consumables to CEV and Lander
– Lunar outpost modules that can be stowed in Lander
• Based off Single Stage, Dual Hab design
– concept #2 Lunar Surface Access Module Study, RFT0020.05JSC
5. Phased In approach
• First flight consists of CEV and Lander
– Lander performs LOI
– Lander deploys first Outpost Module via
attached Flat Bed Transport
• Second and subsequent flights consist of
CEV, PTM and Outpost
Modules/Resupplies
– CEV performs LOI with prop from PTM
8. Mass Allocations
• Lander: 99,000 lb
– Includes 10,000 outpost module capacity
• CEV: 50,000 lb
• PTM: 89,000 lb
– Prop for CEV to perform LOI
– Prop for Lander Descent and Ascent Resupply
– Consumables for Lander
• N2/O2 for cabin represses, Suit cooling H2O
• Outpost Module #X: 10,000 lb max
9. Propellant Mass Estimates (FWD)Lander Total 99000
Gc = 32.174 ft/s^2
Propellant Temp/Press Density
(lbm/ft^3)
MR AR [6] Rho_avg
(lbm/ft^3)
Thrust
(lbf)
ISP CEV
Mass (Wi)
(lbm)
DV
(fps)
Useable
Prop [1]
(%)
Margin
[1] [2]
(%)
Ullage [3]
(%)
LO2 (OMS) 162R / 250 psia 62.11 32310.0 5.3
CH4 (OMS) 170R / 250 psia 23.22 9502.9 5.3
LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3
CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3
Total Propellant Weight 41812.9 4 tanks per propellant
Total Tank Weight 1615.4 8.31 [ft] NTO tank Length
Total Prop plus Tank Weight 43428.3 6.82 [ft] MMH tank length LANDER PERFORMING LOI
Total Helium Weight 1313.4 1 tanks per propellant
Total Helium Tank Weight 1643.2 5.82 [ft] NTO He tank diameter
Total Helium plus Tank Wt 2956.5 5.37 [ft] MMH He tank diameter
Total He, Prop, & Tank Wt 46384.8
Lander Wet Mass Post LOI 55873.7
Gc = 32.174 ft/s^2
Propellant Temp/Press Density
(lbm/ft^3)
MR AR [6] Rho_avg
(lbm/ft^3)
Thrust
(lbf)
ISP CEV
Mass (Wi)
(lbm)
DV
(fps)
Useable
Prop [1]
(%)
Margin
[1] [2]
(%)
Ullage [3]
(%)
LO2 (OMS) 162R / 250 psia 62.11 18807.9 5.3
CH4 (OMS) 170R / 250 psia 23.22 5531.7 5.3
LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3
CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3
Total Propellant Weight 24339.7 2 tanks per propellant
Total Tank Weight 912.2 9.45 [ft] NTO tank Length
Total Prop plus Tank Weight 25251.9 7.72 [ft] MMH tank length LANDER PERFORMING DESCENT
Total Helium Weight 764.5 1 tanks per propellant
Total Helium Tank Weight 1152.0 4.86 [ft] NTO He tank diameter
Total Helium plus Tank Wt 1916.5 4.48 [ft] MMH He tank diameter
Total He, Prop, & Tank Wt 27168.4
Lander Wet Mass Post Landing 20769.5
and post Module Deploy 10000
Gc = 32.174 ft/s^2
Propellant Temp/Press Density
(lbm/ft^3)
MR AR [6] Rho_avg
(lbm/ft^3)
Thrust
(lbf)
ISP CEV
Mass (Wi)
(lbm)
DV
(fps)
Useable
Prop [1]
(%)
Margin
[1] [2]
(%)
Ullage [3]
(%)
LO2 (OMS) 162R / 250 psia 62.11 6991.3 5.3
CH4 (OMS) 170R / 250 psia 23.22 2056.3 5.3
LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3
CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3
Total Propellant Weight 9047.6 1 tanks per propellant
Total Tank Weight 361.1 7.37 [ft] NTO tank Length
Total Prop plus Tank Weight 9408.7 6.08 [ft] MMH tank length
LANDER PERFORMING ASCENT
Total Helium Weight 284.2 1 tanks per propellant
Total Helium Tank Weight 603.5 3.49 [ft] NTO He tank diameter
Total Helium plus Tank Wt 887.6 3.22 [ft] MMH He tank diameter
Total He, Prop, & Tank Wt 10296.3
Lander Dry Mass (excludes Prop tanks) 5150.5
LO2 and Methane
Wp
(lbm)
3.4 150 44.99 900 362 149000 3600 98.0% 3.5% 41812.9
3.2 60 44.40 100 345 149000 0 100.0% 3.5% 0.0
LO2 and Methane
Wp
(lbm)
3.4 150 44.99 900 362 55873.7 6200 98.0% 3.5% 24339.7
3.2 60 44.40 100 345 55873.7 0 100.0% 3.5% 0.0
LO2 and Methane
Wp
(lbm)
3.4 150 44.99 900 362 20769.5 6200 98.0%
345 20769.5 0 100.0%3.2 60 44.40 100 3.5% 0.0
3.5% 9047.6
If estimates are correct only 5150
lb for all Lander systems except
prop wet mass
10. Propellant Mass Estimates (Back)
Gc = 32.174 ft/s^2
Propellant Temp/Press Density
(lbm/ft^3)
MR AR [6] Rho_avg
(lbm/ft^3)
Thrust
(lbf)
ISP CEV Mass
(Wf)
(lbm)
DV
(fps)
Useable
Prop [1]
(%)
Margin
[1] [2]
(%)
Ullage [3]
(%)
Volume
(FT3)
LO2 (OMS)162R / 250 psia 62.11 10982.7 5.3 186.20
CH4 (OMS)170R / 250 psia 23.22 3230.2 5.3 146.49
LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00
CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00
Total Propellant Weight 14212.9 3 tanks per propellant
Total Tank Weight 3819.2 27.36 [ft] NTO tank Length
Total Prop plus Tank Weight 18032.2 21.81 [ft] MMH tank length Lander Performs Ascent
Lander RNDZ Burnout weight 20,000
Total Helium Weight 1225.2 1 tanks per propellant Lander pre Ascent 35,438
Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter
Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter
Total He, Prop, & Tank Wt 20827.2
Gc = 32.174 ft/s^2
Propellant Temp/Press Density
(lbm/ft^3)
MR AR [6] Rho_avg
(lbm/ft^3)
Thrust
(lbf)
ISP CEV Mass
(Wf)
(lbm)
DV
(fps)
Useable
Prop [1]
(%)
Margin
[1] [2]
(%)
Ullage [3]
(%)
Volume
(FT3)
LO2 (OMS)162R / 250 psia 62.11 24951.6 5.3 423.02
CH4 (OMS)170R / 250 psia 23.22 7338.7 5.3 332.80
LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00
CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00
Total Propellant Weight 32290.3 3 tanks per propellant
Total Tank Weight 3819.2 27.36 [ft] NTO tank Length Lander Performs Descent
Total Prop plus Tank Weight 36109.6 21.81 [ft] MMH tank length Lander Payload 10,000
Lander Touchdown weight 45,438
Total Helium Weight 1225.2 1 tanks per propellant Lander pre Deorbit Burn 78,954
Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter
Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter
Total He, Prop, & Tank Wt 38904.6
Gc = 32.174 ft/s^2
Propellant Temp/Press Density
(lbm/ft^3)
MR AR [6] Rho_avg
(lbm/ft^3)
Thrust
(lbf)
ISP CEV Mass
(Wf)
(lbm)
DV
(fps)
Useable
Prop [1]
(%)
Margin
[1] [2]
(%)
Ullage [3]
(%)
Volume
(FT3)
LO2 (OMS)162R / 250 psia 62.11 36110.4 5.3 612.21
CH4 (OMS)170R / 250 psia 23.22 10620.7 5.3 481.64
LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00
CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00
Total Propellant Weight 46731.2 3 tanks per propellant
Total Tank Weight 3819.2 27.36 [ft] NTO tank Length Lander Performs LOI Burn
Total Prop plus Tank Weight 50550.4 21.81 [ft] MMH tank length Trans Lunar Stack 176,910
Post LOI Burn 128,954
Total Helium Weight 1225.2 1 tanks per propellant TLI Constraint 149,000
Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter Lander Allocation 99000
Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter Margin -27,910
Total He, Prop, & Tank Wt 53345.4
3.5% 0.0
LO2 and Methane
Wp
(lbm)
3.5% 46731.2
3.2 60 44.40 100 345 128954 0 100.0%
362 128954 3600 98.0%3.4 150 44.99 900
3.5% 0.0
3.5% 32290.3
3.2 60 44.40 100 345 45438 0 100.0%
362 45438 6250 98.0%3.4 150 44.99 900
3.5% 0.0
LO2 and Methane
Wp
(lbm)
3.5% 14212.9
3.2 60 44.40 100 345 20000 0 100.0%
LO2 and Methane
Wp
(lbm)
3.4 150 44.99 900 362 20000 6250 98.0%
Includes 50,000
for CEV
11. Lander Systems
• Propulsion
– 4 +Z Direction 10Klb engines
• Lunar Descent and Ascent
– 4 +X Direction 10lkb engines
• For LOI and Deorbit Burn
• Allows for g loads eyeballs in for LOI
– 4 RCS Quads located on Engine Pods
• 870 lb engines for attitude control and translation
– 4 RCS Tris located on Engine Pods
• 870 lb engines for attitude control and translation
– Tanks not optimized for size and shape
• 3 He tanks
• 7 Lox tanks
• 7 CH4 tanks
12. Lander Systems
• GNC
– 3 IMUs
– 2 Star Camera for IMU alignments
– RNDZ Sensors
• IROC
• SROC
• LROC
• Lidar
• Aux Computers for image processing
• Transponders for comm with CEV or outpost
• Sensor redundancy is covered by the CEV that can rescue Lander for failed rndz
– Descent Sensors
• Ground Proximity sensors
• Ground Radar
• Power
– Solar Arrays
• It may be possible to oversize solar arrays such that post landing crew can remove
arrays for use in outpost solar array farm
– Battery backup for night pass and supplement arrays during peak loading
– Three redundant buses
13. Lander Systems
• DPS
– 3 Computers
– BIUS
– AUX computers for rndz sensor navigation
– 1553 Data Bus
• ECLSS
– Consumables to support two cabin depress/repress
cycles
• Nominally should only require one depress post descent and
then repress for ascent
– Suit Cooling and Recharge capabilities
– Resupply consumables from PTM
20. Cockpit Internal Side View
Lids
O2
Tank
N2
Tank
Propellant
Transfer
Lines
Cockpit
Displays
Ground
Radar
Computer
Porch and Ladder in
Stowed Position
Crew member in
Eva Suit for
Landing
Star Tracker
IMU
21. Cockpit Forward Facing
GND
Radar
Propellant tanks
Propellant
Pressurization tanks
Star Tracker Doors
O2
TankN2
TankGround Radar
Electronics
IMUsH2O
Tank
Computers
Star Tracker
Assemblies
Lids
Transfer
connections
FU
OX
He
ECLSS
Stowage
Computer
Stowage
22. Lander Forward Facing
Solar Array
Panels
RNDZ
Sensors
RNDZ
Sensors
GND
Radar
Porch and Ladder in
Stowed Position
Propellant tanks
Propellant
Pressurization tanks
RCS
Quad
Landing Gear
4 per Pod Descent/Ascent
Engine
Star Tracker Doors
23. Flat bed Transport
Battery Electric
Drive
Plow attachment for
regolith movement
RMS
Flat Bed
Attach Point
Transport can be
used without flat bed
for rover ops
Computer
Solar
Array
Panel
Suit O2 Supply
tank for extended
rover ops
Outpost Solar
Array Panel
stowed in Flatbed
Suit H2O Supply
tank for extended
rover ops
Hatch to non-
pressurized cockpit
28. Flight One
flat bed deploys Outpost
Module with RMS
Lunar Regolith for Shielding
29. Flight Two
CEV2 with Crew
Rotation
PTM with DeltaV
for LOI and Lander
resupply
Outpost Module #2
CEV2 Performs Lunar orbit
Insertion
30. Flight TwoCEV2 with Crew
Rotation
PTM with DeltaV for LOI
and Lander resupply
Outpost Module #2
CEV2 Station keeps with
CEV1 awaiting Lander
CEV1
31. Flight One Termination
Crew egresses outpost and
takes off in Lander
Lunar Regolith for Shielding
Solar Array Farm
32. Crew RotationCEV2 with Crew
Rotation
CEV2 Station keeps with CEV1
Lander docks to outpost module #2
CEV1
33. Crew Rotation
CEV2 with Crew
Rotation
CEV2 Station keeps with CEV1
Lander grapples outpost module #2
CEV1
34. Crew Rotation
CEV2 with Crew
Rotation
CEV2 Station keeps with CEV1
Lander with outpost module #2 grappled
undocks at PTM separation planeCEV1
35. Crew Rotation
CEV2 with Crew
Rotation
CEV2 Station keeps with CEV1
Lander stows outpost module #2
CEV1
36. Crew Rotation
CEV2 with Crew
Rotation
CEV2 Station keeps with CEV1
Lander redocks with PTM
PTM resupplies Lander with propellant and consumables
CEV2 crew modes CEV2 to loiter and ingresses PTM
CEV1
37. Crew RotationCEV2
CEV2 Station keeps with CEV1
Lander undocks with CEV2 at CEV separation plane
CEV2 crew flies Lander while CEV1 crew loiters in PTM
CEV1
44. Lunar Outpost
1 2
3
4
5
N1 N2
Airlock
Solar
Array
Farm
Regolith Berm for
radiation shielding
Mini
Supply
Module
Node
Two Landers allows 8 person Outpost
crew rotating 4 crew members every
3 months
Future Add-on Point
Future Add-on
Point
Node
48. Total Mass Rollup
• Prop Dry: 10,000 lb excluding valves/manifolds
• GNC: 100 lb
• DPS: 200 lb excluding wiring
• Power: 2,000 lb
• LIDS: 1,000 lb
• Crew: 1,280 lb (4 crew, suits and accommodations)
• RMS: 1000 lb
• ECLSS: ?
• Structure: ?
• ATCS: ?
• Total: CBE 20,000 (15,580 + ?) not including 10,000 for OM (outpost
module)
• Lander total:
– CBE+ OM+PROP (fwd) = 107500 (8,500 Negative Margin)
• Prop wet mass for Lander: ~77500
– CBE+ OM+PROP (Back) = 126,910 (28,000 Negative Margin)
• Prop wet mass for Lander: ~96,910
49. Conclusion
• Reusable Lander is Not closed Design
– Significant Negative Margin (8,500-28,000)
• Limits of current design
– Based on limited tools from Smart Buyer Effort
• Prop Sizing Generic 6.xls for prop budget
• CEV SBT Master Workbook for equipment mass
– Based on limited engineering development
• MOD notional concept based on Smart Buyer experience
• Is concept viable?
– Necessitates further study