A CubeSat (U-class spacecraft) is a type of miniaturized satellite for space research that is made up of multiples of 10×10×10 cm cubic units. CubeSats have a mass of no more than 1.33 kilograms per unit.
A CubeSat (U-class spacecraft) is a type of miniaturized satellite for space research that is made up of multiples of 10×10×10 cm cubic units. CubeSats have a mass of no more than 1.33 kilograms per unit.
從 Web Site 到 Web Application,從 Web Services 到 Mobile ServicesKuo-Chun Su
從 Web Site 到 Web Application,從 Web Services 到 Mobile Services - 談談使用與管理上的一些有趣小問題,包括前端如何使用 JavaScript 呼叫 Web Services,JSON 格式的小秘密,以及整合 OpenID/OAuth 等內容。
Delivering more effective marketing through the right technologyJeffrey Evans
ADMA Whitepaper looks at;
What comprises the technology stack
How to define the stack for your organisation
How planning ahead can help drive successful implementation
Choosing the best way of implementing your technology stack
Future developments in products and providers
Addressing the skills gap
Conclusions for marketers
A GEO satellite’s distance from earth gives it a large coverage area, almost a fourth of the earth’s surface and also have 24 hour view of a particular area.This will be very helpful to army,navy etc.,These factors make it ideal for satellite broadcast and other multipoint applications.Continuous monitoring is done and also cost effective in long term, risk-less.
Monitoring Oceans - Chris Atherton - SRD23SURFevents
In recent years, the integration of fibre optic telecommunication cable monitoring technologies has not been fully achieved, hindering novel applications and research in Earth science. However, recent collaborations among national seismic and oceanographic infrastructures, National Research and Education Networks (NRENs), universities, research institutes, and industry in Europe have developed techniques to monitor the Earth and its systems using submarine optical telecommunication fibres. The SUBMERSE project aims to create a pilot research instrument that can continuously monitor existing submarine fibre optic cables, promoting sustainable development goals and leading to new scientific collaborations. This requires the collaboration of multiple stakeholders both nationally and internationally.
This is the presentation given at the end of the Space studies program at NASA Ames, August 2009. The ACCESS Mars project stands for Assessing Cave Capabilities and Evaluating Specific Solutions (ACCESS) Mars explores the future of robotic and human exploration missions to Mars via subsurface habitation.
Mission statement: "...to develop a mission architecture for an initial settlement on Mars by assessing the feasibility of cave habitation as an alternative to proposed surface-based solutions".
This paper covers the Avalanche Risk Assessment proposal in detail. The ARA project's goal is to determine areas at risk from avalanches by measuring snow accumulation using laser altimeter systems.
This presentation details the Avalanche risk Assessment proposal. The mission of this proposal is to determine areas of risk from avalanches based on measuring snow accumulation using laser altimeter systems.
This presentation details the NASA Tech Integration project. This portion of the project covers the interface developed for predicting NAS impact on carbon dioxide emissions.
Management, Cost, and Schedule Paper for Project A.D.I.O.S.Sung (Stephen) Kim
A Deimos Impact and Observation Spacecraft
This paper covers the management plan, the cost budget, and the project schedule in detail for project A.D.I.O.S.
Management, Cost, and Schedule Presentation for Project A.D.I.O.S.Sung (Stephen) Kim
A Deimos Impact and Observation Spacecraft
This presentation details the management plan, the cost budget, and the project schedule for project A.D.I.O.S.
Water scarcity is the lack of fresh water resources to meet the standard water demand. There are two type of water scarcity. One is physical. The other is economic water scarcity.
Hybrid optimization of pumped hydro system and solar- Engr. Abdul-Azeez.pdffxintegritypublishin
Advancements in technology unveil a myriad of electrical and electronic breakthroughs geared towards efficiently harnessing limited resources to meet human energy demands. The optimization of hybrid solar PV panels and pumped hydro energy supply systems plays a pivotal role in utilizing natural resources effectively. This initiative not only benefits humanity but also fosters environmental sustainability. The study investigated the design optimization of these hybrid systems, focusing on understanding solar radiation patterns, identifying geographical influences on solar radiation, formulating a mathematical model for system optimization, and determining the optimal configuration of PV panels and pumped hydro storage. Through a comparative analysis approach and eight weeks of data collection, the study addressed key research questions related to solar radiation patterns and optimal system design. The findings highlighted regions with heightened solar radiation levels, showcasing substantial potential for power generation and emphasizing the system's efficiency. Optimizing system design significantly boosted power generation, promoted renewable energy utilization, and enhanced energy storage capacity. The study underscored the benefits of optimizing hybrid solar PV panels and pumped hydro energy supply systems for sustainable energy usage. Optimizing the design of solar PV panels and pumped hydro energy supply systems as examined across diverse climatic conditions in a developing country, not only enhances power generation but also improves the integration of renewable energy sources and boosts energy storage capacities, particularly beneficial for less economically prosperous regions. Additionally, the study provides valuable insights for advancing energy research in economically viable areas. Recommendations included conducting site-specific assessments, utilizing advanced modeling tools, implementing regular maintenance protocols, and enhancing communication among system components.
Overview of the fundamental roles in Hydropower generation and the components involved in wider Electrical Engineering.
This paper presents the design and construction of hydroelectric dams from the hydrologist’s survey of the valley before construction, all aspects and involved disciplines, fluid dynamics, structural engineering, generation and mains frequency regulation to the very transmission of power through the network in the United Kingdom.
Author: Robbie Edward Sayers
Collaborators and co editors: Charlie Sims and Connor Healey.
(C) 2024 Robbie E. Sayers
Cosmetic shop management system project report.pdfKamal Acharya
Buying new cosmetic products is difficult. It can even be scary for those who have sensitive skin and are prone to skin trouble. The information needed to alleviate this problem is on the back of each product, but it's thought to interpret those ingredient lists unless you have a background in chemistry.
Instead of buying and hoping for the best, we can use data science to help us predict which products may be good fits for us. It includes various function programs to do the above mentioned tasks.
Data file handling has been effectively used in the program.
The automated cosmetic shop management system should deal with the automation of general workflow and administration process of the shop. The main processes of the system focus on customer's request where the system is able to search the most appropriate products and deliver it to the customers. It should help the employees to quickly identify the list of cosmetic product that have reached the minimum quantity and also keep a track of expired date for each cosmetic product. It should help the employees to find the rack number in which the product is placed.It is also Faster and more efficient way.
Immunizing Image Classifiers Against Localized Adversary Attacksgerogepatton
This paper addresses the vulnerability of deep learning models, particularly convolutional neural networks
(CNN)s, to adversarial attacks and presents a proactive training technique designed to counter them. We
introduce a novel volumization algorithm, which transforms 2D images into 3D volumetric representations.
When combined with 3D convolution and deep curriculum learning optimization (CLO), itsignificantly improves
the immunity of models against localized universal attacks by up to 40%. We evaluate our proposed approach
using contemporary CNN architectures and the modified Canadian Institute for Advanced Research (CIFAR-10
and CIFAR-100) and ImageNet Large Scale Visual Recognition Challenge (ILSVRC12) datasets, showcasing
accuracy improvements over previous techniques. The results indicate that the combination of the volumetric
input and curriculum learning holds significant promise for mitigating adversarial attacks without necessitating
adversary training.
Fundamentals of Electric Drives and its applications.pptx
Mission Concept Presentation for Project A.D.I.O.S.
1. Mission Concept
Team 3
FRUITCAKE - Focused Recoil Under ImpacT: Cubesat Analyzing Kinetic Experiment
DIOS MIO - Deimos Impact & Observation Spacecraft: Mars Intercept Orbit
Jeff Anderson, Thomas Blachman, Andrew Fallon, John Franklin, Samuel Gaultney,
David Habashy, Brian Hardie, Brandon Hing, Zujia Huang, Sung Kim, Jonathan Saenger
2. Mission Objectives
Objectives:
- Primary: Analysis of Deimos utilizing a spectrometer during a flyby analysis of a debris cloud created
by an artificial impactor.
- Secondary: Close proximity imaging of one face of Deimos.
Driving Requirements:
- Ability to create big enough plume to be analyzed.
- Ability to analyze plume and relay data back to earth.
- Ability to direct and release impactor off of main systems.
Overview:
Utilizing a 6U cubesat and the Mars 2020 trajectory, we plan to release an impactor into Deimos
to release a large dust plume. This plume will be analysed during a flyby with the spectrometer on board our
cubesat. In addition, our cubesat will take images of Deimos to improve the understanding of it’s geography.
This will also serve as our descope Both of these objectives fit well with the desired science objectives of the
Decadal survey.
3. Mission Success Criteria
Trajectory: Impactor impacts Deimos, Observer flyby successful
- Liftoff - Separation from M2020 rover
- Earth-Mars transfer orbit insertion - Mid-term adjustment burn
- Mars SOI adjustment burn - Final adjustment burn
- Impactor-Observer separation
Spacecraft: Both Impactor and Observer operational
- Post launch check - Mid-term check
- Mars SOI - major systems awaken - ADCS & spectrometer operational
- Imager operational
Systems: Data successfully transmitted
- Plume size enough for analysis - Image resolution and quality
- Antenna operational - Data upload sequence
Descope options:
- In the event that the impactor misses or malfunction the cubesat will take close up pictures of the surface.
- In the event of spectrometer failure images of plume can still provide data about the composition
- In the event of star tracker failure reduncies will be included.
6. Impactor Feasibility and Design.
- Impactor:
- Impact speed: 3.75 km/s max.
- Impactor mass: 4 kg.
- Impact energy: 28.09375 MJ.
- Plume Calculation:
- Scaled to Deep Impact’s data.
- Impacted at 10.7 Km/s, mass of 200kg.
- Ejected 1.2*10^6 kg of material.
- Impact energy: 10,000 MJ.
- Plume Calculation:
- Material ejected: 2551 Kg.
-Lower risk and less complicated than landing.
-1 to 2 U’s in size.
-Contains own propulsion, navigation, and power for
post separation phase of flight.
- Propulsion:
- C-POD micro-cold gas propulsion system.
-Small and lightweight .5 U’s 1.25 kg
- Navigation:
- Star tracker: BCT Standard NST
-Off the shelf
- Vision based navigation: TBD
-Better suited for mission
- Power:
- Solar: 7.5 Watt surface panel
-Can provide power for long d
- 3 mah battery
-Smaller and cheaper
- Cost: TBD
7. Navigation/Trajectories
- Incoming Mars velocity = 1.515 km/s
- Ideal Deimos location (v = 1.35 km/s)
- ΔV < 0.1 km/s
- Worst case Deimos location
- Phase off by 180°
- Speed up
- ΔV = 0.257 km/s
- Slow down
8. Prograde vs Retrograde Trade-off
- Prograde
- Smaller impact velocity
- 1.05 km/s
- Smaller plume (less data)
- More time for flyby analysis
- Retrograde
- Higher impact velocity
- 3.75 km/s
9. Morphological Matrix - Architecture Alternatives
Architecture Decision Option 1 Option 2 Option 3 Option 4
Communication
EWC 27 HDR-TM X
Band Transmitter
MarCO
Spectrometer
Compact Ion and
Neutral Mass
COSIMA Amptek X-123SDD
Propulsion System Chemical Electric Cold Gas Hybrid
Chemical Hydrazine AF-M315E
Attitude Control Reaction Wheels Cold Gas Electrospray
Attitude Determination Star Trackers IMU Sun Sensors
Command & Data Handling iOBC Cube Computer
10. Spectrometer
Amptek X-123SDD
- Cost: $41,600
- Size: 7 x 10 x 2.5 cm
- Power: 2.5 Watts
- Weight: 180 grams
- Communication options through USB, Ethernet, or RS-232
- Data Transmission Rate: 9.6 kb/s (uplink and downlink)
- Current Application: X-ray Fluorescence (XRF)
- System Reliability: Miniature X-Ray Solar Spectrometer mission launched on December 6, 2015.
Compared to Compact Ion and Mass Spectrometer and COSMIA.
11. Propulsion
- Main Propulsion: Aerojet Rocketdyne 2U
MPS-130
- Dry Mass: 2.2 kg, Wet Mass: 3.5 kg
- MRL & TRL: 6
- Chemical Monopropellant: AF-M315E
- Expected Isp of 240 seconds
- 45% more dense than hydrazine
- Available 𝚫V = 367 m/s
- Assuming Spacecraft Payload Mass: 5.5 kg
- 3-axis stabilization
- Sensors
- IMU
- SMG Ellipse-A
- Star trackers
- BCT Thin Slice NST
- Actuators
- Thrusters
- Reaction wheels
- BCT RWP050
- Blue Canyon Technologies XACT ACS
- Contains Star Trackers, Reaction Wheels
- 1-sigma cross-axis pointing error better than
Attitude Determination
& Control
12. Power
- 2 Ukube-1 Single Deployable, Double-
Sided Solar Cells
- 6.5 mm Profile fits to 6U structure
- 40 W Peak Power at Mars, 20.8 W Average Orbit
Power
- Clyde Space XU CubeSat EPS
- Up to 12 Solar Panels
- 98% Efficient at 5V and 3.3V Regulators
- 18650B Lithium Ion Batteries
13. Communication
- Utilize MRO to transmit signal on DSN
- X-Band transmitter, 3 meter high gain antenna
- Need to be able to downlink 10 kb/s
- EWC 27 HDR-TM X-Band Transmitter
- Developed by SyrLinks
- Capable of LEO transmission to Earth DSN dish
- Downlink 5 Gb/s to 3 meter dish
- TRL9, 10W Power Req, 10x10x3cm, 300 g
- MarCO’s X-Band transmitter
14. Thermal Management
Combination of a variety of methods
- Structure
- Thicker structure surrounding payload allows better
heat dispersion.
- Payload set in trays to reduce heat loss/gain to
conduction
- Plastics utilized for insulation, Metals for heat
conduction
- Radiators
- Over electronics that will heat in use to disperse
15. Command and Data Handling
ISIS On Board Computer (iOBC); Flight Heritage since 2014
400 MHz 32-bit ARM9 processor and 3.3V power supply
94g mass with dimensions 96 x 90 x 12.4 mm
Two 8GB high reliability SD cards or two any size standard SD cards
TRL: 6 to 7
iOBC Costs: $4918.76 to $11,011.31 (EM/FM daughter Boards Optional)
Cube Computer
4-48 MHz, 32-bit ARM Cortex-M3-based MCU
16. References
- "Green High Delta V Propulsion for Cubesats." Web. <http://www.rocket.com/files/aerojet/documents/CubeSat/crop-MPS-
130%20data%20sheet-single%20sheet.pdf>
- Spores, Ronald, Robert Masse, Scott Kimbrel, and Mclean Chris. "GPIM AF-M315E Propulsion System." 15 July 2013. Web.
<https://www.rocket.com/files/aerojet/documents/CubeSat/GPIM%20AF-M315E%20Propulsion%20System.pdf>.
- Richardson, J. E., Dr. (2013, February/March). An examination of the Deep Impact collision site on Comet Tempel 1 via Stardust-NExT:
Placing further constraints on cometary surface properties.
<https://www.researchgate.net/publication/256461959_An_examination_of_the_Deep_Impact_collision_site_on_Comet_Tempel_1_via_Star
dust-NExT_Placing_further_constraints_on_cometary_surface_properties>
- http://www.syrlinks.com/en/products/cubesats/hdr-x-band-transmitter.html
- http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=2915&context=smallsat
- https://marscubesatworkshop.jpl.nasa.gov/static/files/presentation/Asmar-Matousek/07-MarsCubeWorkshop-MarCO-update.pdf
- http://www.cubesatshop.com/product-category/command-and-data-handling/
- http://bluecanyontech.com/wp-content/uploads/2016/07/RW.pdf
- http://bluecanyontech.com/wp-content/uploads/2016/07/NST.pdf
- http://bluecanyontech.com/wp-content/uploads/2016/08/ADCS_F.pdf
- http://www.nasa.gov/sites/default/files/files/3_Mars_2020_Mission_Concept.pdf
- https://directory.eoportal.org/web/eoportal/satellite-missions/m/minxss#foot7%29
- http://amptek.com/products/x-123sdd-complete-x-ray-spectrometer-with-silicon-drift-detector-sdd/#6
- http://lasp.colorado.edu/home/minxss/
Editor's Notes
Princess kenny chan desu
I saw somehwere that the impactor for deepimpact was made of bronze since the plume would not contain bronze, then the signal is filtered out
10 cm x 10 cm x 22.4 cm
Green propellant
Lower freezing point
dV = Isp g0 ln(m0/mf)
dV = 257 m/s (worst case)