From ca42f89442fdd19c86fdbb41a5edc10119cea985 Mon Sep 17 00:00:00 2001 From: ricoThaka <134652418+ricoThaka@users.noreply.github.com> Date: Tue, 19 Nov 2024 14:24:47 -0800 Subject: [PATCH] header h1:before { content: "./BUBBLEGUMPOP"; font-size: 4rem; } --- README.md | 620 +++++++++++++++--- .../2024-11-19-WorkTweets-LoggableTweets.md | 0 _sass/base.scss | 224 +------ 3 files changed, 573 insertions(+), 271 deletions(-) create mode 100644 _posts/2024-11-19-WorkTweets-LoggableTweets.md diff --git a/README.md b/README.md index 6bbc389c6f..34153ce75b 100644 --- a/README.md +++ b/README.md @@ -1,85 +1,541 @@ -# The Hacker-Blog theme - -*Hacker-Blog is a minimalistic, responsive jekyll theme built for hackers. It is based on the [hacker theme](https://github.com/pages-themes/hacker) for project pages.* - -Demo: [https://ashishchaudhary.in/hacker-blog](https://ashishchaudhary.in/hacker-blog) - -### Included - -1. Pagination -2. SEO tags -3. Archive Page -4. About Page -5. RSS (`https://base-url/atom`) -6. Sitemap (`https://base-url/sitemap`) -7. Google Analytics (optional) - -## Usage - -1. Fork and Clone this repository -2. Customize your blog -3. Add a new post in `_posts/` directory with proper name format (as shown in placeholder posts) -4. Commit and push to master on a repository named ``. -5. Visit `.github.io` - -## Local Build - -If you want to see the changes before pushing the blog to Github, do a local build. - -1. [`gem install jekyll`](https://jekyllrb.com/docs/installation/#install-with-rubygems) -2. `gem install jekyll-seo-tag` -3. `gem install jekyll-paginate` -4. `gem install jekyll-sitemap` -5. (`cd` to the blog directory, then:) `jekyll serve --watch --port 8000` -6. Go to `http://0.0.0.0:8000/` in your web browser. - -*Note: In case you have set a `baseurl` different than `/` in `_config.yml`, go to `http://0.0.0.0:8000/BASEURL/` instead.* - -### Local build using docker - -```bash -docker run --rm -p 8000:8000 \ - --volume="LOCATION_OF_YOUR_JEKYLL_BLOG:/srv/jekyll" \ - -it tocttou/jekyll:3.5 \ - jekyll serve --watch --port 8000 -``` - -Replace `LOCATION_OF_YOUR_JEKYLL_BLOG` with the full path of your blog repository. Visit `http://localhost:8000/` to access the blog. - -*Note: In case you have set a `baseurl` different than `/` in `_config.yml`, go to `http://0.0.0.0:8000/BASEURL/` instead.* - -## Customizing - -### Configuration variables - -Edit the `_config.yml` file and set the following variables: - -```yml -title: [The title of your blog] -description: [A short description of your blog's purpose] -author: - name: [Your name] - email: [Your email address] - url: [URL of your website] - -baseurl: [The base url for this blog.] - -paginate: [Number of posts in one paginated section (default: 3)] -owner: [Your name] -year: [Current Year] -``` - -*Note: All links in the site are prepended with `baseurl`. Default `baseurl` is `/`. Any other baseurl can be setup like `baseurl: /hacker-blog`, which makes the site available at `http://domain.name/hacker-blog`.* - -Additionally, you may choose to set the following optional variables: - -```yml -google_analytics: [Your Google Analytics tracking ID] -``` - -### About Page - -Edit `about.md` +# Rashard Kelly NasaJpl MRO JUNO iSS + +[![Twitter Follow](https://img.shields.io/badge/Social-ricoThaka__-blue?style=social&logo=X)](https://twitter.com/ricothaka) +[![.github/workflows/ci.yaml](https://github.com/pages-themes/leap-day/actions/workflows/ci.yaml/badge.svg)](https://github.com/pages-themes/leap-day/actions/workflows/ci.yaml) [![Gem Version](https://badge.fury.io/rb/jekyll-theme-leap-day.svg)](https://badge.fury.io/rb/jekyll-theme-leap-day) + +![NASAJPL](https://space.jpl.nasa.gov/msl/headers/msl.gif) + +![Thumbnail of Rashard](https://pbs.twimg.com/media/GYBdj5Eb0AI5dIy?format=jpg&name=large) + + +![Perservere](https://science.nasa.gov/wp-content/uploads/2024/03/1065.gif) +![PioNeer10](https://upload.wikimedia.org/wikipedia/commons/e/ed/Pioneer_10_-_Pioneer_11_-_mission_patch_-_Pioneer_patch.png) + +[Pioneer 10](https://en.wikipedia.org/wiki/Pioneer_10) (originally designated Pioneer F) is a NASA space probe launched in 1972 that completed the first mission to the planet Jupiter.[6] + +/PDS/CATALOG/ +https://hirise-pds.lpl.arizona.edu/PDS/CATALOG/MISSION.CAT +PDS_VERSION_ID = PDS3 +LABEL_REVISION_NOTE = "2006-07-24, R. Sharrow, initial; + 2006-12-15, S. Slavney, reformatted & revised; + 2007-07-30, S. Slavney, Aerobraking subphases" +RECORD_TYPE = STREAM + +OBJECT = MISSION + [MISSION_NAME = "MARS RECONNAISSANCE ORBITER"](https://hirise-pds.lpl.arizona.edu/PDS/CATALOG/MISSION.CAT) + + OBJECT = MISSION_INFORMATION + MISSION_START_DATE = 2005-08-12 + MISSION_STOP_DATE = UNK + MISSION_ALIAS_NAME = "MRO" + MISSION_DESC = " + + Mission Overview + ================ + + The Mars Reconnaissance Orbiter spacecraft was launched from Cape + Canaveral Air Force Station on 12 August 2005 aboard a Lockheed-Martin + Atlas V-401 launch vehicle. After a five-month cruise and a two-month + approach to Mars, MRO entered Mars' orbit on 10 March 2006 and began + aerobraking. The primary science phase began on 8 November, 2006. The + primary science phase is planned to last one Mars year (approximately two + Earth years), after which an extended mission may be scheduled. + + Note: This description has been written early in the Primary Science + Phase of the MRO mission. It will be revised at least once by the + end of the mission. + + Mission Phases + ============== + + The Mars Reconnaissance Orbiter Mission is divided in time into six + phases: Launch, Cruise, Approach and Orbit Insertion, Aerobraking, + Primary Science, and Relay. + + LAUNCH + ------ + Launch extended from the start of the countdown to the initial + acquisition, by the DSN, of the orbiter in a safe and stable + configuration. + + The baseline launch vehicle for the MRO mission was the Lockheed-Martin + Atlas V 401. This launch vehicle was selected by NASA-KSC (Kennedy + Space Flight Center) via a competitive procurement under the NASA + Launch Services (NLS) contract. The Atlas V 401 was a two-stage + launch vehicle consisting of the Atlas Common Core Booster and a + single engine Centaur upper stage. The Centaur upper stage could + perform multiple restarts of its main engine. For precise pointing and + control during coast and powered flight, the Centaur used a flight + control system that was 3-axis stabilized. The Atlas large payload + fairing was used to protect MRO during the Atlas boost phase. This + fairing had a diameter of 4.2m and a length of 12.2m. + + The launch and injection of MRO occured during the Mars opportunity + of August 2005. The Atlas booster, in combination with the Centaur + upper stage, delivered the MRO spacecraft into a targeted parking + orbit. After a short coast, a restart of the Centaur upper stage + injected MRO onto an interplanetary transfer trajectory. + + Mission Phase Start Time : 2005-08-12 + Mission Phase Stop Time : 2005-08-12 + + CRUISE + ------ + Duration: About five months. The cruise phase extended from DSN + initial acquisition, in a safe and stable configuration, until two + months prior to the Mars Orbit Insertion (MOI) maneuver. Primary + activities during cruise included spacecraft and payload checkout and + calibration. These activities, along with daily monitoring of orbiter + subsystems, were performed in order to fully characterize the + performance of the spacecraft and its payload prior to arrival at + Mars. In addition, standard navigation activities were performed + during this flight phase, the first being the largest TCM performed + fifteen days after launch. + + Mission Phase Start Time : 2005-08-12 + Mission Phase Stop Time : 2006-01-10 + + APPROACH AND ORBIT INSERTION + ---------------------------- + This phase extended from two months prior to Mars Orbit Insertion + (MOI), through MOI, and until the orbiter was checked out and ready to + begin aerobraking. The orbiter was inserted into a nearly polar orbit + with a period of 35 hours. + + During the last sixty days of the interplanetary transit, spacecraft + and ground activities were focused on the events necessary for a + successful arrival and safe capture at Mars. Navigation techniques + included the use of delta-DOR measurements in the orbit determination. + This technique yielded a precise determination of the inbound + trajectory with a series of final TCMs used to control the flight path + of the spacecraft up to the MOI maneuver. + + Also during the approach phase, MRO performed the Optical Navigation + experiment. This involved pointing the optical navigation camera + (ONC) at the moons of Mars - Phobos and Deimos, and tracking their + motion. By comparing the observed position of the moons to their + predicted positions, relative to the background stars, the ground was + able to accurately determine the position of the orbiter. + + Upon arrival at Mars on March 10, 2006, the spacecraft performed its + MOI maneuver using its six main engines. MOI inserted the spacecraft + into an initial, highly elliptical capture orbit. The delta-V + required to accomplish this critical maneuver was 1015 m/s and took + about 26 minutes to complete. For most of the burn, the orbiter was + visible from the DSN stations. The signal was occulted as the orbiter + went behind Mars, and appeared again a short time later. The reference + MRO capture orbit had a period of 35 hours and a periapsis altitude of + 300km. The orientation of the ascending node was 8:30 PM LMST. The + capture orbit was been selected such that aerobraking would be + completed prior to the start of solar conjunction (September 23, + 2006). + + Mission Phase Start Time : 2006-01-10 + Mission Phase Stop Time : 2006-03-10 + + + AEROBRAKING + ----------- + The Aerobraking Phase of the mission consisted of three sub-phases, + Aerobraking Operations, Transition to PSO Operations, and Solar + Conjunction. + + Aerobraking Operations Sub-Phase + -------------------------------- + + One week after MOI, aerobraking operations commenced. During this + time period, the orbiter used aerobraking techniques to supplement its + onboard propulsive capability and to reduce its orbit period to that + necessary for the primary science orbit (PSO). Aerobraking Operations + consisted of a walk-in phase, a main phase, and a walkout phase, and + was followed by a transition to the PSO. During the walk-in phase, the + spacecraft established initial contact with the atmosphere as the + periapsis altitude of the orbit was slowly lowered. The walk-in phase + continued until the dynamic pressures and heating rate values required + for main phase, or steady state aerobraking, were established. During + the main phase of aerobraking operations, large scale orbit period + reduction occurred as the orbiter was guided to dynamic pressure + limits. Main phase aerobraking continued until the orbit lifetime of + the orbiter reached 2 days. (Orbit lifetime is defined as the time it + takes the apoapsis altitude of the orbit to decay to an altitude of + 300km.) When the orbit lifetime of the orbiter reached 2 days, the + walkout phase of aerobraking operations began. During the walkout + phase, the periapsis altitude of the orbit was slowly increased as the + 2 day orbit lifetime of the orbiter was maintained. Once the orbit of + the orbiter reached an apoapsis altitude of 450km, the orbiter + terminated aerobraking by propulsively raising the periapsis of its + orbit out of the atmosphere. + + Because the PSO had nodal orientation requirements, the aerobraking + phase of the MRO mission had to proceed in a timely manner and be + completed near the time the desired nodal geometry was achieved. After + approximately 4.5 months of aerobraking, the dynamic pressure control + limits were reset such that the orbiter will fly to the desired 3:00 + pm LMST nodal target. + + Transition to PSO Operations Sub-Phase + -------------------------------------- + + Once the orbit apoapsis altitude was reduced to 450 km, the orbiter + terminated aerobraking by raising periapsis to a safe altitude and + begin a transition to the Primary Science Phase. The periapsis of + the transition orbit rotated around Mars from over the equatorial + latitudes to the North Pole. When periapsis reached the North Pole, + apoapsis was reduced propulsively to 255 km and orbit rotation stopped + - the orbit was frozen with periapsis over the South Pole and apoapsis + over the North Pole. The SHARAD antenna and the CRISM cover were + deployed, the instruments were checked out and remaining calibrations + were performed. The payloads collected data in their normal operating + modes to ensure that the end-to-end data collection and processing + systems worked as planned. + + Solar Conjuction Sub-Phase + -------------------------- + + Orbiter activities in preparation for science were then temporarily + suspended during a four week period surrounding solar conjunction. + + + Mission Phase Start Time : 2006-03-17 + Mission Phase Stop Time : 2006-11-07 + + Aerobraking Operations Sub-Phase Start Time: 2006-03-17 + Aerobraking Operations Sub-Phase Stop Time: 2006-09-15 + + Transition to PSO Operations Sub-Phase Start Time: 2006-09-15 + Transition to PSO Operations Sub-Phase Stop Time: 2006-10-09 + + Solar Conjunction Sub-Phase Start Time: 2006-10-09 + Solar Conjunction Sub-Phase Stop Time: 2006-11-07 + + + PRIMARY SCIENCE + --------------- + The 255 x 320 km Primary Science Orbit (PSO) is a near-polar orbit + with periapsis frozen over the South Pole. It is sun-synchronous with + an ascending node orientation that provides a Local Mean Solar Time + (LMST) of 3:00 p.m. at the equator. Because of the eccentricity of + the Mars orbit around the Sun, true solar time varies by nearly 45 + minutes over the course of one Mars year. + + The Primary Science Phase of the mission began after solar conjunction + and after turn-on and checkout of the science instruments in the + Primary Science Orbit. The phase started on 8 November 2006, will + extend for one Mars year, and will conclude prior the next solar + conjunction near the end of 2008. + + The science investigations are functionally divided into daily global + mapping and profiling, regional survey, and globally distributed + targeting investigations. The global mapping instruments are the MCS + and the MARCI. The targeted investigations are HiRISE, CRISM, and + CTX. The survey investigations are CRISM and CTX (in survey modes), + and SHARAD. The global mapping instruments require nadir pointing, + low data rate, and continuous or near-continuous operations. The + global mapping investigations are expected to use less than 5% of the + expected downlink data volume. The targeted and survey instruments + are high data rate instruments and will require precise targeting in + along-track timing and/or cross-track pointing for short periods of + time over selected portions of the surface. It is expected that more + than 95% of the available downlink data volume will be used for + targeted and survey investigations. All instruments can take data + simultaneously. + + Toward the end of the primary science phase, other Mars missions + launched in the 2007 opportunity will begin to arrive. Phoenix, the + first of the Mars Program's Scout missions has been selected to launch + in the 2007 Mars opportunity. Phoenix, a lander mission that will + collect and analyze subsurface ice and soil material, will arrive in + late May 2008. Phoenix will need MRO to characterize its prime landing + site choices early in the Primary Science Phase. MRO will provide + relay support for Entry, Descent, and Landing (EDL) activities and for + telecommunications late in the PSP after Phoenix arrives at Mars. + Phoenix and MRO will also coordinate some observations to maximize + science return to the Mars Exploration Program. Another mission, the + Mars Science Laboratory (MSL) is currently proposed for launch in + 2009, with arrival in 2010, during the MRO Relay Phase. + + MSL will need MRO to provide and characterize candidate landing sites + using observations taken during the MRO PSP. (Final certification of + the prime MSL landing sites may require limited observations by the + science payload in 2009 during the Relay phase. However, this has not + been committed to by MRO) MRO will also provide EDL support and relay + telecommunications for MSL. During the primary science phase, periodic + instrument calibrations will be performed to verify the measurement + characteristics, stability and health of the instruments. At the + conclusion of the Primary Science Phase, these calibrations will be + repeated, so that the final instrument characteristics are known. + + NASA may approve, as resources and on-orbit capability permit, + continuation of science observations beyond the Primary Science Phase + until end of the Relay Phase (also End of Mission). The orbiter will + remain in the Primary Science Orbit during the Relay Phase. + + Mission Phase Start Time : 2006-11-08 + Mission Phase Stop Time : 2008-11-09 + + + RELAY + ----- + MRO will provide critical relay support to missions launched as part + of the Mars Exploration Program after MRO. For spacecraft launched in + the 2007 opportunity, this relay support will occur before the end of + the MRO Primary Science Phase. Following completion of the Primary + Science Phase, MRO will continue to provide critical relay support for + Mars missions until its end of mission. + + While all of the missions that MRO will support have not yet been + selected, Phoenix, the first of the Mars Program's Scout missions has + been selected to launch in the 2007 Mars opportunity. Phoenix, a + lander mission that will collect and analyze soil samples, will arrive + in late May 2008. It will need science imaging support for site + characterization and selection and relay support for its Entry, + Descent and Landing activities and for its science data return. + Another mission, the Mars Science Laboratory (MSL) is proposed for the + 2009 Mars opportunity. MSL will also need science imaging support for + site characterization and selection and relay support for EDL and + science data return. The MRO Mission Plan describes the generic + support activities for any mission as well as current early planning + in support of Phoenix and MSL. Activities regarding site + characterization and selection will be described as part of the + Primary Science Phase, and activities regarding relay support will be + described as part of the Relay Phase. + + The orbiter has been designed to carry enough propellant to remain + operational for 5 years beyond the end-of-mission (EOM) on December + 31, 2010 to support future MEP missions. As this is beyond the EOM, + no activities have been planned for this time period. To ensure that + the orbiter remains in a viable orbit during this time, its orbit + altitude will be increased at EOM to about 20 km inside the orbit of + the Mars Global Surveyor spacecraft. + + The MRO approach to planetary protection differs from any previous + Mars orbiter. The NASA requirements for planetary protection, + NPG8020.12B, allow a class III mission, like MRO, to use either the + 'probability of impact/orbit lifetime' or a 'total bio burden' + approach. Implementing the Level 1 MRO requirements with the + instruments selected via the NASA AO requires low orbits whose + lifetimes are incompatible with a 'probability of impact/orbit + lifetime' approach to Planetary Protection. Therefore, MRO is + implementing the requirements of NPG8020.12B using the 'total + bio-burden' approach. This approach has been documented in the MRO + Planetary Protection Plan (D-23711). The details of cleaning + requirements are documented in the MRO Planetary Protection + Implementation Plan, MRO 212-11, JPL D-22688. The MRO launch targets + will be biased away from a direct intercept course with Mars to ensure + a less than 1 in 10,000 chance of the launch vehicle upper stage + entering Mars atmosphere. + + The End-of-Mission (EOM) is planned for December 31, 2010 just prior + to the third solar conjunction of the mission. The orbiter will + perform a propulsive maneuver to place itself in a higher orbit to + increase the orbit lifetime and enable extended mission operations. + + Mission Phase Start Time : 2008-11-09 + Mission Phase Stop Time : 2010-12-31 + " + + MISSION_OBJECTIVES_SUMMARY = " + + The driving theme of the Mars Exploration Program is to understand the + role of water on Mars and its implications for possible past or + current biological activity. The Mars Reconnaissance Orbiter (MRO) + Project will pursue this 'Follow-the-Water' strategy by conducting + remote sensing observations that return sets of globally distributed + data that will: 1) advance our understanding of the current Mars + climate, the processes that have formed and modified the surface of + the planet, and the extent to which water has played a role in surface + processes; 2) identify sites of possible aqueous activity indicating + environments that may have been or are conducive to biological + activity; and 3) thus identify and characterize sites for future + landed missions. + + The MRO payload is designed to conduct remote sensing science + observations, identify and characterize sites for future landers, and + provide critical telecom/navigation relay capability for follow-on + missions. The mission will provide global, regional survey, and + targeted observations from a low 255 km by 320 km Mars orbit with a + 3:00 P.M. local mean solar time (ascending node). During the one + Martian year (687 Earth days) primary science phase, the orbiter will + acquire visual and near-infrared high-resolution images of the + planet's surface, monitor atmospheric weather and climate, and search + the upper crust for evidence of water. After this science phase is + completed, the orbiter will provide telecommunications support for + spacecraft launched to Mars in the 2007 and 2009 opportunities. The + primary mission will end on December 31, 2010, approximately 5.5 years + after launch. + + + Science Questions Addressed + --------------------------- + + The MRO mission has the primary objective of placing a science orbiter + into Mars orbit to perform remote sensing investigations that will + characterize the surface, subsurface and atmosphere of the planet and + will identify potential landing sites for future missions. The MRO + payload will conduct observations in many parts of the electromagnetic + spectrum, including ultraviolet and visible imaging, visible to + near-infrared imaging spectrometry, thermal infrared atmospheric + profiling, and radar subsurface sounding, at spatial resolutions + substantially better than any preceding Mars orbiter. In pursuit of + its science objectives, the MRO mission will: + + - Characterize Mars' seasonal cycles and diurnal variations of water, + dust, and carbon dioxide. + - Characterize Mars' global atmospheric structure, transport, and + surface changes. + - Search sites for evidence of aqueous and/or hydrothermal activity. + - Observe and characterize the detailed stratigraphy, geologic + structure, and composition of Mars surface features. + - Probe the near-surface Martian crust to detect subsurface structure, + including layering and potential reservoirs of water and/or water ice. + - Characterize the Martian gravity field in greater detail relative to + previous Mars missions to improve knowledge of the Martian crust and + lithosphere and potentially of atmospheric mass variation. + - Identify and characterize numerous globally distributed landing sites + with a high potential for scientific discovery by future missions. + + In addition, MRO will provide critical telecommunications relay + capability for follow-on missions and will conduct, on a + non-interference basis with the primary mission science, telecom and + navigation demonstrations in support of future Mars Exploration + Program (MEP) activities. Specifically, the MRO mission will: + + - Provide navigation and data relay support services to future MEP + missions. + - Demonstrate Optical Navigation techniques for high precision delivery + of future landed missions. + - Perform an operational demonstration of high data rate Ka-band + telecommunications and navigation services. + + Designed to operate after launch for at least 5.4 years, the MRO + orbiter will use a new spacecraft bus design provided by Lockheed + Martin Space Systems Company, Space Exploration Systems Division in + Denver, Colorado. The orbiter payload will consist of six science + instruments and three new engineering payload elements listed as + follows: + + Science Instruments + - HiRISE, High Resolution Imaging Science Experiment + - CRISM, Compact Reconnaissance Imaging Spectrometer for Mars + - MCS, Mars Climate Sounder + - MARCI, Mars Color Imager + - CTX, Context Camera + - SHARAD, Shallow (Subsurface) Radar + + Engineering Payloads + - Electra UHF communications and navigation package + - Optical Navigation (Camera) Experiment + - Ka Band Telecommunication Experiment + + To fulfill the mission science goals, seven scientific investigations + teams were selected by NASA. Four teams (MARCI, MCS, HiRISE, and + CRISM) are led by Principal Investigators (PI), each responsible for + the provision and operation of a scientific instrument and the + analysis of its data. The MARCI PI and Science Team also act to + provide and operate, as Team Leader (TL) and Team Members, the CTX + facility instrument that will provide context imaging for HiRISE and + CRISM, as well as acquire and analyze independent data in support of + the MRO scientific objectives. The Italian Space Agency (ASI) will + provide a second facility instrument, SHARAD, for flight on MRO. ASI + and NASA have both selected members of the SHARAD investigation team. + In addition to the instrument investigations, Gravity Science and + Atmospheric Structure Facility Investigation Teams will use data from + the spacecraft telecommunications and accelerometers, respectively, to + conduct scientific investigations. + + The MRO shall accomplish its science objectives by conducting an + integrated program of three distinct observational modes: + + - Daily global mapping and profiling observations + - Regional survey observations, and + - Globally distributed, targeted observations + + These observation modes will be intermixed and often overlapping. + Some instruments have more than one observational mode. In addition, + many targeted observations will involve nearly simultaneous, + coordinated observations by more than one instrument. This program of + scientific observation will be carried out for one Mars year or more + in order to characterize the full seasonal variation of the Martian + climate and to target hundreds of globally distributed sites with high + potential for further scientific discovery. + + Mission Success Criteria + ------------------------ + + The following mission success criteria have been established for the + MRO Project. The mission success criteria are described and controlled + in the MRO Project Implementation Plan. + + For Full Mission Success, the following criteria must be met: + + - Operate the orbiter and all six (6) science instruments in the + Primary Science Orbit in targeting, survey and mapping modes, as + appropriate, over the one Mars year of the Primary Science Phase; + conduct the gravity and accelerometer investigations. Each science + instrument shall have capabilities that meet or exceed their + respective science instrument requirements. + + - Return, over the one-Mars-year Primary Science Phase, representative + data sets for each instrument for a total science data volume return + of 26 Tbits or more. Included in the returned data volume shall be + information describing hundreds of globally distributed targets. + + - Process, analyze, interpret, and release data in a timely manner, + including archival of acquired data and standard data products in the + PDS within 6 months of acquisition or as negotiated in the Science + Data Management Plan (JPL D22218). + + - Conduct relay operations for U.S. spacecraft launched to Mars in the + 2007 and 2009 opportunities. + + + For Minimum Mission Success, the following criteria must be met: + + - Operate the orbiter and its science payload in targeting, survey and + mapping modes, as appropriate, in the Primary Science Orbit during the + one-Mars-year of the Primary Science Phase; conduct gravity and + accelerometer investigations. Science instruments shall have + capabilities that meet their respective science instrument + requirements. + + - Return 10 Tbits of science data from HiRISE or CRISM or from their + combined operations, plus 5 Tbits of representative science data over + the one-Mars-year Primary Science Phase from at least 3 of the 4 other + instruments (CTX, MARCI, MCS, SHARAD); conduct gravity and + accelerometer investigations. Included in the returned data volumes + shall be information describing 100 or more globally distributed + targets. + + - Process, analyze, interpret, and release data in a timely manner, + including archival of acquired data and standard data products in the + PDS. + + - Conduct relay operations for U.S. spacecraft launched to Mars in the + 2007 and 2009 opportunities. + " + + END_OBJECT = MISSION_INFORMATION + + OBJECT = MISSION_HOST + INSTRUMENT_HOST_ID = MRO + OBJECT = MISSION_TARGET + TARGET_NAME = MARS + END_OBJECT = MISSION_TARGET + END_OBJECT = MISSION_HOST + + OBJECT = MISSION_REFERENCE_INFORMATION + REFERENCE_KEY_ID = "UNK" + END_OBJECT = MISSION_REFERENCE_INFORMATION + +END_OBJECT = MISSION + +END + + + +### Running tests + +The theme contains a minimal test suite, to ensure a site with the theme would build successfully. To run the tests, simply run `script/cibuild`. You'll need to run `script/bootstrap` once before the test script will work. ### Layout diff --git a/_posts/2024-11-19-WorkTweets-LoggableTweets.md b/_posts/2024-11-19-WorkTweets-LoggableTweets.md new file mode 100644 index 0000000000..e69de29bb2 diff --git a/_sass/base.scss b/_sass/base.scss index 3cc3b7feb1..d1270fded5 100644 --- a/_sass/base.scss +++ b/_sass/base.scss @@ -10,166 +10,22 @@ -html, -body, -div, -span, -applet, -object, -iframe, -h1, -h2, -h3, -h4, -h5, -h6, -p, -blockquote, -pre, -a, -abbr, -acronym, -address, -big, -cite, -code, -del, -dfn, -em, -img, -ins, -kbd, -q, -s, -samp, -small, -strike, -strong, -sub, -sup, -tt, -var, -b, -u, -i, -center, -dl, -dt, -dd, -ol, -ul, -li, -fieldset, -form, -label, -legend, -table, -caption, -tbody, -tfoot, -thead, -tr, -th, -td, -article, -aside, -canvas, -details, -embed, -figure, -figcaption, -footer, -header, -hgroup, -menu, -nav, -output, -ruby, -section, -summary, -time, -mark, -audio, -video { - margin: 0; - padding: 0; - border: 0; - font-size: 100%; - font: inherit; - vertical-align: baseline; -} -/* HTML5 display-role reset for older browsers */ -article, -aside, -details, -figcaption, -figure, -footer, -header, -hgroup, -menu, -nav, -section { - display: block; -} -body { - line-height: 1; -} -ol, -ul { - list-style: none; -} -blockquote, -q { - quotes: none; -} -blockquote:before, -blockquote:after, -q:before, -q:after { - content: ""; - content: none; -} -table { - border-collapse: collapse; - border-spacing: 0; -} - -* { - box-sizing: border-box; -} -/* ~~~~~~~~~~~~~~~~~~~~~ h1, h2, h3, h4, h5, h6 { - margin: 0 0 50px; - padding-left: 820px; -} */ - -* { - box-sizing: border-box; -} - - html { -font-family: "Comfortaa", -apple-system, Ubuntu, "Ariel Black", Verdana; -font-size: 1rem; + margin:0px; padding:0px; color: white; height: 100%; width: 100%; margin: 15px; -background: -linear-gradient(45deg, - #08a0e9 25%, - dodgerblue 0, - dodgerblue 50%, - #08a0e9 0, - #08a0e9 75%, - dodgerblue 0), url(https://t4.ftcdn.net/jpg/01/11/31/93/360_F_111319320_3gSczDAUKn9b5DAbQdkILWgvA28p4lrx.jpg) ; -background-size: 80.4px 80.4px; -font-family: "VT323", monospace; -background-attachment: fixed; -height: 100vh; -width: 100vw; +background : #0D0D0D; +background-image : + linear-gradient(#262626 1px, transparent 0), + linear-gradient(90deg, #262626 1px, transparent 0); +background-size: 30px 30px; + background-attachment: fixed; + height: 100vh; + width: 100vw; } @@ -193,7 +49,8 @@ body { /* seems resource heavy text-shadow: 0 0 11px #ffffff; */ color: white; - + font-family: "IBM Plex Sans","Comfortaa", -apple-system, Ubuntu, "Ariel Black", Verdana; + font-size: 1rem; } p { @@ -401,51 +258,40 @@ li:hover ul { float: right; flex-wrap: nowrap; } + +@import url('https://fonts.googleapis.com/css2?family=Anybody:wght@900&family=Fredoka+One&display=swap'); + h1 { - font-size: 170%; - color: white; - /* background: linear-gradient(45deg, - #F2D338 25%, #262626 0, #262626 50%, - #F2D338 0, #F2D338 75%, #262626 0); -background-size: 80.4px 80.4px; */ - font-family: "VT323", monospace; - - background: linear-gradient(to top, transparent, #b1b1b1 100%), - #262626 - repeating-linear-gradient( - 45deg, - transparent, - transparent 35px, - rgba(255, 255, 255, 0.5) 35px, - rgba(255, 255, 255, 0.5) 70px - ); - background-clip: padding-box; - border-left: 1px solid rgba(255, 255, 255, 0.3); - border-top: 1px solid rgba(255, 255, 255, 0.7); - box-shadow: 0px 1px 3px 1px #969494; - background-attachment: fixed; + + + display: block; + word-break: break-all; +font-size: 3rem; + line-height: 1.7rem; + margin: auto; + font-family: 'Fredoka One', 'Anybody', -apple-system, Ubuntu, "Ariel Black", Verdana; + + text-shadow: + + 0 0 42px #0DCBFF, + 0 0 82px #0DCBFF, + 0 0 92px #0DCBFF, + 0 0 102px #0DCBFF, + 0 0 125px #0DCBFF; + letter-spacing: -1px; + + + } h2 { background: transparent url(https://photojournal.jpl.nasa.gov/jpeg/PIA20753.jpg) center repeat; - font-size: 140%; + font-size: 2rem; color: white; } -header h1:before { - content: "./BUBBLEGUMPOP"; - font-size: 4rem; -} - -header h2 { - content: "./BUBBLEGUMPOP_SARTU_LETS_GO ~>"; - font-size: 1em; - font-weight: 300; - color: #fff; - -} /* Buttons