Exploration Mission-1(Redirected from Exploration Mission 1)
Exploration Mission-1 or EM-1 (previously known as Space Launch System 1 or SLS-1) is the uncrewed first planned flight of the Space Launch System and the second flight of the Orion Multi-Purpose Crew Vehicle. The launch is planned for June 2020 from Launch Complex 39B at the Kennedy Space Center. The Orion spacecraft will spend approximately 3 weeks in space, including 6 days in a retrograde orbit around the Moon. It is planned to be followed by Exploration Mission 2 in 2023.
Artist concept of SLS Block 1 configuration in flight
|Mission type||Lunar orbital test flight|
|Mission duration||Planned: 3 weeks|
|Spacecraft type||Orion MPCV|
|Manufacturer||Lockheed Martin / Airbus|
|Start of mission|
|Launch date||Planned: June 2020|
|Rocket||SLS Block 1|
|Launch site||Kennedy LC-39B|
|End of mission|
|Landing site||Pacific Ocean|
|Orbital insertion||Planned: 2020|
The Block 1 version of SLS used on this mission will consist of two five-segment Solid Rocket Boosters, four RS-25D engines built for the Space Shuttle program and an Interim Cryogenic Propulsion Stage. EM-1 is intended to demonstrate the integrated spacecraft systems prior to a crewed flight, and in addition, test a high speed reentry (11 km/s) on Orion's thermal protection system.
On 16 January 2013, NASA announced that the European Space Agency will build the Orion Service Module based on its Automated Transfer Vehicle, so the flight could also be regarded as a test of ESA hardware as well as American, and of how the ESA components interact with the American Orion components.
The Exploration Flight Test 1 (EFT-1) flight article was consciously constructed in a way that if all the missing components (seats, life support systems) were added, it would not meet the mass target. It was planned that subsequent capsules would be modified to be lighter, based on manufacturing experience.
In January 2015 NASA and Lockheed announced that some components in the EM-1 capsule would be up to 25 percent lighter compared to the previous one. This would be achieved by changes to the primary structure - the EM-1 article would be welded together from 3 panels for the cone, as opposed to 6 panels used for the EFT-1 article. The total number of welds was reduced from 19 to 7, thus saving the additional mass of the weld material. Other savings would be due to revisiting its various components and wiring. For EM-1 the capsule will be outfitted with complete life support system and crew seats, but will be left uncrewed. However, in February 2017 NASA announced that Robert M. Lightfoot Jr., the agency's Acting Administrator, had asked the Human Exploration and Operations Mission Directorate to study the feasibility of redesigning the mission to include a crew.
The mission will be uncrewed, however NASA did initiate a study to investigate a crewed version of the mission. A crewed version of EM-1 would be composed of a crew of two astronauts, and will be much shorter than the uncrewed version due to safety reasons. The study investigated a crewed mission even with the possibility of further delays to the launch. On 12 May 2017 NASA revealed that it will not be sending astronauts to space for Orion's EM-1 mission following a months-long feasibility study.
|Mission Elapsed Time||Event||Location|
|00:00:00||Launch||Kennedy Space Center|
|00:02:00||Solid Rocket Boosters separation||Altitude 45 km / 28 miles|
|00:03:40||Service Module Panels and Launch Abort System Jettisoned||Altitude 91 km / 57 miles|
|00:08:14||Main Engine Cutoff and 1st Stage Separation||Altitude 157 km / 98 miles|
|00:16:14||Solar Panels Deployed||Altitude 484 km / 301 miles|
|00:54:05||Perigee Raise Maneuver (ICPS)||Altitude 1,791 km / 1,113 miles|
|01:25:00||Trans-Lunar Injection (ICPS)||Altitude 601 km / 373 miles|
|01:53:00||ICPS Stage Separation||Altitude 3,849 km / 2,392 miles|
|Days 1-4||Outbound Coasting Phase||Distance from Earth: 3,849 - 394,501 km / 2,391 - 245,131 miles|
Periodic Trajectory Correction Maneuvers
|4 days 7 h 18 m||Lunar Gravity Assist||Distance from Earth: 401,643 km / 249,569 miles|
Distance to Moon: 100 km / 62 miles
|Days 7-13||Distant Retrograde Orbit||Distance from Earth: 348,931 - 437,321 km / 216,815 - 271,739 miles|
|20 days||Return Powered Flyby||Distance from Earth: 358,558 km / 222,798 miles|
|Days 21-25||Inbound Coasting Phase||Distance from Earth: 364,804 - 67,527 km / 226,678 - 41,959 miles|
Periodic Trajectory Correction Maneuvers
|25 days 11 h 30 m||Crew and Service Module Separation||Altitude 5,140 km / 3,194 miles|
|25 days 11 h 34 m||Reentry||Altitude 100 km|
Vehicle Speed: 11 km/second / 24,500 mph
|Reentry||Altitude 80 km|
Vehicle Temperature: 5,000 °F / 2,760 °C
|25 days 12 h||Parachute Deployment Sequence||Altitude 24,000 ft|
|25 days 12 h||Crew Module Splashdown||Location: Pacific Ocean|
NASA has partnered with the German Aerospace Center (DLR) and the Israel Space Agency (ISA) in conjunction with StemRad and Lockheed Martin to perform the Matroshka AstroRad Radiation Experiment (MARE), which will measure tissue dose deposition and test the effectiveness of the AstroRad radiation vest in a radiation environment beyond low Earth orbit. While radiation shielding strategies of the past have relied on storm shelters in which astronauts can seek refuge as solar storms erupt, the AstroRad's ergonomic design provides a mobile protection system with the same shielding factor as storm shelters without hindering the astronauts’ ability to perform mission sensitive tasks.
The crew compartment of the unmanned EM-1 Orion spacecraft will include two female anthropomorphic phantoms which will be exposed to the intense radiation environment along the lunar orbit, including solar storms and galactic cosmic rays. One phantom will be shielded with the AstroRad and the other will be left unprotected. The phantoms provide the opportunity to precisely measure radiation exposure not only at the surface of the body, but also at the exact location of sensitive organs and tissues inside the human body. Radiation exposure will be measured with implementation of both passive and active dosimeters intentionally distributed throughout the inside of the anthropomorphic phantoms at precise locations of sensitive tissues and high stem cell concentrations. The results of MARE should enable Orion as a platform for other scientific experiments, provide accurate radiation risk projections of deep space exploration, and validate the protective properties of the AstroRad.
Thirteen low-cost CubeSat missions were competitively selected as secondary payloads on the EM-1 test flight. They will reside within the second stage on the launch vehicle from which they will be deployed. Two CubeSats have been selected through NASA's Next Space Technologies for Exploration Partnership, three through the Human Exploration and Operations Mission Directorate, two through the Science Mission Directorate, and three were chosen from submissions by NASA's international partners. The CubeSat spacecraft selected are:
- Lunar Flashlight is a spacecraft that will seek exposed water ice, and map its concentration at the 1-2 kilometer scale within the permanently shadowed regions of the lunar south pole.
- Near-Earth Asteroid Scout is proof-of-concept of a controllable CubeSat solar sail spacecraft capable of encountering near-Earth asteroids (NEA). Observations will be achieved through a close (≈10 km) flyby and using a high resolution science-grade monochromatic camera to measure the physical properties of a near-Earth asteroid. A variety of potential targets would be identified based upon launch date, time of flight, and rendezvous velocity.
- BioSentinel is an astrobiology mission that will use yeast to detect, measure, and compare the impact of deep space radiation on living organisms over long durations beyond low-Earth orbit.
- SkyFire is a spacecraft designed by Lockheed Martin to fly by the Moon and collect surface spectroscopy and thermography.
- Lunar IceCube, designed at the Morehead State University, will search for additional evidence of lunar water ice from a low lunar orbit.
- CubeSat for Solar Particles (CuSP), designed at the Southwest Research Institute will study the dynamic particles and magnetic fields that stream from the Sun and as a proof of concept for the feasibility of a network of stations to track space weather.
- Lunar Polar Hydrogen Mapper (LunaH-Map), designed at the Arizona State University, will map hydrogen within craters near the lunar south pole, tracking depth and distribution of hydrogen-rich compounds like water. It will use a neutron detector to measure the energies of neutrons that interacted with material in the lunar surface. Its mission is planned to last 60 days and perform 141 orbits of the Moon.
- EQUULEUS, designed by JAXA and the University of Tokyo, will image Earth's plasmasphere to study the radiation environment around the Earth while demonstrating low thrust maneuvers for trajectory control in the space between Earth and the Moon.
- OMOTENASHI, designed by JAXA, is a lander/impact probe to study the lunar radiation environment.
- ArgoMoon, designed by Argotec and coordinated by ASI, is designed to image the Interim Cryogenic Propulsion Stage (ICPS) of Orion for mission data and historical records. It will demonstrate technologies necessary for a small spacecraft to maneuver and operate near the ICPS.
The remaining three slots were selected through a competition pitting CubeSat teams from the United States against each other in a series of ground tournaments called 'NASA's Cube Quest Challenge', and were announced by NASA Ames on 8 June 2017. The competition was to contribute to opening deep-space exploration to non-government spacecraft. These slots were awarded to:
- Cislunar Explorers will demonstrate the viability of water electrolysis propulsion and interplanetary optical navigation to orbit the Moon. It was designed by Cornell University, Ithaca, New York.
- Earth Escape Explorer (CU-E3) will demonstrate long-distance communications while in heliocentric orbit. It was designed by the University of Colorado in Boulder.
- Team Miles will demonstrate long-distance communications while in heliocentric orbit and show low-thrust trajectory control techniques by employing a hybrid ion thruster. It was designed by Fluid and Reason, LLC, Tampa, Florida.
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