With great intention to travel into space one day in the future via one of the LEO (Low Earth Orbit) flights that are being offered by a host of commercial cosmonaut companies, combined with an infinite love and curiousity for space exploration, I have been following diligently the developments of the Orion Multi-Purpose Crew Vehicle for some time.
Realizing just how important Orion is to mankind's future, I have decided to share Orion's updated activities as a series of spacecraft under the Orion label make its way into production, and eventually into the cosmos.
Below is a historical summary of Orion. I will follow this up with a host of interviews, news reports, etc. But for now - take it all in!
Orion
 |
|---|
| Description |
|---|
| Role: | Beyond LEO, back-up for commercial cargo and crew to the ISS[1] |
| Crew: | 2–6[2] |
| Carrier rocket: | Space Launch System[3](planned-deep space),
|
| Launch date: | December 2013 or later (uncrewed test launch)[4] |
| Dimensions |
|---|
| Height: | |
| Diameter: | 5 m (16.5 ft) |
| Pressurized volume: | 19.56 m3 (691 cu ft) [5] |
| Habitable volume: | 8.95 m3 (316 cu ft) [5] |
| Capsule mass: | 8,913 kg (19,650 lb) |
| Service Module mass: | 12,337 kg (27,198 lb) |
| Total mass: | 21,250 kg (46,848 lb) |
| Service Module propellant mass: | 7,907 kg (17,433 lb) |
| Performance |
|---|
| Total delta-v: | 1,595 m/s |
| Endurance: | 21.1 days[2][5] |
[edit]Mission
The spacecraft is named for for the famous
Orion constellation.
[17]
[edit]History
Our second goal is to develop and test a new spacecraft, the Crew Exploration Vehicle, by 2008, and to conduct the first manned mission no later than 2014. The Crew Exploration Vehicle will be capable of ferrying astronauts and scientists to the Space Station after the shuttle is retired. But the main purpose of this spacecraft will be to carry astronauts beyond our orbit to other worlds. This will be the first spacecraft of its kind since the Apollo Command Module.
[18]
After the replacement of
Sean O'Keefe, NASA's procurement schedule and strategy completely changed, as described above. In July 2004, before he was named NASA administrator, Michael Griffin participated in a study called "Extending Human Presence Into the Solar System"
[19] for The
Planetary Society, as a co-team leader. The study offers a strategy for carrying out Project Constellation in an affordable and achievable manner. Since Griffin was one of the leaders of the study, it can be assumed that he agrees with its conclusions, and the study may show insight into possible future developments of the CEV. Griffin's actions as administrator supported the goals of the plan.
According to the executive summary, the study was built around "a staged approach to human exploration beyond low Earth orbit (LEO)."
[19] It recommends that Project Constellation be carried out in three distinct stages. These are:
- Stage 1 – "Features the development of a new crew exploration vehicle (CEV), the completion of the International Space Station (ISS), and an early retirement of the shuttle orbiter. Orbiter retirement would be made as soon as the ISS U.S. Core is completed (perhaps only 6 or 7 flights) and the smallest number of additional flights necessary to satisfy our international partners’ ISS requirements. Money saved by early orbiter retirement would be used to accelerate the CEV development schedule shorten the hiatus in U.S. capability to reach and return from LEO."[19]
- Stage 2 – "Requires the development of additional assets, including an updated CEV capable of extended missions of many months in interplanetary space. Habitation, laboratory, consumables, and propulsion modules, to enable human flight to the vicinities of the Moon and Mars, the Lagrange points, and certain near-Earth asteroids."[19]
- Stage 3 – "Development of human-rated planetary landers is completed in Stage 3, allowing human missions to the surface of the Moon and Mars beginning around 2020."[19]
A number of changes to the original CEV acquisition strategy were explained in a NASA study called the
Exploration Systems Architecture Study. The results were presented at a news conference held on 19 September 2005.
[20] The ESAS recommends strategies for flying the manned Orion by 2014, and endorses a
Lunar Orbit Rendezvous approach to the Moon. The LEO versions of Orion were intended carry crews of four to six to the ISS. The lunar version of the Orion would carry a crew of four and the Mars Orion would carry six.
[citation needed] Cargo would also be carried aboard an unmanned version of Orion, similar to the Russian
Progress cargo ships. The contractor for the Orion is
Lockheed Martin, which was selected by NASA in September, 2006 and is the current contractor for the Space Shuttle's External Tank and the
Atlas V EELV.
Orion is Apollo-like, not a
lifting body or
winged vehicle like the now retired Shuttle. Like the Apollo Command Module, Orion would be attached to a service module for life support and propulsion. It is intended to land in water but past versions had included plans for it to land on land. Landing on the west coast would allow the majority of the reentry path to be flown over the Pacific Ocean rather than populated areas. Orion will have an
AVCOAT ablative[21] heat shield that would be discarded after each use.
The Orion spacecraft (CEV) will weigh about 25 tons (23 tonnes), slightly less than the mass of the
Apollo Command/Service Module at 33 tons (30 tonnes). The
Orion Crew Module will weigh about 9.8 tons (8.9 tonnes), greater than the equivalent
Apollo Command Module at 6.4 tons (5.8 tonnes). With a diameter of 16.5 feet (5 metres) as opposed to 12.8 feet (3.9 metres), it will provide 2.5 times greater volume.
[22]
Accelerated lunar mission development was slated to start by 2010, once the Shuttle was retired. The
Lunar Surface Access Module (LSAM) and heavy-lift boosters were to be developed in parallel and would both be ready for flight by 2018. The eventual goal is to achieve a lunar landing by 2020. The LSAM would be much larger than the
Apollo Lunar Module and is anticipated to be capable of carrying up to around 23 tons (21 tonnes) of cargo to the lunar surface to support a future
lunar outpost. This weight in cargo is greater than the mass of the entire
Apollo Lunar Module.
Like the Apollo Lunar Module, the LSAM would include a descent stage for landing and an ascent stage for returning to orbit. The crew of four would ride in the ascent stage. The ascent stage would be powered by a
methane/
oxygen fuel for return to lunar orbit (later changed to liquid hydrogen and liquid oxygen, due to the infancy of oxygen/methane rocket propulsion). This would allow a derivative of the same lander to be used on later Mars missions, where methane propellant can be manufactured from the Martian soil in a process known as
in-situ resource utilization (ISRU). The LSAM would support the crew of four on the lunar surface for about a week and use advanced roving vehicles to explore the lunar surface. The huge amount of cargo carried by the LSAM would be extremely beneficial for supporting a lunar base and for bringing large amounts of scientific equipment to the lunar surface.
[edit]Design revisions and updates
Comparison of 604, 605 and 606 versions
- July 2006 design revisions
In late July 2006 NASA's second design review resulted in major changes to the spacecraft design.
[23] Originally, NASA wanted to use liquid
methane (LCH
4) as the SM fuel, but due to the infancy of oxygen/methane-powered rocket technologies and the need to launch the Orion by 2012, the switch to
hypergolic propellants was mandated in late July 2006. This switch will allow NASA to man-rate the Orion and Ares I stack by no later than 2011,
[citation needed] and eliminate one potential cause of the gap between the shuttle's retirement in 2010 and the first manned Orion flight.
[24]
- April 2007 contract revision
On 20 April 2007 NASA and Lockheed-Martin signed a modification to the Orion contract. The updated contract adds two years to the Orion project design phase, adds two test flights of Orion's launch abort system, and deletes from the initial design phase production of a pressurized cargo carrier for the International Space Station.
[25]
- May 2007 design update
An article in "Aerospace Daily & Defense Report" indicates that in the latest Orion design revision, called configuration "606" by
Lockheed Martin, the service module will have exterior panels that are jettisoned shortly after the second stage engine of the
Ares I ignites. This configuration will save 1,000 pounds of the mass compared with the prior "605" configuration.
[26]
- August 2007 design update
On 5 August, a report surfaced stating that the airbag landing system was removed from the next Orion design cycle ("607") in a weight saving measure, opting to return to an Apollo-style splashdown for the vehicle's end of mission.
[27]
[edit]2009 Human Space Flight Plans Committee
Rollout of Ares I-X at Kennedy Space Center Launch Complex 39 secured by four bolts on a mobile launcher platform.
On 8 September 2009, the
Human Space Flight Plans Committee was scheduled to release a report proposing a short list of different long term plans for the US Government's human space flight program. The review was commissioned by the
Obama Administration to take into account several objectives. These include support for the
International Space Station, development of missions beyond
low Earth orbit (including the
Moon) and use of commercial space industry. These objectives must fit within a defined budget profile.
[28]
Among the parameters to be considered in the course of the review are "crew and mission safety, life-cycle costs, development time, national space industrial base impacts, potential to spur innovation and encourage competition, and the implications and impacts of transitioning from current human space flight systems". The review considered the appropriate amounts of research and development and "complementary robotic activity necessary to support various human space flight activities". It also "explores options for extending International Space Station operations beyond 2016".
[29]
On 11 October 2010, with the cancellation of the Constellation Program, the Ares program ended and development of the original Orion vehicle was renamed as the MPCV, planned to be launched on top of an alternative
Space Launch System. Following cost overruns and schedule delays caused by insufficient funding, the Obama Administration proposed cancellation of the Constellation program in February 2010 which was signed into law 11 October.
[30] However, the Orion spacecraft continued to be developed because it supported new presidential goals.
An inflatable seal between the clean room and the Orion space capsule which is superior to the ones used on Apollo and the shuttle was tested on December 3, 2012.
[31]
An expanded view of Orion and its spacecraft adapter and launch escape system (2009).
The
Orion Crew and Service Module (CSM) stack consists of two main parts: a conical Crew Module (CM), and a cylindrical Service Module (SM) holding the spacecraft's propulsion system and expendable supplies. Both are based substantially on the
Apollo Command and Service Modules (Apollo CSM) flown between 1967 and 1975, but include advances derived from the space shuttle program. "Going with known technology and known solutions lowers the risk," according to Neil Woodward, director of the integration office in the Exploration Systems Mission Directorate.
[32]
The MPCV resembles its Apollo-era predecessors, but its technology and capability are more advanced. It is designed to support long-duration deep space missions of up to six months. The spacecraft's life support, propulsion, thermal protection and avionics systems are designed to be upgradeable as new technologies become available.
The MPCV spacecraft includes both crew and service modules, and a spacecraft adaptor.
The MPCV's crew module is larger than Apollo's and can support more crew members for short or long-duration spaceflight missions. The service module fuels and propels the spacecraft as well as storing oxygen and water for astronauts. The service module's structure is also being designed to provide locations to mount scientific experiments and cargo.
[edit]Crew Module
Test of Orion's parachute system in July 2012.
The Orion CM will hold four crew members, compared to a maximum of three in the smaller Apollo CM or seven in the larger space shuttle. Despite its conceptual resemblance to the 1960s-era Apollo, Orion's CM will use several improved technologies, including:
- "Glass cockpit" digital control systems derived from that of the Boeing 787.[33]
- An "autodock" feature, like those of Russian Progress spacecraft and the European Automated Transfer Vehicle, with provision for the flight crew to take over in an emergency. Previous American spacecraft (Gemini, Apollo, and Space Shuttle) have all required manual piloting for docking.
- Improved waste-management facilities, with a miniature camping-style toilet and the unisex "relief tube" used on the space shuttle (whose system was based on that used on Skylab) and the International Space Station (based on the Soyuz, Salyut, and Mir systems). This eliminates the use of the much-hated plastic "Apollo bags" used by the Apollo crews.
- A nitrogen/oxygen (N2/O2) mixed atmosphere at either sea level (101.3 kPa or 14.69 psi) or slightly reduced (55.2 to 70.3 kPa or 8.01 to 10.20 psi) pressure.
- Much more advanced computers than on previous manned spacecraft.
Another feature will be the partial reusability of the Orion CM.
[dated info] Both the CM and SM will be constructed of the
aluminium lithium(Al/Li) alloy like that was used on the shuttle's
external tank, and is in use on the
Delta IV and
Atlas V rockets. The CM itself will be covered in the same
Nomex felt-like thermal protection blankets used on parts on the shuttle not subject to critical heating, such as the payload bay doors. The reusable recovery parachutes will be based on the parachutes used on both the Apollo spacecraft and the
Space Shuttle Solid Rocket Boosters, and will also use the same Nomex cloth for construction. Water landings will be the exclusive means of recovery for the Orion CM.
[27][34]
To allow Orion to mate with other vehicles it will be equipped with the
NASA Docking System, which is somewhat similar to the
APAS-95 docking mechanism used on the Shuttle fleet. Both the spacecraft and docking adapter will employ a
Launch Escape System (LES) like that used in Mercury and Apollo, along with an Apollo-derived "Boost Protective Cover" (made of
fiberglass), to protect the Orion CM from aerodynamic and impact stresses during the first
2 1⁄2 minutes of ascent.
The Orion Crew Module (CM) is a 57.5°
frustum shape, similar to that of the
Apollo Command Module. As projected, the CM will be 5.02 meters (16 ft 6 in) in diameter and 3.3 meters (10 ft 10 in) in length,
[35] with a mass of about 8.5 metric tons (19,000 lb). It is to be built by the
Lockheed Martin Corporation.
[36] It will have more than 2.5 times the volume of an Apollo capsule, which had an interior volume of 5.9 m
3 (210 cu ft), and will carry four to six astronauts.
[37] After extensive study, NASA has selected the Avcoat
ablator system for the Orion crew module. Avcoat, which is composed of
silica fibers with a resin in a honeycomb made of
fiberglass and
phenolic resin, was previously used on the Apollo missions and on select areas of the space shuttle for early flights.
[38]
The crew module is the transportation capsule that provides a habitat for the crew, provides storage for consumables and research instruments, and serves as the docking port for crew transfers. The crew module is the only part of the MPCV that returns to Earth after each mission.
The crew module will have 316 cubic feet (8.9 m
3) and capabilities of carrying four astronauts for 21 day flights itself which could be expanded through additional service modules.
[39] Its designers claim that the MPCV is designed to be 10 times safer during ascent and reentry than the
Space Shuttle.
[15]
Orion ground test article in
Colorado on 13 May 2011.
EFT-1 Orion after final weld on 22 June 2012.
The Orion MPCV ground test vehicle is lifted into the acoustic chamber at Lockheed Martin’s facilities near
Denver in preparation for the Launch Abort Vehicle Configuration Test.
The Orion ground test vehicle sits on a work stand in the Operations and Checkout O&C Facility at NASA's Kennedy Space Center in Florida.
[edit]Service Module
Orion Service Module serves as the primary power and propulsion component of the spacecraft system, but is discarded at the end of each mission. In January 2013, the European
ATV based service module was announced.
[14]
[edit]ATV-based Service module
Orion spacecraft including the ATV derived Service Module with a propulsion stage attached at the back
In May 2011 the
ESA director general announced a possible collaboration with NASA to work on a successor to the ATV.
[40] On 21 June 2012, Astrium announced that they had been awarded two separate studies, each worth €6.5 million, to evaluate the possibilities of using technology and experience gained from ATV and
Columbus related work for future missions. The first looked into the possible construction of a service module which would be used in tandem with the Orion capsule.
[41] The second examined the possible production of a versatile multi purpose orbital vehicle.
[42]
On November 21, 2012, the ESA decided they will construct an ATV derived Service Module ready to support the Orion capsule on the maiden flight of the Space Launch System in 2017.
[43] service module will likely be manufactured by
EADS Astrium in Bremen, Germany.
[44]
| "ESA’s contribution is going to be critical to the success of Orion’s 2017 mission" |
| —NASA Orion Program manager[14] |
NASA announced on January 16, 2013, that ESA will construct the service module for Exploration Mission-1 in 2017.
[14]The European Space Agency will use hardware from their current Automated Transfer Vehicle to construct a compatible service module to the spacecraft.
[edit]Launch Abort System
In the event of an emergency on the
launch pad or during ascent, a
launch escape system called the Launch Abort System (LAS) will separate the Crew Module from the launch vehicle using a
solid rocket-powered launch abort motor (AM), which is more powerful than the
Atlas 109-D booster that launched astronaut
John Glenn into
orbit in 1962.
[45] There are two other propulsion systems in the LAS stack: the attitude control motor (ACM) and the jettison motor (JM). On 10 July 2007,
Orbital Sciences, the prime contractor for the LAS, awarded
Alliant Techsystems (ATK) a $62.5 million sub-contract to, "design, develop, produce, test and deliver the launch abort motor." ATK, which had the prime contract for the first stage of the
Ares I rocket, intended to use an innovative "reverse flow" design for the motor.
[46] On 9 July 2008 NASA announced that ATK had completed a
vertical test stand at a facility in
Promontory, Utah to test launch abort motors for the Orion spacecraft.
[47] Another long-time space motor contractor,
Aerojet, was awarded the jettison motor design and development contract for the LAS. As of September 2008 Aerojet has, along with team members Orbital Sciences, Lockheed Martin and NASA, successfully demonstrated two full-scale test firings of the jettison motor. This motor is important to every flight in that it functions to pull the LAS tower away from the vehicle after a successful launch. The motor also functions in the same manner for an abort scenario.
[edit]Testing
[edit]Environmental testing
[edit]Pathfinder
On March 2nd 2009, the LAS Pathfinder began its transfer from the Langley Research Center to the White Sands Missile Range, New Mexico, for launch tests. The Pathfinder is a combination of the Orion Boilerplate and LAS module. The 45 ft (14 m)-long rocket assembly will begin its first Pad Abort 1 Test on the Missile Range.
[49]
[edit]Abort Flight Test (AFT)
Test-firing of Orion LAS jettison motor (
shock diamonds are clearly visible in the exhaust plumes)
ATK successfully completed the first Orion launch-abort test on 20 November 2008. The abort motor will provide 500,000
lbf (2,200
kN) of thrust for an emergency on the launch pad or during the first 300,000 feet (91 km) of the rocket's climb to orbit. The test firing was the first time a motor with reverse flow propulsion technology at this scale has been tested.
This abort test firing brought together a series of motor and component tests conducted in 2008 as a preparation for the next major milestone, a full-size mock-up or
boilerplate test scheduled for the spring of 2009.
[53]
On May 10th, 2010, NASA successfully executed the PAD-Abort-1 test at White Sands New Mexico, launching a boilerplate Orion capsule to an altitude of approximately 6000 feet. The test used three solid-fuel rocket motors - a main thrust motor, an attitude control motor and the jettison motor.
[54]
[edit]Post-landing Orion Recovery Test (PORT)
The PORT Test is to determine and evaluate what kind of motions the astronaut crew can expect after landing. This will include conditions outside the capsule for the recovery team. The evaluation process will support NASA's design of landing recovery operations including equipment, ship and crew necessities.
The Port Test will use a full-scale boilerplate of NASA's Orion crew module and will be tested in water under simulated and real weather conditions. Tests began 23 March 2009 with a Navy-built, 18,000-pound boilerplate. It will be placed in a test pool at the Naval Surface Warfare Center's Carderock Division in West Bethesda, Md. Full sea testing will begin 6 April 2009, in a special location off the coast of NASA's Kennedy Space Center with media coverage.
[55]
[edit]Missions
List only includes relatively near missions, more missions are planned than are listed below.
[edit]Existing craft and mockups
- The Boilerplate Test Article (BTA) underwent splashdown testing at the Hydro Impact Basin of NASA's Langley Research Center.[59] The BTA contains over 150 sensors to gather data on its test drops.[60] Testing of the 18,000 pound mockup ran from July 2011 to 6 January 2012.[61]
- The Ground Test Article (GTA) stack, located at Lockheed Martin in Denver, is undergoing vibration testing.[62] It is made up by the Orion Ground Test Vehicle (GTV) combined with its Launch Abort System (LAS). Further testing will see the addition of Service Module simulator panels and Thermal Protection System (TPS) to the GTA stack.[63]
The Orion Drop Test Article during a test on 29 February 2012
- The Drop Test Article (DTA), also known as the Drop Test Vehicle (DTV) is undergoing test drops at the US Army’s Yuma Proving Ground in Arizona. The mock Orion parachute compartment is dropped from an altitude of 25,000 feet from a C-130.[63] Testing began in 2007. Drogue chutes deploy around 15,000 and 20,000 feet. Testing of the reefing staged parachutes includes partial failure instances including partial opening and complete failure of one of the three main parachutes. With only two chutes deployed the DTA lands at 33 feet per second, the maximum touchdown speed for Orion's design.[64] Other related test vehicles include the now-defunct Orion Parachute Test Vehicle (PTV) and its replacement the Generation II Parachute Test Vehicle (PTV2). The drop test program has had several failures in 2007, 2008, and 2010.[65] The new PTV was successfully tested 29 February 2012 deploying from a C-17. Ten drag chutes will drag the mock up's pallet from the aircraft for the drop at 25,000 feet. The landing parachute set of eight is known as the Capsule Parachute Assembly System (CPAS).[66] The test examined air flow disturbance behind the mimicked full size vehicle and its effects on the parachute system. The PTV landed at 17 mph to the desert floor.[67] A third test vehicle, the PCDTV3, is scheduled for a drop on 17 April 2012. In this testing “The CPAS team continued preparation activities for the Parachute Compartment Drop Test Vehicle (PCDTV3) airdrop test, scheduled for April 17, which will deploy the two drogue parachutes in the highest dynamic pressure environment to date, and will demonstrate a main parachute skipped second stage.”[68]
- Exploration Flight Test 1 (EFT-1) Orion (re-designation of OFT-1) constructed at Michoud Assembly Facility,[12] was delivered by Lockheed Martin to the Kennedy Space Center on July 2, 2012.[69]
[edit]Orion Lite
Orion Lite was an unofficial name used in the media for a lightweight crew capsule proposed by
Bigelow Aerospace in collaboration with
Lockheed Martin. It was to be based on the
Orion spacecraft that Lockheed Martin was developing for
NASA. It would be a lighter, less capable and cheaper version of the full Orion.
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