Shuttl Bequemer hin und wieder weg.
Shuttle Inc. ist ein in Taiwan gegründetes Unternehmen, das Hauptplatinen und Design-Barebone-PCs im Small-Form-Factor-Format herstellt. Seit ist Shuttle Inc. eine börsennotierte Aktiengesellschaft. Der Hersteller unterteilt seine. Das Barebone ist die Basis für Ihren PC. Bei Shuttle sind Netzteil, Mainboard, Kabel und das spezielle Kühlsystem bereits in einem attraktiven Gehäuse. Für alle Produkte der Marke Shuttle gilt eine Gewährleistung von 2 Jahren; Fachhändler erhalten auf bestimmte Barebone-Produkte 3 Jahre Gewährleistung. Du teilst du dir das Shuttle und den Preis mit netten Menschen, die in eine ähnliche Richtung wollen. Aber keine Sorge, hierdurch kommt es nur zu minimalen. Ein Shuttle (auch Kanalfahrzeug oder Satellitenfahrzeug) ist ein Gerät zur automatischen Bedienung von Kanallagern. Anwendung im Kanallager[Bearbeiten.
The Space Shuttle was the first operational orbital spacecraft designed for reuse. Each Space Shuttle orbiter was designed for a projected lifespan of launches or ten years of operational life, although this was later extended.
The KSC was responsible for launch, landing and turnaround operations for equatorial orbits the only orbit profile actually used in the program , the U.
Air Force at the Vandenberg Air Force Base was responsible for launch, landing and turnaround operations for polar orbits though this was never used , the Johnson Space Center JSC served as the central point for all Shuttle operations, the MSFC was responsible for the main engines, external tank, and solid rocket boosters, the John C.
Stennis Space Center handled main engine testing, and the Goddard Space Flight Center managed the global tracking network.
The orbiter had design elements and capabilities of both a rocket and an aircraft to allow it to launch vertically and then land as a glider.
Each wing had an inboard and outboard elevon to provide flight control during reentry, along with a flap located between the wings, below the engines to control pitch.
The orbiter used retractable landing gear with a nose landing gear and two main landing gear, each containing two tires.
The main landing gear contained two brake assemblies each, and the nose landing gear contained an electro-hydraulic steering mechanism.
The Space Shuttle crew varied by mission. The test flight had only two members each, the commander and pilot, who were both qualified pilots that could fly and land the orbiter.
The on-orbit operations, such as experiments, payload deployment, and EVAs, were conducted primarily by the mission specialists who were specifically trained for their intended missions and systems.
Early in the Space Shuttle program, NASA flew with payload specialists, who were typically systems specialists who worked for the company paying for the payload's deployment or operations.
The final payload specialist, Gregory B. Jarvis , flew on STSL , and future non-pilots were designated as mission specialists.
The crew compartment comprised three decks, and was the pressurized, habitable area on all Space Shuttle missions.
The cockpit consisted of two seats for the commander and pilot, as well as an additional two to four seats for crew members.
The mid-deck was located below the cockpit, and was where the galley and crew bunks were set up, as well as three or four crew member seats.
The mid-deck contained the airlock, which could support two astronauts on an extravehicular activity EVA , as well as access to pressurized research modules.
An equipment bay was below the mid-deck, which stored environmental control and waste management systems.
On the first four Shuttle missions, astronauts wore modified U. Air Force high-altitude full-pressure suits, which included a full-pressure helmet during ascent and descent.
From the fifth flight, STS-5 , until the loss of Challenger , the crew wore one-piece light blue nomex flight suits and partial-pressure helmets.
After the Challenger disaster, the crew members wore the Launch Entry Suit LES , a partial-pressure version of the high-altitude pressure suits with a helmet.
The flight deck was the top level of the crew compartment, and contained the flight controls for the orbiter. The commander sat in the front left seat, and the pilot sat in the front right seat, with two to four additional seats set up for additional crew members.
The instrument panels contained over 2, displays and controls, and the commander and pilot were both equipped with a heads-up display HUD and a Rotational Hand Controller RHC to gimbal the engines during powered flight and fly the orbiter during unpowered flight.
Both seats also had rudder controls, to allow rudder movement in flight and nose-wheel steering on the ground. The MCDS displayed the flight information at the commander and pilot seats, as well as at the aft seating location, and also controlled the data on the HUD.
In , Atlantis was upgraded with the Multifunction Electronic Display System MEDS , which was a glass cockpit upgrade to the flight instruments that replaced the eight MCDS display units with 11 multifunction colored digital screens.
The aft section of the flight decked contained windows looking into the payload bay, as well as an RHC to control the Remote Manipulator System during cargo operations.
Additionally, the aft flight deck had monitors for a closed-circuit television to view the cargo bay. The mid-deck contained the crew equipment storage, sleeping area, galley, medical equipment, and hygiene stations for the crew.
The crew used modular lockers to store equipment that could be scaled depending on their needs, as well as permanently installed floor compartments.
The mid-deck contained a port-side hatch that crew used for entry and exit while on Earth. Additionally, each orbiter was originally installed with an internal airlock in the mid-deck.
The internal airlock was replaced with an external airlock in the payload bay on Discovery , Atlantis , and Endeavour to improve docking with Mir and the ISS , along with the Orbiter Docking System.
The orbiter was equipped with an avionics system to provide information and control during atmospheric flight. Its avionics suite contained three microwave scanning beam landing systems , three gyroscopes , three TACANs , three accelerometers , two radar altimeters , two barometric altimeters , three attitude indicators , two Mach indicators , and two Mode C transponders.
During reentry, the crew deployed two air data probes once they were travelling slower than Mach 5. The orbiter had three inertial measuring units IMU that it used for guidance and navigation during all phases of flight.
The orbiter contains two star trackers to align the IMUs while in orbit. The star trackers are deployed while in orbit, and can automatically or manually align on a star.
In , NASA began upgrading the inertial measurement units with an inertial navigation system INS , which provided more accurate location information.
While in orbit, the crew primarily communicated using one of four S band radios, which provided both voice and data communications.
Two of the S band radios were phase modulation transceivers , and could transmit and receive information. The other two S band radios were frequency modulation transmitters , and were used to transmit data to NASA.
Additionally, the orbiter deployed a high-bandwidth K u -band radio out of the cargo bay, which could also utilized as a rendezvous radar.
The orbiter was also equipped with two UHF radios for communications with air traffic control and astronauts conducting EVA. From to , the orbiter vehicles were upgraded to the APS, which improved the memory and processing capabilities, and reduced the volume and weight of the computers by combining the CPU and IOP into a single unit.
During ascent, maneuvering, reentry, and landing, the four PASS GPCs functioned identically to produce quadruple redundancy, and would error check their results.
In case of a software error that would cause erroneous reports from the four PASS GPCs, a fifth GPC ran the Backup Flight System, which used a different program and could control the Space Shuttle through ascent, orbit, and reentry, but could not support an entire mission.
The five GPCs were separated in three separate bays within the mid-deck to provide redundancy in the event of a cooling fan failure.
After achieving orbit, the crew would switch some of the GPCs functions from guidance, navigation, and control GNC to systems management SM and payload PL to support the operational mission.
Space Shuttle missions typically brought a portable general support computer PGSC that could integrate with the orbiter vehicle's computers and communication suite, as well as monitor scientific and payload data.
The payload bay comprised most of the orbiter vehicle's fuselage , and provided the cargo-carrying space for the Space Shuttle's payloads.
Two payload bay doors hinged on either side of the bay, and provided a relatively airtight seal to protect payloads from heating during launch and reentry.
Payloads were secured in the payload bay to the attachment points on the longerons. The payload bay doors served an additional function as radiators for the orbiter vehicle's heat, and were opened upon reaching orbit for heat rejection.
The orbiter could be used in conjunction with a variety of add-on components depending on the mission. The RMS, also known as Canadarm, was a mechanical arm attached to the cargo bay.
It could be used to grasp and manipulate payloads, as well as serve as a mobile platform for astronauts conducting an EVA. The RMS was built by the Canadian company Spar Aerospace , and was controlled by an astronaut inside the orbiter's flight deck using their windows and closed-circuit television.
The RMS allowed for six degrees of freedom, and had six joints located at three points along the arm. The Spacelab module was a European-funded pressurized laboratory that was carried within the payload bay and allowed for scientific research while in orbit.
The Spacelab module contained two 2. Astronauts entered the Spacelab module through a 2. The Spacelab equipment was primarily stored in pallets, which provided storage for both experiments as well as computer and power equipment.
The titanium alloy reusable engines were independent from the orbiter vehicle, and would be removed and replaced in between flights. The RS is a staged-combustion cycle cryogenic engine that used liquid oxygen and hydrogen, and had a higher chamber pressure than any previous liquid rocket.
The original main combustion chamber operated at a maximum pressure of The nozzle is cooled by 1, interior lines carrying liquid hydrogen, and is thermally protected by insulative and ablative material.
The RS engines had several improvements to enhance reliability and power. Throughout the flight, they were used for orbit changes, as well as the deorbit burn prior to reentry.
The orbiter was protected from heat during reentry by the thermal protection system TPS , a thermal soaking protective layer around the orbiter.
In contrast with previous US spacecraft, which had used ablative heat shields, the reusability of the orbiter required a multi-use heat shield.
The TPS primarily consisted of four types of tiles. Thicker RCC tiles were developed and installed in to prevent damage from micrometeoroid and orbital debris , and were further improved after RCC damage caused in the Columbia disaster.
Beginning with STS , the orbiter vehicles were equipped with the wing leading edge impact detection system to alert the crew to any potential damage.
The Space Shuttle external tank ET carried the propellant for the Space Shuttle Main Engines, and connected the orbiter vehicle with the solid rocket boosters.
The orbiter vehicle was attached to the ET at two umbilical plates, which contained five propellant and two electrical umbilicals, and forward and aft structural attachments.
The exterior of the ET was covered in orange spray-on foam to allow it to survive the heat of ascent.
The ET separated from the orbiter vehicle 18 seconds after engine cutoff, and could be triggered automatically or manually. At the time of separation, the orbiter vehicle retracted its umbilical plates, and the umbilical cords were sealed to prevent excess propellant from venting into the orbiter vehicle.
After the bolts attached at the structural attachments were sheared, the ET separated from the orbiter vehicle.
At the time of separation, gaseous oxygen was vented from the nose to cause the ET to tumble, ensuring that it would break up upon reentry.
The ET was the only major component of the Space Shuttle system that was not reused, and it would travel along a ballistic trajectory into the Indian or Pacific Ocean.
Further research determined that the foam itself was sufficiently protected, and the ET was no longer covered in latex paint beginning on STS The LWT's weight was reduced by removing components from the LH 2 tank and reducing the thickness of some skin panels.
The SRB's subcomponents were the solid-propellant motor, nose cone, and rocket nozzle. The solid-propellant motor comprised the majority of the SRB's structure.
Its casing consisted of 11 steel sections which made up its four main segments. The nose cone housed the forward separation motors and the parachute systems that were used during recovery.
Following separation, they deployed drogue and main parachutes, landed in the ocean, and were recovered by the crews aboard the ships MV Freedom Star and MV Liberty Star.
The rocket motor, igniter, and nozzle were then shipped to Thiokol to be refurbished and reused on subsequent flights.
The SRBs underwent several redesigns throughout the program's lifetime. Subsequent flights until STS used cases that were 0.
After the Challenger disaster as a result of a failed O-ring in cold temperature, the SRBs were redesigned to provide a constant seal regardless of the ambient temperature.
The Space Shuttle's operations were supported by vehicles and infrastructure that facilitated its transportation, construction, and crew access.
The orbiter vehicle was prepared at the Orbiter Processing Facility OPF and transferred to the VAB, where a crane was used to rotate it to the vertical orientation and mate it to the external tank.
Both tanks were slowly filled up until the launch as the oxygen and hydrogen evaporated. The launch commit criteria considered precipitation, temperatures, cloud cover, lightning forecast, wind, and humidity.
In addition to the weather at the launch site, conditions had to be acceptable at one of the Transatlantic Abort Landing sites and the SRB recovery area.
The original meaning of the word shuttle is the device used in weaving to carry the weft. By reference to the continual to-and-fro motion associated with that, the term was then applied in transportation and then in other spheres.
Thus the word may now also refer to:. Transport systems operating at frequent intervals on a short, mostly non-stop route between two places.
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