1、航空英语证书考试(PEC)-飞行器术语Abort - Early mission termination due to failure(s) that preclude mission continuation. Return to Earth of the crew is accomplished inside the spacecraft designed for Earth return and landing (see Abort to Earth, Abort to Orbit).Abort to Earth - Early mission termination, with dir
2、ect return to the Earths surface as the immediate objective.Abort to Orbit - An early mission termination that has an immediate objective of placing the flight system (CEV) in Earth orbit, prior to return to the Earths surface.Acceptance Tests - Tests conducted to verify that hardware delivered to h
3、igher-level assembly prior to delivery to the flight test and prior to delivery to the operational inventory or for operational spares conforms to program requirements. Acceptance testing also includes final “sell-off“ of the fully assembled CEV.Annunciate - To provide a visual, tactile or audible i
4、ndication.Ascent - The time from liftoff from the Earths surface, to spacecraft insertion into Earth orbit.Ascent Abort - Early mission termination due to failure(s) that preclude mission continuation. Return to Earth of the crew is accomplished inside the spacecraft designed for Earth return and la
5、nding.Attitude and Pointing Constraints - Constraints, restrictions or requirements on the vehicles orientation in space. These may include things such as requirements to orient a sensor at a specific target (such as a specific star), or a constraint limiting the amount of time a vehicle axis can be
6、 oriented toward a particular target (such as the sun, or deep space). They also include constraints or restrictions on maneuver rates and attitude deadbands.Automated control - Automatic, as opposed to human operation or control of a process, equipment or a system; or the techniques and equipment u
7、sed to achieve this. Automation is the control or execution of actions with no human interaction. Automated control does not exclude the capability for manual intervention / commanding, but manual intervention / commanding is explicitly not required to accomplish the function.Autonomous operations -
8、 Defined as a flight vehicle operating independent of external commands or control (i.e., commands from mission control on Earth). Autonomous operations can be fully automated or require some degree of manual commanding/intervention by the onboard crew. Autonomous operations that do not require onbo
9、ard crew involvement are, by definition, automated; therefore, the term “autonomous operations“ used in the requirements assumes onboard crew involvement in the operations.Berthing - A method of mating two or more Exploration elements in space. During a berthing operation, the two elements are mecha
10、nically connected prior to the structural capture and final mating (i.e., one element grapples the other with a robotic arm). One element controls the trajectory and attitude of the other element for the contact and capture. Final mating is generally performed by the berthing mechanism.Catastrophic
11、Hazard - A condition that may cause death or permanently disabling injury, major system or facility destruction on the ground, or major systems or vehicle destruction during the mission.CEV Acquisition Strategy Phase 1 - This is the formulation phase for the CEV. This phase begins in 2005 with contr
12、act award to multiple contractors and continues through PDR for each design.CEV Acquisition Strategy Phase 2 - This is the implementation phase for the CEV. This phase begins in 2008 with down select to one contractor and continues through 2014, with the first human launch of the CEV. This vehicle i
13、s a spiral 2-capable vehicle that also satisfies all spiral 1 capabilities.CEV Acquisition Strategy Post-Phase 2 - This is both the initial operations phase and the spiral 3 upgrade phase for the CEV. The initial operations phase begins in the negotiation of firm options into the 2008 contract for a
14、dditional CEV flight and also includes the sustaining engineering of the production vehicles. The spiral 3 upgrade phase has the contractor upgrade their CEV design to incorporate all spiral 3 capabilities. This phase will not occur if the contractor incorporated all spiral 3 requirements in their o
15、riginal design.CEV System - Includes the spacecraft and all CEV-unique ground systems needed to support standalone and integrated operations.CEV System Flight Tests - Operating flight tests during the development phase used to qualify that the integrated flight vehicle system (including the launch v
16、ehicle) and ground support equipment, as procured and verified by the acceptance test procedures, conform to the Constellation program requirements.CEV System Level Requirements (CEV) - Requirements that will be developed by Constellation SE current architectures require delivery of the EDS and LSAM
17、 through use of the CDS to rendezvous orbits.Critical Hazard - A condition that may cause a severe injury or occupational illness, loss of mission, or major property damage to facilities, systems, or flight hardware.Demo Flight - The 2008 demonstration flight performed as part of the flight test pro
18、gram.Depot Operations - The operations performed offline to receive and accept new flight hardware components, recertify previously flown hardware components for reuse, and to perform maintenance and repairs within the Line Replaceable Units (LRUs).Destination Surface to Destination Vicinity Phase -
19、 Starts with the initiation of the ascent (T0) from the destination surface. Representative mission activities include: ascent, abort, and orbit insertion or libration capture. Phase ends after successful destination vicinity insertion/capture.Destination Vicinity Operations Phase A - Starts at the
20、successful insertion/capture at the destination vicinity. Representative mission activities include: loiter and phasing, vehicle and system checkout, crew-cargo transfers, undocking and separation. Phase ends at the successful separation of surface lander system for descent burn.Destination Vicinity
21、 Operations Phase B - Starts after the successful destination orbit insertion or libration point capture, following ascent from destination surface. Representative mission activities include: phasing, vehicle-system checkout, crew-cargo transfer, undocking and separation maneuver, element disposal a
22、nd/or safing. Phase ends at the completion of the Trans-Earth Injection burn.Destination Vicinity to Earth Phase - Begins with completion of Trans-Earth Injection burn and includes mid-course corrections, cruise to Earth vicinity, element separation and element disposal. Ends with arrival at Earth e
23、ntry interface or successful Earth orbit injection.Destination Vicinity to Surface Phase - Starts at the initiation of the descent burn from destination vicinity (destination deorbit burn or libration departure burn to destination). Representative mission activities include: descent to destination s
24、urface, descent aborts, landing, propulsion system shutdown and safing. For libration architectures, additional activities include orbit capture, phasing, and de-orbit maneuvers. Phase ends when the vehicle has completed all landing activities on the destination surface, including propulsion system
25、shutdown and safing.Development Tests - Any test that provides data needed to reduce risk, to design hardware or software, to define manufacturing processes, to define qualification or acceptance test procedures, or to investigate anomalies discovered during test or operations. Verification credit c
26、annot be taken during development testing.Docking - A method of mating two or more Exploration elements in space. In a docking operation, the structural mechanisms are brought into contact and captured through independent control of the two vehicles flight path and attitude. Final mating is generall
27、y accomplished by the docking mechanism.Earth Ascent Target Orbit - The planned CEV orbit, upon completion of ascent (separation from Crew Launch Vehicle).Earth Departure Stage (EDS) - EDS will be used to provide the propulsive force needed to transfer the various flight elements to destination phas
28、ing orbits (including the CEV and LSAM). EDS will be launched on a Cargo Launch Vehicle, and are considered part of the CDS, except when mated to and operating with a crew-occupied flight element.Earth Orbit Operations Phase A - Starts with completion of Earth orbit insertion. Representative activit
29、ies include: phasing, rendezvous, docking and loiter. Ends with completion of a burn to leave Earth orbit (i.e., Trans-Lunar Injection burn or de-orbit burn).Earth Orbit to Destination Vicinity Phase - Starts after completion of vehicle injection burn (i.e., Trans-Lunar Injection) and includes mid-c
30、ourse corrections, element separation/disposal, and cruise to destination vicinity. Ends with successful insertion/capture at destination vicinity.Earth Re-entry Phase - Begins with completion of Earth orbit injection. Ends with de-orbit burn completion. Encompasses activities necessary to successfu
31、lly execute direct-to-Earth aborts during ascent.Earth Reference Orbit - The orbit designated for assembly of Exploration System elements prior to departure for exploration destinations, defined by the following parameters: Inclination: 28.5-29.0 degrees; Launch Azimuth: 90+/- 5 degrees; Altitude: 3
32、07 km - 407 km.Earth to Orbit Phase - Starts with liftoff. Representative activities include liftoff through ascent to orbit, ascent crew escape/abort and re-entry/descent during aborts, disposal of elements. Ends with insertion to a stable, 24 hour Earth orbit or return to Earth.Electromagnetic Int
33、erference (EMI) - What occurs when electromagnetic fields from one device interfere with the operation of some other device.Entry footprint - Region on Earths surface defined by the boundaries of the CEV Earth entry corridor.Escape - Early mission termination that requires emergency egress of the Cr
34、ew from the failing spacecraft, possibly using an escape system (e.g., extraction, ejection, escape pod).Evaluation Factors - Criteria (cost and non-cost) by which a contractors proposal will be evaluated to make a contract award.Exploration Spiral 1 (Crew Transportation System Earth Orbit Mission)
35、- Encompasses the capabilities necessary to insert humans into Earth orbit and return them safely to Earth, employing a post-Space Shuttle flight system. A programmatic constraint has been imposed on Spiral 1: “NASA shall conduct the initial test flight for the Crew Exploration Vehicle before the en
36、d of the decade in order to provide an operational capability to support human exploration missions no later than 2014“. The flight elements of the Exploration Spiral 1 Crew Transportation System are the Crew Exploration Vehicle and Crew Launch Vehicle. Robotic Precursor Missions that are scheduled
37、to launch prior to the Earth orbit demonstration of the Spiral 1 CTS are considered Exploration Spiral 1 missions.Exploration Spiral 2 (Extended-Duration Lunar Campaign) - Encompasses the capabilities necessary to execute extended-duration human lunar exploration. Extended duration lunar missions wi
38、ll be 4-14 days in duration on the lunar surface, and do not require pre-deployed surface systems (e.g., Habitation Module or Surface Power). A programmatic constraint has been imposed on Spiral 2: “NASA shall conduct the first extended human expedition to the lunar surface as early as 2015, but no
39、later than the year 2020, in preparation for human exploration of Mars and other destinations“. Robotic Precursor Missions scheduled to launch after the Spiral 1 CTS flight demonstration, and prior to the first Spiral 3 Lunar mission are considered Exploration Spiral 2 missions.Exploration Spiral 3
40、(Long-Duration Lunar Campaign) - Encompasses the capabilities necessary to execute a long-duration human lunar exploration campaign. This campaign requires development of extensive surface systems (e.g., habitation and surface power system), and long-duration lunar-vicinity parking capability of the
41、 crew transportation system. Long-duration lunar missions will extend from 14-98 days. Robotic Precursor Missions that are scheduled to launch after the last Spiral 2 extended- duration lunar mission, and prior to the initial Exploration Spiral 4 mission are considered Exploration Spiral 3 missions.
42、Exploration Spiral 4 (Crew Transportation System Mars Flyby) - Encompasses the capabilities to conduct a Mars flyby mission using elements of the Human-Mars Crew Transportation System. Upon completion of successful Mars flyby(s), Exploration Spiral 5 will commence. Robotic Precursor Missions schedul
43、ed to launch prior to the first Human-Martian surface mission are considered Spiral 4 missions.Exploration Spiral 5 (Human Mars Surface Campaign) - Spiral 5 encompasses the capabilities necessary to execute human Mars exploration missions. Robotic Precursor Missions scheduled to launch after the fin
44、al Mars flyby mission, and prior to the start of Exploration Spiral 6 (TBD content) are considered Spiral 5 missions.Export Control - U.S. export control laws and regulations, including the International Traffic in Arms Regulations (ITAR), and the Export Administration Regulations (EAR) (see FFS 182
45、5)Export Licenses - Licenses or other approvals from the Department of State of the Department of Commerce related to export of hardware, technical data, or software, or provides technical assistance to a foreign destination or “foreign person“ (see NFS 1852.225-70)Extended-Duration (Lunar Mission)
46、- Human missions to the lunar surface ranging from 4 days (96 hours) through 14 days. This capability is an objective of Exploration Spiral 2. Extended-duration lunar missions do not require pre-deployed Surface Systems (e.g., habitation modules or surface power system).Extensibility - Capable of be
47、ing extended.Facilities - Includes vehicle processing facilities, integration facilities, launch pads, mission control centers, launch control centers, control rooms, training, test, checkout, and assembly facilities with associated data processing and communication systems.Facility Loading - The le
48、vel that a facility is expected to be used. For example, if nominal usage is defined as 40 hours of simulation support per week and 50 hours are required during key periods, facility loading would be 110%.Facility Systems - Systems necessary to support the operations of the facility. Examples are fa
49、cility electrical power, water, pneumatics, cranes, etc. It does not include ground support equipment.Fault Tolerance - The ability of a system to cope with internal problems and still continue to operate with minimal impact.FDIR - Fault Detection, Isolation, and Recovery. The means to detect off-nominal conditions, isolate the problem to a specific subsystem/component, and recover of vehicle systems and capabilities. FDIR may be accomplished by the onboard crew, onboard software algorithms, ground commanding, or a combination of the preceding methods.FDIR Algorithm - An onboard softwar
