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..., which adds the rate to its current know attitude, updating its knowledge spacecraft's orientation. There are two sets of rate gyros that are referred to as BMA Both gyro assemblies are typically caged and determine only the spacecraft's rate. The rate is then sent to the GDC. The three BMAG switches on MDC-1 ...

...is used to attach the [[Command Module]] to the [[Lunar Module]] or other spacecraft. ...o the CM, pulling the two spacecraft together into a 'hard dock' where the spacecraft will latch together with an air-tight seal and electrical connection. ...

...o_Lunar_Module|Lunar Module (LM)]]''' was the lander portion of the Apollo spacecraft built for the US Apollo program to achieve the transit from moon orbit to t [[Category:Spacecraft]] ...

...Module]] into Earth orbit, which made it invaluable for testing the Apollo spacecraft while the larger [[Saturn V]] needed to send them to the moon was still bei [[Category:Spacecraft]] ...

[[Category:Spacecraft]] [[Category:Fictional spacecraft]] ...

#AOH ''Apollo Operations Handbook Block II Spacecraft - Volume 1 Spacecraft Description.'' SM2A-03-Block II. October 15, 1969. [http://history.nasa.gov #AOH2 ''Apollo Operations Handbook Block II Spacecraft - Volume 2 Operational procedures reference.'' SM2A-03-Block II-J-(2). July ...

...or short) are small explosive devices used for many purposes on the Apollo spacecraft. The main spacecraft pyros are armed by two switches<cite>I</cite> on Panel 8 on the left-hand s ...

...rs. It is also used to initiate several transfer commands, to transfer the spacecraft control from CMC to SCS control for example. The real THC is basically a ki * The clockwise switch (CW) will transfer spacecraft control from [[CMC]] to [[SCS]]. It may also transfer control between certa ...

SATTYPE specifies the type of Saturn spacecraft the config file refers to. For example, the [[Saturn INT-20]] config file u Specifies the number of active engines on the first stage of the spacecraft (max 8). For example, the INT-20 config file sets this to 4, but you could ...

...ere designed to check out procedures and methods to rendevous with another spacecraft, in this case the SIVB. The SPS phase checked out the ability of the SPS to At about T+12min Engine cutoff occurs, the spacecraft is in the almost circular '''Earth Parking Orbit (EPO)'''. ...

One of the major functions of the vAGC is to provide navigation of the Spacecraft with respect it orientation and its position in relation to the Earth and M ...

The '''Reaction Control System (RCS)''' provides the thrust to control spacecraft rates and rotation in all three axis in addition to any minor translation m ...tion Control System (CM RCS) provides the impulse required for controlling spacecraft rates and attitude during the terminal phase of the mission after SM separa ...

* Orbiter-like control of the spacecraft * Realistic behavior of the spacecraft ...

...) provides a capability for monitoring and controlling the attitude of the spacecraft, for translational manoeuvers and SPS thrust vector control. Also the SCS i ...form of reference to the IMU. The GDC updates its current knowledge of the spacecraft's attitude by adding rate data from the BMAGs. This is referred to as the G ...

...familiar with the Apollo spacecraft without to have to care about the real spacecraft systems like the [[RHC]], the [[THC]] or realistic attitude control. So nor ...ntroller]] (THC) controlling the [[PGNCS]] or [[SCS]]. The historic Apollo spacecraft had two "joysticks", the [[RHC]] and the [[THC]], to allow simultaneous con ...

...ngine, and is responsible both for the final part of the launch to put the spacecraft in orbit, and for the [[TLI]] burn to boost them on a trajectory that will [[Category:Spacecraft]] ...

== General controls for both spacecraft == ...

...egrated Manned Program was the Space Shuttle, a fully or parially reusable spacecraft designed to carry men and equipment to the various low Earth orbit spacesta ....ntrs.nasa.gov/19680009769_1968009769.pdf Integrated Manned Interplanetary Spacecraft Concept Definition, Final Report Vol.1, Summary]'', January, 1968 ...

...ut are really doing what the original switches did. So you can operate the spacecraft as the real astronauts did. ...CTRL> <UP/DOWN/LEFT/RIGHT> key combination is used as in any other Orbiter spacecraft and as explained in the Orbiter manual. The navigation between the panels i ...

...nd_Module_.28CM.29|Command Module (CM)]] is the nerve center of the Apollo spacecraft, as it functions as primary control and navigation platform during the miss ...ut are really doing what the original switches did. So you can operate the spacecraft as the real astronauts did, at least the more important subsystems. Additio ...

...ike Orbiter vessels than the real spacecraft and without the simulation of spacecraft systems or the Virtual AGC. There are already realistic panels, but only ve ...

...tion Hand Controller (RHC)''' provides the capability of manual control of spacecraft rotation in either direction about each axis. Also the RHC may be used for ...RHC displacement from the null position. These signals are used to command spacecraft rotation rates during [[SCS]] proportional rate mode and to command [[SPS]] ...

...alues can be compared to a chart in the CSM launch checklist to ensure the spacecraft is on a proper trajectory. A second aide, the FDAI 1 error needles, point t ...

...help users to get a better understanding and feeling how to work with the spacecraft systems. ...ing System lights indicate a failure or an unusual condition in one of the spacecraft systems. Some lights will remain on until they are manually reset using the ...

...ndicator (FDAI)''' is used to display various attitude informations of the spacecraft, similar to a artificial horizon of an aircraft. The FDAIs provide displays ...read "pitch 0°", "bank 0°" and "ball centered") is not necessary when the spacecraft is nose on the horizon, "wings" at level and pointing toward the heading. ...

...s the '''TLI''' for short. A single burn of the SIVB engine will allow the spacecraft to escape the EPO and extend the orbit in order to reach the moon. In futur At T-1:30, the AGC will orient the spacecraft prograde, and at T-0:00 the main engine will ignite. ...

...een recently updated, the optics should be zeroed and in CMC mode, and the spacecraft should be in CMC auto mode. After calling Program 20 the DSKY displays a fl ...the computer determines the latitude, longitude and the altitude of either spacecraft at that specific time. The reading will be accurate so long as no delta-V m ...

...itude with respect to an inertial, star-fixed system. Independent from the spacecraft's manoevers the IMU platform, also called "Stable Member", is kept fixed wi ...0405" (two stars not available) in R1. In this case press RSET, change the spacecraft's attitude to a better position (for example pitch up 90°) and key in "V32 ...

...ations have Acquision of Signal (AOS) or Loss of Signal (LOS) based on the spacecraft’s ground track and whether or not it is on the far side of the moon. Curr ...and Accept” before proceeding with the uplink. The CAPCOM will inform the spacecraft of the uplink’s contents and when it has both begun and completed. If the ...

...e of guidance. The PGNCS also provides automatic control over parts of the spacecraft via the Command Module Computer (CMC). The GN system can receive power from ...it (IMU). The CSS applies this information to its current knowledge of the spacecraft's position and calculates a new estimate, what is called the state-vector. ...

...e the engine. Due to limitations of Orbiter's guidance control with docked spacecraft you may need to put the SIVB into prograde orientation manually before the ...

Provide on-board Spacecraft navigation ...r launch. It torques the Stable Member for launch orientation based on the spacecraft position and launch azimuth. This program then automatically starts Program ...

[[Image:Apollo_spacecraft_stacking.jpg|thumb|right|Stacking of the Apollo spacecraft in the VAB.]] ...

At about T+12min Engine cutoff occurs, the spacecraft is in the almost circular '''Earth Parking Orbit (EPO)'''. You can control ...

Crew transport would be by Apollo derivative spacecraft capable of carrying the entire three man crew to the lunar surface. Power w ...a portion of the lunar surface that could be reached using standard Apollo spacecraft. ...

...m. Finally, the lunar position can be used as a sighting mark to align the spacecraft to the universal coordinate system. ...

...115V AC power, and a 10Hz signal from the central timing equipment in the spacecraft. It can operate by using an internal tuning fork as a reference if the timi ...

...Module control panel and most of the internal systems, and support for new spacecraft. It is also capable of flying most of an Apollo mission using the Virtual A * Realistic simulation of most major spacecraft systems. ...

...the spacecraft systems. In the following procedures it is assumed that the spacecraft is in a "stable condition" without flying manoeuvers with ECS in "flight co ...

...the orbital entry, in which rolling was used to fine-tune the path of the spacecraft (nominally rolling from one side to the other by 60 degrees or so). Next, t ..., there are a few things that need to be known about reentry in the Apollo Spacecraft. The first is the event known as Entry Interface. Entry Interface occurre ...

...if the mission is flown from a different launch pad to the default for the spacecraft (e.g. the Skylab 'milk stool' for the Saturn 1b). ...Saturn V. This is used to name the separated stages and components of the spacecraft. ...

...tion of these systems is accurate, and effects of various power outputs on spacecraft systems can be observed. See [[Environmental Control System (CSM)]] for mor ...

* All types of IMU transformation matrizes (REFSMMAT) used for the Apollo spacecraft. ...FSMMATs can be calculated by the AGC itself, but most were uplinked to the spacecraft from the ground. The REFSMMATs that can be calculated with this MFD are: ...

After Service Module separation, control of the spacecraft is automatically handed over to the CM RCS. However, if this fail to happen ...

...itude of the spacecraft needs to be changed. Also it's possible to put the spacecraft into a very slow roll motion, so that the propellant lines are heated perio ...

There are plenty of candidates for future additions to the spacecraft simulated in '''Project Apollo''' after the basic historical [[Command/Serv ==Spacecraft== ...

...'Service Module Reaction Control System (SM RCS)''' is utilized to control spacecraft rates and rotation in all three axis in addition to any minor translation m ...

<td>Indicates the altitude of the spacecraft in feet. </td> <td>Displays the acceleration along the spacecraft X-axis in g. </td> ...

...drift. This, along with several other factors regarding the health of the spacecraft would decide whether they were "Go for TLI." All of this inspection work i ...