Revision as of 03:39, 15 January 2009

State Vector MFD

This is the image caption

Project home: StateVectorMFD at Orbit Hangar Author: Tim 'tblaxland' Blaxland Current version: Unknown Compatibility: Unknown

StateVectorMFD is basic MFD for displaying a vessel's state vectors at the current time and at a some other time relative to the present time.

Operation

Loading the MFD

Load the MFD by pressing the MFD "SEL" button and select "State Vector". The MFD will show the current state vectors in a column on the left hand side and the state vectors for a future time in a column on the right hand side.

If it is the first time you have started the MFD in the simulation session T+ will be equal to zero and both sets of state vectors will display the same numbers.

The origin of the coordinate system (the reference body) will be set to the current major gravitational influence on the vessel.

Changing T+

To change the time used for predicting the future state vectors, press the T+ button and enter a time (in seconds).

Changing the Reference Body

Press the REF button and select a new reference body.

Changing Vessel Focus

When you change vessel focus, the MFD will remember the settings for each vessel and MFD position.

Credits

This MFD uses the Kepler Orbital Simulation Toolkit (KOST) by CJ Plooy and Tim Blaxland.

It also use the built-in Orbiter pop-up menus for selecting the reference body. Thanks to C J Plooy for his work in making this functionality available.

Copyright Notice

StateVectorMFD is free software: you can redistribute it and/or modify it under the terms of the GNU Lesser General Public License as published by the Free Software Foundation, either version 3 of the License, or (at your option) any later version.

StateVectorMFD is distributed in the hope that it will be useful, but WITHOUT ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU Lesser General Public License for more details.

You should have received a copy of the GNU Lesser General Public License along with StateVectorMFD. If not, see <http://www.gnu.org/licenses/>.

@@ Line 1: / Line 1: @@
-= ZTC Tether-Sling Transportation System =
+= State Vector MFD =
-[[Image:Put some image here|right|thumb|300px|This is the image caption]]
+[[Image:Put a screenie here|right|thumb|300px|This is the image caption]]
 {{Addon|
-=[http://www.orbiter-forum.com/showthread.php?t=684 ZTC Tether-Sling at Orbiter-Forum]|
+=[http://www.orbithangar.com/some_location StateVectorMFD at Orbit Hangar]|
-=[http://www.orbiter-forum.com/member.php?u=86 Tim 'tblaxland' Blaxland]; [http://www.orbiter-forum.com/member.php?u=163 n0mad23]
+=[http://www.orbiter-forum.com/member.php?u=86 Tim 'tblaxland' Blaxland]
 }}
-The ZTC Tether-Sling Transportation System project uses momentum exchange tethers for nearly propellant free transfers of payloads between solar system bodies.
+StateVectorMFD is basic MFD for displaying a vessel's state vectors at the current time and at a some other time relative to the present time.
-It is expected that some propellant will be used by fine-tuning of transfer trajectories. Testing has shown that for lunar transfers corrections of less than 25m/s are typically required.
+== Operation ==
-== Principle ==
+=== Loading the MFD ===
-The basic principle of a momentum exchange tether is to take momentum from the tether's orbit and transfer it into the payload's orbit. The momentum of an Earth based tether can then be recharged over time using solar powered electrodynamic propulsion to allow it to prepare to transfer further payloads.
+Load the MFD by pressing the MFD "SEL" button and select "State Vector". The MFD will show the current state vectors in a column on the left hand side and the state vectors for a future time in a column on the right hand side.
-== Research ==
+If it is the first time you have started the MFD in the simulation session T+ will be equal to zero and both sets of state vectors will display the same numbers.
-Both NASA and Tethers Unlimited have done significant research into momentum exchange tethers over the years. NASA's most recent Technology Assessment Group report confirmed that the principle behind the project is sound however significant but feasible advances in materials would be required for the project to become a reality.
+The origin of the coordinate system (the reference body) will be set to the current major gravitational influence on the vessel.
-== Electro-Dynamic Propulsion ==
+=== Changing T+ ===
-Electro-dynamic propulsion uses the interaction between an electric current in the tether with the Earth's magnetic field. The thrust generated is a result of the Lorentz force on the electrons flowing in the tether. The Earth's ionosphere is used as a distributed return path for the tether current by way of anodes and cathodes on each end of the tether.
+To change the time used for predicting the future state vectors, press the T+ button and enter a time (in seconds).
-A simplified model of the Earth's magnetic field will be used for the purpose of simulating the electro-dynamic propulsion.
+=== Changing the Reference Body ===
-== Tether Locations ==
+Press the REF button and select a new reference body.
-Tethers are planned for Earth (Ananke for lunar transfers and Ananke-MX for Mars transfers), Moon (Khronos) and Mars. Development work is progressing on Ananke at present.
+=== Changing Vessel Focus ===
-=== Earth ===
+When you change vessel focus, the MFD will remember the settings for each vessel and MFD position.
-==== Ananke ====
+== Credits ==
-Ananke is a 120km long tether for lunar transfers that orbits the Earth in an elliptical (eccentricity approx 0.45) equatorial orbit. An equatorial orbit is used so the regression of the ascending nodes does not over complicate the planning of lunar transfer trajectories. The periapsis of the tether is approximately 340km altitude and this places the catcher mechanism at 250km altitude for rendezvous with the payload.
+This MFD uses the [[Kepler Orbital Simulation Toolkit]] (KOST) by CJ Plooy and Tim Blaxland.
-The tether rotates at approximately 1 degree per second. The resulting centripetal force on the payload is approximately 2.8gees.
+It also use the built-in Orbiter pop-up menus for selecting the reference body. Thanks to C J Plooy for his work in making this functionality available.
-The design payload mass is 20-25 metric tonnes.
+== Copyright Notice ==
-One of the key challenges of the system is affecting a successful rendezvous between the payload and the catcher on the end of the tether. The rendezvous is more challenging than a typical space rendezvous due to the rapidly rotating tether forcing the capture window to be very small in both space and time. Specialised guidance tools for the rendezvous of the payload with the catcher mechanism are being developed.
+Copyright 2009 by Tim Blaxland (tblaxland@gmail.com)
-==== Ananke-MX ====
+StateVectorMFD is free software: you can redistribute it and/or modify it under the terms of the GNU Lesser General Public License as published by the Free Software Foundation, either version 3 of the License, or (at your option) any later version.
-Ananke-MX is a stretched version of Ananke for transferring payloads to Mars. MX is short for Mars eXpress.
+StateVectorMFD is distributed in the hope that it will be useful, but WITHOUT ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU Lesser General Public License for more details.
-=== Moon ===
+You should have received a copy of the GNU Lesser General Public License along with StateVectorMFD. If not, see <http://www.gnu.org/licenses/>.
-==== Khronos ====
-Khronos is a rotovator type tether design to be able place and pickup payloads directly from the surface of the moon. Khronos will most likely be placed in a near polar orbit to maximise rendezvous opportunities with payloads coming in from Earth.
-=== Mars ===
-== Vessels ==
-=== Tortoise Class Lunar Transfer Vessel ===
-The Tortoise Class Lunar Transfer Vessel is designed to be transferred from low Earth orbit to the lunar surface and back again. Capture and landing at the moon is by way of the Khronos tether. Capture at Earth is by way of aerobraking.

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