Stk component browser design tools download

Scientific notation is not required. Epoch Label This field displays the epoch against which the import data will be validated. Validate Click this button to attempt to parse the input data and convert it to CBI. Validation result label This section displays the outcome of the validation attempt. Choice Description Notes Status label Indicates the result of the Compute operation Possible results include: No valid solution computed State to state solution Body to body solution Departure or arrival body not set Initial DeltaV The magnitude of the impulse required for the Lambert arc.

Final DeltaV The magnitude of the impulse required to match velocity with the arrival conditions. Time of Flight The duration of the Lambert arc. If the selected solution is Fixed Time: This should be consistent with the time specified in the Time of Flight field in the top-left section. Departure C3 The equivalent C3 energy to depart on the Lambert arc. This field applies to body-to-body solutions: If the departure R magnitude is greater than 0, the C3 value is computed by converting the departure position and velocity post-impulse to Target Vector Outgoing Asymptote coordinates at the departure body.

Departure RA The equivalent right ascension of the impulse to depart on the Lambert arc. This field applies to body-to-body solutions: If the departure R magnitude is greater than 0, the RA value is computed by converting the departure position and velocity post-impulse to Target Vector Outgoing Asymptote coordinates at the departure body.

Departure Dec The equivalent declination of the impulse to depart on the Lambert arc This field applies for body-to-body solutions: If the departure R magnitude is greater than 0, the Dec value is computed by converting the departure position and velocity post-impulse to Target Vector Outgoing Asymptote coordinates at the departure body.

The angle of the departure point in the velocity-normal plane, measured from the orbit normal of the Lambert arc. Select this check box to have the velocity conditions at the departure point pre-impulse be consistent with a two-body circular orbit about the departure body.

Select this check box to have the departure position rotated backward to periapsis of a hyperbola, and the pre-impulse velocity is the circular velocity consistent with the departure position. The angle of the arrival point in the velocity-normal plane, measured from the orbit normal of the Lambert arc.

Select this check box to have the velocity conditions at the arrival point post-impulse be consistent with a two-body circular orbit about the departure body. Use this field to select the state variable representation associated with the state variables to import. Possible results include: No valid solution computed State to state solution Body to body solution Departure or arrival body not set.

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Add mission-specific depth to STK with sophisticated modeling, simulation, and analysis capabilities for any domain. Enhance STK with advanced analysis features, integration capabilities, and terrain and imagery. This website uses cookies and other tracking technologies to enhance site navigation and analyze usage. By clicking "Accept", you agree to the storage of cookies on your device per our Cookie Policy. Radar STK Radar provides a quick setup and thorough radar system analysis.

Use the Lambert Solver. Create a custom transfer arc. Create a heliocentric interplanetary trajectory. Click the Create a Scenario button. When the scenario loads, click Save. A folder with the same name as your scenario is created for you.

In the Save As window, verify the scenario name and location and click Save. Save Often! Scenario Basic Time The scenario analysis period defines the epoch and the start and stop times of your scenario.

Set the Animation Step Size to 1 hr sec. Click Apply. Disable the Subplanet Points and Labels You'd like to see the planet orbits and not have the subplanet points and labels visible. Select the 2D Graphics - Global Attributes properties page. Bring the 2D Graphics window to the front. Click the Close button found in the upper right hand corner of the window. Insert the Earth The Planet object models orbital and other properties of a planet, a moon, an asteroid or the sun.

In the Object Browser, open Planet1's properties. Set the Ephemeris Source to DE Click OK. Create Pathfinder The Satellite object models the properties and behavior of a vehicle in orbit around a central body. In the Object Browser, rename the Satellite object "Pathfinder".

Open Pathfinder's properties. On the Basic - Orbit page, set the Propagator to Astrogator. Select the 2D Graphics - Pass page. Select the 3D Graphics - Model page. Locate the Detail Thresholds field. Slide the Simple Model, Label slider bar to the far right. Click OK to save your changes and close the properties panel. In the Object Browser, right-click on Pathfinder and select Copy. Open 3D Graphics 1 - Earth's properties.

Select the Grids page. Select the Ecliptic Coordinates - Show check box. Select the Window Properties page. Change the Title: to Earth. Select the Advanced page. Heliocentric View Extend the View menu on the main toolbar. Bring the 3D Graphics 2 - Earth window to the front. Open the Properties for the 3D Graphics 2 - Sun window. Change the Title: to Sun. Mars-Centered View Extend the View menu on the main toolbar. Bring the 3D Graphics 3 - Earth window to the front.

Open 3D Graphics 3 - Mars's properties. Change the Title: to Mars. Globe Manager Select the Sun window. Zoom out and adjust the angle of the view so that the Earth, Mars, and Sun are all visible in the window.

In the Globe Manager window, right-click on the Moon and clear the Label option. Create a custom Transfer Arc Use the Component Browser to begin designing the transfer trajectory for the mission. Extend the Utilities menu. Select the Component Browser option. In the Components list, select Design Tools. Click duplicate.