Dave Jarvis' Repositories

git clone https://repo.autonoma.ca/repo/autonoma.ca.git

Adds credits

Author djarvis <email>
Date 2024-12-04 00:44:38 GMT-0800
Commit 8421f4bbae0cb136231149c4ba088f3f4e5d4455
Parent 63bc6d6
calculators/rocket/payload/index.html
Helps determine whether a payload can be inserted into a stable orbit.
Form field values are explained in the <a href="#equations">Equations</a>
- section, below.
+ section, below. Based on Professor Aaron Ridley's
+ <a href="https://github.com/aaronjridley/Kepler/blob/main/OrbitalInsertion/launch.py">implementation</a>.
</p><form id="calculator"><button class="submit">Simulate</button><fieldset id="mission"><legend>Mission</legend><label for="initial_velocity">Initial velocity (Mach)</label><input tabindex="3" class="variable" type="number" step="1" min="0" value="6" id="initial_velocity" name="initial_velocity"><label for="initial_latitude">Initial latitude (°)</label><input tabindex="4" class="variable" type="number" step="any" min="0" value="1.469167" id="initial_latitude" name="initial_latitude"><label for="initial_altitude">Initial altitude (m)</label><input tabindex="5" class="variable" type="number" step="1" min="0" value="6212" id="initial_altitude" name="initial_altitude"><label for="target_altitude">Target altitude (km)</label><input tabindex="6" class="variable" type="number" step="1" min="1" value="400" id="target_altitude" name="target_altitude"></fieldset><fieldset id="rocket"><legend>Rocket</legend><label for="diameter">Diameter (m)</label><input tabindex="7" class="variable" type="number" step="any" min="0" value="0.6" id="diameter" name="diameter"><label for="wet_mass">Wet mass (kg)</label><input tabindex="8" class="variable" type="number" step="10" min="1" value="250" id="wet_mass" name="wet_mass" oninput="this.value = Math.abs(this.value)"><label for="payload">Payload mass (kg)</label><input tabindex="9" class="variable" type="number" step="1" min="1" value="25" id="payload_mass" name="payload_mass" oninput="this.value = Math.abs(this.value)"><label for="drag_coefficient">Drag coefficient</label><input tabindex="10" class="variable" type="number" step="any" min="0" value="0.219" id="drag_coefficient" name="drag_coefficient"><label for="specific_impulse">Specific impulse (s)</label><input tabindex="11" class="variable" type="number" step="10" min="1" value="1700" id="specific_impulse" name="specific_impulse"></fieldset><fieldset id="result"><legend>Result</legend><div id="plots"></div></fieldset></form><a name="equations"></a><h1>Equations</h1><p>
This section describes equation inputs and outputs.
calculators/rocket/payload/launch.xsl
Helps determine whether a payload can be inserted into a stable orbit.
Form field values are explained in the <a href="#equations">Equations</a>
- section, below.
+ section, below. Based on Professor Aaron Ridley's
+ <a href="https://github.com/aaronjridley/Kepler/blob/main/OrbitalInsertion/launch.py">implementation</a>.
</p>
Delta 4 lines added, 2 lines removed, 2-line increase