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<h2 class="hd hd-2 unit-title">The Ideal Rocket Equation</h2>
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<h2>2.3.1 The Ideal Rocket Equation</h2>
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Apply the Ideal Rocket Equation to calculate the performance of single- and multi-stage rockets" type="button" id="LD">MO 2.3</button></p>
<p style="text-align: center;"><em><span style="font-family: 'Open Sans', Verdana, Arial, Helvetica, sans-serif;"><img src="/assets/courseware/v1/fd2026c340b5742325c26572bddd12e9/asset-v1:MITx+16.00x+2T2019+type@asset+block/STS114Launch400.png" alt="Launch of Space Shuttle Discovery on STS-114 " type="saveimage" target="[object Object]" height="500" width="400" /></span></em></p>
<p style="text-align: center;"><em><span style="font-family: 'Open Sans', Verdana, Arial, Helvetica, sans-serif;">Launch of Space Shuttle Discovery on STS-114 (Source: NASA)</span></em></p>
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<p>In this section, we will learn why it is so expensive to launch payloads into space. In particular, we will discuss the various components of mass on a rocket and use these quantities to derive the Rocket Equation in free space (also known as the Ideal Rocket Equation or simply the Rocket Equation).</p>
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<h3 class="hd hd-2">Video: The Ideal Rocket Equation</h3>
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<h2 class="hd hd-2 unit-title">Implications of the Rocket Equation</h2>
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<h2>2.3.2 Implications of the Rocket Equation</h2>
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<p style="float: left; margin: 20px;"><img src="/assets/courseware/v1/6ce4b2152c8e204ba04138408b21cbe3/asset-v1:MITx+16.00x+2T2019+type@asset+block/Tsiolkovsky200.gif" alt="Konstantin Tsiolkovsky" type="saveimage" target="[object Object]" /></p>
<p>The Rocket Equation was developed by the Russian scientist Konstantin Tsiolkovsky, and uses the principle of conservation of momentum to relate the maximum change in velocity (\(\Delta V\)) to the propellant exhaust velocity and the initial and final rocket mass (\(m_i\) and \(m_f\), respectively). Using just basic physics and math (with a little bit of calculus), the Rocket Equation expresses one of the most fundamental relations in all of astronautics and has significant implications for spaceflight.</p>
<p>As you watch the following video, pay special attention to what the various quantities in the Rocket Equation imply for propellant fraction and rocket performance. You will be asked to apply what you have learned to complete several problems.</p>
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<h3 class="hd hd-2">Video: Implications of the Rocket Equation</h3>
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<h2 class="hd hd-2 unit-title">Review of Concepts: The Ideal Rocket Equation</h2>
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<h2>2.3.3 Review of Concepts: The Ideal Rocket Equation (EQ)</h2>
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Mass of a Rocket
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<p>According to the Ideal Rocket Equation, what components comprise...</p>
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Constructing the Rocket Equation
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Construct the correct expressions for the logarithmic and exponential forms of the Tsiolkovsky Ideal Rocket Equation. </p>
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Rocket Propulsion Conceptual Question
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<p>Consider a rocket in free space having two engines with identical \(I_\text{sp} \), connected to a single propellant system. Recall that the relationship between specific impulse and exhaust velocity is \( V_\text{ex} = g_0\, I_\text{sp} \). </p>
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<legend id="6160014513e94485a136db9f2e1239df_2_1-legend" class="response-fieldset-legend field-group-hd">If one engine fails, what is the impact on the total \(\Delta V\) that can be obtained from the system?</legend>
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<h2 class="hd hd-2 unit-title">Rocket Staging</h2>
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<h2>2.3.4 Rocket Staging</h2>
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<p style="text-align: center;"><em><span style="font-family: 'Open Sans', Verdana, Arial, Helvetica, sans-serif;">First-stage separation of Saturn V rocket during the Apollo 11 mission (Image credit: NASA)</span></em></p>
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<p>Now that we are familiar with the Ideal Rocket Equation, we will discuss another important aspect of rocket propulsion: rocket staging. As we will see, achieving Earth orbit requires a very large \(\Delta V\) and a considerable propellant mass fraction --- so much so that it is unrealistic to do this with a single-stage rocket. In a multi-stage rocket, once the propellant in the first stage is consumed, the first stage structure is discarded, and the rocket continues onward using propellant from the second stage; once the second stage propellant is exhausted, the second stage structure is discarded, and the rocket continues onward using the third stage propellant, and so on. This approach allows the rocket to achieve a larger \(\Delta V\) for the same initial mass at launch.</p>
<!--<p>The figure on the left shows the first-stage separation of the Saturn V rocket during the Apollo 11 launch, the first mission to land humans on the surface of the moon, on July 16, 1969.</p>-->
<p>After watching following video about rocket staging, you will have an opportunity to apply what you learned to solve a two-stage rocket problem.</p>
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<h2 class="hd hd-2 unit-title">Review of Concepts: Rocket Staging</h2>
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<h2>2.3.5 Review of Concepts: Rocket Staging</h2>
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<label class="problem-group-label" for="input_783476bfd93e455b8b58119a203c7642_4_1" id="label_783476bfd93e455b8b58119a203c7642_4_1">Recall that the relationship between specific impulse and exhaust velocity is: \( V_\text{ex} = g_0\, I_\text{sp} \). Assuming that \(I_\text{sp} = 450\,\text{s}\) and \(g_{0} = 9.81\,\text{m/s}^2\), what is the value of \(\Delta V\) in m/s that this rocket will produce if all the propellant is consumed in one stage?</label>
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<h3 class="hd hd-3 problem-header" id="05280c185a36497d92f6d4d1405fb290-problem-title" aria-describedby="block-v1:MITx+16.00x+2T2019+type@problem+block@05280c185a36497d92f6d4d1405fb290-problem-progress" tabindex="-1">
Part 2: Multi-Stage
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<p>Now break the rocket into two equal stages, with each stage containing half the propellant and half the structure of Part 1 (i.e., 50,000 kg of propellant and 5000 kg of structure in each stage). The 5000 kg of payload goes on the front of the second stage.</p>
<p>Note: A diagram might be useful to help you keep track of the various quantities. Make sure you are very clear in your work about what variables correspond to what quantities. Remember that \(m_f\) of the first stage includes the first stage structure, but \(m_i\) of the second stage does not include the first stage structure, since that is lost during staging.</p>
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