Landing Trajectory Generation and Energy Optimization for Unmanned Lunar Mission

<div>Fuel consumption during <span class="nowrap"><svg height="8.8423pt" id="M94" style="vertical-align:-0.2064009pt" version="1.1" viewbox="-0.0498162 -8.6359 17.3109 8.8423" width="17.3109pt" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink"><g transform="matrix(.013,0,0,-0.013,0,0)"><path d="M822 650H589L583 622C660 617 677 607 674 561C672 534 664 481 647 390L600 137H596L273 650H126L120 622C176 620 194 615 207 594C221 571 225 557 214 504L161 257C141 166 129 112 121 85C108 42 83 30 29 28L23 0H260L266 28C193 33 173 42 176 89C178 122 186 172 202 255L256 527H259L583 -8H612L690 390C708 481 720 535 728 558C744 603 756 619 816 622L822 650Z"></path></g><g transform="matrix(.013,0,0,-0.013,10.91,0)"><path d="M384 0V27C293 34 287 42 287 114V635C232 613 172 594 109 583V559L157 557C201 555 205 550 205 499V114C205 42 199 34 109 27V0H384Z"></path></g></svg>.</span></div>

Mathematical Problems in Engineering

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Figure 5

Figure 5: Landing Trajectory Generation and Energy Optimization for Unmanned Lunar Mission 