Current Power: N/A

Table of Masses Original Conceptual Design Data: Gravity = 9.8 kg/m^2 Lander Mass = 220 kg Payload Mass = 674.9852 kg Rocketdyne XLR-132 MR-107 Mass = 54 kg Mass = 0.885 kg Isp = 340 sec Isp = 220 sec Vpt-a = 10974.15m/sec Vp = 12000 m/sec Vpt-a = 10974.147m/sec Delta V1 =-1025.85m/sec Vp = 12000 m/sec Mission Delta V Final Prop Phase (m/sec) Mass(kg) Mass(kg) Actual 20% SF Last Descent 20 24 222.655 2.4923808 First Descent 1665 1998 279.14738 229.30916 De-Orbit Burn 20 24 508.45654 5.6916186 TCM #5 20 24 514.14816 5.7553301 Lunar Orbit Insertion 825 990 519.90349 179.87374 TCM #4 20 24 699.77723 7.8332459 TCM #3 20 24 707.61048 7.9209306 TCM #2 20 24 715.53141 8.0095968 TCM #1 20 24 723.541 8.0992555 Earth Departure Burn -1025.85 -1231.02 731.64026 0 Total Prop Mass for XLR-132 409.1829 Total Prop Mass for MR-107 45.80236 Total Prop Mass Used 454.985 Max Lander Mass = 455 kg Table of Masses (Not Jettisoning the XLR-132) Data: Gravity = 9.8 kg/m^2 Lander Mass = 220 kg Payload Mass = 764.1026kg Rocketdyne XLR-132 MR-107 Mass = 54 kg Mass = 0.885 kg Isp = 340 sec Isp = 220 sec Vpt-a = 10974.15m/sec Vp = 12000 m/sec Vpt-a = 10974.147m/sec Delta V1 =-1025.85m/sec Vp = 12000 m/sec Mission Delta V Final Prop Phase (m/sec) Mass(kg) Mass(kg) Actual 20% SF Last Descent 20 24 276.655 3.0968522 First Descent 1665 1998 333.75185 274.1647 De-Orbit Burn 20 24 607.91655 6.8049653 TCM #5 20 24 614.72151 6.8811395 Lunar Orbit Insertion 825 990 621.60265 215.05914 TCM #4 20 24 836.66179 9.3655198 TCM #3 20 24 846.02731 9.4703566 TCM #2 20 24 855.49767 9.576367 TCM #1 20 24 865.07403 9.683564 Earth Departure Burn -1025.85 -1231.02 874.7576 0 Total Prop Mass for XLR-132 489.2238 Total Prop Mass for MR-107 54.87876 Total Prop Mass Used 544.103 Max Lander mass = 420 kg Table of Masses (No Aux. Thrusters) Data: Gravity = 9.8 kg/m^2 Lander Mass = 220 kg Payload Mass = 652.48854kg Rocketdyne XLR-132 MR-107 Mass = 54 kg Mass = 0.885 kg Isp = 340 sec Isp = 220 sec Vpt-a = 10974.15m/sec Vp = 12000 m/sec Vpt-a = 10974.147m/sec Delta V1 =-1025.85m/sec Vp = 12000 m/sec Mission Delta V Final Prop Phase (m/sec) Mass(kg) Mass(kg) Actual 20% SF Last Descent 20 24 274 1.9807143 First Descent 1665 1998 275.98071 226.70786 De-Orbit Burn 20 24 502.68858 3.6338775 TCM #5 20 24 506.32245 3.6601464 Lunar Orbit Insertion 825 990 509.9826 176.44136 TCM #4 20 24 686.42396 4.9620794 TCM #3 20 24 691.38604 4.9979497 TCM #2 20 24 696.38399 5.0340793 TCM #1 20 24 701.41807 5.0704701 Earth Departure Burn -1025.85 -1231.02 706.48854 0 Total Prop Mass for XLR-132 482.03 Total Prop Mass for MR-107 34.69 Total Prop Mass Used 516.72 Max Lander mass = 435 kg

- Fuel Requirements
- Type
- XLR-132 Monomethyl Hydrazine
- MR-107 Hydrazine

- Masses
- See charts above for different cases.
- See charts above for different cases.

- Volumes
- Using the masses stated above and the densities, the volume can be calculated.
- Same as above.

- Type
- Oxidizer Requirements
- Type
- XLR-132 Nitrogen Textroxide
- MR-107

- Type

The Charts above were run for three different cases:

- Original Design of one main engine, XLR-132, which is used for the three main engine burns, and three aux. thrusters, MR-107, which are responsible for the TCM's and the last phase of Descent.
- Same Original Design but not jettisoning the XLR-132
- One engine, the XLR, to accomplish all manuevers

In each case a test was run to check the maximum lander mass that would still satisfy the maximum payload of 2000 kg for the launcher. These values are listed in each chart of the different cases.

So far a few monopropellant Hydrazine Thrusters look sufficient. These include the MRE-0.1. Due to its low thrust range (0.3 to 0.9N) it may not be able to accept a severe load. It would require too great a burn time. The MRE-1, MRE-4, and MRE-5/GRO appear to be contenders.

The current plan does not include coupling these thrusters. However, that is still an option. It is believed that single thrusters will not cause a detrimental translation. This would result in six thrusters, one for each direction for each axis. Coupled thrusters would require twelve thrusters.

Other than that we hope to continue on with our schedule that was submitted as an earlier progress report.

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