Chapter 4 - Sample Return Mission
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Chapter 4 - Sample Return Mission
Chapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return Missionst important scientific tasks we are conducting during this mission will be the return of a Martian soil and rock sample. This mission lasts for the duration of the astronauts stay in Martian orbit. The astronauts have the task of using the two different rovers to collect the sample and perform othe Chapter 4 - Sample Return Missionr scientific measurements. Note that the rovers are located on opposite sides of the planet for maximum communication time. This mission will play a sChapter 4 - Sample Return Mission
ignificant roleAAE 450 Senior Spacecraft Design Spring 2004167Chapter 4 - Sample Return Missionfor future manned missions to the surface of mars. We wChapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return Missionrs. In conjunction with the data collected from the Mars Exploration and Pathfinder missions the soil and rock data from our robotic missions will help choose an appropriate landing site for such a mission. Another benefit we gain from the sample return mission is the demonstration of producing the Chapter 4 - Sample Return Missionrequired propellant for a Mars to orbit launch. This is a very important technology that must be proven before a human landing is possible. Other techChapter 4 - Sample Return Mission
nological benefits such as precision landing will are also demonstrated in our rover missions. The rock and soil samples once returned to Earth will pChapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return Missionre launched shortly after the aero-capture maneuver for the spacecraft has been completed. Two landers are sent to the surface to ensure the success of the sample return mission in the event that one fails. These failures include but are not limited to unsuccessful landing, improper rover or sample Chapter 4 - Sample Return Missionreturn vehicle (SRV) deployment, complications in propellant production or unfavorable weather conditions. We target the landers at two different landChapter 4 - Sample Return Mission
ing sites on different sides of the planet. We need two landing locations for two different reasons; variety of samples and communication. In the evenChapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return MissionPlacing the rovers on opposite sides of the planet allows for the design of our spacecraft’s orbit to ensure that the astronauts are always in contact with at least one landing site. After the landers touchdown and deploy the rovers a subsystem of the lander starts producing the propellant for the s Chapter 4 - Sample Return Missionample return vehicle using in-situ production processes (section 4.6.4). It is necessary' that the SRV should employ this technology not only for theChapter 4 - Sample Return Mission
reduction in mass but also to prove these techniques for future manned missions. During this time the astronaut controlled rovers collect up to ten kiChapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return Missionng. The rest of this chapter discusses the details of these components and procedures.AAE 450 Senior Spacecraft Design Spring 2004168chapter 4 - Sample Return Mission4.2Launch of Rovers4.2.1 Release of Landers - Allison BahnsenAlter the Transport Vehicle performs derocapture and the periapsis-raise Chapter 4 - Sample Return Missionmaneuver, and prior to the apo-twist maneuver, we release the two landers that venture to the surface of Mars.The side, cross-sectional profile of theChapter 4 - Sample Return Mission
landers in the Transport Vehicle is shown on the left of Error: Reference source not found. As we can see, the landers are housed within the body of Chapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return Missiondicated by allows. Prior to release, these doors slide open to reveal the landers.Protective Doors•Clive DoorsFig. 4.2 Side View of Landers in Transport and Pl Created by Ben Toleman and David GoecWe release the landers when the Transport Vehicle is traveling as slowly as possible Io reduce propella Chapter 4 - Sample Return Missionnt costs. The slowest point in the Transport Vehicle’s orbit, seen in blue in Fig. 4 .2, occurs at apoapsis, where we release the first lander. This rChapter 4 - Sample Return Mission
elease at apoapsis costs 1.05 nvs, AAE 450 Senior Spacecraft Design Spring 2004169Chapter 4 - Sample Return Missionand places the first lander on the Chapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return Missionl (half a Martian day) to release the second lander. Now that the spacecraft is no longer at apoapsis, we must find the orbit that intersects the current location of the Transport Vehicle and has a periapsis altitude of 100 km. We can see this trajectory in red in Fig. 4 .2, and can transfer to it f Chapter 4 - Sample Return Missionor a cost of 1.17 m/s. These results are obtained using the MATLAB code in Appendix G.------- Trajectory of 2nd LanderFig. 4.2 Lander TrajectoryFor thChapter 4 - Sample Return Mission
e above calculations we assume that the Transport Vehicle is in the same plane as the landing sites: the equatorial plane. In actuality the Transport Chapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return Missiong site is a node between the ecliptic and equatorial planes. This plane change would cause the release Av’s (or change in velocity) to be three-dimensional, but their magnitudes would not be much larger than those of the aforementioned values. Solving for these three-dimensional Av’s and the impleme Chapter 4 - Sample Return Missionntation times of hitting the two selected landing sites are not trivial matters by any means, and thus are out of the scope of this study. This in noChapter 4 - Sample Return Mission
way affects the feasibility of the mission, it simply adds to the complexity of time lining the overall mission when it comes to fruition.4.2.2Cruise Chapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mos Chapter 4 - Sample Return Missionuise configuration. The cruise stage resemblesAAE 450 Senior spacecraft Design Spring 2004170Chapter 4 - Sample Return MissionChapter 4 - Sample Return Mission4 Sample Return Mission4.1Mission OverviewFig. 4.1 Created By Ben Toleman4.1.1Introduction - Matt MaierOne of the mosGọi ngay
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