Jupiter System Observer Mission Study: Final Report - Lunar and ...

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01 NOVEMBER 2007 2007 JUPITER SYSTEM OBSERVER MISSION STUDY: FINAL REPORT SECTION 3—MISSION ARCHITECTURE ASSESSMENT Task Order #NMO710851 1 m class, is more risky because of the need to reduce mass either by using lightweight material or a segmented mirror with active control. Architecture 4 has significant technology challenges as discussed in §3.4.3. The “intangibles” ratings take into account factors that may not be covered elsewhere. They include factors such as public excitement, science community support, proper timing of results of other missions. Architectures 2 and 3 were ranked higher in public excitement and community support as compared to architecture 1 because of innovation (e.g., mission design in architecture 2, Hubble going to Jupiter in architecture 3). Architecture 4 was down graded because Juno results would not have been available at the time needed for the probe design as discussed in §3.4.3. As a result of the above considerations, architectures 1 and 2 (reference numbers 3 and 4) were chosen for the next level of detailed design. 3.4.5 Final Two Architectures The two architectures selected for detailed study both assume a Jupiter tour with JSO ultimately achieving orbit at Ganymede. To demonstrate that viable and robust missions can be carried out, it must be shown that significant observations can be made using launch vehicles with different capabilities. Because a magnetosphere sub-satellite is not a viable option (§3.3.2), the SDT determined that a single orbiter that first spends a year in an intermediately inclined (60°) orbit to sample both the external Jupiter field and the Ganymede field (to understand how they are convolved) followed by a second year in a highly inclined (> 85°) low-altitude circular orbit will achieve most of the required objectives. The circular orbit is also ideal for gravity measurements, high resolution remote sensing and other system science. This architecture has the most capability and is the JSO “Baseline” mission. Because the second architecture relies on a smaller, less capable, launch vehicle, compromises in the ability to achieve the science are required. The major difference between the two architectures is that the second does not provide a close circular orbit at Ganymede. It is instead restricted to an intermediately inclined elliptical orbit. Because of this, there is a significant 3-8 degradation to the gravity and the magnetosphere data while objectives for Jupiter atmosphere and satellites remain relatively unaffected. This second architecture is designated the “Descoped” mission. In addition, the SDT also re-examined the notional payload for the two architectures prior to the down select to arrive at a more balanced and more optimized payload suite that is consistent with the two final architectures and with the available mass and power.
2007 JUPITER SYSTEM OBSERVER MISSION STUDY: FINAL STUDY 01 NOVEMBER 2007 Task Order #NMO710851 SECTION 4—MISSION CONCEPT IMPLEMENTATION 4.0 MISSION CONCEPT IMPLEMENTATION 4.1 Mission Architecture Overview The JSO mission is composed of 3 segments: launch, flight, and ground, as shown in Fig. 4.1-1. The launch segment is composed of the launch vehicle and the launch site. For the baseline JSO mission, the launch vehicle is the Delta IV-H. The Delta IV-H is the most capable LV of the Delta IV family. The first stage and the two strap-on boosters use cryogenic propellants (liquid oxygen and liquid hydrogen). The 5-m diameter second stage also uses cryogenic propellants. The composite fairing is 5 m in diameter and 19.8 m long. For planetary missions, the Delta IV-H is launched from the Eastern Range (ER) in Florida. The Space Launch Complex (SLC) of the ER, designated SLC-37, is located at Cape Canaveral Air Force Station (CCAFS). The flight segment, also known as the spacecraft, is composed of the bus and the Thruster Clusters (8) Pressurant Tanks (3) Ground Penetrating Radar Flight Segment 4-1 payload. The bus is made up of subsystems including telecommunication, thermal, propulsion, structures and mechanisms, power, attitude and articulation control, command and data handling, and flight software. Section 4.4 provides a detailed description of the bus. The planning payload for the baseline mission has nine notional instruments. The high resolution camera and the VIS-NIR spectrometer share a 50-cm aperture front optics. The remaining are the medium-resolution stereo camera, laser altimeter, UV and thermal spectrometers, radar, magnetometer, plasma spectrometer/ energetic particle detector. Radio science is conducted through the telecommunications subsystem using dual Ka- and X-band frequencies. §4.2 provides more detailed description of the payload. The ground segment is composed of the Deep Space Network (DSN), the Flight Operations Center (FOC), and the Science Operations Center (SOC). The DSN is operated out of JPL and includes 3 Deep Space Communications Complexes (DSCC) located Radiation Vault MMRTGs (8) Louvered Radiator (2) HGA Main Engine (890 N) Ground Segment Launch Segment DSN FOC SOC Figure 4.1-1. JSO Mission Architecture
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