Quasi-Synchronous Orbits Around Phobos in the Context of a Phobos Sample Return Mission

Gil, P. J. S.; Schwartz, Julia

doi:10.2514/6.2008-6429

Cited by 3 publications

(4 citation statements)

References 6 publications

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“…The Deimos' gravity is so slight that the conlinear libration points in the Mars-Deimos restricted three-body problem (i.e., L 1 and L 2 ) are located inside the body of Deimos, 19) and even less than the J 2 perturbing acceleration at the encounter points. At the encounter, the acceleration due to J 2 is…”

Section: Design Methodologies For Working Orbitmentioning

confidence: 99%

“…One is a quasi-synchronous orbit (QSO) keeping around Deimos, which is considered to be the best approach for photographing Deimos all the time. 19) However, the Keplerian-type way cannot be used to orbit Deimos because the mass of Deimos is too small in relation to its close distance to Mars; especially considering the fact that the Lagrange points are located inside the surface of Deimos. Quite similar to the formation flying theory, both the spacecraft and Deimos are dominated by the gravitational attraction of Mars.…”

Section: Design Methodologies For Working Orbitmentioning

confidence: 99%

“…One is to fly around Phobos or Deimos in a special kind of orbit designated as a quasi-synchronous orbits (QSO). 19) In the rotating synodic reference frame, a coplanar QSO relative to the orbital plane can be described as an elliptical epicycle drifting back and forth in the direction of the orbital velocity of the body. An advantage of this mode is keeping the spacecraft in the vicinity of the moons for a long time, which is more beneficial for imaging.…”

Section: Introductionmentioning

confidence: 99%

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Deimos Encounter Trajectory Design for Piggyback Spacecraft Launched for Martian Surface Reconnaissance

Wang

2015

Trans. Japan Soc. Aero. S Sci.

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This paper discusses a trajectory design for imaging both Mars and Deimos, which meets the requirements of the next Chinese mission to Mars and Deimos. Compared to Viking-1, being weak in systematic schedules in its original and extended missions, which resulted in the use of more fuel and reducing encounter opportunities, a multipurpose design is addressed in this paper for imaging both Mars and Deimos at Pre-Phase A, not after launch. A frozen and repeating orbit is employed to provide as many as 280 periodic encounters within 100 km of Deimos, in contrast to the fly-around mode used by Phobos-1/2 and Phobos-Grunt, requiring much fuel to guide the spacecraft to the vicinity of Phobos from the highly elliptical captured orbit. To enable encounters with Deimos under all of the perturbations and orbital control and determination errors, the station-keeping strategies for the arguments of periareon and latitude are implemented by some corrections to the semi-major axis and inclination, respectively. A numerical simulation is used to verify the encounter opportunities with the help of the station-keeping strategies. Detailed investigations on imaging, lighting and access conditions show that a working orbit is beneficial for imaging both the Martian surface and Deimos. Therefore, it is concluded that designing the trajectory of the piggyback spacecraft to be carried by the main orbiter in the next Chinese Mars mission during Pre-Phase A is practical from the engineering perspective.

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Section: Design Methodologies For Working Orbitmentioning

confidence: 99%

Section: Design Methodologies For Working Orbitmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Deimos Encounter Trajectory Design for Piggyback Spacecraft Launched for Martian Surface Reconnaissance

Wang

2015

Trans. Japan Soc. Aero. S Sci.

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“…For the Mars-Phobos or Mars-Deimos system, because the Hill sphere of both Phobos and Deimos are very small, researchers used the model of the three-body problem to study orbits around those Martian moons. Gil and Schwartz 17) used the three-body model to study the quasisynchronous orbit around Phobos for a sample return mission. Wallace et al 18) studied several types of orbits in the threebody problem for a Phobos exploration mission.…”

Section: Introductionmentioning

confidence: 99%

Systematic Orbital Design for a Jovian Moon Exploring Mission

CHEN,

XU,

FENG

et al. 2023

Trans. Japan Soc. Aero. S Sci.

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The Jovian moons have been visited by several flyby missions and are attracting more attention for long-term observation. However, because of Jupiter's gravitational perturbations and the J 2 and C 2,2 terms of the Jovian moons, orbits around these moons are unstable, especially those orbits with high inclinations. This study considers a scenario in which the spacecraft flies at a high altitude equipped with a payload having a small field-of-view angle. The coverage rate is achieved by numerical integration, and the largest coverage rate can be found using the particle swarm optimization method. The results highlight the possibility of obtaining a greater coverage rate, as well as considerable imaging resolution and mission duration by choosing suitable candidate orbits. A station-keeping algorithm is introduced to produce a more accurate estimation of gravitational models that is indexed using the station-keeping cost and estimation accuracy. Based on the five aspects mentioned above, a systematic evaluation of candidate orbits was created for orbit design.

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Design of Transfer Trajectories Between Planar and Spatial Quasi-Satellite Orbits

Pushparaj

Baresi

Kawakatsu

2020

AIAA Scitech 2020 Forum

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Quasi-Synchronous Orbits Around Phobos in the Context of a Phobos Sample Return Mission

Cited by 3 publications

References 6 publications

Deimos Encounter Trajectory Design for Piggyback Spacecraft Launched for Martian Surface Reconnaissance

Deimos Encounter Trajectory Design for Piggyback Spacecraft Launched for Martian Surface Reconnaissance

Systematic Orbital Design for a Jovian Moon Exploring Mission

Design of Transfer Trajectories Between Planar and Spatial Quasi-Satellite Orbits

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