Mission design of DESTINY+

Paper number

IAC-16,C1,5,5,x35057

Coauthor

Dr. Takayuki Yamamoto, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Shunsuke Sato, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Yosuke Kawabata, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan

Coauthor

Dr. Stefano Campagnola, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Bruno Sarli, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan

Coauthor

Mr. Satoshi Ogura, The University of TOKYO, Graduate school, Japan

Coauthor

Dr. Yasuhiro Kawakatsu, Japan Aerospace Exploration Agency (JAXA), Japan

Year

2016

Abstract

DESTINY+ is a small-seized and high performance deep space vehicle proposed for public offering small-sized plan space science mission of ISAS/JAXA. DESTINY+ is injected into an extended elliptical orbit launched by Epsilon rocket. The orbit is spiraled upward by the low-thrust of IES. And the swing-by is designed to give DESTINY momentum to Asteroid Phaethon flyby. After Phaethon flyby, DESTINY+ plan to go back to Earth for gravity assist and go to another asteroid. 
DESTINY+ has several mission objectives, including: demonstration and experiment of space technology of interplanetary voyage; Phaethon flyby with reusable probe; compact avionics as for Engineering mission, and the investigation of the process to the end of evolution of primitive body; the limitation of initial state and the evolution process of the meteor shower dust as for Science mission.
This paper discusses DESTINY+’s low-thrust trajectory design and the related system analysis. As for the spiral upward trajectory phase, the low-thrust trajectory is optimized by the multi-objective optimization using genetic algorithm. In this phase, we minimize the time of flight, the passage time of radiation belt, the work time of IES and the shadow time. After the spacecraft reaches to the moon’s path, it utilizes the moon swing-by several times to connect to the transfer trajectory for Asteroid Phaethon. 
Parallel to the trajectory design, the radiation effect analysis, thermal environmental analysis, attitude analysis and ground station visibility analysis for operation are achieved.
From these study, we can show the feasibility of the mission design of DESTINY+.

Abstract document

IAC-16,C1,5,5,x35057.brief.pdf

Manuscript document

IAC-16,C1,5,5,x35057.pdf (🔒 authorized access only).

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