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[其他发射] 2014年12月隼鸟-2Hayabusa2小行星样本返回探测器由H-2A发射>采样进行中..

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wsl2005 发表于 2014-6-17 22:48 | 显示全部楼层
cmj9808 发表于 2014-2-4 10:35
本次任务搭载一颗60kg的微卫星procyon,使用电推进器进行小行星flyby任务

http://cwe.ccsds.org/sea/doc ...

PRELIMINARY MISSION DESIGN OF PROCYON: A MICRO SPACECRAFT TO ASTEROID
1.png

2.png

This paper describes the trajectory design for 50kg-class micro-spacecraft, PROCYON (PRoximate Object Close flYby with Optical Navigation) mission, and its proximity navigation and guidance for asteroid flyby. PROCYON, which is mainly developed by the University of Tokyo in collaboration with the Japan Aerospace Exploration Agency (JAXA), has two broad missions: technology demonstration of micro spacecraft for deep space exploration and proximity flyby to asteroids (closest approach distance from asteroid is aimed around 10 kilometer). The spacecraft is scheduled to be launched as a secondary payload in December 2014 with Hayabusa 2 spacecraft.
PROCYON will be launched in an Earth resonant trajectory that allows the spacecraft to cruise back to the Earth. This particular orbit is due to the fact that the orbit is the same as Hayabusa 2, which uses solar electric propulsion leverage, or Electric Delta-VEGA (hereafter simply called EDVEGA), in December 2014 and June 2015 launch window. Therefore, the spacecraft expands the number of candidate asteroids using an Earth gravity assist.
The trajectory sequence for PROCYON is as follows: 1) EDVEGA phase (Earth to Earth), 2) Transfer phase (Earth to 1st Asteroid), and 3) Proximity Asteroid Flyby phase (Flyby to 1st Asteroid), as shown in Figure 2. If there is extra fuel after the 1st flyby, the spacecraft will transfer to the trajectory for flyby to another asteroid as an extra mission. In the EDVEGA and Transfer phases, the spacecraft uses radio navigation for determining the trajectory and miniature ion propulsion system for low-thrust transfer; however, around 10 km proximity flyby requires more accurate orbit determination. Therefore, optical navigation, which allows the spacecraft to determine precise trajectory relative to the asteroid when the spacecraft approach the asteroid, is applied in the Proximity Asteroid Flyby phase. The optical navigation can be effectively used less than a week before the close approach to the asteroid. This shortage of guidance duration requires higher-thrust propulsion system. Hence, we developed the ion engine and Xenon cold gas jet combined system, which resolve not only the mission requirement but also sizing requirement for micro-spacecraft. This system has one ion engine thruster for interplanetary maneuver and eight cold gas jet thrusters for both proximity trajectory correction maneuver and momentum unloading.
The mission design of such a small scale spacecraft possesses many challenges: i) the thrust of the ion engine is only 0.3 mN which is three orders of magnitudes less than a typical low-thrust mission; ii) the flyby of the asteroid will rely on optical navigation which depends on the lighting condition of the approach trajectory; iii) the very low specific impulse (25 seconds) of the cold gas engine used for correction maneuver during the asteroid flyby ; iv) requirements on the power and thermal conditions and communication link with the ground station must be satisfied; v) the fuel mass is only 2 kg (Delta-V is only 9 m/s if we use all fuel for cold gas jet). Moreover, the launch trajectory for the spacecraft is restricted by the Hayabusa 2 trajectory. Therefore we have to optimize these mission design altogether. For example, low-thrust interplanetary maneuver helps to decrease the fuel amount for trajectory correction maneuver in proximity asteroid flyby phase. This paper presents the selection of the target asteroid and trajectory design considering the aforementioned requirements and constraints
snscm 发表于 2014-9-1 07:52 | 显示全部楼层
cmj9808 发表于 2014-9-1 18:43 | 显示全部楼层
wsl2005 发表于 2014-6-17 22:48
PRELIMINARY MISSION DESIGN OF PROCYON: A MICRO SPACECRAFT TO ASTEROID

PROCYON的参数 图片1.png

图片2.png

图片3.png

点评

1000s的比冲是不是偏低?  发表于 2014-9-1 19:12
cmj9808 发表于 2014-9-1 19:39 | 显示全部楼层
本帖最后由 cmj9808 于 2014-9-1 19:41 编辑

@ssizz
比冲受限于功率(35W)
wsl2005 发表于 2014-9-2 20:54 | 显示全部楼层
日本公开展示“隼鸟”-2小行星探测器
http://www.dsti.net/Information/News/90222

[据日本ajw.asahi网站2014年9月1日报道]  日本宇宙航空研究开发机构(JAXA)8月31日公开展示了一个新航天探测器。该探测器有望在2014年晚些时候发射升空,执行小行星探测任务,以帮助揭开太阳系中生命起源的神秘面纱。

“隼鸟”-2探测器的研发成本约2.8亿美元,将用于从1999 JU3小行星上收集样本。1999 JU3是一个近球形的小行星,直径约900米,其围绕位于地球和火星之间的轨道运行。


“隼鸟”-2重600千克,尺寸为1.6米X1米X1.25米,与之前的“隼鸟”探测器的尺寸几乎相同。“隼鸟”-2太阳帆展开后,探测器宽6米。“隼鸟”在2010年成为世界上首个从Itokawa小行星采集样本返回地球的探测器。


与Itokawa不同,1999 JU3小行星富含碳元素,这意味着样本中将可能包括原有的水物质和矿物质,可能为寻找生命起源提供线索。“隼鸟”-2将从种子岛航天中心发射,有望在2020年返回地球。(中国航天系统科学与工程研究院 陈菲)


cmj9808 发表于 2014-9-2 22:46 | 显示全部楼层
测试已基本完成,月底启运种子岛
http://www.spaceflightnow.com/ne ... busa2/#.VAXXVmIaySM
月神号特快 发表于 2014-9-30 12:51 | 显示全部楼层

Launch of "Hayabusa2" by H-IIA Launch Vehicle No. 26



September 30, 2014 (JST)

Mitsubishi Heavy Industries, Ltd.
Japan Aerospace Exploration Agency (JAXA)

Mitsubishi Heavy Industries, Ltd. and the Japan Aerospace Exploration Agency (JAXA) decided to launch the H-IIA Launch Vehicle No. 26 (H-IIA F26) with the Asteroid Explorer "Hayabusa2" onboard in the following schedule.
To capitalize on the excess launch capability of the H-IIA F26, we will also provide launch and orbit injection opportunities for three small secondary payloads (piggyback payloads).

Scheduled date of Launch
November 30 (Sunday), 2014 (Japan Standard Time)
Launch time
1:24:48 p.m. (Japan Standard Time) (*1)
Launch site
Yoshinobu Launch Complex at the Tanegashima Space Center

*1: Launch time will be set for each launch day if the launch is delayed.

http://global.jaxa.jp/press/2014/09/20140930_h2af26.html




 楼主| hkhtg090201 发表于 2014-9-30 18:12 | 显示全部楼层
月神号特快 发表于 2014-9-30 12:51
Launch of "Hayabusa2" by H-IIA Launch Vehicle No. 26



这年头,项目能做到不耽搁,甚至有些提前,可以了,尽管是1号的重复。
wsl2005 发表于 2014-10-22 23:10 | 显示全部楼层
Collaboration Between OSIRIS-REx and Hayabusa-2

山姆大叔也当起学生了!那个视频见本贴25楼!
20141017_jaxa-h2-flight-unit.png

kktt 发表于 2014-11-8 11:54 | 显示全部楼层
[管区水路通報] 十管区2014年633項
北太平洋西部  ロケット打上げ
宇宙航空研究開発機構種子島宇宙センター(30-24-04N 130-58-39E)において、
H-?Aロケット26号機の海上警戒及び打上げが、下記のとおり実施される。
 海上警戒期間  平成26年11月30日(予備日12月1日〜9日)、0855〜1355
 海上警戒区域  8地点を結ぶ線及び陸岸で囲まれる区域
      (1) 30-25-40N 130-58-22E(岸線上)
(2) 30-26-48N 130-59-53E
(3) 30-33-54N 131-03-45E
(4) 30-33-54N 131-29-25E
(5) 30-15-00N 131-29-25E
(6) 30-15-00N 130-57-49E
(7) 30-21-57N 130-57-49E
(8) 30-22-23N 130-57-40E(岸線上)
 落 下 物     固体ロケットブースタ、衛星フェアリング
 海面落下予想期間  平成26年11月30日(予備日12月1日〜9日)、1330〜1351
 海面落下予想区域1 固体ロケットブースター
           5地点で囲まれる区域
  (9) 30-11-26N 132-59-44E
(10) 30-12-41N 133-01-33E
(11) 30-01-00N 133-56-00E
(12) 29-38-00N 133-52-00E
(13) 29-50-00N 132-56-00E
2 衛星フェアリング
4地点により囲まれる区域
  (14) 29-08-00N 137-42-00E
    (15) 29-57-00N 137-50-00E
    (16) 29-30-00N 140-34-00E
    (17) 28-41-00N 140-26-00E
 海 図  W1221−JP1221−W1001
 出 所  宇宙航空研究開発機構
cmj9808 发表于 2014-11-13 13:19 | 显示全部楼层
德国宇航局的着陆器MASCOT安装完毕,准备合罩 BlickMascot2_630.jpg


BlickMascot5_630.jpg


BlickMascot6_630.jpg


http://www.dlr.de/blogs/en/deskt ... 023/11643_read-775/
wsl2005 发表于 2014-11-22 20:37 | 显示全部楼层
假定太阳不动,那么隼鸟-2号从发射到返回的空间里程大约是52.4亿公里。
hayabusa2_faq_01.gif

而事实上,太阳以220公里/秒的速度围绕银河系中心运转,所以空间的距离概念其实没有太大实际意义。
wsl2005 发表于 2014-11-22 21:21 | 显示全部楼层
wsl2005 发表于 2014-11-22 21:56 | 显示全部楼层
本帖最后由 wsl2005 于 2014-11-22 22:09 编辑

“隼鸟-2号”运抵种子岛发射场岛内运输视频
http://www.56.com/u34/v_MTMwMjUxNTUx.html

“隼鸟-2号”公开展示视频
http://jda.jaxa.jp/result_strm.php?lang=e&id=d6c47b9a7fe16aa1e62615176a1c4918

“隼鸟-2号”任务详解视频
http://baidu.ku6.com/watch/04920626350394416756.html?page=videoMultiNeed

HaleBoppComet 发表于 2014-11-22 23:29 | 显示全部楼层
感觉受制于核电源RTG的利用 日欧深空项目只能做内太阳系的 外太阳系想做也做不了 只能中美俄了
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wsl2005 发表于 2014-11-23 10:44 | 显示全部楼层
本帖最后由 wsl2005 于 2014-11-23 11:45 编辑

JAXA把计划12月发射的隼鸟-2号任务提前到11月30日,这是对ESA一再推迟“科隆博任务”的无声抗议,,

h2_副本.jpg
wsl2005 发表于 2014-11-23 12:30 | 显示全部楼层
2014年1月19日拍摄的发射场:
TNSC.jpg

4.jpg

5.jpg


wsl2005 发表于 2014-11-23 14:45 来自航空航天港手机版! | 显示全部楼层
本帖最后由 wsl2005 于 2014-11-23 16:07 编辑
cmj9808 发表于 2014-11-13 13:19
德国宇航局的着陆器MASCOT安装完毕,准备合罩




这个MASCOT着陆器可不能只说是德国人的,否则cnes要找您算账,,,
MASCOT_landed_2.jpg

MSC_EQM_attached_to_HY2.png


wsl2005 发表于 2014-11-23 15:55 | 显示全部楼层
wsl2005 发表于 2014-11-23 14:45
这个MASCOT着陆器可不能只说是德国人的,否则cnes要找您算账,,,

DLR和CNES合作开发的MASCOT着陆器在小行星上只能依靠自身携带的电池工作约12小时,能够爬3个点,这让我想到了罗塞塔-菲莱着陆器,接触67P/C-G彗星也是3个点啊,,,
MASCOT携带的仪器如下:
To meet its scientific objectives, the lander MASCOT has 4 scientific instruments:
  • MicrOmega, a hyperspectral infrared microscope for in situ mineralogical analyses of the ground, developed by IAS (Institut d'Astrophysique Spatiale).
  • CAM, a multispectral wide field camera to provide geological images of the visited sites, developed by DLR (Berlin) (German Space Agency).
  • MAG, a magnetometer, developed by Braunschweig Technology University.
  • MARA, a radiometer to determine the surface temperature and the thermal inertia of the asteroid, developed by DLR (Berlin) (German Space Agency).
MicrOmega is MASCOT main instrument.
StdNormDist 发表于 2014-11-23 17:11 | 显示全部楼层
wsl2005 发表于 2014-11-23 12:30
2014年1月19日拍摄的发射场:

同样是两个发射工位,比文昌秀气多了
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