orbit determination of interplanetary kite-craft .... sho ta… · 03/11/2016 · 1 orbit...

1

Orbit Determination of Interplanetary Kite-craft Accelerated

by Radiation of the Sun (IKAROS)

By Sho TANIGUCHI1)

, Takafumi OHNISHI1), Osamu MORI2)

, Hideki KATO2), Yuya MIMASU2), Naoko OGAWA2), Atsushi

TOMIKI2), Hiroshi TAKEUCHI2), Tsutomu ICHIKAWA2), Makoto YOSHIKAWA2) and Shota KIKUCHI3)

1)Science Solutions Division, Fujitsu limited, Tokyo, Japan 2)The Institute of Space and Astronautical Science, JAXA, Sagamihara, Japan

3)Department of Aeronautics and Astronautics, The University of Tokyo, Tokyo, Japan

Abstract

The IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun) was launched along with the Venus

Climate Orbiter Akatsuki in May 2010. IKAROS was successful missions that have been planned for first half year. This

phase has been able to operate a stable orbit determination. And we acquired the skills to consider polarization bias and to

eliminate spin modulation. Those were required for orbit determination of the spin solar sail.

After the Venus flyby in Dec 2010, it was carried out an extended mission. IKAROS has achieved a variety of results in

the extended mission. In orbit determination in low spin rate it was necessary to correspond to changes in spin rate in orbit

determination arc.

IKAROS was performed a reverse spin operation in order to solve the problem of spin rate uncontrolled by the fuel

depletion in Oct 2011. After this operation IKAROS began to repeat the hibernation of the 10-month period by

substantially fixed attitude in inertial coordinate while maintaining the spin rate between 5rpm and 6rpm without fuel. After

wake up from hibernation, it is necessary to difficult orbit determination for 10 months or more the long-term trajectory

prediction. In order to perform the orbit determination of long-term arc to construct an optical model of the solar sail back

surface. And we study to estimate the uncertainty orbit determination error.

In this paper, we present orbit determination in each phase of the IKAROS.

Key Words: IKAROS, orbit determination, predict, Solar Sail.

1. Introduction

The world’s first solar sail IKAROS was launched along

with the Venus Climate Orbiter Akatsuki. The dual launch to

deep space was first experience in JAXA (Japan Aerospace

Exploration Agency). The sub spacecraft and piggyback

spacecraft have restriction of antenna station resources.

Resources of antennas for deep space are not enough for

initial orbit determination more than one spacecraft in parallel.

Therefore IKAROS’s antennas predictions are using an

Akatsuki’s orbit determination result which was made by

sufficient tracking station resources1)

.

IKAROS achieved various success of experiment in the

nominal operation phases as shown in Figure 3.1. In this phase,

the spin rate of IKAROS was maintained between 1.2 rpm to

2.5 rpm using spin up thruster. In this stage, we were able to

make a stable orbit determination.

In the extension phase, IKAROS implemented low spin rate

operation, large angle attitude control, and reverse spin

operation. In low spin rate operation, it was maintained from

0.2 rpm to 0.5 rpm. In this phase, the spin rate significantly

decreased in an orbit determination arc and the orbit

determination was more difficult than in the previous phase.

After reverse spin operation, rotational torque around the

spin axis due to solar radiation pressure increases the spin rate,

the attitude motion shifts from sun orientation to inertia

orientation, and eventually it went into hibernation in January

2012. We are still maintaining operation of IKAROS repeating

the power generation period and hibernation period cycle for 10

months. Even though we cannot be obtained enough observation

data, it has been determined orbit with a long-term propagation

over several years for the search operation after the woke up

from hibernation.

2. Overview of IKAROS

IKAROS is constructed to maintain the shape of a huge 14

m x 14m square by spinning, and the square of the

quadrilateral have a mass attached. Spin rate and attitude are

controlled through the tether by thruster of the main body in

the center. An outline of IKAROS is shown in Fig 2.1.

☆展開した衛星の断面積は183.93m2 約14m×14m

の正方形

☆衛星本体は直径1.6m×高さ0.8mの円筒形、全部の重さは310kg

深宇宙初のソーラ・セイル宇宙機The world's first solar sail spacecraft in the deep space.

☆The cross-sectional area of expanded spacecraft is 183.93m2

The shape is square about 14m×14m ☆Cylindrical spacecraft body is diameter 1.6m ×height 0.8m,the total weight is about 310kg

Fig 2.1 IKAROS’s Overview.

2

As a characteristic of IKAROS, rotational torque called the

wind turbine effect occurred due to unbalance of solar

radiation pressure caused by unevenness of the large film.

Since this torque worked in the direction of gradually

decreasing the spin, regular operation period from launch to

Venus swing-by had to spin up by thruster periodically.

It was possible to maintain spin rate without consuming fuel

due to changing direction of spin rate and rotational torque by

solar radiation pressure after reverse spin operation carried

out.

The acceleration due to solar radiation pressure is about 100

m / sec in a half year. In search operation after wake up from

hibernation, it was necessary that a long-term prediction

orbital trajectory more than 10 months which considering the

solar radiation pressure. For that purpose, we are constructing

an attitude dynamics model 3)

to predict attitude in the future,

making it possible to create a future trajectory over several

years.

Fig3.1 Conceptual diagram of solar radiation pressure model

of IKAROS

3. Orbit determination for nominal phase.

In the nominal phase, it was necessary to remove the spin

rate modulation and perform orbit determination. There was a

polarization bias due to the spin rate and it was necessary to

consider it in the orbit determination.

The equation of Doppler bias due to polarization is shown

in (1).

𝑓𝑏𝑖𝑎𝑠 = 𝐶 (1

𝑓𝑇+

1

𝑓𝑅)𝜔 (1)

Table 3.1 shows the definition of variables.

Table 3.1 Doppler bias due to polarization

C: Speed of light(m/sec)

fT: transmit frequency(Hz)

fR: Receive frequency(Hz)

ω: Spin rate(round/sec)

fbias: Doppler bias due to polarization(m/sec)

The solar radiation pressure model used is shown in Table

3.2. A huge thin film of solar sail is thought to emit absorbed

sunlight with almost no time delay. Therefore, a model

considering the thermal radiation was needed. Fig 3.2 shows a

conceptual view of the model considering the thermal

radiation.

The solar radiation pressure acceleration for a plane

perpendicular to the spin axis Zs is given as follows (2).

(2)

Sun

　　Γ Spin axis

Unit Vector Ｄ

θ　　　A（absorption）

Unbalanced component of radiationBack side A×（Back F-Face F）

Face side　　　（２Γ COS(θ ）＋２／３ D）×COS(θ ）

（２Γ COS(θ ）＋２／３ D）×SIN(θ ）　１－Γ －Ｔ＝Ａ＋Ｄ

　Adsorption of diffusion　　　　Adsorption of absorption

2/3 A（F2-F1)×SIN(θ ）　　　　　　　Unbalanced component of radiation

２Γ COS(θ ）＋２／３ DSpecular reflection and diffuse reflection

rrFFAD

rFFAD

rm

S

c

RS

ss

sss

s

srp

rrz

rr

s

cos3

2

3

2cos2

cos)(3

2

3

2cos2cos1

1

12

2

122

2

00

1st Hibernation Fitr （2012/9/6）

2nd Hibernation Fitr

（2013/6/20）

3rd Hibernation Fitr

（2014/5/22）

6th Hibernation Fiter Earth Flyby

（2016/11～12 plan）

5th Hibernation Fiter（2016/1～2 plan）

4th Hibernation Fitr （2015/4/16）

Hibernation mode

Inertial motion

Launch

(2010/5/21)

Reverse spin operation

Membrane deployment

Power generation by thin film solar cells

Minimum success (in several weeks)

Full success (in six months)

Extra success (after flyby)

flyby Venus (2010/12/8)

Demonstration of photon propulsion by solar sail.

Demonstration of guidance,navigation and control by solar sail.

Fig 3.1 Mission sequence.

3

The definition of the solar radiation pressure model is shown

in Table 3.2.

Table 3.2 IKAROS solar radiation presser model.

The estimated value of the solar radiation model was

gradually changing in nominal phase.

4. Orbit determination for extended phase.

In extended operation, we mainly operated with low spin

rate. We conducted a number of experiments, such as

operation and guidance control where the attitude of the spin

axis was largely changed. In anticipation of depletion of fuel,

reverse spin operation was carried out to stabilize the spin rate

without fuel. As a result, the spin rate gradually increased

without fuel and the moment of inertia increased gradually, so

the attitude changed from solar tracking to inertial fixation. In

the end, IKAROS could not maintain the power and

hibernated.

In this phase, the spin rate/rate in the trajectory determination

arc became large and spin modulation could not be removed

with fixed parameters. In addition, the quality of tracking data

worsened as the distance to the earth gradually increased. The

uncertainty of attitude by low spin rate has also appeared. The

accuracy of orbit determination worsened than the previous

phase.

Therefore we have constructed a system that simultaneously

performs attitude motion and orbit determination. We were

able to achieve highly accurate orbit determination.

5. Orbit determination for Long-term prediction and

search operation.

IKAROS hibernated because the spin rate increased and the

inertial directivity increased. After that, the search operation

became necessary.

The problem of this phase was the long-term orbit prediction,

highly reliable trajectory determination and prediction of

attitude motion model was necessary. The initial attitude

motion model was roughly classified into three models3)

. As a

result, it was discovered using a model with strong inertial

orientation.

5.1 First search operation.

In the first recapture, the radiation pressure parameter 2)

on

the back side was also studied, and the orbital error was

propagated after considering the thermal radiation model from

the large film. The area of error by the orbit determination was

estimated to be about 2 to 3 times (3σ) of the half beam-width

of USUDA deep space station, but it took several months to

receive signal from IKAROS. This is due to the uncertainty of

the orbit determination error as well as the uncertainty of the

attitude transition when the sunlight shining the back side

while long-term prediction. As a result, we succeeded in

receiving signal from IKAROS, searching using an attitude

dynamics model that maintains the inertia attitude even if

sunlight shining the back side. The search area of the forecast

value including the uncertainty of the attitude transition model

was about 10 times the Usuda antenna half width of capture

range. After in the first search operation, we were obtain one

nominal Doppler data and three Doppler data created by post

processing of data acquired from Open Loop receiver. Totally

four Doppler data and AZ EL data when it was successfully

received signals were newly added for observation data.

Since this AZ and EL data were obtained by performing

offset operation while observing the sensitivity by human eyes

in program tracking. It is guaranteed that the actual IKAROS

trajectory is an error on the order of half beam-width of Usuda,

but actual observation does not guarantee passing through the

middle of the data. For this reason, it is difficult to evaluate

because even if the O-C residual becomes flat, the result is not

necessarily correct.

5.2 Second search operation.

In the second search operation, we had predicted that the

search area due to propagation 3 sigma errors were about 10

times the half beam-width of Usuda, but it was able to be

found in the initial search operation. In addition to being able

to search about 2 to 3 times the half beam-width at maximum

by the time offset if it is an error in the direction of spacecraft

progression. In addition to the fact that the motion model itself

of the attitude was unclear in the first search operation. It can

be said that narrowing of the comprehensive search area

became a factor in the initial success because it was able to

predict the parameter of attitude dynamics model using

observation data of solar angle and spin rate earth angle in the

first search operation. In this operation, 7 Doppler data created

by post processing from Open Loop receiver and AZ EL data

when it was receiving signals were added as observation data.

5.3 Third search operation.

In the third search operation, the first search was conducted

on April 22, 2014 and succeeded in the third search. We

succeeded in searching using forecast values improved on the

back and surface optical parameters by observation data

acquired in 2012 and 2013. In the search operation of 2014,

the assumption of the search area spreads to about 30 times

(3σ) of Usuda's half beam width, as compared with the search

operation in the last time in 2013. Fig 5.1 shows the transition

of the assumed error ellipse 3σ of the search operation from

the first search operation to the third. Although the axes are

Right Accession (RA) and Declination (DEC), the scale in the

Dec direction is enlarged twice the RA direction.

S0: Solar constant (= 1.35 × 103 [W/m 2])

R0: 1A.U.(=1.4959787×108[km])

c: Speed of light ms: S / C mass S: Area of the plane

Γ: Reflection coefficient D: Diffusion coefficient T: Transmittance r: S / C position vector of the sun center zs: Unit vector in the inertial space of the S / C spin axis

θs Solar orientation angle (cos θ s = (- r / r) ・ Z s)

A Absorption rate A =1 - D - Γ - T: T = 0

F1 The emissivity ratio of the surface

F2 Emissivity ratio on the back side

4

The offset value add to the nominal antenna prediction is

expressed as an error ellipse in Fig 5.1. The inclination of the

principal axis of the error ellipse changes because the speed

direction at that time was tilted with respect to the equatorial

plane. The error ellipse is enlarging. In the fourth search

operation, the distribution of search area in each orbit

determination case and the variance of the error ellipse due to

the error covariance did not coincide. In the fourth search

operation, the distribution of the search area in each orbit

determination case and the variance of the error ellipse due to

the error covariance did not coincide. For orbit propagation

from November 2011 to June 2014 in order to prepare forecast

values, some new attempts such as shifting the initial value to

2012 and binding the initial covariance were carried out.

In addition, in the third search operation after hibernation,

not only the conventional time offset search but also the offset

search in the RA DEC direction converting to the AZ EL

offset using the instantaneous azimuth / latitude gradient by

the predicted value was also performed.

5.4 Fourth search operation.

The fourth search operation started searching on March 5,

2015 and spent a period of one and a half months until

discovery. We have succeeded in searching by applying a new

search method 4)

such as post-processing analysis using 1-way

data with open loop receiver. The ID’s 0100 to 0130 shown in

Fig. 5.2 are the ID’s of the antenna predict values actually

used in operation. It is possible to conduct 2 to 3 search areas

with about 6 hours of operation. Perform time offsets of

several cases per one search area.

Instead of the offset search for the time, the offsets of RA

and DEC were used as the search area. We searched for RA

DEC offset search area by converting it into AZ EL offset

search area for antenna prediction. We went searching while

updating candidates of forecast values to nominal 0100 at 3/5,

0110 at 3/19, 0120 at 4/2, 0130 at 4/16.

On 9th and 16th April, we changed to 1Way data extensive

search method and searched RA offset values from -0.180 deg.

to 0.06 deg. and DEC offset values from -0.006 deg. to 0.165

deg. at 0.03 deg. step. This rhombus shape area roughly

including all forecast values by orbit determination. On

April 23, we were exploring the area where IKAROS

subcarriers could be confirmed from the result of 1 Way

searching on 9th and 16th April, and successfully confirmed

Fig 5.2 Distribution of antenna predictions in each orbit determination results.

03-04d

03-12g

03-17-2

03-17-3

03-17-5

03-17-7

03-17-8

03-17-11

03-04dL104-02-1 04-02-8

04-02-10

04-21i add DP2

04-27e

04-27f 03-04a

16.40

16.60

16.80

71.78 71.98 72.18 72.38

EL(d

eg)

AZ(ｄｅｇ)

Distribution of Antenna prediction in each orbit determination results at 2015/4/9 00:00:00 for IKAROS

03-04b 03-04c

03-04d 03-04e

03-04f 03-04g

03-05h 03-05i

03-12a 03-12b

03-12c 03-12d

03-12e 03-12f

03-12g 03-12h

03-12i 03-17-1

03-17-2 03-17-3

03-17-4 03-17-5

03-17-6 03-17-7

03-17-8 03-17-9

03-17-10 03-17-11

03-17-12 03-04aL1

03-04dL1 03-17-2L1

04-02-1 04-02-2

04-02-3 04-02-4

04-02-5 04-02-6

04-02-7 04-02-8

04-02-9 04-02-10

04-02-11 04-02-12

04-15-4 04-15-5

04-02-6 04-15-7

04-15-8 04-15-9

04-21i add DP2 04-27a

04-27c 04-27e

04-27f 05-01a

03-04a

4/4 ID 0110

4/4 ID 0120

3/18 ID 0110

4/4 ID 01004/16 ID 0130

Ellipse radius is 0.02deg

-4.00E-03

-2.00E-03

0.00E+00

2.00E-03

4.00E-03

6.00E-03

8.00E-03

1.00E-02

1.20E-02

0 1,000 2,000 3,000 4,000 5,000 6,000

O-C

(km

/se

c)

Time

IKAROS LONG TERM 03-17-5 DP2 O-C(km/sec)

IKAROS USUDA XX DP2( KM/S)

-4.00E-03

-3.00E-03

-2.00E-03

-1.00E-03

0.00E+00

1.00E-03

2.00E-03

3.00E-03

4.00E-03

5.00E-03

0 1,000 2,000 3,000 4,000 5,000 6,000

O-C

(km

/se

c)

Time



-3.00E-04

-2.00E-04

-1.00E-04

0.00E+00

1.00E-04

2.00E-04

3.00E-04

4.00E-04

5.00E-04

6.00E-04

7.00E-04

0 1000 2000 3000 4000 5000 6000

O-C

(km

/se

c)

Time

IKAROS LONG TERM 03-04a DP2 O-C(km/sec)


-5.00E-04

0.00E+00

5.00E-04

1.00E-03

1.50E-03

2.00E-03

2.50E-03

0 1000 2000 3000 4000 5000 6000

O-C

(km

/se

c)

Time



-3.00E-04

-2.00E-04

-1.00E-04

0.00E+00

1.00E-04

2.00E-04

3.00E-04

4.00E-04

5.00E-04

6.00E-04

7.00E-04

0 1000 2000 3000 4000 5000 6000

O-C

(km

/sec

)

Time


IKAROS USUDA XX( HZ)

-3.00E-04

-2.00E-04

-1.00E-04

0.00E+00

1.00E-04

2.00E-04

3.00E-04

4.00E-04

5.00E-04

6.00E-04

7.00E-04

0 1000 2000 3000 4000 5000 6000

O-C

(km

/se

c)

Time

IKAROS LONG TERM 03-03d DP2 O-C(km/sec)


-2.50E-03

-2.00E-03

-1.50E-03

-1.00E-03

-5.00E-04

0.00E+00

5.00E-04

1.00E-03

1.50E-03

2.00E-03

2.50E-03

3.00E-03

0 1000 2000 3000 4000 5000 6000

O-C

(km

/se

c)

Time



-0.15

0

0.15

-0.60 -0.45 -0.30 -0.15 0.00 0.15 0.30 0.45 0.60

De

c(d

eg)

Ra(deg)

Error ellipse from Earth Center 3σ

1st Hibernation Fiter 3σ 2nd Hibernation Fiter 3σ 3th Hibernation Fiter 3σ

Fig 5.1 1st～3rd Error Ellipse from Earth Center

5

the 2Way carrier lock on the signal form a spacecraft. The

carrier position found by 1 Way wide area search was found at

the position offset to RA - 0.015 deg. DEC - 0.022 deg. with

respect to nominal ID 0130 (04-02-10).

From the third search to the fourth search, it is difficult to

match the dynamic model to the whole of orbit determination

arc by long-term propagation, and it became not possible to

determine the best orbit determination result from the O-C's

residual shape. And, the tendency of the error ellipse by the

covariance analysis was not appropriate. Therefore, the

dispersion of search area was calculated by assigning the

estimated parameters using ordinary orbit determination

knowledge.

Fig. 5.2 shows the distribution of forecast values at 00:00:00

on April 9, corresponding to each orbit determination case.

The O-C graph in Fig. 5.2 is the residual of Doppler in 2012

and 2013, which is a representative case O-C arranged in data

order instead of time. It can be understood that the case of

3-17-5, 03-17-11, 03-17-8 where the RMS of the O - C

extends to several m/sec are out of the distribution of the

whole. Even if the O - C residual is several m / sec, there are

cases like case 03-17-02 which is almost in the center of

distribution. The case of 03-07-02 seems to be consistent

azimuth direction because there is flat in Doppler residual an

arc in a day. But a predict position of orbit determination case

which has a large residual of Doppler is largely moving from

the relative predicts position of the whole when the evaluation

time changes.

5.5 Fifth search operation.

In the 5th search operation, a program was created so that a

search in a wide range can be automatically carried out by

adding an offset of the search area planned in advance to the

antenna prediction value. It is possible to detect weak received

data by FFT analyzing the received frequency data at offline.

The 5th search is very close in terms of distance but

IKAROS's transmitting and receiving antennas are facing the

back side and could not be found. Perhaps it seems that radio

waves were weaker than assumed, or it was hibernating rather

than being as expected. The search area is shown in Figure 5.3.

It was searched that about 1.5 deg. x 0.5 deg. range.

5.6 Sixth search operation.

In the sixth search operation, the range data was created

pseudo by using at the timing when the frequency sweep

ended. It was possible to create one point pseudo range data

for each period at 2013 and 2015. It was formulating spin

modulation and statistically processing, we were able to

reduce the error of each data to 8000 km and 1000 km

respectively. As a result of orbital determination while

assigning parameters using these data, the search area could

be reduced as shown in Fig 5.3. In January 2016, the search

area when sweep timing pseudo range data is used is indicated

by red solid line. The search area when sweep timing pseudo

range data is not used is indicated by a pink dashed line.

In the sixth search, it can be considered that the transmitting /

receiving antenna is facing the earth, so it is an assumption

that stronger radio waves can be received than the fifth search.

For this reason, it is possible to search an area wider than the

5th search area. Fig. 5.5 shows the search area up to the

present. I expect it to analyze offline, but it has not been

discovered as of December 2016. It seems that the spin torque

force is reversed from the observed spin rate data. Therefore,

we plan to restructure the spin torque motion model.

Fig.5.5 Search area by Usuda deep space station for 3 days

6. Summary.

Search operation of IKAROS due to hibernation has been

successful as a result of trial and error in the past 4 times. In

01-24 CASE11

01-24 CASE12

u64.IKAROS_2016_CASE14




u64.IKAROS.160122d_new_RA2_rev16

14.4

14.6

14.8

15

15.2

15.4

15.6

15.8

16

106 106.2 106.4 106.6 106.8 107 107.2

EL(d

eg)

AZ(deg)

Azimuth and elevation by predicted trajectory of each orbit determination result at 2016/1/24 01:00:23 (distance form Earth 70,000,000km)

Search range reduction efect by sweep timeing range data

- - Search range not using sweep range data

━ Search range using sweep range data

Fig 5.4 Search area for IKAROS in 2016/1/24

-0.60

-0.50

-0.40

-0.30

-0.20

-0.10

0.00

0.10

0.20

0.30

0.40

0.50

0.60

-1.0 -0.9 -0.8 -0.7 -0.6 -0.5 -0.4 -0.3 -0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5

De

c(d

ec)

Ra(dec)

RA,DEC Offset Search Range For Auto Search CASE 160122d Ra Dec Offset(dec)

01-24 CASE7

01-24 CASE8

01-24 CASE9

01-24 CASE10

01-24 CASE11

01-24 CASE12

01-24 CASE7 RER

01-24 CASE RER BIAS

01-24 CASE13

01-24 CASE160122b

01-24 CASE13 RER

01-24 CASE13 BIAS

01-24 CASE160122c

01-24 CASE160122d

01-24 CASE160122e

01-24 CASE160122f

01-24 CASE 160122g

01-24 CASE12 RA

01-24 CASE160122h

Search at 1/24

Search at 1/25

Search at 1/26

Search at 1/27

2/4-

2/5-

Remark point

Fig. 5.3 RA DEC Offset Search Area



-1.2

-1.0

-0.8

-0.6

-0.4

-0.2

0.0

0.2

0.4

0.6

-0.8 -0.6 -0.4 -0.2 0.0 0.2 0.4 0.6

DEC

(de

g)

RA(deg)

RA DEC offset search area by Orbit Determination results in 2016/11/03 20:00:30u64.IKAROS.160122d_new_RA2_rev10































11/7（UT）Search Area



6

the fifth time, there was a possibility of receiving signal but

we could not catch the signal from the IKAROS's antenna.

In the sixth search operation, automatic offset program

makes search area larger, offline FFT analysis made it

possible to pick up weak signal. Pseudo-created range greatly

reduced search area. As these results, the search area is

considered to be no problem. We think that it is necessary to

extend the attitude motion model. It is the spin motion model

changes possible to deal with all direction from handling the

angle around the sun orientation. As a result, it will be

possible to predict a more precise period of wake up from

hibernation.

7. Conclusion

IKAROS's orbit determination requires technical elements

that are not ordinary operation such as construction of attitude

motion model and long - term prediction due to hibernation.

These technical elements to be useful in next solar power sail

spacecraft.

References

1) Sho Taniguchi, Takafumi Ohnishi, Hiroshi Takeuchi,

Yuichi Tsuda, Tsutomu Ichikawa, Takaji Kato, Hiroshi

Takeuchi, Makoto Yoshikawa, Application to Hayabusa2

initial acquisition of IKAROS initial acquisition results,

JAXA Astrodynamics and Flight Mechanics,( 2014). 2) Sho Taniguchi, Takafumi Ohnishi, Yuya Mimasu, Yuji

Shirasawa, Katsuhide Yonekura, Mori Osamu, Hiroshi

Takeuchi, Tsutomu Ichikawa, and Makoto Yoshikawa,

Orbit Determination and Evaluation of Prediction Error to

Acquire IKAROS, 57th Space Science and Technology

Conference. (2013).

3) Yuya Mimasu, Sho Taniguchi, Hiroshi Takeuchi, Yuji

Shirasawa, Katsuhide Yonekura, Osamu Mori, Ryu Funase,

Yuichi Tsuda, Attitude and Orbit Prediction of Solar Power

Sail Demonstrator IKAROS, 30th Induction Control

Symposium Presentation Papers, (2013) 4) Shota Kikuchi, Hiroshi Takeuchi, Osamu Mori, Yuya

Mimasu, Yoji Shirasawa, Hideki Kato, Naoko Ogawa and

Sho taniguchi, Progress of Search Operation for IKAROS

by means of Open-loop Tracking Data, 30th International

Symposium on Space Technology and Science, (2015).

orbit determination of interplanetary kite-craft .... sho ta… · 03/11/2016 · 1 orbit...

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