Epsilon

Launch Vehicle

User’s Manual✓ Single launch✓ Rideshare
July 2018
Revision A

Epsilon User’s Manual

PrefaceThis document is prepared to provide customers with technical information on the Epsilon Launch
Vehicle, its launch services including optional ones, and related facilities and equipment for the purposeof customers’ planning.

-2-

Epsilon User’s Manual

Configuration control sheet
Date

Revision number

Change Description

February, 2016

First Edition

NC

July, 2018

Second Edition- Addition of multiple payload launch function- Amendment to interface information on PL-3-

Epsilon User’s ManualContents

1.

Introduction .................................................................................................................................. - 8 1.1. Purpose of the User’s Manual ................................................................................................ - 8 1.2. Epsilon LV Outline .................................................................................................................. - 8 1.3. Epsilon Technology Heritage and Enhancement .................................................................... - 9 1.4. History of Epsilon LV .............................................................................................................- 11 1.5. Mission Management ........................................................................................................... - 12 2. Vehicle Overview ........................................................................................................................ - 13 2.1. Epsilon LV General Data ...................................................................................................... - 13 2.2. Coordinate System .............................................................................................................. - 19 3. General Performance Information .............................................................................................. - 21 3.1. Introduction .......................................................................................................................... - 21 3.2. Definition of Launch Capability ............................................................................................. - 21 3.3. Typical Mission Profile.......................................................................................................... - 21 3.4. Launch Capability ................................................................................................................ - 28 3.5. Injection Accuracy ................................................................................................................ - 30 3.6. Mission Duration .................................................................................................................. - 31 3.7. Launch Window ................................................................................................................... - 31 3.8. Separation Conditions .......................................................................................................... - 32 3.8.1. PL Separation Condition Outline ................................................................................... - 32 3.8.2. Altitude Control in PL Separation ................................................................................... - 32 4. PL Accommodation .................................................................................................................... - 35 4.1. PL Fairing (PLF)................................................................................................................... - 35 4.1.1. PL Usable Volume ........................................................................................................ - 35 4.1.2. Access Door / Radio Frequency (RF) Windows............................................................. - 37 4.2. PL Requirements ................................................................................................................. - 40 4.2.1. PL Mass ........................................................................................................................ - 40 4.2.2. Static Unbalance ........................................................................................................... - 41 4.2.3. Stiffness of PL ............................................................................................................... - 44 4.3. Mechanical Interfaces .......................................................................................................... - 45 4.4. Electrical Interfaces.............................................................................................................. - 46 4.4.1. Separation Connector / Umbilical Connector ................................................................. - 46 4.4.2. Electrical Functions for PL ............................................................................................. - 46 4.4.3. Telemetry Transmission and Power Supply to PL .......................................................... - 47 4.4.4. PL Battery Life ............................................................................................................... - 47 4.4.5. Separation Switches...................................................................................................... - 47 4.4.6. Bonding ......................................................................................................................... - 48 4.4.7. Electromagnetic Environment........................................................................................ - 49 4.4.8. Communication Link to PL............................................................................................. - 52 4.5. PL Environment ................................................................................................................... - 53 -4-

Epsilon User’s Manual

4.5.1. Mechanical Environment ............................................................................................... - 53 4.5.2. Temperature and Humidity Environment........................................................................ - 62 4.5.3. Cleanliness Environment ............................................................................................... - 68 4.6. PL Compatibility Verification Requirements .......................................................................... - 69 4.6.1. Verification Logic ........................................................................................................... - 69 4.6.2. Safety Factor ................................................................................................................. - 70 5. Uchinoura Space Center ............................................................................................................ - 71 5.1. General Overview ................................................................................................................ - 71 5.1.1. Introduction ................................................................................................................... - 71 5.1.2. PL Arrival ....................................................................................................................... - 74 5.1.3. PL Preparation at USC .................................................................................................. - 76 5.1.4. Facilities for Launch Operation ...................................................................................... - 81 5.2. General Characteristics of Facilities ..................................................................................... - 83 5.2.1. Climate Conditions ........................................................................................................ - 83 5.2.2. Power Supply ................................................................................................................ - 83 5.2.3. Communication and Data Network ................................................................................ - 84 5.2.4. Transportation and Handling ......................................................................................... - 85 5.2.5. Fluids and Gases .......................................................................................................... - 86 5.3. Operation Policy................................................................................................................... - 87 5.3.1. Site Security .................................................................................................................. - 87 5.3.2. Safety ............................................................................................................................ - 87 5.3.3. Support to Customer for PL Team at USC ..................................................................... - 87 6. Mission Management ................................................................................................................. - 88 6.1. Outline of Mission Management ........................................................................................... - 88 6.2. Mission Integration ............................................................................................................... - 91 6.3. System Engineering Support................................................................................................ - 92 6.3.1. Interface Management .................................................................................................. - 92 6.3.2. Mission Modification ...................................................................................................... - 93 6.3.3. Mission Analysis ............................................................................................................ - 94 6.3.4. PL Design Compatibility Verification .............................................................................. - 95 6.3.5. Post-Flight Analysis ....................................................................................................... - 96 6.4. Launch Campaign ................................................................................................................ - 97 6.4.1. Launch Campaign Organization .................................................................................... - 97 6.4.2. PL Pre-Launch Activities................................................................................................ - 98 6.5. Safety Assurance ................................................................................................................ - 111 --5-

Epsilon User’s Manual

Glossary
ACS: Attitude Control SystemAT: Acceptance Test

CB

: Clean Booth

CCAM: Collision and Contamination Avoidance Maneuver

C.G.

: Center of Gravity

CLA: Coupled Load Analysis

CR: Clean Room

ECC

: Epsilon Control Center (ECC)

EGSE: Electrical Ground Support Equipment

ESC: Epsilon Support Center (ESC)ESMS: Epsilon Satellite Mounting Structure

E-SSOD: Epsilon Small Satellite Orbital Deployer

FEM: Finite Element ModelFM: Flight Model

FMA: Final Mission Analysis

GSE: Ground Support Equipment

HTPB: Hydroxyl terminated polybutadiene

ICD: Interface Control Document

IRD: Interface Requirement Document

ISAS: Institute of Space and Astronautical ScienceISO: International Organization for Standardization

JAXA: Japan Aerospace eXploration Agency

JEM: Japanese Experiment Module

JOP: Joint Operation Plan

J-SSOD: JEM Small Satellite Orbital Deployer

LEO: Low Earth Orbit

LSP: Launch Service Provider

LV: Launch Vehicle

MLI: Multi Layer Insulation

OIS: Operational Inter-communication System

PAF: Payload Attach Fitting

PBS: Post Boost Stage

PFM: Protoflight ModelPL: PayLoad

PLF: PayLoad Fairing

QT: Qualification Test

RCS

: Reaction Control System

RF: Radio Frequency

S/C: SpaceCraft

SMSJ: Solid Motor Side Jet

SOW: Statement Of Work

SPL

: Sound Pressure Level

SRB: Solid Rocket Booster-6-

Epsilon User’s Manual

SRM: Solid Rocket Motor

SSO: Sun Synchronous Orbit

TNSC: TaNegashima Space Center

TVC: Thrust Vector Control

USC: Uchinoura Space Center-7-

Epsilon User’s Manual

1. Introduction
1.1. Purpose of the User’s ManualThis User’s Manual is intended to provide customers (Customer) with basic information on the Epsilon
Launch Vehicle (LV) and its launch operations at the Uchinoura Space Center (USC).
The contents encompass the followings:
・ The Epsilon Launch Vehicle description;
・ Launch performance and typical mission profiles;
・ LV’s environmental conditions and corresponding requirements for Payload (PL) design andverification;
・ Description of interfaces between PL and LV;・ PL preparation and ground operations performed at USC;
・ Mission Management including a mission integration and support services for Customer.
1.2. Epsilon LV Outline
The Epsilon LV is a next-generation solid propellant rocket, which is developed in a Japanese national
program led by JAXA. After the completion of the development, it has been positioned as a Japanese
flagship LV. It plays a key role in securing Japan’s autonomous capability to launch small satellites forobservation and scientific missions. It can also offer effective launch opportunities to small satellites forcommercial missions.
Epsilon is a highly-reliable vehicle for space transportation fully reflecting Japanese rocket technology
long accumulated through many vehicle programs such as a former M-V and currently operated H-IIA/B
LV (Figure 1-1). Epsilon offers user-friendly launch services with newly incorporated technologies, such as
next-generation ground support / check-out systems, highly accurate orbit injection system, advanced
built-in PL vibration-suppression system, and multi-satellite mounting structure.
Epsilon rocket(2013- ）L rocket（1970）

M-3S rocket(1980-1995)

M-V rocket(1997-2006）

K rocket（1960s）

Pencil rocket(1955)

Figure 1-1 Genealogy up to Epsilon LV-8-

Epsilon User’s Manual

1.3. Epsilon Technology Heritage and Enhancement
Epsilon builds on the heritage of successful M-V and H-IIA/B technologies as shown in Figure 1-2.
Since its first flight (Epsilon-1), Epsilon’s launch capability has been steadily enhanced (Figure 1-3)
and verified by Epsilon-2 and Epsilon-3. From the next flight, Epsilon-4, onward, the LV will have theability of multiple-payload launch (in this document, multiple payload launch is called “multi launch” or“multiple launch”) (Figure 1-4). Epsilon has been evolving in response to users’ demand.

H-IIA has been Japan’s
flagship heavy lifter for morethan 16 years and more than
100 SRBs have been useduntil now.

M-V was the largest solidpropellant rocket in the world.
It was a medium payload liftermainly for scientific payloads
for ISAS with 6 successful
flights.

Payload fairing
M-V 4th stage for Epsilon 3rd stage

Post Boost Stage
Avionics

M-V 3rd stage for Epsilon 2nd stage

Inter-stage separation systems
H-IIA’s Booster for Epsilon 1st stage

Solid Rocket LV Integration Technology

M-V

EpsilonFigure 1-2 Epsilon LV Heritage

-9-

H-IIA

Epsilon User’s Manual

The enlarged 2nd solid motor
The enlarged 2nd solid motor isis exposedfromfairing
exposedfromthethefairing
to to
carry
a
payloadwith
morecarry a spacecraft with moremass
mass andand value.
volume.

Epsilon
1st
Epsilon-1

Epsilon 2nd～
Epsilon-2 and following
flights

Figure 1-3 Epsilon’s Launch Capability Enhancement

The microsatellite separation
Microsatellite separation is byuses
8-inchmade
Lightband®
Lightband®
by PSC madeby
PSC
(Planetary
Systems(Planetary Systems
Corporation) thatwhich
has usehas a
Corporation),results intracka numberof satellite
provenrecordof having
been used for many satellites..
The newly developed CubeSat
deployer
based
Cubesat (E-SSOD)
deployer isisbased
onon
J-SSOD,a using
provendeployer
the deployer
on theinstalled
onSpace
JEMStation.
of theInternational
International Space Station.

Mutisatellites
structureMultisatellitemount
mount structure

CubeSat

J-SSOD

JEM

Figure 1-4

Systems for Multiple Payload Launch- 10 -

Epsilon User’s Manual

1.4. History of Epsilon LV
The Epsilon LV’s launch history is shown in Figure 1-5.

2013

2014

2015

2016

2017

2018

1st

2nd

3rd

4th

SPRINT-A

ERG

ASNARO-2

Commercial

Development：SUCCESS：PLAN

Enhanced capability
Multi-Launch

2013/9/14
1st

2016/12/20
2nd

Figure 1-5

2018/1/18
3rd

Launch History- 11 -

Epsilon User’s Manual

1.5.

Mission Management

Mission Management, together with Safety Supervision, is provided to Customer by Epsilon Launch
Service Provider (LSP). A Program Director is assigned as a single point of contact with Customer.
The Mission Management Scheme is depicted in Figure 1-6.
The details of a standard Mission Management are explained in Chapter 6.

Customer

Launch Service Provider
Program Director
Mission Management
Mission Integration
System Engineering Support

Launch Campaign
Safety Supervision
LV Manufacturing

Figure 1-6

Mission Management- 12 -

Epsilon User’s Manual

2. Vehicle Overview
2.1.

Epsilon LV General Data

Epsilon, a three-stage solid propellant launch vehicle, offers a basic
configuration and an optional configuration with PBS (Post-Boost Stage), which
enhances its orbit injection accuracy. This optional configuration can mountadditional structures on the third stage to provide small satellites with a rideshareoption. Table 2-1 shows the difference between the specifications of these
configurations.
Figure 2-1 shows the exploded view of Epsilon’s configurations with and without
PBS, and Table 2-2 shows Epsilon’s general specifications.

Table 2-1

Difference between specifications of Epsilon’s configurations

DeviceBasic
configuration(Without PBS)

Single Launch

Multi Launch

PAF-937M

1

1

1

Lightband®

-

-

3

CubeSat Deployer （E-SSOD）

-

-

2

Damper

✔

✔

✔

PBS

-

✔

✔

PayloadSeparation
SystemOptional configuration(With PBS)✔: Installed- 13 -

Epsilon User’s Manual

Multi-Satellite
Mount StructureLightband® 8inch
E-SSOD(CubeSat Deployer)

Post Boost Stage
Separation Systems

PAF-937M

3rd Stage SRM(KM-V2c)

Avionics

2nd Stage SRM(M-35)

PLF

1st Stage SRM(SRB-A3)

Separation Systems

Figure 2-1

Epsilon Configurations- 14 -

Epsilon User’s Manual

Table 2-1

Epsilon Specifications
Overall

Length [m]26

Diameter [m]2.6

Total Weight [ton]96Stages
1st stage

2nd stage

3rd stage

PBS*1

PLF

SRB-A3

M-35

KM-V2cLength [m]

11.7

4.3

2.3

1.2

11.1

Diameter [m]

2.6

2.6

1.4

1.5

2.6

Weight [ton]

75.0

17.0

3.3

0.1

1.0

Propellant [ton]

66.3

15.0

2.5

0.1

-

Thrust [kN]

2,271

372

99.8

0.4

-

Burn time [s]

116

140

90

1100

-

Propellant

Solid

Solid

Solid

HTPB

HTPB

HTPB

Isp [s]

284

300

301

Control

TVC

TVC

SMSJ

RCS

(Solid Thruster)(Thruster)Items*1: only for the optional configuration- 15 -

Hydrazine
215

-

Spin

ThrusterEpsilon User’s Manual

Assembling 1st motor(1) First Stage (SRB-A3)
The first stage is a solid propellant motor slightly modified an
H-II A/B’s solid rocket booster SRB-A3. The motor case is madeof filament-wound monolithic composite materials, the same asthat of the second and third stages. The propellant is HTPB
composite, also the same as that of the second and third
stages. The nozzle is gimballed by electromechanical thrust
vector control (TVC) units.
(2) Second Stage (M-35)
The first Epsilon’s second stage motor (M-34c) was developed
based on the third stage of MV Rocket. The motor was thenimproved into the current M-35, whose performance wasdemonstrated by Epsilon-2. M-35 has 1.4 times the propellant
mass of M-34c, increasing Epsilon’s launch capability.

Combustion test of 2nd motor(3) Third Stage (KM-V2c)
The third stage KM-V2c is a partially modified fourth stage of MV(KM-V2).

3rd stage(4) Post Boost Stage (PBS) (option)
The newly developed PBS, based on the monopropellant
reaction control system (RCS) of H-II A/B, enhances orbit
injection accuracy.

PBS- 16 -

Epsilon User’s Manual(5) PL Fairing (PLF)
The PLF employs the proven track record technology of H-II
A/B PLF. It has aluminum-skin, aluminum-honeycomb-sandwich
structure and incorporates the clamshell separation system.
Several access doors and one RF transparent window can beinstalled on the PLF to provide access to a satellite inside after
encapsulation.

PLF(6) Separation Systems
Epsilon has 4 separation systems, each of which has aMarman clamp band and redundant system. It also has Marmanclamp band catchers to prevent a separated band from colliding
with rocket structures or satellites.
While stages are separated by using pyrotechnics, thesatellite is released by a non-pyrotechnic device in order toreduce a shock to the satellite in case of PL (Single Launch) /small satellite (Multi Launch).

Separation test

- 17 -

Epsilon User’s Manual(7) Multi-satellite mount structure
The multi-satellite mount structure, now under development, will
be demonstrated on Epsilon-4. This structure can mount up to 3
Micro satellites with a small satellite being installed atop. Its
separation system uses a proven-record 8-inch Lightband®.

Multi-satellite mount structureLightband® 8-inch size(8) CubeSat deployer (E-SSOD)
Two CubeSat deployers can be bound on the multi-satellite
mount structure and each can accommodate one 3U CubeSat at
most. It uses the time-proven technology of J-SSOD, a deployer
now in operation on the International Space Station.

CubeSat Deployer (E-SSOD)- 18 -

Epsilon User’s Manual

2.2.

Coordinate System

Figure 2-2 shows the coordinate system of LV. The station (STA) at the top of FL in this figure indicatesthe origin of x-axis, values of which increases toward lower stages.
Table 2-3 shows the standard coordinate system of each PL. This coordinate system is used forenvironment conditions and mechanical interfaces in this document.
The details of standard coordinate systems of Micro satellite and CubeSat are shown in the AppendixB and Appendix-C, respectively.

Table 2-3 PL coordinate (standard)
Payloadcoordinate

originFigure 2-2

The center of theseparation plane

Figure 2-3

The center ofthe upper ring
contact surface ofLightband®

Figure 2-3

The geometry centerof the CubeSatshape

PL (Single Launch)
Small satellite (Multi Launch)

Micro satellite (Multi Launch, Lightband®)1U to 3U CubeSat- 19 -

Epsilon User’s ManualRoll(+)

XB
STA
0

270°
(Ⅲ)
0°
(Ⅳ)
(Up range)
Yaw(+)

YB

ZB

90°
(Ⅰ)

180°
(Ⅱ)
(Down range)

Pitch(+)

Figure 2-2 Coordinate system of LV
XB

XB

Ysc

Xsc

CubeSat
Zsc

Micro satellite
Zsc

Xsc
Ysc

XSC,YSC,ZSC：Satellite Axis (standard)

Figure 2-3 Coordinate system of PLs in Multi-Launch (standard)- 20 -

Epsilon User’s Manual

3. General Performance Information
3.1. Introduction
This section provides the information necessary to make preliminary performance assessments of the
Epsilon LV. The following paragraphs present Epsilon’s typical performance, typical injection accuracy,
mission duration, separation conditions and collision avoidance maneuver.
The data provided here cover a wide range of missions for sun-synchronous orbits (SSO), and low
circular or elliptical orbits (LEO), etc.
Performance data presented in this document are for assumed reference missions; therefore, actual
performance will be fully optimized based upon Customer’s specific mission data.

3.2. Definition of Launch Capability
Epsilon launch capability in this section is defined based upon the following conditions:(1) PL lift mass is without Payload Attach Fitting (PAF), and(2) Launch from USC with applicable range safety operations.

3.3. Typical Mission Profile
The typical event sequences are shown as below:
Basic configuration (Without PBS)
: Figure 3-1
Optional configuration (With PBS)
: Figure 3-2
Typical mission profiles are shown as Table 3-1.

Table 3-1 Typical Mission Profiles

SSO
Single Launch
Optional
configuration Multi Launch(With PBS)
LEO
Basic configuration(Without PBS)

Path

AltitudeFigure 3-3

Figure 3-5

Figure 3-4

Figure 3-5 &Figure 3-6

Figure 3-9

Figure 3-10

- 21 -

Velocity

Acceleration

Figure 3-7

Figure 3-8

Figure 3-11

Figure 3-12

Epsilon User’s Manual

Flight safety control period
2ndStage burn out

2nd stage ignition

spin
0.5-1.0Hz

2nd/3rd stage
separation

3rd stage
ignitionSC
PL
separation

3rd stage
burn out

Deorbitation

1st/2nd stage separation

Fairing separation

1st stage burn out

1st stage ignition

Figure 3-1

Event Sequence: Nominal Mission Profile (without PBS)

Flight safety control period
2ndStage burn out★

2nd stage ignition

spin
0.5-1.0Hz

2nd/3rd stage
separation

3rd stage
ignition

3rd stage
burn out

1st/2nd stage separationrd

3 /PBS stage
separation

Despin& maneuver

The SOE up to thispoint is the same assingle PL
S/C launch

Fairing separation

PLSC
separation

st
1PL
SC
separation

1st stage burn out
PBS phase-C(Deorbitation)

Repeat maneuver& PL
SC Separation

Discharging
Propellant
Start

BBQ spin

PBS phase-C(Deorbitation)

Earth
BBQspin1

st

stage ignition★

★
Data downlink

PL Orbit
S/C(Target)1st PLS/C Orbit(Target)Single S/C launch

Figure 3-2

Receiving stationon the ground

Multi-satellites launch

Event Sequence: Nominal Mission Profile (with PBS)

- 22 -

Epsilon User’s Manual

90

60

2nd motor burn out

Geodetic latitude[degN]30

2nd/3rd motor separation
3rd motor ignittion
3rd motor burn out
3rd motor/PBS separation

0

PBS firing(Phase-A)

Payload separation
Spacecraft-30

PBS firing(Phase-B)
Coasting Phase(PBS 3axis control)

-60

-90

0

40

80

120

160

200

240

280

320

360

Geodetic longitude[degE]

Figure 3-3

Nominal ground path for SSO Mission (with PBS, single launch)90
MissionEnd:X+5290s

60

Down-link

Geodetic latitude[degN]30

SC6 separation
PL6
SC5 separation
PL5
SC4 separation
PL4
SC3 separation
PL3
SC2 separation
PL2

2nd motor burn out
2nd/3rd motor separation
3rd motor ignittion
3rd motor burn out
3rd motor/PBS separation

0

PBS firing(Phase-A)

SC1separation
PL1

-30

PBS firing(Phase-B)
Coasting Phase(PBS 3axis control)

-60

-90

0

40

80

120

160

200

240

280

320

Geodetic longitude[degE]

Figure 3-4

Nominal ground path for SSO Mission (with PBS, multi launch)- 23 -

360

Epsilon User’s Manual

1400

1200

1000

Altitude[km]2nd /3rd motor separation
3rd motor ignition

Payload separation
Spacecraft

800
3rd motor burn out
600

3rd motor / PBS separation

400

Coasting Phase(PBS 3 axis control)

PBS firing(Phase-A)

200

PBS firing(Phase-B)

2nd motor burn out
1st /2nd motor separation, 2nd motor ignition
Faring jettison
1st motor burn out

0
0

500

1000

Figure 3-5

1500

2000

2500

Time[s]

3000

3500

4000

4500

5000

Nominal altitude for SSO Mission (with PBS)

520
Apogee, Osculating
515

Perigee，Apogee[km]510

Perigee, Osculating
Apogee, Mean
Perigee, Mean

505

500

495

PL1
SC1 separation

SC2 separation
PL2
PL3
SC3 separation
PL4
SC4 separation

490

PL5
SC5 separation

PL6
SC6 separation

485
CCAM

480

475
3100

3300

3500

3700

3900

4100

Time[s]※Altitude until PL1 separation is the same as Figure 3-5
Figure 3-6

Nominal altitude for SSO Mission (with PBS, multi launch)- 24 -

4300

Epsilon User’s Manual

10000
Payload separation
Spacecraft

PBS firing(Phase-A)

8000

PBS firing(Phase-B)

Coasting Phase(PBS 3 axis control)

Inertial Velocity[m/s]

3rd motor / PBS separation

6000

3rd motor burn out

4000

2nd /3rd motor separation , 3rd motor ignition
2nd motor burn out

2000
1st /2nd motor separation, 2nd motor ignition
Faring jettison
1st motor burn out
0
0

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

Time[s]Figure 3-7

Nominal velocity for SSO mission (with PBS)

8

7

6

1st motor burn out

Acceleration[G]5

1st /2nd motor separation, 2nd motor ignition
2nd motor burn out

43

2nd /3rd motor separation , 3rd motor ignition

3rd motor burn out

2
3rd motor / PBS separation
Payload separation
Spacecraft

1
PBS firing(Phase-B)
PBS firing(Phase-A) Coasting Phase(PBS 3 axis control)

0
0

500

1000

Figure 3-8

1500

2000

2500

Time[s]

3000

3500

4000

Nominal acceleration for SSO mission (with PBS)

- 25 -

4500

5000

Epsilon User’s Manual

90

60
2nd motor burn out
3rd motor/PBS separation

Geodetic Latitude[degN]30

PBS firing(Phase-A)0
3rd motor burn out
2nd/3rd motor separation ,3rd motor ignition

PBS firing(Phase-B)-30
Payload separation
Spacecraft

-60

-90
0

30

60

90

120

150

180

210

240

270

300

330

360

Geodetic Longitude[degE]

Figure 3-9

Nominal ground path for LEO Mission (with PBS)

1400

PBS firing(Phase-B)

1200

1000

PBS firing(Phase-A)

800

Altitude[km]Payload separation
Sacecraft

3rd motor/PBS separation
3rd motor burn out
2nd/3rd motor separation, 3rd motor ignition

600

400
2nd motor burn out

200
1st/2nd motor separation, 2nd motor ignition
Fairing Jettison
1st motor burn out

0
0

500

1000

Figure 3-10

1500

2000

2500

Time[s]

3000

3500

4000

Nominal altitude for LEO Mission (with PBS)

- 26 -

4500

5000

Epsilon User’s Manual

8000
PBS firing(Phase-A)

PBS firing(Phase-B)

Payload separation
Sacecraft7000
3rd motor/PBS separation
3rd motor burn out

6000
2nd motor burn out

Inertial velocity[m/s]

5000

4000

2nd/3rd motor separation, 3rd motor ignition

3000

2000
1st/2nd motor separation, 2nd motor ignition
Faring jettison

1000

1st motoro burn out

0
0

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

Time[s]Figure 3-11

Nominal velocity for LEO mission (with PBS)

8

7

6
1st motor burn out
1st/2nd motor separation, 2nd motor ignition

5

Acceleration[G]2nd motor burn out

4

2nd/3rd motor separation, 3rd motor ignition

3

3rd motor burn out

2Payload separation
Spacecraft

3rd motor/PBS separation

1

PBS firing(Phase-B)

PBS firing(Phase-A)

0

0

500

1000

1500

2000

2500

3000

3500

4000

Time[s]Figure 3-12

Nominal acceleration for LEO mission (with PBS)

- 27 -

4500

5000

Epsilon User’s Manual

3.4. Launch Capability
The launch capability of each configuration is shown in Figure 3-13 and Figure 3-14.

1600

LEO Mission

1400-Elliptical Orbit(Perigee 250[km])・Elliptical
Orbit(Perigee
250[km])-Inclination≒30 [deg]・inclination≒30[deg]1200

Payload [kg]

1000

800

600

400

200

0
0

5000

10000

15000

20000

25000

30000

35000

40000

Apogee [km]Figure 3-13 Launch Capability (Basic Configuration (without PBS))- 28 -

45000

50000

Epsilon User’s Manual

700

600

500

Payload [kg]

400

300

SSO Mission
200

100

0
500

550

600

650

700

750

800

Orbit Altitude [km]

1100

1000

900

Payload [kg]800

LEO Mission
700

・Elliptical Orbit(Perigee 200[km])・Inclination≒30[deg]

600

500

400

300
500

600

700

800

900

Orbit Altitude [km]Figure 3-14 Launch Capability (Optional Configuration (with PBS))- 29 -

1000

Epsilon User’s Manual

3.5.

Injection Accuracy

Each injection accuracy (3σ) for LEO and SSO is shown in Table 3-2.
Table 3-3 shows flight results.

Table 3-2 Injection accuracy
Perigee
Altitude[km]

ApogeeAltitude[km]

OrbitalInclination
[deg]

LEO
(500 km Circular Orbit,
Inclination 30.5 deg)

±10

±10

±0.1

SSO
(500 km Circular Orbit,
Inclination 97.4 deg)

±10

±10

±0.2

LEO
(Perigee 250 km, Apogee 500 km,
Inclination 31.0 deg)

±25

±100

±2.0

Elliptical(Perigee 250 km, Apogee 30700 km,
Inclination 31.0 deg)

±25

±2000

±2.0

Perigee
Altitude[km]

ApogeeAltitude[km]

OrbitalInclination
[deg]

+1.46

+1.64

-0.03

Configuration/Orbit

Optional
configuration(with PBS)

Basic
configuration(without PBS)

Table 3-3 Flight results
Configuration

Optional
configuration(with PBS)

SSO
(approximately 500 km Circular Orbit)- 30 -

Epsilon User’s Manual

3.6.

Mission Duration

Epsilon’ mission duration from lift-off through PL separation for the final orbit depends on the specificorbital parameters and the ground station visibility conditions at the time of PL separation.
Critical mission events including PL separation are executed within fields of view of tracking stations.
This allows each station to receive near-real-time information on relevant flight events, orbital parameter
on-board estimation and separation conditions.
(In multi launch, whether or not PLs except the first separated PL, Small satellite or, in some cases,
one of Micro satellites, are separated within the fields of view is determined based on advancearrangements.)
A typical mission duration is about 60 minutes in the configuration with PBS and about 15 minutes in
the configuration without PBS. Actual mission duration will be determined in the detailed mission
analysis.

3.7.

Launch Window

Launch windows are set based on Customer’s requirements and other conditions.
Once the windows are fixed, any change of launch windows must be coordinated in timely manner inconsideration of availability of alternative windows.

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Epsilon User’s Manual

3.8.

Separation Conditions

PL separation is defined as a state of the mechanical fitting between PL and LV being separated.

3.8.1.

PL Separation Condition Outline(1) LV collision avoidance maneuver after PL separation
LV shall maneuver into a lower orbit to avoid collision or contact with PL.
(2) PL operation
Each PL’s sequence of events, such as activation of propulsion system, deployment of solar paddle
and emission of radio frequency, is determined in an Interface Control Document (ICD) prepared foreach PL.
For multi-payload launch, any PL other than the Small satellite shall be released in cold launch method
in principle and be allowed to start their event sequence after 200 seconds from the separation.
(3) PL separation order in multiple PL launch
PL separation order in multiple PL launch is decided by agreement between Customer and Program
Director.
3.8.2.

Altitude Control in PL Separation

The attitude control process in PL separation is defined for each PL.
PL is separated by the spin separation in the basic configuration without PBS, and PL in single launchand Small satellite in multi launch are separated by the spin separation or the 3-axis stabilization in theoptional configuration with PBS.
The actual pointing accuracy is defined by the results of each PL’s mission analysis.
The standard pointing accuracies just before PL separation with 3-axis stabilization by PBS are shownin Table 3-4, and those with spin separation in Table 3-5.

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Epsilon User’s Manual

Table 3-4PayloadPL (single launch)
Small satellite(multi launch)Standard separation condition (3-axis stabilization)
Pointing error[deg]Angular velocity error[deg/s]Roll

Pitch/Yaw±3(For 600 kg PL)±2±1

0.5±0.1±3(For 200 kg Small satellite
to be first separated)±5±50.5±0.1

N/A

±7

±7

0.2 to 0.6

Micro satellite(multi launch)

See Chapter 4.2.2.1 for detail. The center of gravity(CG) of the satellite greatly influences its separation
rate.

Single CubeSat in a
deployer (E-SSOD)

To be defined in ICD for each PL.
Details are described in Appendix-C.

2 or 3 CubeSats in a
deployer (E-SSOD)

Separation
velocity [m/s]When two or three CubeSats are housed in a deployer,
spring plungers installed on the CubeSats will push eachother and produce its separation rate. Details of thespring plunger are described in Appendix-C.

- 33 -

1.1 to 1.7(For one 3U
weighing 4.5 kg)

Epsilon User’s Manual

Table 3-5PayloadPL(single launch)
Small satellite(multi-launch)PL(single launch)Standard separation condition (spin separation)

PBS

Separation condition

Precondition

Optional
configuration(With PBS)

Error of angular: 30 [deg] or lessSpin rate: 10 [deg/s]
Separation velocity: 0.5 [m/s]Basicconfiguration(Without PBS)

Error of angular: 30 [deg] or lessSpin rate: 360 [deg/s]
Separation velocity: 2.0 [m/s]

Direction of angular momentum※ Target*Error of angular

Error of angular momentum direction

Direction of spin

Angle of nutation

Track of nutation*: In a basic configuration without PBS, target is the direction of LV velocity vector at the time of orbital
injection.

Figure 3-15

Definition of the attitude angle- 34 -

Epsilon User’s Manual

4. PL Accommodation
4.1. PL Fairing (PLF)
PLF protects PLs from the external environment during the accelerated flight in the atmosphere. It
consists of two halves of aluminum hull with aluminum honeycomb core sandwich structure.
The separation bolt system is used for PLF separation; PLF is opened like a clamshell by jettison springs
over jettison hinges along its rim.

4.1.1.

PL Usable Volume

Figure 4-1 shows PLF dynamic envelope, or PL usable volume, in single launch.
PL usable volume is defined as a volume that accommodates a static PL on a Payload Attach Fitting(PAF) or other connecting devices, PL manufacturing tolerances, thermal blankets and otherappendices, and allows for PL’s dynamic displacement to be caused during flight under the condition
that the six degrees of freedom of both PL and PAF or other connecting devices are fixed.
No multilayer insulation (MLI) shall be installed near PAF which connects PL and LV.
As for multi launch, see each section in Appendix as shown below:
・Small satellite
Appendix-A PAF-937M I/F・Microsatellite
Appendix-B Lightband® I/F
・CubeSat
Appendix-C E-SSOD I/F- 35 -

Epsilon User’s Manual

2735
2358

φ204

φ2092
φ1822

100

2660

503.5

Detail A

Detail B

100(2places)

φ600
φ959
φ2120
Figure 4-1

PL Usable Volume (single launch)- 36 -

Epsilon User’s Manual

4.1.2. Access Doors / Radio Frequency (RF) Window(1) Access doors
Access doors, several to be set on PFL for access to PL in single launch or Small satellite in multi launch,have three types as below. Their available locations are shown in Figures 4.1.2-2, 4.1.2-3, and 4.1.2-4.
Refer to Appendix-E for details because access doors may not be approachable in some cases due tothe positional relation of pillars and floor in the M Assemble Tower. For the interference caused by opening
and closing doors, contact your Program Director.
・・・

Square with 600 mm x 600 mm: (1 place in standard)
Circle with a diameter of 180 mm: (2 places in standard)
Circle with a diameter of 350 mm: (None in standard)*: These dimensions indicate values on the developed outside panel of PL with a diameter of 2570 mm.
*: Restrictions on distances between each openings of doors and a window are shown on the figures.

(2) RF transparent window
A RF transparent window, only one to be set on PFL for RF link interface with PL in single launch or
Small satellite in multi launch, has one type as below. Its available locations are shown in Figure 4.1.2-5.
If PL in single launch or Small satellite in multi launch needs RF link tests before launch, consider the
direction of the pick-up antenna in USC (See Appendix-D).
・

Circle with a diameter of 400 mm: 1 place

Figure 4.1.2-1 PFL access door

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Epsilon User’s Manual

Development drawing of PL outside panel (Φ2570 mm)- □: Available areas for door edges: Available areas for door centers- Restriction on distances: Neighboring access doors and a RF window
shall be placed more than the distances away: three times their radii
and the same length as the diagonal from each of their centers.

▧

Figure 4.1.2-2 Access door (Square 600 mm)

Development drawing of PL outside panel (Φ2570 mm)- □: Available areas for door edges: Available areas for door centers- Restriction on distances: Neighboring access doors and a RF window
shall be placed more than the distances away: three times their radii
and the same length as the diagonal from each of their centers.

▧

Figure 4.1.2-3 Access door (Φ180 mm)- 38 -

Epsilon User’s Manual

Development drawing of PL outside panel (Φ2570 mm)- □: Available areas for door edges: Available areas for door centers- Restriction on distances: Neighboring access doors and a RF window
shall be placed more than the distances away: three times their radii
and the same length as the diagonal from each of their centers.

▧

Figure 4.1.2-4 Access door (Φ350 mm)

Development drawing of PL outside panel (Φ2570 mm)- □: Available areas for door edges: Available areas for door centers- Restriction on distances: Neighboring access doors and a RF window
shall be placed more than the distances away: three times their radii
and the same length as the diagonal from each of their centers.

▧

Figure 4.1.2-5

RF transparent window (Φ400 mm)- 39 -

Epsilon User’s Manual

4.2.

PL Requirements

4.2.1.

PL Mass

The mass of each PL is limited as shown in Table 4.2.1-1.

Table 4.2.1-1
PL

PL Mass
Mass

PL (single launch)

See Chapter 3.4

Small satellite (multi launch)

170 - 200 kg

Micro satellite (multi launch)

40 - 65 kg

CubeSat1U size

0.13 - 1.5 kg

2U size

0.26 - 3.0 kg

3U size

0.39 - 4.5 kg- 40 -

Epsilon User’s Manual

4.2.2.

Static Unbalance

PL static unbalance, or C.G. allowance, is limited as shown in Table. 4.2.2-1.

Table 4.2.2-1

PL Center of Gravity (C.G.)

PL

C.G.
Separation planeheightPL (single launch)

0 ± 15 mm

Figure 4.2.2-1

Small satellite (multi launch)

0 ± 15 mm

570 mm or less

Micro satellite (multi launch)Within a sphere of 20 mm radiusfrom the geometric center of each CubeSat

PL mass [kg]

1U to 3U CubeSat

See Chapter 4.2.2.1

PL C.G. height from separation plane [mm]Figure 4.2.2-1 Allowable range of PL mass and C.G. in single launch- 41 -

Epsilon User’s Manual

4.2.2.1. Limit of CG of Micro satellite
C.G. of a Micro satellite shall be limited as described in (1) and (2) as follows.
(1) C.G. of Xsc, Ysc
C.G. of a Micro satellite on the axes of Xsc and Ysc shall be limited to either (A) or (B) as below. If C.G.
lies in B, notify your Program Director of its C.G. and mass at least 7 months before the launch. If a
Micro satellite is difficult to satisfy these C.G. limitations, contact your Program Director(A) The C.G. shall be limited within 5 mm (0 ± 5 mm) from the origin.

Figure 4.2.2-2 Limit of C.G. (Xsc, Ysc) of Micro satellite (A)(B) The nominal C.G. (± 5 mm) shall be limited within 15 mm (0 ± 15 mm) from the origin.

Ysc
15

5

-5

-15

nominal

5
-5

15

Xsc

-15

Figure 4.2.2-3 Limit of C.G. (Xsc, Ysc) of Micro satellite (B)- 42 -

Epsilon User’s Manual(2) C.G. of Zsc
C.G. of a Micro satellite on the axis of Zsc shall be within the allowable range shown in Figure 4.2.2-4
and their nominals shall be ± 15 mm. As this limitation may be changed according to mass
characteristics of other rideshare satellites, the details are defined in your ICD.

500
450
400

C.G. (Zsc) [mm]

350
300
250
200
150
100
50
0
30

35

40

45

50

55

60

65

70

75

80

Mass [kg]Figure 4.2.2-4 Limit of C.G. (Zsc) of Micro satellite and the mass

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Epsilon User’s Manual

4.2.3.

Stiffness of PL

To prevent dynamic coupling with LV, PL shall be designed to have an appropriate structural stiffness
which meets the following requirements in Table 4.2.3-1.
The natural frequencies of PL tightly cantilevered on the interface of a standard adapter shall meet therequirements in Table 4.2.3-1:
If these requirements cannot be satisfied, some measures, such as CLA, can be provided to confirm thestiffness. Contact your Program Manager for details.

Table 4.2.3-1(1/2)

Stiffnessfrequencies

PayloadYB
PL (single launch)

ZB≥ 30 [Hz]Small satellite (multi launch)

Table 4.2.3-1(2/2)

XB≥ 45 [Hz]Stiffnessfrequencies

Payload
Xsc

Ysc≥ 40 [Hz]Micro satellite (multi launch)

Zsc≥ 80 [Hz]≥ 113 [Hz]1U to 3U CubeSat**: CubeSat’s minimum natural frequency shall satisfy this requirement on condition that all ends ofthe four rails of the CubeSat are tightly fixed.

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Epsilon User’s Manual

4.3.

Mechanical Interfaces

Mechanical interfaces with PAF or other connecting devices are described as follows.
・PL (single launch)
Appendix-A PAF-937M I/F
・Small satellite (multi launch) Appendix-A PAF-937M I/F・Micro satellite (multi launch) Appendix-B Lightband® I/F
・CubeSat
Appendix-C E-SSOD I/F- 45 -

Epsilon User’s Manual

4.4.

Electrical Interfaces

4.4.1. Separation Connector / Umbilical Connector
Table 4.4.1-1 shows the number and availability of the separation connectors and umbilical connectors
for each PL.
The umbilical connectors are available for PL in single launch and Small satellite in multi launch.

Table 4.4.1-1 Separation Connector and Umbilical Connectors

PL

Separation Connector(Connection between
PL and PAF)

LV UmbilicalConnector(Connection
between PL and LV
avionics devices)

Facilities UmbilicalConnector(Connection between PL
and ground facilities)

2 LinesSee Appendix-A

N/A (standard) /Available (option)
See Chapter 4.4.2

Available
See Appendix-D

2 LinesSee Appendix-B

N/A

N/A

N/A

N/A

N/A

PL (single launch)
Small satellite(multi launch)
Micro satellite(multi launch)
CubeSat

4.4.2. Electrical Functions for PL
For PL in single launch and Small satellite in multi launch, electrical command as shown below can beprovided as optional via the separation connectors and LV umbilical connector during flight :(1) Command channels(2) Command Signal(3) Output Voltage(4) Output Current(5) Output duration(6) Purpose(7) Grounding: 4 ch max: 28 [V] discrete: 24 – 34 [V]: 0.35 [A] max @High, 1.5 [mA] max @ Low: 100 +/-10 [ms]: per PL requirement.
: Command Return is grounded on the side of LV. (PL shall be isolated.)- 46 -

Epsilon User’s Manual

4.4.3.

Telemetry Transmission and Power Supply to PL

Monitoring, sending commands to, and power supply to PL in single launch or Small satellite in multilaunch are available during launch operation on ground via separation connectors and umbilicalconnectors.
During flight, neither telemetry transmission nor power supply via LV is provided.

4.4.4.

PL Battery Life

If any on-board battery of PL cannot be charged via LV (i.e. Micro satellites and CubeSats in multi launch,and PL without umbilical lines due to its specifications), such PL is recommended to have a sufficientbattery life span in consideration of a period between PL mating and launch. The timing of PL mating with
LV is decided for each PL.

4.4.5.

Separation Switches

4.4.5.1. LV Separation Switches and Transmission of Separation Status
The specifications of LV separation switches for each PL are described in Table 4.4.5-1.
The separation status of PL in single launch or Small satellite in multi launch will be given to Customer
by LSP.
The separation status of Micro satellites and CubeSats in multi launch will be provided according to their
ICDs.

Table 4.4.5-1

Separation switches (LV)

PL

numberdetailPL (single launch)2

Small satellite (multi launch)2

Micro satellite (multi launch)

2 for each satellite

See Appendix-B

CubeSat (multi launch)

2 for each E-SSOD―

See Appendix-A- 47 -

Epsilon User’s Manual

4.4.5.2. PL Separation Switch
The standard specifications of PL separation switches for each PL are described in Table 4.4.5-2.
If needed, contact your Program Director.

Table 4.4.5-2

Separation switches (PL)PL

numberdetailPL (single launch)2

Small satellite (multi launch)2

Micro satellite (multi launch)

2

Appendix-B

4 at max.

Appendix-C

Appendix-A

CubeSat (multi launch)

4.4.6. Bonding and Shielding
4.4.6.1. Bonding
PL shall be electrically connected with PAF at a resistance of 1 ohm or less through electrical connection
at PL separation plane. The coatings on PL separation plane of PAF is described in Appendix-A andAppendix-B.
PL is required to expose part of its inner metal, or bonding point, with a diameter of 10 mm or more so
as to be measured for bonding resistance.
CubeSat, especially, shall have its bonding point on the side of an access door in case it should need
to be handled after being installed in E-SSOD.

4.4.6.2. Shielding(1) Power Line
Shields of power umbilical lines are grounded on the side of the ground facilities and floated on theside of PL. (The boundary of both sides is at the connecting point of PL and LV .)(2) Signal Line
Shields of signal umbilical lines are grounded on both sides of the ground facilities and LV. (Theboundary of both sides is at the connecting point of the ground facilities and LV in PFL.)
Shields of PL and LV are electrically connected at PL separation plane on PAF.
The further information on the umbilical line shields is described in Appendix-D.

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Epsilon User’s Manual

Electromagnetic Environment

4.4.7.

4.4.7.1. Electromagnetic Environment From LV
The levels of electrical-field (E-Field) at PL separation plane generated by emissions from on-board RF
equipment and USC facilities are shown in Figure 4.4.7-1.
Radio properties of launch facilities in and around USC are shown in Table 4.4.7-1.

180

160
B

D
E､F

C

Electric Field leve[dBμV/m]

140

G
A

120

100

80

60

40

20

0
0.01

0.1

1

10

frequency[MHz]

100

1000

Frequency (MHz)Electrical Field Level (dBμV/m)

Reference Character

400 - 500

121

A

2200 - 2290

150

B

3050

134

C

5230 - 5790

154

D

9410

148

E

9730 - 9740

149

F

10000 - 10550

135

G

10000

*1 Electrical field level at other frequencies (14 kHz – 10 GHz) is 116 dBμV/m.
*2 For micro satellite in multi launch, electrical field may exceed these electric field levels at
frequencies more than 10 MHz for a very short time (less than 0.5 sec. during separation).

Figure 4.4.7-1 Levels of Electrical-Field Generated by LV and Facilities- 49 -

Epsilon User’s Manual

Table 4.4.7-1

Radio properties of launch facilities in and around USC

Facility

1

2

3

4

5

Transmit
Frequency

10000-10250 [MHz]10500-10550 [MHz]9740 [MHz]9730 [MHz]9410 [MHz]3050 [MHz]TransmitPower

55.1 [dBm]

50 [kW]

25 [kW]

25 [kW]

30 [kW]- 50 -

Epsilon User’s Manual

4.4.7.2. PL RF Emissions
PL shall not emit E-Field beyond the levels at PL separation plane given in Figure 4.4.7-2.
Micro satellites and CubeSats, which are in principle released in cold launch method, shall not emit any
E-Field.

C

D

B

A

C
B

A

Frequency (MHz)Electrical Field Level (dBμV/m)

Reference Character

400～500

17A

1530～1565

60

B

1565～1585

30

C

1585～1620

60

D*Electrical field level at other frequencies (14 kHz – 10 GHz) is 127 dBμV/m.

Figure 4.4.7-2

Maximum Electrical-Field Levels Acceptable to LV at PL separation plane- 51 -

Epsilon User’s Manual

4.4.8.

Communication Link to PL

Specifications of radio frequencies for communication link with PL are determined after a specificmission is assigned.
(1) RF telemetry and command link
RF telemetry and command links are provided between PL and its EGSE. The links are available during
a period from PL operation on ground through just before liftoff.
The links are not available to Micro satellites and CubeSats in multi launch.

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Epsilon User’s Manual

4.5.

PL Environment

4.5.1. Mechanical Environment
4.5.1.1. Steady State Acceleration
Steady state acceleration is shown in Table 4.5.1-1.
These figures show the upper limit of the acceleration during the entire duration from the start of PL
launch operation on ground through the end of PL separation.

Table 4.5.1-1

Steady State Acceleration (At PL C.G., except for PL on ground)Longitudinal

On Ground

1st
Stage

-9.8±19.6 [m/s2]

22.4±11.2 [m/s2]

Lateralnote±9.8 [m/s2]- Acceleration applied to a point
where PL is hanged by a standard
crane of USC.
- Acceleration applied to the PL/LV
connecting point by LV operations
after PL is mated with LV.

24.5 [m/s2]- Acceleration applied by response
to a gust at maximum dynamic
pressure during 1st stage flight.
- Sign-equivalent vibration is also
added to in 1st stage flight

60 [m/s2]
2nd
Stage

- Acceleration applied by motor
thrust during 2nd stage flight.

(Basic Configuration)
55 [m/s2]

9.8 [m/s2](Optional

In

Configuration)

Flight98 [m/s2]
3rd(Basic Configuration)

Stage

66 [m/s2](Optional Configuration)

9.8 [m/s2]
Spin Rate (on the roll axis):to 360 [deg/s]

Spin Rate (on the roll axis):
Spin upPhase-- Acceleration applied by motor
thrust during 3rd stage flight.

to 360 [deg/s]
Spin Rate Acceleration (onthe roll axis): to 90 [deg/s2]- 53 -- Acceleration applied by spin up
to stabilize 3rd stage spin before
2nd/3rd stage separation.
- Direction of rotation is clockwise
on the roll axis of LV coordinate
system (Xb)Epsilon User’s Manual

4.5.1.2. Sine-Equivalent Vibration
Sine-equivalent vibration is shown in Table 4.5.1-2.

Table 4.5.1-2

Sine-Equivalent Vibration*1

Longitudinal

LateralFrequency

Amplitude [(m/s2)0-p]

Frequency

Amplitude[Hz]at PL separation plane[Hz][(m/s2)0-p]
at PL C.G.

SingleLaunch43 - 53

8.0 (Basic Configuration)
4.9 (Optional Configuration)

53 - 57

Sweep Rate： 4 [oct/min]

All axes

launch3.0

4.9

Sweep Rate： 0.2 [oct/min]Multi

20 - 100

Frequency

Amplitude [(m/s2)0-p][Hz]

at PL separation plane

43 - 539.8

53 - 57

4.9

Sweep Rate： 0.2 [oct/min]*1 AT level- 54 -

Epsilon User’s Manual

4.5.1.3. Random Vibration Environment
Random vibration environment is shown in Table 4.5.1-3.

Table 4.5.1-3

Random Vibration Environment

PL (single launch)
Small satellite (multi launch)

N/A:
Random vibration environment of Small Satellite is coveredby the section below, 4.5.1.4. Acoustic Vibration Environment.

Micro satellite (multi launch)

Figure 4.5.1-1, Table 4.5.1-4
All values are at the upper plane of Lightband® upper ring.

CubeSat (multi launch)

Figure 4.5.1-2, Table 4.5.1-5
All values are at installation plane on E-SSOD.

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Epsilon User’s Manual

0.1
Direction in PL attaching face: Xsc、Ysc
Direction of PL separation: Zsc

G2/Hz

0.01

0.001

0.0001
10

100

1000

10000

Frequency [Hz]Figure 4.5.1-1

Randam Vibration Environment of Micro Satellite

Table 4.5.1-4

Randam Vibration Environment of Micro Satellite

Xsc, Ysc

Zsc

20 -

100 [Hz]：

6 [dB/oct]100 -600 [Hz]：1.45 [(m/s2)2/Hz]

600 -1000 [Hz]：-6.5 [dB/oct]1000 [Hz]：0.481 [(m/s2)2/Hz]

1000 -

2000 [Hz]：-10 [dB/oct]

30 secO.A. ：

35.3 [(m/s2)rms]

20 -100 [Hz]：

6 [dB/oct]

100 -300 [Hz]：1.53 [(m/s2)2/Hz]

300 -1000 [Hz]：-4.6 [dB/oct]1000 [Hz]：0.242 [(m/s2)2/Hz]

1000 -

2000 [Hz]：-10 [dB/oct]

30 secO.A. ：

29.4 [(m/s2)rms](0.0151 [G2/Hz])(0.005 [G2/Hz])(3.6 [Grms])(0.0159 [G2/Hz])(0.00252 [G2/Hz])(3.0 [Grms])*1 AT level

Ysc
衛星取付面内方向

Zsc
衛星取付面外方向

Xsc
衛星取付面内方向- 56 -

Epsilon User’s Manual

0.1

G2/Hz

0.01

0.001

0.0001
10

100

1000

10000

Frequency [Hz]Figure 4.5.1-2

Random Vibration Environment of CubeSat

Table 4.5.1-5

Random Vibration Environment of CubeSat

20 -100 [Hz]：0.0908 [(m/s2) 2/Hz]

100 -300 [Hz]：11.1 [dB/oct]

300 -500 [Hz]：5.21 [(m/s2) 2/Hz]

500 -2000 [Hz]：-9.5 [dB/oct]

30 secO.A. ：All axes

50.0 [(m/s2) rms]

*1 AT level- 57 -(0.000944 [G2/Hz])(0.0542 [G2/Hz])(5.1 [Grms])

Epsilon User’s Manual

4.5.1.4. Acoustic Vibration Environment
Acoustic vibration environment is shown in Table 4.5.1-6. This environment is not applicable to Microsatellites and CubeSats.
This environment covers the acoustic vibrations induced by 1st stage motor during liftoff and by pressure
fluctuations during flight in the atmosphere.

Frequency [Hz]Figure 4.5.1-3 Acoustic Vibration Environment
Table 4.5.1-6

O.A.

Acoustic Vibration Environment

Frequency [Hz]SPL [dB]

31.5

117.2

63.0

123.7

125

128.7

250

132.5

500

126.7

1000

114.4

2000

107.6

4000

105.0

8000

102.0

135.0dB

30 [seconds]*1 : AT level*2 : 0 dB = 2 x 10-5 Pa- 58 -

Epsilon User’s Manual

4.5.1.5. Shock Environment
Shock environment is defined for each PL because it depends on PL mass characteristics and annular
stiffness of PL back frame.
For reference, a standard shock environment is shown in Table 4.5.1-7. All the values are based on thetime of PL separation and applied to both in axial and radial directions. Shock levels are shock response
spectra (SRS) with a Q factor of 10.

Table 4.5.1-7
PL mass

Standard Shock Environment

Frequency

Shock Level (AT)note

50 - 1000 [Hz]10 [dB/oct]Figure 4.5.1-41000 - 4000 [Hz]9810 [m/s2](1000 [G])40 - 65 [kg]

100 - 1000 [Hz]7.8 [dB/oct](Micro Satellite)

1000 - 4000 [Hz]4952 [m/s2] (505 [G])100 - 1000 [Hz]8.28 [dB/oct]1000 - 4000 [Hz]4067 [m/s2] (415 [G])170 - 1200 [kg]CubeSatFigure 4.5.1-5(at Lightband® upper ring)
Figure 4.5.1-6(at installation plane on ESSOD)

10000

Gsrs

1000

100

10

1
10

100

1000

10000

Frequency [Hz]Figure 4.5.1-4 Standard Shock Environment of 170-1200 kg PL- 59 -

Epsilon User’s Manual

10000

Gsrs

1000

100

10

1
10

100

1000

10000

Frequency [Hz]Figure 4.5.1-5 Standard Shock Environment of 40-60 kg PL

10000

Gsrs

1000

100

10

1
10

100

1000
Frequency [Hz]Figure 4.5.1-6 Standard Shock Environment of CubeSat- 60 -

10000

Epsilon User’s Manual

4.5.1.6. Static Pressure inside PLF
The depressurization rate inside PLF during flight does not exceed 5.0 [kPa/s.]
A typical pressure profile inside PLF is shown in Figure 4.5.1-7. A typical depressurization rate profile
inside PLF is shown in Figure 4.5.1-8

Figure 4.5.1-7 Typical Pressure Profile inside PLF

0

減圧率[ｋPa/s]
Rate [kPa/s]
Depressurization

-1
-2
-3
-4
-5

-6
0

10

20

30

40
50
60
time [s]打上後秒時[s]

70

80

90

100

Figure 4.5.1-8 Typical Depressurization Rate Profile inside PLF- 61 -

Epsilon User’s Manual

4.5.2. Temperature and Humidity Environment
4.5.2.1. Temperature and Humidity Environment on Ground
Temperature and humidity environment on ground for PLs is defined in each ICD based on PL thermal
characteristics and launch season.
For reference, temperature and humidity environment on ground is shown in Table 4.5.2-1
Configuration of the air-conditioning system on the launch pad is shown in Figure 4.5.2-1.

Table 4.5.2-1 Temperature and Humidity Environment on Ground of Standard PL
M Assembly Building
Location

M Assembly Tower
Clean room

In Container

Clean BoothOn Launch Pad

In PLFLV Assembly

Task

PL
Assembly

Condition

Air Conditioner
Building AC(AC)

Transferto Clean Booth

Assemblywith LV Upper Stage

Transfer
into M Assembly
Tower

LV Upper
Stage
VOS

N/A

Building AC

Umbilical AC

N/A

without umbilical with umbilicalAC
AC

Launch padroll out

Building AC

Umbilical AC

Fluid

Air

Air

Air

Air

Air

Flow rate[Sm3/min]

N/A

N/A

28

N/A

20-28

Temperature
[℃]

21-25

20-25

8-27 *1

15-25

8-27 *1

Humidity
[％]

40-50

40-50

40-50

50-60

CleanlinessClass

100,000

100,000

5000

100,000

not controllednotcontrolled

40-50

Launch40-50 *2
5000

*1 Temperature control accuracy is ±2℃.
*2 Air conditioning without humidification is available at Customer’s request.

- 62 -

Epsilon User’s Manual

Cooling air inlet

Temperature/Humidity
Measuring Point

Figure 4.5.2-1

Configuration of the air-conditioning system on the launch pad (and in M
Assembly Building as option)- 63 -

Epsilon User’s Manual

4.5.2.2. Thermal Environment in Flight
Thermal environment in each phase during flight depends on heat factors as Table 4.5.2-2.
CubeSats are not affected by these heat factors because they are inside E-SSODs.

Table 4.5.2-2

Heat Factor for PL✔：exist、－：not exist
Multi Launch

PL
Flight Phaseheat factor

Lift off

Radiation

from- Fairing separation

inner surface

detailPLF

Aerothermal heat flux
Fairing separation- PL separation

Lift off- PL separation

Heat conduction with
Lightband®

Micro

Cube

Launch) satellite

satellite

Sat

✔

✔

✔

―

4.5.2.2.2 (1)

✔

✔

✔

―

✔

✔

✔

―

✔

✔

✔

―

✔

✔

✔

―

4.5.2.2.2 (3)

✔

✔

✔

―

Lightband®
temperature
tolerance:
between -24
and ＋56℃

―

―

✔

―

4.5.2.2.2 (2)Earth albedo radiation
3rd stage motor ignition Radiation by 3rd motor
plume- PL separation

Small

4.5.2.2.1

Sunlight radiation
Earth infrared radiation(Single- 64 -

Epsilon User’s Manual

4.5.2.2.1. Before PLF Jettison
The thermal flux density radiated by PLF is less than 1,000 [W/m2]

4.5.2.2.2. After PLF Jettisoning(1) Aerothermal Heat Flux
Aerothermal heat flux of free molecular flow is less than 1,135 [W/m2].
For reference, the result of an aerothermal heat flux of free molecular flow in a nominal flight course ofa standard SSO mission is shown in Figure 4.5.2-3.

Aerothermal heat flux of free molecular flow [W/m2]

1.E+08
Standard SSO Mission

1.E+07
1.E+06
1.E+05

PL Interface condition of aerothermal heat flux of free molecular flow
: under 1135 W/m2

1.E+04
1.E+03
1.E+02

PLF Separation

11.3

1.E+01
1.E+00
1.E-01

0

500

1000

1500

2000

time [s]Figure 4.5.2-3

Result of Aerothermal Heat Flux of Free Molecular Flow in Nominal Flight
Course of Standard SSO Mission(2) Radiation by Sunlight, Earth Infrared Radiation and Earth Albedo
Sunlight direction profile will be presented if needed after Mission Analysis.

- 65 -

Epsilon User’s Manual(3) Thermal Flux from the Motor Plume

1.3
1.2

stage motor plume[kW/m2]

Thermal flux reflected from the 3rd

Thermal flux coming from 1st, 2nd, and PBS stages is negligibly small. Thermal impingement on PL
external surface caused by 3rd stage is shown in Figure 4.5.2-4.
Heat area of Micro satellite in multi launch is shown in Figure 4.5.2-5.

1.1
1
0.9
0.8
0.7
0.6
0.5
0.4
400

500

600

700

800

900

1000

Radius distance[mm]Radius distance(Thermal flux definition region)
Payload usable volume

Thermal flux definition plane

PayloadAdapter

3rd.stage
motor

Payload separation plane

Figure 4.5.2-4 (1/2) Thermal Flux from 3rd Motor Plume- 66 -

1100

Epsilon User’s Manual

180°
＋ZB
(Xsc,Zsc)=(190,0)(138.36mm)(-85,450)
Direction of
separation
分離方向

（4°)

90°
＋YB

＋Zsc
Ysc

(494.02mm)(-300,630)＋Xsc(504.9mm)(-150,520)

ライトバンドUpperRing取付面中心
Microsatellite origin（衛星座標原点）

270°

XB(173.24mm)

PL usable volume(φ2120)in single launch
衛星包絡域（参考）(φ2070)0°
超小型衛星搭載部
PL usable
volume of microsatellite
in multi launch
最大包絡域（参考）BOTTOM VIEW

複数衛星搭載構造
ESMS
lower panel（ESMS)下部パネル

複数衛星搭載構造の影に隠れず、
Heat area to Micro satellite in multi launch
3段プルーム輻射加熱を受ける領域
Figure 4.5.2-5 Thermal Flux from 3rd Motor Plume- 67 -

Epsilon User’s Manual

4.5.3. Cleanliness Environment
4.5.3.1. Cleanliness
Cleanliness Environment is shown in Table 4.5.3-1.

Table 4.5.3-1

Cleanliness Environment

Task

Location

Cleanliness class

PL Assembly

Clean Room

100,000

Transfer to Clean Booth(In transfer container)

not controlled

Assembly with LV upper stages

Clean Booth

100,000

Transfer into M Assembly Tower

until Lift off(Encapsulated)in PLF(Encapsulated)in PLF

5,000*1

5,000*1*1: Property of conditioning air at PLF inlet

4.5.3.2. Contamination
The maximum organic contamination on PL surface is kept below the following values:
From being carried in M Assembly Building to encapsulation : 2 [mg/m2 per week]
From encapsulation through separation: 4 [mg/m2]
After 3rd stage separation : To be defined in each ICD. CubeSats are not affected by contamination
because they are in each E-SSOD.

- 68 -

Epsilon User’s Manual

4.6.

PL Compatibility Verification Requirements

4.6.1. Verification Logic
PL structure and its on-board equipment shall have the capability of withstanding expected maximum
LV ground and flight environments. PL compatibility shall be verified through tests as shown in Table 4.61.

Table 4.6-1
PL
Development

SineStatic

approach

Structure
Test Model

Randomvibration

Acoustic

Qualification
Test

QT

QT

(QT)
QT

Model

or

(PFM)

by heritage*1(FM)equivalent
dynamics

Protoflight

Flight Model

PL Verification Logic

by heritage*1

CoveredShock

Shock Test andAnalysis
Shock Test and

PFM

by

PFM

Analysis

Test*2

acoustic

Test*2

or

test

AT

by heritage*1

ATby heritage*1*1: If qualification is claimed by heritage, the representativeness of the structure test model with respect of theactual flight must be demonstrated.
*2: PFM approach means QT levels with AT duration / sweep rate.

4.6.1.1. Dummy Case for Vibration Tests of CubeSats
A dummy case is available for vibration tests of CubeSats.
Details are shown in Appendix-C.

- 69 -

Epsilon User’s Manual

4.6.2. Safety Factor
PL qualification and acceptance test levels are determined based on safety factors given in Table 4.6-2.
PL shall have enough margins for these safety factors.

Table 4.6-2 Test Factors and Duration
Qualification
PL Tests

StaticSafetyDurationProtoflight
SafetyAcceptance

Duration

Safetyfactors

factors

factors

1.25×Limit

1.25×Limit

1.0×Limit

Duration

SineEquivalent
Dynamics

×2
1.25×Limit×1
1.25×Limit

Random×1
1.0×Limit

Covered by acoustic

Vibration
Acoustic

Limit +3 [dB]

120 [s]Limit +3 [dB]

30 [s]

Limit Level

30 [s]

Shock

Limit +3 [dB]

2 times

Limit +3 [dB]

1 timeLimit Level

1 time- 70 -

Epsilon User’s Manual

5.

Uchinoura Space Center

5.1.

General Overview

5.1.1. Introduction
JAXA owns and operates two space launch sites in Kagoshima Prefecture, which encompasses thesouthernmost part of Kyushu Island and a chain of small islands stretching to the south. (See Figure 5.1.11).
(1) Tanegashima Space Center (TNSC) for Japan’s heavy lifters: H-IIA and H-IIB(2) Uchinoura Space Center (USC) for Japan’s small lifters: Epsilon LV and sounding rockets SS-520
and others
USC is located in the southeast of Kyushu Island and its nearest airport, Kagoshima International Airport,
is two-hour flight from Tokyo. The local time is GMT – 9 h.
USC is the historic place for Japanese space development, from which the first Japanese spacecraft
Ohsumi was launched by a solid propellant L-4S Rocket in 1970. Since then, more than 400 solid
propellant rockets, including sounding rockets, have been launched from USC.
USC has a clear launch azimuth from the East to the South and comprises the two major areas andfacilities: (See Figure 5.1.2-1)
・Launch Complex (Nagatsubo Area)
Launch Complex, used for pre-launch activities from PL preparation through PL/LV integration,
consists of the following facilities:
M Assembly Building
M Assembly Tower
Launching Pad

M Control Center・Mission Control Complex (Miyabaru Area)
Mission Control Complex is located approximately 2.5 km southwest of Launch Complex. This
complex is used mainly for controlling final launch preparation and liftoff and for tracking LV. It
consists of the following facilities:
 Epsilon Control Center Epsilon Support Center- 71 -

Epsilon User’s ManualTokyo

100 kmUchinoura Space Center

Kagoshima International Airport(2Hr.bybycar)
car)
Access Route (3Hr.

Kanoya City

Uchinoura Space Center(USC）

Tanegashima Space Center (TNSC）

Figure 5.1.1-1 Location of USC and TNSC

- 72 -(USC）

Epsilon User’s Manual

Nagatsubo Area

Miyabaru Area

M Assembly Tower/ M Assembly Building

Epsilon Control Center (ECC)/ Support Center (ESC)

2.5 kmLaunch Complex(M Center Plateau)

Mission Control Complex
Figure 5.1.1-2 Outline of Uchinoura Space Center (USC)- 73 -

Epsilon User’s Manual

5.1.2.

PL Arrival(1) Kagoshima International Airport (See Figure 5.1.2-1)
Kagoshima International Airport, the nearest airport to USC, has a 3,000 meter long runway. The airport
is connected with USC by a main road (about 110 km long) appropriate for cargo transportation andlaunch campaign team travel. The customs office is open on a daily basis for cargo import clearance ina bonded area.

©MLIT

Figure 5.1.2-1 Kagoshima International Airport- 74 -

Epsilon User’s Manual(2) Shibushi Harbor (See Figure 5.1.2-2)
Shibushi Harbor is located on the coast of Shibushi-Wan Bay on the Ohsumi Peninsula. The distanceform this harbor to USC is approximately 40 km on land. This harbor can be used for loading andunloading of heavy and bulky cargos transported by vessel.

©MLIT

Figure 5.1.2-2 Shibushi Harbor- 75 -

Epsilon User’s Manual

5.1.3.

PL Preparation at USC

PL preparation at USC is mainly performed in Launch Complex (M Center Plateau). (Figure 5.1.3-1)
The complex includes M Assembly Building, M Control Center, M Assembly Tower, and Launching Pad.
M Assembly Building has a Clean Room available for non-hazardous operations for PL. It also has a
Clean Booth for hazardous operations such as propellant loading, tank pressurization and pyro installation.
These hazardous operations are remotely monitored from M Control Center where Customer’s EGSE
for PL can be installed. (During launch time, all staff and operators have to evacuate M Control Center.)
Hazardous materials can be stored in Dangerous Goods Warehouse next to M Assembly Building.
Propellant can be temporarily stored in Clean Booth for temperature stabilization before fueling.
In Clean Booth of M Assembly Building, PL is mated with LV upper stage and encapsulated in PLF. After
that, the encapsulated PL is transferred to M Assembly Tower by a dedicated car to be launched on
Launching Pad.

N

M Assembly
Tower

M Assembly Building

Launching Pad
M Control Center

Figure 5.1.3-1 Launch Complex (M Center Plateau) Birds-Eye View
- 76 -

Epsilon User’s Manual(1) M Assembly Building
Figure 5.1.3-2 depicts the layout of M Assembly Building, which is composed of the following sections:1) Assembly Room for LV integration preparation
2) Clean Room (179 m2) dedicated to PL non-hazardous operations3) Clean Booth (108 m2) for PL hazardous operations, such as propellant loading and pyroinstallation, and PL/LV mating operation
4) Check-out Room (next to Clean Room) for PL operations for check out
Forklifts are available for loading and unloading PL containers and others.
Equipment for the communication and network in Clean Room and Clean Booth is described in AppendixD.
PL/LV mating operation is conducted in Clean Booth of M Assembly Building. After being fueled, PL is
fixed with Payload Attach Fitting (PAF), then integrated onto LV’s 3rd Stage and finally encapsulated inside
PLF in vertical position. Encapsulated PL is transferred to M Assembly Tower for integration onto the lower
part of LV.

- 77 -

Epsilon User’s ManualCR

CB Front room

CB

11m

Clean
Room
(CR)

Changing
Room
Charging Room

Door

Clean
Booth
Front
Room

Air
Lock
Check-OutRoom

Air Shower(Up range side)

Clean
Booth
(CB)

Air Shower
ChangingRoom
RoomCharging

Assembly
Room

Door

(Down range side)

M Assembly Building

M Assembly Tower& Launch Pad

Figure 5.1.3-2

M Assembly Building Layout- 78 -

Epsilon User’s Manual(2) M Assembly Tower (See Figure 5.1.3-3)
M Assembly Tower is used for Epsilon LV integration and launch preparations. All stages, including
PLF encapsulating PL, are hoisted and stacked on Launching Pad one by one using a travelling ceiling
crane installed in M Assembly Tower. Then, facilities umbilical connector is connected, and composite
electrical readiness test and launch preparations are performed. The environment in PLF is maintainedby a ventilation duct connected between the mast and PLF. Access to PL is available on the 8th and 9th
floors through optional access doors installed on PLF.
R
11UF

11F
10F
9F

8F

PL Access Floor

7F

6F
5F
4F

3F
2UF
2F
2MF
1F

Figure 5.1.3-3

M Assembly Tower

1st motor assembly

2nd motor
assembly

Transport PL with PFL(M Assembly room→M Asembly tower)

Figure 5.1.3-4 LV Assembly in M Assembly Tower- 79 -

Epsilon User’s Manual(3) Launching Pad (See Figure 5.1.3-5)
On a launch day, an Epsilon LV with PL on Launching Pad is rolled out from M Assembly Tower to its
launching position for terminal count down. After the final check out followed by terminal count down,
lift-off is initiated.

N

M assembly tower＋YB
Launcher boom
＋ZB
LV

＋ZB

Turning＋YB

Figure 5.1.3-5 Epsilon LV on Launching Pad(4) M Control Center
M Control Center, located near M Assembly Building and M Assembly Tower, is available for PL teamduring PL operations on ground, in addition to PL Control Room described in Chapter 5.1.4.

- 80 -

Epsilon User’s Manual

5.1.4.

Facilities for Launch Operation

PL team shall stay in Epsilon Control Center and Epsilon Support Center of Mission Control Complex in
Miyabaru Area, during launch preparation and countdown for PL remote operation.
(1) Epsilon Control Center (See Figure 5.1.4-1)
Epsilon Control Center is a two-story building used for administrative operation such as management
and coordination of launch preparation and countdown by LV and PL teams.
The Epsilon Control Center is composed mainly of two rooms:
1) PL Control Room dedicated to PL team for PL remote operations, and
2) Launch Control Room (See Figure 5.1.4-2)
This Center is used for the following operations:1) PL Check-out
2) LV and PL Battery Charging
3) Launch Countdown
4) LV Tracking

Figure 5.1.4-1 Epsilon Control Center

Figure 5.1.4-2 Launch Control Room- 81 -

Epsilon User’s Manual(2) Epsilon Support Center (See figure 5.1.4-3)
Epsilon Support Center has office rooms for both LV and PL teams. The building is connected with
Epsilon Control Center by a roofed corridor on their 2nd floors. Four office rooms are available for PL teamwith desks, chairs, and working table, etc.

EpsilonControl Center
EpsilonSupport Center

Figure 5.1.4-3 Epsilon Support Center- 82 -

Epsilon User’s Manual

5.2. General Characteristics of Facilities
5.2.1.

Climate Conditions

The average climate conditions at USC are as follows:
・The ambient air temperature varies between: -5[°C] ≤ T ≤ 35[°C]・The relative humidity varies between: 30[%] ≤ r ≤ 100[%]

5.2.2.

Power Supply

The USC’s power facilities can supply non-intermittent electrical power of Japanesestandard (100[V]/200[V] - 60[Hz]). If electrical power with other specifications is needed,
contact your Program Director.
Uninterruptible power-supply system (UPS) is also available. If needed, contact yourProgram Director.

- 83 -

Epsilon User’s Manual

5.2.3.

Communication and Data Network

5.2.3.1. Operational Data Network
Data links are provided between the Customer EGSE and PL during launch preparation. PL
data can be also transmitted to the Epsilon Control Center during final countdown.
Telemetry / Telemetry command between Customer’s EGSE and PL are directly transmitted
by the followings:
1) RF signals in S-band,2) Wired link: transmission speed depends on protocols. (up to 64 [kbps] for RS-422)
Dedicated network is provided between PL Control Room and Customer Rooms.
If other data networks are needed, contact your Program Director.

5.2.3.2. Communication Network
The communication networks are available for Customer to communicate inside and outside
USC facilities. The Operational Intercommunication System (OIS) is provided during a launch
campaign for communications among operators. One channel is allocated for the exclusive
use of PL team.

5.2.3.3. Telephone
Personal Handy-phone System (PHS) connecting the outside line are available in USC.

5.2.3.4. Internet
Internet ports are available in Customer’s office rooms of Epsilon Support Center.

5.2.3.5. Standard Time
Standard time signal can be provided as optional services. If needed, contact your Program
Director.

- 84 -

Epsilon User’s Manual

5.2.4.

Transportation and Handling

PL is transported in two ways as below:(1) Covered in a dedicated PL Container between Clean Room and Clean Booth,(2) Encapsulated inside PLF between M Assembly Building and M Assembly Tower.
PL Container’s environment is equivalent to that of Clean Room. The Container in Figure
5.2.4-1 is available for Customer use.
Handling equipment including cranes and trolleys is available for Customer to transfer PL
and its support equipment inside the facility. Specific handling equipment for PL shall be
prepared by Customer. Table 5.2.4-1 shows the cranes’ capabilities for PL team handling
operations.

Figure 5.2.4-1 Payload Container between Clean Room and Clean Booth
Table 5.2.4-1

Crane Capability for PL Handling

Facility

Room

Capabilityqt.

M Assembly Building

Clean Room

5 [ton]1

Clean Booth

2.5 [ton]

2

Assembly Room

50 [ton]1- 85 -

Epsilon User’s Manual

5.2.5.

Fluids and Gases

The following fluids and gases with industrial quality standards can be supplied as optional
services based upon Customer’s requests.
1) Compressed gas for tools
2) Gaseous nitrogen (GN2)3) Gaseous Helium (GHe)4) Liquid Nitrogen (LN2)5) Ethyl alcohol
6) Isopropyl alcohol (IPA)
7) Demineralized water
The specifications of each fluid and gas are to be determined based upon the specific mission
assigned.
Compressed air for breathing and distilled water are available in Clean Booth of M Assembly
Building and in M Assembly Tower for hazardous operations.

- 86 -

Epsilon User’s Manual

5.3. Operation Policy
5.3.1.

Site Security

JAXA takes security measures compliant with Japanese laws and regulations in USC.
The security measures include the followings, but not limited to,:(1) During launch operation, access to USC is restricted and the entrances of roads to
Nagatsubo and Miyabaru areas are controlled by security staff.
(2) All entrances to facilities for PL preparation are controlled by a dedicated electronic card
reader system and limited to authorized personnel with ID cards.
(3) All the offices and integration areas such as Clean Room and Clean Booth of M Assembly
Building are locked.

5.3.2.

SafetyPL team is required to submit the following data for safety hazard evaluation:
1) Propellants: name/specifications/weight2) Pyrotechnics: name/specifications/weight3) High pressure gases: name/specifications/pressure/volume
USC takes basic safety measures, such as keeping fire extinguishers and first-aid kits inplace.
Before a launch campaign, all on-site operators of PL team are required to attend a safety
training course provided by JAXA.
During launch operations, JAXA’s Launch Site Safety Team supervises the prescribedhazardous operations. PL team is required to submit procedures for any operations involving
potential danger to the Launch Site Safety Team for approval.

5.3.3.

Support for PL Team at USC

LV team offers several optional services to PL team. For details, contact your Program
Director.

- 87 -

Epsilon User’s Manual

6. Mission Management
6.1. Outline of Mission Management
LSP provides Mission Management aimed at successful completion of launch services during
a contract term. Mission Management covers various activities as listed below:
1) Mission Integration
2) System Engineering Support
3) Launch Campaign
4) Safety Supervision
Contractual responsibilities between LSP and Customer are specified in a statement of work
(SoW) and technical specifications (ICD and JOP as described in Chapter 6.3.1).
Based on these responsibilities, a program director, representative of LSP, is appointed asa point of contact with Customer and is responsible for contractual and technical coordination
throughout the program.

Each activity is described in the following sections.
Mission management starts from appointment of program director and ends with submissionof Launch Evaluation Report (see section 6.3.5). Launch schedule is determined based on the
SoW, ICD and JOP agreed by Customer.

A typical schedule for a mission management until launch day is shown in Figure 6.1-1.

- 88 -

- 89 -

CLA

▽ICD rev0▽IRD rev0▽CLA model

-6

-5

-4

-3

PhaseⅡ▽JOP rev0▽ICD rev2

PhaseⅢ▽Safety Review

1

2

0

Figure 6.1-1(1/2) Typical schedule for mission management until launch day (Single Launch)-1

Launch Operation

Joint Operation

1

2

Post Flight Analysis▽FMAR
Final Mission Analysis▽PMAR
Preliminary Mission Analysis▽ICD rev1▽Safety Review

0▽Launch-1▽Mate SC/PAF-937M-2access doors（*）▽mass property▽position of fairing

Phase０/Ⅰ

access doors▽number of fairing▽Safety Review▽CLA report▽Launch Service Agreement-7▽Fit check（SC/PAF-937M）-8Month before LAUNCH -25 -24 -23 -22 -21 -20 -19 -18 -17 -16 -15 -14 -13 -12 -11 -10 -9 -8 -7 -6 -5 -4 -3 -2(*)Standard combination of access doors is（□600mm×1,φ180mm×2,RF transparent window×1, see chapter 4.1.2）

Launch Operation

Mission Analysis

Interface Document

SC

Milestone

Month before LAUNCH -25 -24 -23 -22 -21 -20 -19 -18 -17 -16 -15 -14 -13 -12 -11 -10 -9

Epsilon User’s ManualCubeSat

micro satellite

small satellite- 90 CLA▽ICD rev0▽IRD rev0

-2

-1

0

1

▽Launch2

PhaseⅡ▽JOP rev0▽ICD rev2

PhaseⅢ▽Safety Review

0

1

2

Figure 6.1-1(1/2) Typical schedule for mission management until launch day (Multi Launch)-1

Launch Operation

Joint Operation▽FMAR
Final Mission Analysis▽PMAR
Preliminary Mission Analysis▽ICD rev1▽Safety Review▽mass property▽mass property

Post Flight Analysis▽Install CubeSat to E-SSOD
access doors（*）▽mass property▽position of fairing

Phase０/Ⅰ

access doors▽number of fairing▽Safety Review▽CLA report(small satellite）▽CLA model-3▽Mate samll satellite/PAF-937M-4▽Mate micro satellite/Lightband®

-5（Cubesat/Fit check case）（small satellite/PAF-937M）-6（micro satellite/Lightband®Upper ring）-7

Month before LAUNCH -25 -24 -23 -22 -21 -20 -19 -18 -17 -16 -15 -14 -13 -12 -11 -10 -9 -8 -7 -6 -5 -4 -3 -2(*)Standard combination of access doors is（□600mm×1,φ180mm×2,RF transparent window×1, see chapter 4.1.2）

Launch Operation

Mission Analysis

Interface Document

SC

Milestone▽Launch Service Agreement-8

Fit check ▽Month before LAUNCH -25 -24 -23 -22 -21 -20 -19 -18 -17 -16 -15 -14 -13 -12 -11 -10 -9

Epsilon User’s ManualEpsilon User’s Manual

6.2. Mission Integration
Mission Integration starts from the Kick-off Meeting and various activities are carried out tointegrate Customer’s mission into Epsilon launch operations through updating ICD, etc.
Customer shall submit necessary information such as IRD based on ISO standards at the
Kick-off Meeting.
LSP will prepare an ICD draft based on Customer’s requirements and information. Its typicalschedule is shown in Chapter 6.1.

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Epsilon User’s Manual

6.3. System Engineering Support
6.3.1.

Interface Management

The technical interfaces are controlled by two documents as follows. If needed, otherdocuments can be added. Schedules for preparation of these documents is shown in Chapter
6.1.
Document

Contents

Interface Control Documents (ICD)

Technical interface between PL and LV is definedand mission analysis is performed based on thisdocument.
(Typical example)
Rev 0: after signing a contract
Rev 1: before Preliminary Mission Analysis
Rev 2: before Final Mission Analysis

Joint Operation Plan (JOP)

Plan for joint operation of PL Team and LV Teamon Launch Site.

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Epsilon User’s Manual

6.3.2.

Mission Modification

Mission Modification Items, which can be set through interface arrangements between
Customer and LSP, are shown in Table 6.3-1.

Table 6.3-1 Mission Modification Items
Items

PLF Access Doors/
RF Window

PL

Items to be modified

PL (Single Launch)
Small Satellite (Multi Launch)

Location and number of PLF Access
Doors and location of an RF Window

Micro Satellite (Multi Launch)

N/A(Access doors may be set througharrangements with other rideshare
PLs)

CubeSat (Multi Launch)

N/A

PL (Single Launch)
Small Satellite (Multi Launch)

Phases of separation switches,separation springs and separation
connectors may be changed.

Micro Satellite (Multi Launch)

Phases of separation switches andseparation connectors may bechanged.

CubeSat (Multi Launch)

N/A

PL (Single Launch)
Small Satellite (Multi Launch)
Micro Satellite (Multi Launch)

Phases of Xsc and Ysc of PL may bechanged from standard phases within
PL usable volume

CubeSat (Multi Launch)

PL can be set by rotating on Zsc
axis, provided its setting meets theinterface requirements described in
Chapter 4 and is determined before
Preliminary Mission Analysis.

PL (Single Launch)
Small Satellite (Multi Launch)
Micro Satellite (Multi Launch)

PL Usable Volume may be adjusted
as long as PAF and PLF are notaffected.

CubeSat (Multi Launch)

N/AInterface with PAF

PL Crocking Position

PL Usable Volume- 93 -

Epsilon User’s Manual

6.3.3.

Mission Analysis

Mission Analysis is conducted to ensure the achievement of the mission objectives and thecompatibility of the PL and LV. It generally consists of two phases:(1) Preliminary Mission Analysis (PMA)(2) Final Mission Analysis (FMA)
Typical Mission Analyses are shown in Table 6.3-2. These analyses can be selectableaccording to a mission status through discussion with Customer.

Table 6.3-2 Typical Mission Analyses
Type of Analysis

Preliminary
Mission Analysis

Final Mission
Analysis

Trajectory Analysis○○

Separation Analysis○○

Collision Avoidance Analysis○○

Contamination Analysis○

Thermal Analysis○

Coupled Load Analysis (CLA)○- 94 -

Epsilon User’s Manual

6.3.4.

PL Design Compatibility Verification

Some tests shown in Table 6.3-3 can be carried out as options to verify the compliance ofthe mechanical and electrical interfaces between PL and LV and confirm PL environmental
condition.

Table 6.3-3
Items

Optional Tests for Compliance Verification

PL

Typical Contents
Fit-check can be carried out using a flight model of

PL(Single Launch)

PAF to:- Verify mechanical interfaces with PAF, separation
switches, umbilical connectors and separation springs- Verify electrical interfaces with umbilical connectors

Fit-Check

Small Satellite(Multi Launch)and separation switches- Measure pull power of umbilical connecters- Measure bonding
Fit-check can be carried out using an actual (orMicro Satellite(Multi Launch)

CubeSat(Multi Launch)equivalent) Lightband® upper ring, or it can be done
as part of fit-check of PAF.
- Customer shall confirm fit-check using a Fit-Check
Case.
* Details of Fit-Check Case are shown in Appendix-D

PL(Single Launch)

If needed, separation tests with PAF are available as

Test

Small Satellite(Multi Launch)

Director.

Electric Test of

PL(Single Launch)

Separation

Umbilical Lineand
Separation
Connector
EMC Test
RF Linkage
Test
Accessibility
Test

Small Satellite(Multi Launch)
All PLAll PLAll PLan option. For more information, contact your Program

End to End Tests of Umbilical Line and Separation
Connector are performed during Launch Preparation.

To be arranged for each PL
If needed, contact your Program Director
To be arranged for each PL
If needed, contact your Program Director
To be arranged for each PL
If needed, contact your Program Director.

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Epsilon User’s Manual

6.3.5.

Post-Flight Analysis

Quick-look data for orbit parameters and altitude data are provided to Customer in 15
minutes after PL separation. Mission Evaluation Report based on actual flight data are issued
to Customer in one month after the launch.

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Epsilon User’s Manual

6.4. Launch Campaign
6.4.1.

Launch Campaign Organization

A designated Program Director serves as a liaison with Customer throughout LaunchCampaign including Pre-launch and Launch Activities. (See Figure 1-5)

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Epsilon User’s Manual

6.4.2.

PL Pre-Launch Activities

PL Pre-Launch Activities at USC are divided into three phases as follows:(1) Phase 1. PL Setup and Checkout- Stand-alone activities of PL(2) Phase 2. PL Hazardous Operations- Hazardous operations such as tank pressurization, propellant loading, and pyroinstallation etc.
(3) Phase 3. Combined Operations with LV- Joint operations by PL and LV teams such as electrical/radio performance
evaluation tests and combined launch rehearsal.
Typical PL Pre-Launch Activities and schedule are shown in Figure 6.4-1.
The specific schedule is arranged and agreed with Customer.

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- 99 -

CB

CR
&
ECC

Setup andCheckout

1

CB
&
ECC

Hazardous
Operations

Combined
Operations

2

3

ECC

－

7)-4 Countdown

Post Launch Operation

Operations
Spacecraft arrival

-11

-10

Work Day
-12

-9

-8

-7

-6

-5

-4

-2

-1

Review-3and LV) based on customer's requirement.

The duration will be adjusted (between customer-13

the custmer's requirement.

The duration depends on←-14*1：SC Preparations through the access door on the PFL, and SC check out are available.
In additon, SC test on the launch point outside of M tower is available with additional days.
The details of the test will be adjusted between customer and rocket based on customer's requiest.
*2：（Option）SC check out is available.

1)-1 SC preparation(as needed by Spacecraft side)1)-2 Functional test
(as needed by Spacecraft side)2)-1 Preparation to transport to CB2)-2 Transportation to CB

3) Spacecraft Propellant Loading (Option)*2

4) Mating with PAF

5) Mating with LV Upper Stage*2

6) Encapsulation into PLF7)-3 LV checkout ＆S/C Preparations*1
M Assembly
tower7)-2 LV assembly&ECC7)-1 Transportation to M Assembly tower (SC &PLF)
7)-0 Transportation to M Assembly tower & Mating(LV Lower Stage)

Workplace

Phase

～
0

Launch date+1

Epsilon User’s Manual

Figure 6.4-1 Typical PL Pre-Launch/Launch Operation Flow

Epsilon User’s Manual

6.4.2.1. Phase 1. PL Setup and Checkout1) PL Setup and Checkout1)-1 Setup
・PL inside transportation container is arrived at M Assembly Room and moved to Air Lock Room throughthe up-range side door. (See Figure 6.4-2)
・PL is unpacked in Air Lock Room and then moved to Clean Room after dust cleaning.
・EGSE can be installed in either Check-out Room of M Assembly Room or M Control Center.
1)-2 Functional Test
・ The following operations are conducted in Clean Room.
- Visual Inspection- Check Out
・ The temperature and humidity in Clean Room are controlled by air conditioners and monitored andrecorded continuously.
・ The following analyses can be performed as options:- Continuous measurement of organic deposits in Clean Room
- Continuous monitoring of particle count in Clean RoomChanging RoomChanging RoomFigure 6.4-2

Transfer Route to Clean Room
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Epsilon User’s Manual

6.4.2.2. Phase 2. PL Hazardous Operations2)-1 Preparation for Transfer to Clean Booth (See Figure 6.4-3)
・PL is mounted on Transfer Cart by PL Team.
・Cart Cover is placed over PL and sealed tightly by LV Team.

PL

Figure 6.4-3

Preparation for Transfer to Clean Booth- 101 -

Epsilon User’s Manual2)-2 Transfer to Clean Booth (See Figure 6-4)
・PL in Transfer Cart is transferred from Clean Room to Clean Booth by LV Team.
・Cart Cover is removed by LV Team.
・LV Team changes the Transfer Cart with one prepared by PL Team.
・The following equipment is available in Clean Booth.
- Scrubbers- SCAPE Suites (protective suites with air supply function), Breathable Air Supply equipment- Toxic Gas Detectors
・Temperature and humidity in Clean Booth are monitored and recorded. Continuous monitoring of particle
count in Clean Booth is provided as an option.

Changing RoomChanging RoomFigure 6-4

Transfer Route from Clean Room to Clean Booth- 102 -

Epsilon User’s Manual

3) Propellant Loading in Clean Booth3)-1 Propellant Loading Equipment Setup (by PL Team)・Fueling Equipment is carried in.
・Fueling Equipment is set up.
3)-2 Propellant Loading (by PL Team)・Fueling
・Tank Pressurization
・Fueling Equipment Decontamination
・Fueling Equipment is carried out.

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Epsilon User’s Manual

6.4.2.3. Phase 3. Combined Operations with LV
4) Mating with PAF (by PL Team and LV Team)・PL is mated with PAF on a PAF Stand in Clean Booth. (PL Team conducts operations until PL is hoisted
over LV Upper Stage, then LV Team takes on subsequent operations.)
5) Mating with Upper Stage of LV (by LV Team)・PL with PAF is mated with LV Upper Stage mounted on the Upper Stage Dolly.
6) Encapsulation into PLF (by LV Team)・PL mated with LV Upper Stage is encapsulated in PLF and then ventilation duct is connected to PLF.
Work flows of PL encapsulation in Single Launch and Multi Launch are shown in Figure 6.4-5 and in
Figure 6.4-6, respectively.

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Epsilon User’s Manual

PLF

Upper
Stage

PAF

Ventilation
Duct

Upper Stage
Dolly

PAF StandFigure 6.4-5

Encapsulation in PLF (Single Launch)

Rocket Structure

Compression
Tool

Tool

Micro Satellite

GSE ForLighband®
Assemble
Lighband®
Upper Side

PrepareLighband®
Lower Side

PrepareLighband®

mate
Lighband®

Mate
MIcrosat
Lightband®

CubeSat
PAF

E-SSOD

Small
Satellite

Unmount
Structure with
Microsat

Mate
E-SSOD with Cubesat

Figure 6.4-6

GSE(transport cart)

Mate
PAF &
SmallSat

Mate Stages

GSE(transport cart)
Mate Stages

Encapsulation in PLF (Multi Launch)- 105 -

GSE
(transport cart)

Epsilon User’s Manual

7) Vehicle on Stand (by LV Team)

Epsilon’s 1st Stage on Transfer Trailer is moved to M Assembly Tower and hoisted to a vertical positionand placed on Launching Pad. (See figure 6.4-7)

Figure 6.4-7


1st Stage on Stand

Then, 2nd Stage is hoisted and positioned atop 1st Stage (See figure 6.4-8)

Figure 6.4-8

2nd Stage on 1st Stage- 106 -

Epsilon User’s Manual7)-1 Transfer to M Assembly Tower (by LV Team)

Encapsulated PL on Upper Stage Dolly, together with an air conditioning car, is transported by Cranefrom Clean Booth to M Assembly Tower through Assembly Room. (See Figure 6.4-9)

Temperature, humidity and air flow rate inside PLF are regulated by the air conditioning car andcontinuously monitored and recorded during the transfer.

inside
PLSC
inside
PLFPFLAir conditioning
carrier

Air conditioning
carrierCrane
Air conditioning Crane
carrier

Figure 6.4-9

Transfer to M Assembly Tower- 107 -

Epsilon User’s Manual7)-2 Mating with 2nd Stage of LV (by LV Team) (See Figure 6.4-10)・

After arriving in M Assembly Tower, encapsulated PL is unloaded from Upper Stage Dolly andhoisted to the upper floor after the removal of ventilation duct. Then the PL is placed atop 2nd Stagefor mating.

・After mating, PL are connected with wire harnesses and ventilation duct.

・

After umbilical line is connected, PL checkout can be conducted using EGSE.

Air conditioning car
Ventilation
Duct

Figure 6.4-10 Mating with 2nd Stage of LV7)-3 Checkout (by both PL Team and LV Team)・

Combined electrical/radio-electrical readiness tests and launch countdown rehearsal are
performed to demonstrate the compatibility between PL, LV and ground facilities.

・For PL in Single Launch and Small Satellite in Multi Launch, PL Checkout and Battery Charge areavailable before the start of countdown.

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Epsilon User’s Manual

ＣＢ7)-4 Countdown (by LV Team)LV on Launching Pad is rolled out from M Rocket Assembly Tower to its launching position outside andpreparedVOS-4
for countdown. (See Figure 6-10) VOS-5
Countdown is carried out step by step based upon countdown procedures as LV Team confirm a green
rightof each step.
全段電気系点検打ち上げ

PL Team can continue to monitor the status of PL and, if needed, can conduct final PL checkout from
Epsilon Control Center.

整備塔

射点
Figure 6.4-11 Final Configuration of Launch Vehicle- 109 -

Epsilon User’s Manual

8) Tracking Operation (by LV Team)
After a successful liftoff, LV Team tracks LV by downrange stations for range safety operation andmonitors critical events during the flight.

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Epsilon User’s Manual

6.5. Safety Supervision
JAXA is responsible for the safety of human lives and properties and the protection of the environment
during all phases of a Launch Campaign at USC from the arrival and transport of Customer’s PL, GSE
and materials/components through liftoff and PL separation. Therefore, Customer is required to observe
JAXA’s safety regulations and PL design and launch operations shall meet the requirements of JMR-002
LAUNCH VEHICLE PAYLOAD SAFETY STANDARD stipulated by JAXA.
Customer is also required to prepare its safety program plan, which is subject to inspection by JAXA
safety authority, Launch Site Safety Team.

- 111 -