VERSION 2.0 | JULY 2024
ZERO - PAYLOAD USER’S GUIDE | VERSION 2.0 - JULY 2024 |CHANGING

ROCKETS, SATELLITES,AND FUTURE OF THE EARTH
Rockets: The Backbone of the Space Transportation Industry
Rockets serve as the only method of reaching orbit.
As a private space technology start-up, our focus is on designing cost-eﬀective rockets
and providing space launch services to meet global demands.

VISIONMISSION

Aspire to a future where the wonders ofspace are accessible to all

Empower the world with rocket solutions

REVISION HISTORY
VersionDate

Update1.0

July 2023

First Release

2.0

July 2024

Updated Release

CONTACThttps://www.istellartech.com/en

launch@istellartech.com

ZERO - PAYLOAD USER’S GUIDE | VERSION 2.0 - JULY 2024 |2

CONTENTS
01 INTRODUCTION

04 FLIGHT ENVIRONMENTS

1.1 COMPANY PROFILE

4.1 NATURAL FREQUENCIES & DAMPING

1.2 VEHICLE OVERVIEW

4.2 QUASI-STATIC LOAD FACTORS

1.3 KEY COMPONENTS

4.3 RANDOM VIBRATION

1.4 COSMOS ENGINE

4.4 SHOCK
4.5 ACOUSTIC

02 PERFORMANCE
2.1 FLIGHT PERFORMANCE
2.2 ORBIT INJECTION ACCURACY

4.6 ELECTROMAGNETIC
4.7 FAIRING THERMAL ENVIRONMENT
4.8 HUMIDITY
4.9 VENTING

0 3 PAYLOAD ACCOMMODATION

05 LAUNCH SITE FACILITIES

3.1 FAIRING CAPACITY

5.1 ABOUT HOKKAIDO SPACEPORT

3.2 PAYLOAD COORDINATE FRAME

5.2 ACCESS

3.3 PAYLOAD CONFIGURATIONS& MECHANICAL INTERFACES

5.3 PAYLOAD PROCESSING FACILITY
5.4 CUSTOMER OFFICE

3.3 ELECTRICAL INTERFACES

06 OPERATIONS
6.1 AVAILABLE SERVICES & EQUIPMENT
6.2 PAYLOAD PROCESSING WORKFLOW
6.3 MISSION & LAUNCH TIMELINE
6.4 MISSION PROFILE

07 ABOUT OUR COMPANY
7.1 TEAM
7.2 ACHIEVEMENTS
7.3 ADVANTAGESZERO - PAYLOAD USER’S GUIDE | VERSION 2.0 - JULY 2024 |3

ACRONYMS
ICDInterface Control Document

LC-1

Launch Complex - 1

LEO

Low Earth Orbit

LCH4

Liquid Methane

LOX

Liquid Oxygen

MAXQ

Maximum Dynamic Pressure

PSD

Power Spectral Density

S1

Stage 1

S2

Stage 2SPL

Sound Pressure level

SSO

Sun-Synchronous Orbit

VAB

Vehicle Assembly Building

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01 INTRODUCTION

1.1 C O M P A N Y P R O F I L EInterstellar is a dynamic Japanese start-up with a vision of making space accessible toeveryone through low-cost and convenient space transportation services.
Headquartered in Taiki, Hokkaido, Interstellar's product development extends across ﬁve
locations, including branches in Tokyo, Fukushima, and Obihiro, as well as a laboratory at
the Muroran Institute of Technology.
Interstellar has achieved three successful spaceﬂights with suborbital launch vehicle
MOMO, making it Japan's ﬁrst private company to reach space. Currently, Interstellar isdeveloping the orbital-class launch vehicle ZERO. Additionally, Interstellar leads Our
Stars, a satellite development project, pioneering Japan's vertically integrated
rocket-satellite service.
Location：149-7 Memu, Taiki, Hiroo-gun, Hokkaido, Japan
Representative：Takahiro Inagawa (Chief Executive Officer)

Main Oﬃce

Welding Factory

Main Factory

Tank Testing Facility

Engine Testing Facility

Propellant Storage Tanks

Control Center

MachineryTokyo Oﬃce

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01 INTRODUCTION

1.2 V E H I C L E O V E R V I E WInterstellar's strength lies in its
comprehensive in-house capabilities fordesign, manufacturing, testing, andlaunch. By managing all development
stages internally, Interstellar eliminates
unnecessary
elements,
accelerates
development and manufacturing, andachieves signiﬁcant cost reductions.
As a result of these streamlined
processes, Interstellar proudly introduces
ZERO, an orbital class launch vehicle.
ZERO operates as an expendable
two-stage launch vehicle, using liquidmethane and liquid oxygen (LOX) as
propellants. It oﬀers ﬂexible spacetransportation
services,
includingdedicated launches and ridesharing,ensuring your satellite is placed into thedesired orbit on your preferred schedule.

HEIGHT
32 m / 1260 inch

FAIRING
HEIGHT : 5.0 m
DIAMETER : 2.3 m

2nd STAGEENGINE x 1
PROPELLANT :Liquid Methane + LOX

1st STAGEENGINE x 9
PROPELLANT :Liquid Methane + LOXDIAMETER
2.3 m / 90.6 inch

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01 INTRODUCTION

1.3 K E Y C O M P O N E N T S

1st STAGE ENGINE [x9]1st STAGE
INTERSTAGE
2nd STAGE ENGINE [x1]2nd STAGEPAYLOAD ATTACH FITTINGFAIRINGAVIONICS
Reliable Systems for Mission Safeguarding
The avionics system serves a mission critical role in ZERO as it holds the responsibility ofmonitoring and controlling the safety of the vehicle. The architecture, mechanical hardware,electronic hardware, FPGA, and software development of the avionics system of ZERO are alldone in-house at Interstellar.

GIMBAL MECHANISM
Enhancing Mission Safety
Gimbal mechanism controls the direction of each engine and consequently the launch vehicle
trajectory and orientation. This allows engine adjustments mid-ﬂight, improving safety for the
missions. This technology has been demonstrated in our suborbital launch vehicle MOMO.

PROPELLANT TANKS
Crafting High-Performance Tanks
Design, manufacturing, welding, and testing of the tanks are done at Interstellar.
High-strength aluminum alloy is used for the tanks that will store the liquid biomethane fueland liquid oxygen oxidizer. A proof and a burst pressure test were done to ensure its capability
to withstand design pressures and to gauge the pressure endurance limits.

ENGINE
Engine Systems Developed In-HouseInterstellar adopted a liquid methane with liquid oxygen engine for ZERO. A cluster of 9 of thesame engines will be used on the ﬁrst stage, and a single engine of the same design with avacuum optimized nozzle will be used on the second stage.

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01 INTRODUCTION

1.4 C O S M O S E N G I N E
GAS GENERATOR CYCLE & REGENERATIVE COOLING SYSTEMSZERO is a bipropellant rocket that uses
liquid bio-methane as fuel and liquid oxygen
as an oxidizer. This represents Interstellar's
ﬁrst use of a gas generator cycle, wherepart of the propellants is burned in a gas
generator to drive a high-speed turbopump.
This turbopump operates at tens of
thousands of rotations per minute,delivering fuel to the combustion chamber
under high pressure. The rocket also
employs regenerative cooling, utilizing thefuel to eﬀectively cool the combustion
chamber walls.
The engine for ZERO has been named
COSMOS by the development team, inspiredby the COSMOS ﬂower, the oﬃcial ﬂower of
Taiki. The engine's pintle injector spraypattern resembles the petals of this ﬂower,
making the name a ﬁtting tribute.

CYCLE DIAGRAM

LCH4

Propellant: LCH4, LOX

Engine Cycle: Gas Generator Cycle

Engine Cooling: Regenerative Cooling

Injector Type: Pintle Injector

Turbopump
LCH4 Pump

LOX Pump

LOX

TurbineTurbineExhaust Port

ExhaustGas Generator

Main Combustion
ChamberHeat Exchange

Regenerative Cooling Line

Pintle Injector

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01 INTRODUCTION

1.4 C O S M O S E N G I N E
HIGH-PERFORMANCE & SUSTAINABLE ROCKET FUEL for ENVIRONMENTALLY-CONSCIOUS LAUNCHESInterstellar's rockets select liquid methane
as a fuel due to its high performance andcost-eﬀectiveness.
Unliketraditional
rocket fuels like kerosene, which are toxic
and diﬃcult to handle, liquid methane iseasier to manage. This makes it an excellent
choice for both rocket production andoperations.
Additionally,using
liquidbiomethane derived from cow manuresigniﬁcantly
contributes
tocarbonneutrality. This initiative not only
addresses odor issues in Hokkaido's dairy
farming regions but also supports local
energyself-suﬃciency,
promotingenvironmentally friendly development.

OPTIMIZED COST PERFORMANCE
Methane > Kerosene > Solid > Hydrogen

Advantages ofMethaneas Rocket Fuel

LOW ENVIRONMENTAL FOOTPRINT
Ocean : Methane <<< Kerosene
Atmosphere : Methane < Hydrogen < Solid

SUPERIOR SPECIFIC IMPULSE
Methane oﬀers a higher speciﬁc impulse
than kerosene

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02 PERFORMANCE

2.1 F L I G H T P E R F O R M A N C E
ZERO can carry payloads up to 800 kg to a mid-inclination Low Earth Orbit (LEO) at 561
km, while maintaining the ﬂexibility to meet various payload and orbit requirements. In
the demanding Sun Synchronous Orbit (SSO), it can eﬃciently launch payloads of up to
250 kg at 561 km. Refer to the performance curve below for more detailed information.

LEO

Orbit
Payload Mass

SSO

42.2°- 561 km

97.6°- 561 km– 800 kg

– 250 kgZERO uses Hokkaido Spaceport as its main
launch site. Facing the ocean to the eastand south, this location provides anadvantageous setting for accommodating awide range of inclination options.

Available Inclinations

42° – 98°

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02 PERFORMANCE

2.2 O R B I T I N J E C T I O N A C C U R A C Y
The target injection accuracies of ZERO for a typical mission are as follows. Theseestimates will be further reﬁned with collected ﬂight data.

Perigee± 10 km

Apogee± 15 km

Inclinations± 0.1 degZERO - PAYLOAD USER’S GUIDE | VERSION 2.0 - JULY 2024 |13

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03 PAYLOAD ACCOMODATION

3.1 F A I R I N G C A P A C I T Y
The payload fairing of ZERO is designed to accommodate a wide range of payload sizes
and conﬁgurations, oﬀering ﬂexibility for various mission requirements. The
accompanying ﬁgure illustrates the dimensions and shape of this space. Detailed
speciﬁcations, including height, diameter, and overall volume, are provided to help you
optimize the integration of your payload.

∅

420mm
16.5 inch∅

1,410 mm55.5 inch

3,800 mm
149.6 inch∅

1,900 mm
74.8 inch

2,550 mm100.4 inch
1,307 mm51.5 inch

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03 PAYLOAD ACCOMODATION

3.2 P A Y L O A D C O O R D I N A T E F R A M E
The origin of the Payload Coordinate System is ﬁxed at the center of the mechanicalinterface between customer-supplied hardware and Interstellar-supplied hardware. This
coordinate frame is used for describing the ﬂight environment conditions andmechanical interfaces outlined in this document. The actual payload coordinate frame
will be further deﬁned in the mission-speciﬁc ICD. For this purpose, assuming a standard
circular interface, the direction aligned with the launch is deﬁned as the "Axial
Direction," while the orthogonal direction is deﬁned as the "Lateral Direction."

Axial Direction

Launch Direction

Lateral Direction

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03 PAYLOAD ACCOMODATION

3.3 PAYLOAD CONFIGURATIONS & MECHANICAL INTERFACESZERO is capable of supporting various types of payloads, including small satellites and
CubeSats. A wide range of separation systems can be accommodated by tailoring thebolt footprint of Interstellar-supplied hardware to match the customer-selected
separation system. Payloads can be arranged and ﬁtted in diﬀerent ways inside thefairing to suit the speciﬁc requirements of each ﬂight.
Please contact us if you have any questions or need assistance in selecting a separation
system.

Small Satellite x 1

Small Satellite x 1
CubeSats x 5

Small Satellites x 4

CubeSats x 4

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03 PAYLOAD ACCOMODATION

3.4 E L E C T R I C A L I N T E R F A C E SInterstellar provides a ﬂexible electrical interface tailored to accommodate diverse
payloads, separation systems, and dispensers. This interface typically includes
redundant payload deployment transmission signals and feedback signals to conﬁrm
deployment status for standard missions. Speciﬁc details regarding the electricalinterface will be outlined in the mission-speciﬁc Interface Control Document.
Please reach out to us for conﬁrmation of our ability to support your preferred deployer
hardware.

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04 FLIGHT ENVIRONMENTS

The ﬂight environments outlined below represent the expected maximum predictedenvironments (MPE) for payloads in a typical mission. The loads and environments
provided in this section are for reference only. The actual mission-speciﬁc environments
will be detailed in the Interface Control Document (ICD) provided to customers.
For any questions about payload environments, please contact our team.

4.1 N A T U R A L F R E Q U E N C I E S & D A M P I N G
The purpose of deﬁning natural frequencies and damping requirements is to ensure thatthe payload’s elastic natural frequencies do not couple with those of the launch vehicle.
All elastic natural frequencies of the payloads must be above 40 Hz and must have aquality factor (Q) between 10 and 50. These requirements are designed to adequately
account for the expected ﬂight environments.
In this document, an elastic natural frequency refers to any frequency response of the
payload that involves modal participation, as determined by a ﬁxed-base modal analysis.

Frequencies Requirements (Q=10~Q=50)
Axis

Axial and Lateral

Frequency

all modes above 40 Hz

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04 FLIGHT ENVIRONMENTS

4.2 Q U A S I - S T A T I C L O A D F A C T O R S
The payload will experience a range of acceleration loads in both the axial and lateralaxes during the ﬂight, as shown in the graph below. This envelope includes static andlow-frequency dynamic loads.
Axial acceleration loads arise from thrust, aerodynamic axial forces, separation forces,
and similar factors. Lateral acceleration loads result from wind gusts, thrust vector
control (TVC) reaction forces, ﬁrst-stage engine shutdown, and other short-term
events.
Mission-speciﬁc accelerations will be further detailed in the mission-speciﬁc Interface
Control Document (ICD), determined by the coupled loads analysis.

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04 FLIGHT ENVIRONMENTS

4.3 R A N D O M V I B R A T I O N
The plot below shows the estimated Maximum Predicted Random Vibration Environment
for microsatellite-class payloads. This estimate is based on an analysis of vehicle
environments and past data and is subject to change as additional ﬂight information andtesting become available.

Frequency [Hz]

20

700

800

925

2000

GRMS

PSD [G^2/Hz]

0.01

0.01

0.03

0.03

0.00644

5.23

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04 FLIGHT ENVIRONMENTS

4.4 S H O C K
The maximum predicted shock response at the payload interface from all sources oflaunch vehicle shock is shown in the graph and table. This level is deﬁned assuming aquality factor (Q) of 10. The estimate is based on an analysis of vehicle environments
and past data and is subject to change as additional ﬂight information and testing
become available.

Frequency [Hz]

100

900

10000

Shock Response Spectrum [G]

50

700

700

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04 FLIGHT ENVIRONMENTS

4.5 A C O U S T I C
The vibroacoustic environment inside the fairing is determined as shown in the graphand table below. This environment encompasses the acoustic vibrations generated by
the ﬁrst-stage engine during lift-oﬀ, as well as the acoustic vibrations from pressure
ﬂuctuations outside the vehicle during atmospheric ﬂight. These conditions will be
redeﬁned as more ﬂight data becomes available.

MAXIMUM PREDICTED ACOUSTIC ENVIRONMENT
Frequency
[Hz]

31.5

40

50

63

80

250

315

400

SPL
[dB]

121

122

123

124

124.9 125.7 126.3 126.7 126.9 126.6

126124.8 123.6

FREQUENCY
[Hz]

630

800

1000 1250 1600 2000 2500 3150 4000 5000 6300 8000 10000

SPL
[dB]

122.2 120.9 119.3

117.5

100

115.5 113.6

125

111.9

160

200

500

110.1 108.4 106.5 104.6 102.8 101.1

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04 FLIGHT ENVIRONMENTS

4.6 E L E C T R O M A G N E T I C
ELECTROMAGNETIC EMISSIONS FROM ZERO AND LAUNCH SITE
This section outlines the worst-case radiated emissions from the Launch Vehicle andLaunch Site. Payloads can expect to encounter an electric ﬁeld (E-Field) from theseemissions, with levels no higher than those indicated in the graph and table below. The
electric ﬁeld level is measured at the payload interface plane.
Components on payloads that are sensitive to RF environments should be veriﬁed forcompatibility with the speciﬁed radiated environment.

E-Field Radiation Emission vs Frequency
Label
Frequency Range [MHz]E-Field Level [dBuV/m]

A

B

0.014-18000 2025-2110
100

128

C

D

E

F

2200-2300

2401-2495

5230-5390

9410

150

107

136

150

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04 FLIGHT ENVIRONMENTS

4.7 F A I R I N G T H E R M A L E N V I R O N M E N T
FAIRING TEMPERATURE AS SEEN FROM PAYLOAD
The temperature proﬁle below shows the maximum fairing spot temperature seen by the
payload. The emissivity of the fairing is approximately 0.9.

FREE MOLECULAR HEATINGThe Payload experiences a maximum free molecular aero-thermal heating rate of under
1135 W/m² at the point of fairing separation. This heating rapidly diminishes andbecomes insigniﬁcant within a few minutes.

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05 PAYLOAD ENVIRONMENTS

4.8 H U M I D I T Y
The maximum relative humidity inside the fairing from lift-oﬀ until just before fairing
separation is 65%. This controlled humidity level ensures the protection and integrityof the payload during the initial phases of the ﬂight. ZERO is designed to maintain
optimal environmental conditions, ensuring the successful deployment and operation of
the payload.

4.9 V E N T I N G
The graph below shows the pressure and decompression rate during ﬂight for a typicalmission. The maximum depressurization rate is 1.9 kPa/s, with brief periods during ﬂight
reaching up to 4.5 kPa/s for only 5 seconds.
Please note that these are preliminary values and are subject to reﬁnement withadditional calculations and ﬂight data.

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Provided by: SPACE COTAN Co.,Ltd.

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05 LAUNCH SITE FACILITIES

5.1 A B O U T H O K K A I D O S P A C E P O R T
Hokkaido Spaceport (HOSPO) is the theglobal commercial spaceport in East Asia,
located in Taiki, Hokkaido, Japan.
Situated at HOSPO, Launch Complex-1(LC-1) serves as the designated launch site
for ZERO missions. LC-1 features a Vehicle
Assembly Building (VAB) and test facilities,
along with an exhaust duct to minimize
engine jet noise and vibration impact onsatellites. LC-1 is designed to blend
seamlessly with the surrounding naturallandscape.

Rendered Image

5.2 A C C E S SHOSPO is located in Taiki, southeastern
Hokkaido Prefecture, easily accessible
from Tokyo within 2.5 hours. The
recommended route is to ﬂy from Haneda
Airport to Tokachi Obihiro Airport in
Hokkaido, then drive to the launch site.

Tokachi Obihiro
Airport40 minby car

100 minby planeTokyo International Airport（Haneda Airport）
Provided by: SPACE COTAN Co.,Ltd.

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05 LAUNCH SITE FACILITIES

5.3 P A Y L O A D P R O C E S S I N G F A C I L I T Y
The following illustrates the layout of the Payload Processing Facility at LC-1, featuring
the payload integration room, airlock, and dedicated customer oﬃce space. Please notethat as the facility is currently under construction, the ﬁnal layout may slightly diﬀer.

Maintenance
Room

Assembly Area

Staff
Workspace

HVAC
Customer
OfficeGowning
Area

Cleanroom

Airlock

Unloading
Area

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05 LAUNCH SITE FACILITIES

5.4 C U S T O M E R O F F I C EInterstellar provides an oﬃce area within the Payload Processing Facility, strategically
positioned adjacent to the payload integration area for convenient access. Although thefacility is currently under construction, the aim is to equip the oﬃce area withessential amenities including Internet connection, air conditioning, and standard oﬃce
equipment such as desks, chairs, and phones.

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6 OPERATIONS

6.1 A V A I L A B L E S E R V I C E S & E Q U I P M E N T
As part of our launch package, Interstellar oﬀers a variety of services and equipment.
Some examples of what we can provide are detailed below. Recognizing the uniquenessof each mission, the speciﬁc services and equipment will be ﬁnalized during the signingof the Launch Services Agreement (LSA). We encourage early discussions during mission
planning to ensure that our oﬀerings align with your schedule and budget.

SERVICES・Dedicated Technical Mission Manager and Customer Support Teams・Development and Provision of Mission-Speciﬁc Interface Control Document (ICD),
Including Veriﬁcation Planning and Deliverables
・Mission Planning and Launch Scheduling・Customization of Launch Conﬁguration, Mechanical and Electrical Interfaces for
Dedicated Missions
・Progress Follow-Up Meetings
・Securing Necessary Launch Licenses from Japanese Authorities
・Guidance and Support for Launch Insurance
・Payload Transportation Assistance・Interstellar Integration Support Personnel
・Accommodation Assistance for Customer's Launch Team・Launch Site Access and Commute Support
・Photography Operations
・Conﬁrmation of Payload Separation and Provision of State Vector to Customer

EQUIPMENT・ISO-8 cleanliness level environment (Class 100K)
・Crane for payload integration operations
・Power provided for electrical ground support equipment (110V AC, 50Hz)
・Isopropyl Alcohol, wipes, gloves, hair nets, gowns, work shoes
・Security guards and video monitoring cameras
・Internet connection and standard oﬃce equipment for customer oﬃce

For information on additional services not listed above that may be required for yourmission, please contact our team.

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6 OPERATIONS

6.2 P A Y L O A D P R O C E S S I N G W O R K F L O W
This section provides an overview of the payload processing workﬂow for a typicalmission. A dedicated Interstellar integration team will be assigned to the customer,
working closely to provide comprehensive support throughout the process.

Payload Delivery to the Launch Complex
The payload will be transported from the customer's facility to our Launch Complex-1 in
Hokkaido. Upon arrival, our team will carefully oﬄoad and move the payload and groundsupport equipment to the designated processing area. Typically, the payload arrives atthe launch site 30 days prior to launch, though this timeline can be adjusted if
necessary.

Payload Final Check-out
Customers will conduct the ﬁnal checkout of the spacecraft, which involves performing
last-minute tests and preparations, such as software loading, powering up, andpropellant fueling. Our facilities oﬀer all the necessary support to ensure your payload
is fully prepared and ready for integration.

Payload Integration
In this step, the payload will be integrated with the separation system, which will thenbe attached to the payload attach ﬁtting of the ZERO launch vehicle. This process also
includes establishing electrical and data connections to the launch vehicle, enabling
communication between the payload and our launch control team.

Fairing Encapsulation
At this stage, the payload, along with the separation system, is integrated with the
payload attach ﬁtting. Once the payload is thoroughly checked, it will be encapsulated
within ZERO's fairing.

Encapsulated Payload Mate with ZERO Launch Vehicle
The encapsulated payload is then carefully transported to the assembly area for
integration with the rest of the launch vehicle. Once integrated, the launch vehicle,
with the payload onboard, will be ready to roll out to the launch pad.

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06 OPERATIONS

6.3 M I S S I O N & L A U N C H T I M E L I N E
The milestones and payload processing schedule for a typical mission are presented
below. If you require an accelerated or extended timeline, Interstellar will work closelywith you to develop mission-speciﬁc milestones.
To explore options for a customized timeline that aligns with your mission objectives,
please contact our team.

L-12months
Sign Contract & Mission Kick-off

L-6 months
Launch Campaign Planning Kick-off

L-3 months
Finalize ICD and Mission Interfaces

L-30 days
Payload Arrival at Processing Facility

Days

PayloadLaunch Vehicle

L-30

Payload Integration

S1, S2, and Fairing
Module Checkouts

L-15

Fairing Encapsulation

L-13

Encapsulated Fairing Mate with S1 and S2

L-10
L-4
L-3
L-2

Launch Complex
Launch Pad andRange Safety
Systems Checkouts

Launch Vehicle and Range Interface Check

RF Checkouts

Final Launch Vehicle Preparation

Final Range
Preparation

L-1

Roll Out

L-0

LaunchL+0

Deliver State Vector to Customer

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06 OPERATIONS

6.4 M I S S I O N P R O F I L E
The following illustration depicts the standard mission proﬁle and staging sequence for
the ZERO rocket. While typical missions follow a similar proﬁle, variations in timing andaltitude for key events may occur based on mission-speciﬁc requirements.

2nd engine
start-2

2nd engine
cutoff-1

2nd engine
cutoff-2

Fairing separation
2nd engine start-1

Payloaddeployment

Stage separation
Main engine
cutoffMAX Q

Lift off

1

2

3

Main
Lift off MAX Q engine
cutoff0

TIME [s]

+ 62

+ 143

4

5

6

7

8

9

10

Stage
separation

2ndenginestart-1

Fairing
separation

2ndenginecutoff-1

2ndenginestart-2

2ndenginecutoff-2

Payloaddeployment

+ 148

+ 153

+ 192

+ 429

+ 3148+ 3149+ 3200ZERO - PAYLOAD USER’S GUIDE | VERSION 2.0 - JULY 2024 | 36

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07 ABOUT OUR COMPANY

7.1 T E A MInterstellar's development team is made upof highly skilled professionals, each withextensive expertise and dedication. Our
engineers include those who have worked on
spacecraft

development

forJapan's

government space agency and experts fromleading global automobile manufacturers. By
merging Japan's industrial technologies,
Interstellar is pioneering a new era of space
exploration.

7.2 A C H I E V E M E N T S
18 ROCKET LAUNCHES
A total of 18 rockets have been manufactured and launched,including three successful space missions. (as of June 2024)

FIRST IN JAPANThe ﬁrst rocket developed by a private Japanese company toreach space.

FIRST IN THE WORLD
The ﬁrst and only private company in the world utilizing
bio-methane liquid-fueled engine.

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07 ABOUT OUR COMPANY

7.3 A D V A N T A G E S
ON-DEMANDYour Destination, Your Timeline
Interstellar facilitates on-demand transportation to the desired orbit and altitude, oﬀering a
dedicated solution that overcomes the limitations of shared transportation for large satellites. By
integrating in-house design, manufacturing, testing, and launch operations, Interstellar signiﬁcantly
reduces the time from contract to launch.

FLEXIBILITY
Tailored Solutions for Your Needs
In-house design and manufacturing capabilities grant ﬂexibility to meet your needs. Interstellar
customizes the system to match your requirements and handle sudden changes, ensuring highcustomer satisfaction.

LOW COST
Globally Competitive Launch Costs
Interstellar oﬀers one of the most competitive price points in the microsatellite launch market.
Striving to reduce prices through the in-house development of core technologies and the active
utilization of cutting-edge technologies such as consumer-grade components and 3D printing.

VERSATILE LAUNCH SITE
Embrace the Allure of the Japanese Spaceport
Hokkaido Spaceport "HOSPO," located in Taiki, Hokkaido, Japan, provides launch capabilities towards
the east and south, making it one of the world's most suitable launch sites.

ZERO - PAYLOAD USER’S GUIDE | VERSION 2.0 - JULY 2024 | 39

ZERO PAYLOAD USER’S GUIDECONTACTSOCIAL MEDIA

launch@istellartech.com
https://www.istellartech.
com/enhttps://youtube.com/@istellartech@istellartech_en@interstellar
technologies.
inc

https://www.linkedin.com/company/ist
ellartech/ZERO - PAYLOAD USER’S GUIDE | VERSION 2.0 - JULY 2024 |