ASCA

Single-Stage-to-Orbit vehicle (Reusable rocket)

Carrying everyone’s hopes and dreams.

ASCA is a single-stage-to-orbit vehicle (reusable rocket) being developed by ISC.
The company aims to gradually implement services starting in 2028, with development being fast and flexibly responsive to market needs through its unique agile structure.

Overview

A world where people and cargo
circle the globe every day,
democratizing point-to-point space travel
and delivering the future.

Once a day, Capable of over 1,000 repeat flights: With a turnaround capability of once a day, and with detailed inspection, maintenance and replacement, the aircraft and propulsion system can fly repeatedly more than 1,000 times.
High payload delivery capability: Capable of launching a 10-ton payload into Earth orbit (altitude of about 400 km)
For daily transportation: Capacity is 50 people, with the same reliability and safety as an aircraft

Roadmap

Steady and Fast.

ASCA's development is divided into three phases. Development is proceeding unwaveringly and at a rapid pace, with the aim of completion in the 2040s.

ASCA 1

Aiming to acquire multiple complementary technologies to launch 100kg class artificial satellites using reusable rockets

2025 ASCA 1.0

ISC's first "takeoff and landing" test aircraft. The goal is to acquire attitude control and guidance control technology for the landing phase by 2025, and to establish maintenance and operation methods for reuse.

Specifications

First launch

the end of 2025
Total length

8,290 mm
Diameter

2,000 mm
Dry mass

2,629 kg

Gross mass

3,192 kg
Flight duration

34 sec.
Maximum altitude

100 m
Down range

50 m

First launch

the end of 2025
Total length

8,290 mm
Diameter

2,000 mm

First launch

the end of 2025
Total length

8,290 mm
Diameter

2,000 mm
Dry mass

2,629 kg
Gross mass

3,192 kg
Flight duration

34 sec.
Maximum altitude

100 m
Down range

50 m

2026 ASCA 1.1

A takeoff and landing test aircraft based on ASCA 1.0. The goal is to reach an altitude of 100km in space.

Specifications

First launch

scheduled in 2026
Total length

14,000 mm
Diameter

2,000 mm
Dry Mass

TBD

Gross mass

TBD
Flight duration

TBD
Maximum altitude

TBD
Down range

TBD

First launch

scheduled in 2026
Total length

14,000 mm
Diameter

2,000 mm

First launch

scheduled in 2026
Total length

14,000 mm
Diameter

2,000 mm
Dry Mass

TBD
Gross mass

TBD
Flight duration

TBD
Maximum altitude

TBD
Down range

TBD

2028 ASCA 1.2

The goal is to acquire a 100kg transport capacity for transcontinental flights and satellite launches. Based on the takeoff and landing technology and maintenance and operation methods for reuse acquired in ASCA 1.0 and 1.1, the goal is also to rapidly reuse the vehicle.

Specifications

First launch

TBD
Transportation capacity

100 kg
Total length

22,400 mm
Diameter

2,030 mm
Dry mass

3,282 kg

1st-stage propellant mass

20,495 kg
2nd-stage propellant mass

2,524 kg
Flight duration

TBD
Maximum altitude

TBD
Down range

TBD

First launch

TBD
Transportation capacity

100 kg
Total length

22,400 mm

First launch

TBD
Transportation capacity

100 kg
Total length

22,400 mm
Diameter

2,030 mm
Dry mass

3,282 kg
1st-stage propellant mass

20,495 kg
2nd-stage propellant mass

2,524 kg
Flight duration

TBD
Maximum altitude

TBD
Down range

TBD

Mission Highlights

Function Check Section

The electrical functions are checked for the guidance section, kerosene tank section, LOX tank section, and engine section.

Cold Flow Test Spacecraft structure (excluding engine) and ground support equipment

Verify that the filling and discharging of propulsion system liquid gases works as expected in conjunction with the equipment systems.

HILs (Hardware In the Loop Simulation) Test Spacecraft structure and ground support equipment

The control, polarity, and response of the end effector will be confirmed, and the GNC system will be verified through flight dynamics simulation.

Captative Fire Test Spacecraft structure and ground support equipment

The spacecraft will be fixed to the firing pad and a combustion test will be carried out to check the behavior of each device and sensor and to see if it can be moved on to flight demonstration.

GTV (Ground Test Vehicle) Spacecraft structure and ground support equipment

A simulation of post-landing will be conducted, and safety procedures will be carried out, QD (Quick Disconnector) will be connected, and propellant will be drained, to confirm operational procedures.

Flight Test Spacecraft structure and ground support equipment

A flight demonstration will be conducted. The spacecraft will be secured to the launch pad, fuel will be filled, and the integrity of the spacecraft, launch pad, and control equipment will be checked before the flight begins. The spacecraft will be raised vertically to 100m and landed at a landing point 50m horizontally from the launch pad. The spacecraft will then be recovered and inspected, and operational data will be collected.

ASCA 2

The goal is to launch manned space flight services that are reliable and safe, and that will enable space travel and P2P (high-speed point-to-point transport). Furthermore, by making it more efficient and lighter, we can reduce the cost of space transportation.

2032 ASCA 2

Aiming to launch manned spaceflight. Implement high-speed point-to-point transportation, space travel, and services to and from the space station. Aim for safety standards and miniaturization, weight reduction, and cost reduction.

Specifications

First launch

the middle of 2030s (plan)
Transportation capacity

100 ㎏
Number of passengers

6
Total length (1st-stage)

63,000 mm
Total Length (2nd-stage)

13,380 mm

Diameter (1st-stage)

5,200 mm
Full span

9,960 mm
Flight duration

TBD
Maximum altitude

TBD

First launch

the middle of 2030s (plan)
Transportation capacity

100 ㎏
Number of passengers

6

First launch

the middle of 2030s (plan)
Transportation capacity

100 ㎏
Number of passengers

6
Total length (1st-stage)

63,000 mm
Total Length (2nd-stage)

13,380 mm
Diameter (1st-stage)

5,200 mm
Full span

9,960 mm
Flight duration

TBD
Maximum altitude

TBD

ASCA 3

We aim to develop a single-stage spaceplane (reusable rocket) and realize frequent, large-scale, and inexpensive space transportation.

2040 ASCA 3

The single-stage spaceplane will be capable of more than 1,000 flights and aims to become a space transportation system carrying 50 passengers and supplies twice a day.

Specifications

First launch

the beginning of 2040s (plan)
Transportation capacity

10-ton cargo / 50 passengers
Total Length

40,700 mm
Diameter

8,100 mm
Full span

2,200 mm

Flight duration

TBD
Maximum altitude

TBD
Dry mass

81,000 kg
Gross mass

716,000 kg

First launch

the beginning of 2040s (plan)
Transportation capacity

10-ton cargo / 50 passengers
Total Length

40,700 mm

First launch

the beginning of 2040s (plan)
Transportation capacity

10-ton cargo / 50 passengers
Total Length

40,700 mm
Diameter

8,100 mm
Full span

2,200 mm
Flight duration

TBD
Maximum altitude

TBD
Dry mass

81,000 kg
Gross mass

716,000 kg

Features

Speed up rocket development with our unique agile development platform.

The research and development platform ‘P4SD’ has been introduced to implement an agile flow in space development. By eliminating the dependency on individual developers and easily utilizing expertise, we can dramatically shorten development times.

Spacecraft manufacturing making maximum use of metal 3D printers

The spacecraft will be manufactured using the WAAM method of metal additive manufacturing. The manufacturing period for each structural part will be approximately six weeks, accounting for around 35% of the spacecraft's mass. In addition, the company will work with universities and trading companies to establish competitive manufacturing technology by adjusting the torch feed speed and shielding gas.

Crossing borders and collaborating with overseas companies to achieve rapid results and growth.

In order to reduce engine development costs, which account for the majority of rocket production costs, and the associated risks, we have purchased and are jointly developing engines that have been used in other rockets from Ursa Major, a US engine manufacturer. This will allow us to move resources away from engine development and focus on vehicle design and production.

Employs model predictive control

Model predictive control (MPC) will be adopted as a guidance and control technology for the return rocket. MPC is a technology used by overseas rocket venture companies, and adopts a rocket motion model to predict flight over a finite future time period, constantly generating a feasible landing trajectory that optimizes factors such as fuel consumption.

Equipped with an autonomous flight safety system

During flight, the rocket itself monitors the trajectory and the durability of the vehicle, and if it detects any abnormalities it will take safety measures. It will decide whether to shut down the rocket or make an emergency landing.

ASCA

Carrying everyone’s hopes and dreams.

Latest info

Roadmap

2025 ASCA 1.0

2026 ASCA 1.1

2028 ASCA 1.2

Mission Highlights

Function Check Section

Cold Flow Test Spacecraft structure (excluding engine) and ground support equipment

HILs (Hardware In the Loop Simulation) Test Spacecraft structure and ground support equipment

Captative Fire Test Spacecraft structure and ground support equipment

GTV (Ground Test Vehicle) Spacecraft structure and ground support equipment

Flight Test Spacecraft structure and ground support equipment

2032 ASCA 2

2040 ASCA 3

Features

Speed up rocket development with our unique agile development platform.

Spacecraft manufacturing making maximum use of metal 3D printers

Crossing borders and collaborating with overseas companies to achieve rapid results and growth.

Employs model predictive control

Equipped with an autonomous flight safety system

Gallery