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Rocket | Innovative Space Carrier Inc. (ISC)

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.

Latest info

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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

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

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

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

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.

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.

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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.

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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.

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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.

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