SMALL SATELLITE LAUNCH VEHICLE
Ensuring your small satellite reaches the orbit you desire with flexible space transportation services, including dedicated launches and ridesharing, all on your schedule.
Provide on-demand transport to the desired orbit and altitude, which is difficult to achieve with shared transport of large satellites. Significantly reduce the time from contract to launch by integrating in-house design, manufacturing, test and launch, and by developing a mass production system.
Tailored Solutions for
Customize the system to meet customer needs and handle sudden changes. Our flexible response ensures high customer satisfaction.
Offer one of the lowest prices in the small satellite launch market. Strive for dramatic price reductions through in-house development of core technologies and active use of cutting-edge technologies such as consumer grade components and 3D printing.
- MAX PAYLOAD WEIGHT
- LEO 800kg
- TOTAL WEIGHT
- 71 tons
- Fuel: Liquid Methane
Oxidizer: Liquid Oxygen
Made of CFRP (carbon fiber reinforced plastic). Protects the payload.
- 2.PAYLOAD SECTION
The part which carries the satellites.
- 3.SECOND STAGE TANK
Tanks for liquefied methane and liquid oxygen. Made of aluminum alloy.
- 4.SECOND STAGE ENGINE
Engine to reach orbit. Engine to reach orbit.
Has a high expansion ratio nozzle.
- 5.FIRST STAGE TANK
Supplied with tanks for liquid methane and liquid oxygen. Made of aluminum alloy. Jettisoned mid-flight with the first stage engines.
- 6.FIRST STAGE ENGINE
Engines to reach space, consisting of 9 engines with a thrust of 130 kN (about 13 tons) per engine. A regenerative cooling and turbopump system is used. To reduce weight, they are jettisoned mid-flight.
- 7.ATTITUDE CONTROL SYSTEM
The gimbal mechanism changes the direction of the engine and controls the direction of thrust. This controls the attitude of the rocket.
Equipped with computers, sensors, and communication devices for rocket control.
The aluminum core material is sandwiched between CFRP (carbon fiber reinforced plastic).
Rocket engines often make up half of the total manufacturing costs. Introducing innovative manufacturing technology and design approaches, IST's engines have been developed with remarkable cost-effectiveness compared to conventional rocket engines, while maintaining high-performance capabilities and facilitating mass production.
The disadvantage of the pintle injector, which makes it difficult to achieve sufficient performance, has been drastically improved through design innovations. The number of parts is reduced to one-tenth of conventional engines, while achieving high combustion efficiency.
Innovative, patent-pending wire-wrapping manufacturing technology enables fast delivery and low cost.
We have developed our own components at low cost and actively use the latest technologies such as 3D printing.
The propellant is liquid methane, which has good performance and is inexpensive. Methane is relatively easy to handle, which makes it excellent for rocket manufacturing and operation. In addition, liquid biomethane, which is liquid biogas produced from cattle manure, is used to contribute to carbon neutrality. This contributes to environmentally friendly development by eliminating the problem of foul odors caused by cow manure, as well as local production for local energy consumption.
Utilizing advanced aluminum welding technology, the fabrication of propellant tanks incorporates an in-house production process that encompasses design, manufacturing, and testing. This comprehensive approach ensures the achievement of cost reduction in the final product.
The gimbal mechanism responsible for controlling the direction of the engine jets is a mechatronic component requiring advanced technology. This component is also utilized in Interstellar's suborbital launch vehicle MOMO.
Interstellar's in-house production covers avionics hardware and software. Semiconductor technology from the automotive and general industrial sectors, combined with state-of-the-art technologies like 3D printing, enables lightweight and cost-effective component development.