Hapith T
PAYLOAD

Feature

The payload fairing of Hapith V is constructed by using lightweight composite honeycomb sandwich structure with ample thermal and environmental protections.

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MATERIALS

Feature

Hapith V is designed to be constructed using mainly lightweight high strength carbon composite flight structure.

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AVIONICS

Feature

TiSPACE avionics and GNC flight control subsystem are developed simultaneously such that their performance can be checked and verified through real time simulations with the enhancement of a high precision rate table testing platform.

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LELIEN

Feature

LELIEN engine is designed based on a high-efficiency N2O/SBR hybrid rocket technology with specially formulated high density and high energy SBR solid grain and N2O injection scheme that gives our propulsion system close to ideal overall thrust performance.

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HAPITH V 
is a cost-effective space launch system using cutting-edge, non-explosive hybrid rocket technologies. Our hybrid rocket engines are delivering class-I rocket engine performance that enables fast turnaround space launch services.

PAYLOAD

MICRO AND SMALL SATELLITES TO LOW EARTH ORBIT (LEO) AND SUN-SYNCHRONOUS ORBIT (SSO)

HAPITH V OVERVIEW

MAX. LEO PAYLOAD MASS
390 KG

MAX. SSO PAYLOAD MASS
350 KG

ALTITUDE
600 – 700 KM

HEIGHT
20 M

DIAMETER
2.2 M

STAGES
3

UPPER STAGE

single hybrid rocket engine with gimbaled thrust vector control (TVC) and a cold-gas reaction control system (RCS)

THRUST  10KN

SECOND STAGE

cluster of four hybrid rocket engines with gimbaled thrust vector control (TVC)

THRUST  80KN

FIRST STAGE

cluster of five hybrid rocket engines with liquid-injection vector control (LITVC)

THRUST  650KN

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