To develop necessary satellite LV technologies by:

  • Designing & performing a flight test of a sounding rocket, HTTP-3A, carrying payloads with Apogee > 100 km
  • Applying Hybrid² Propulsion Technology with modularized engine design concept
  • Performing autonomous control of flight attitude & trajectory during powered ascending phase
  • Performing advanced payload experiments: CubeSat with Quantum Communication Experiment
HTTP-3A Flight Test-2
LV 6
LV 5
HTTP-3A Flight Test
1st Stage Flight Test (HTTP-3A S1)
LV 4
LV 3
glow level
2nd Stage Flight Test (HTTP-3A S2)
2nd Stage Tethered Flight Test (HTTP-3AT)
LV 2
glow level
LV 1
glow level
2nd Stage Vertical Hot-Fire Test

2. Telecommunication System

Downlink: 900MHz
Uplink: 433MHz
Image transmission distance: 50km
Data transmission distance: 150km

4. Recovery System

Cruciform parachutes
Pulled-down apex (PDA)

5. Light-Weight Structure

Carbon fiber winded
Aluminum liner
Working pressure: 300 barA
Carbon fiber winded
HDPE liner
Working pressure: 60 barA
Carbon fiber composite
Working pressure: 70 barA
Carbon & glass fiber composites
Carbon fiber composite + Aluminum alloy
Explosive bolt
Hot staging (fire-in-the-hole)

8. Web-based Visualization System

An interactive web-based browser for visualizing rocket motion is developed in this project with the use of Google Earth API, Cesium API, jQuery and DHTMLX.

1. Payload System

5 U CubeSat & Quantum communication
High dynamic twin-antenna GPSR

3. Avionic System

Latch valve control
Throttling valve control
TVC control

6. 2nd Stage Propulsion System

Throttleable system
3D metal printing
Vacuum thrust: 150 kgf x 4
Vacuum Isp: 305 s
Burning time: > 60 s
Swing angle: +/- 20˚
Angular accuracy: 0.05˚
Angular rate: > 15˚/s

7. 1st Stage Propulsion System

Sea-level thrust level: 10 KN
Full thrust burning time: 60 sec
Sea level Isp: 230 s
Throttleable system
3D metal printing
Sea-level thrust: 120 kgf x 4
Sea-level Isp: 242 s (Stage-1)
Burning time: > 60 s
Swing angle: +/- 20˚
Angular accuracy: 0.05˚
Angular rate: > 15˚/s


4-HELP is designed to achieve platform levitating and flying which only relies on hybrid rocket thrust throttling control propulsion technology.

4-HELP is capable of producing a maximum thrust of 240 kgf from four rocket engines which each creates 60 kgf of thrust. It consists of four combustion chambers, four running tanks, and two common pressurant tanks. Since torque is a necessity for yawing, due to the insufficient torque supplied by the engines, cant angle installation is applied to all four engines of 4-HELP. Nitrogen is used to pressurize the oxidizer stored in the running tanks. 90% concentrated hydrogen peroxide is used as the oxidizer, and plastics as fuel.


To develop necessary upper-stage technologies of satellite LV by:

  • Designing & performing & demonstration a tethered hovering flight test of a "HTTP-UPS" hybrid rocket upper stage system
  • Applying super lightweight single tank single hybrid rocket engine with dual DD-TVC system design concept
  • Applying dual movable RCS system
  • Performing autonomous control of flight attitude & position during hovering flight test