HTTP-3A
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
2. Telecommunication System
Downlink: 900MHz
Uplink: 433MHz
Image transmission distance: 50km
Data transmission distance: 150km
4. Recovery System
Main chute
Cruciform parachutes
Drogue chute
Pulled-down apex (PDA)
5. Light-Weight Structure
N2 Pressure Tank (2nd class)
Carbon fiber winded
Aluminum liner
Working pressure: 300 barA
H2O2 Running Tank (3rd class)
Carbon fiber winded
HDPE liner
Working pressure: 60 barA
N2O Pressure Tank
Carbon fiber composite
Working pressure: 70 barA
Nosecone & Out-casing
Carbon & glass fiber composites
Inner Structure
Carbon fiber composite + Aluminum alloy
Stage Separation System
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
CubeSat
5 U CubeSat & Quantum communication
Scientific Payload
High dynamic twin-antenna GPSR
3. Avionic System
Flight Computer
ARM-based
Hard RTOS
Attitude Sensor
GPSR + IMU + RTK
Attitude Control
Latch valve control
Throttling valve control
TVC control
6. 2nd Stage Propulsion System
Sam-á-tsiáu Engines
Throttleable system
3D metal printing
Vacuum thrust: 150 kgf x 4
Vacuum Isp: 305 s
Burning time: > 60 s
DD-TVC System
Swing angle: +/- 20˚
Angular accuracy: 0.05˚
Angular rate: > 15˚/s
7. 1st Stage Propulsion System
Tsuâ-ing Engine
Sea-level thrust level: 10 KN
Full thrust burning time: 60 sec
Sea level Isp: 230 s
Sam-á-tsiáu Engines
Throttleable system
3D metal printing
Sea-level thrust: 120 kgf x 4
Sea-level Isp: 242 s (Stage-1)
Burning time: > 60 s
DD-TVC System
Swing angle: +/- 20˚
Angular accuracy: 0.05˚
Angular rate: > 15˚/s
4-help
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.
PROTOTYPING UPPER-STAGE ENGINE SYSTEM
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
HTTP-3A
4-help
UPPER
STAGE
STAGE
