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
HTTP-3AT
The HTTP-3AT is an experimental vehicle designed to test the Guidance, Navigation, and Control (GNC) system of the HTTP-3A suborbital launch vehicle. It is equipped with four Sam-á-Tsiáu Engines, same as the second stage of the HTTP-3A. These engines have four main throttle valves and thrust vector control actuators, enabling the HTTP-3AT to adjust both the magnitude and direction of thrust, providing the rocket with full control of its position and attitude during flight. The HTTP-3AT and HTTP-3A share a modular and distributed avionics system, featuring various subsystems such as the flight computer, guidance module, telemetry module, and electronic power system modules. The modular and distributed avionics system enables rapid iteration and testing of various subsystems before they are deployed in the operational HTTP-3A suborbital launch vehicle.
HTTP-4
To achieve precise flight control technology for hybrid rockets, we develop the following technologies and verify them using various methods:
- Demonstrating the flight control ability of the HTTP-4 rocket through vertical takeoff and vertical landing flight tests.
- Verifying the robustness of the throttle valve by subjecting it to varying pressures from the blow-down type oxidizer tank.
- Thrust vector control is achieved by gimballing the engine, which is controlled by two direct-drive servo motors.
- Utilizing two cold gas vernier thrusters to control the rocket's roll axis.
- During hovering, we demonstrated attitude and position control capabilities.
HTTP-3A
HTTP-3AT
HTTP-4
