UCI Rocket Project2015-2016

BackgroundTraditional CubeSat launch cost:

$12,500/kg to as much as $2,000,000/kg

Traditional mesosphere research launch costs:~$4,500/kg to ~$40,000/kg.

UC San Diego, Portland State University, and USC are vying to be the first university to reach space

Project Goal:

Reduce the cost of mesosphere launches by 400% and CubeSat launches by 20%, and be the first University to launch a rocket into space (100km) by using a Rockoon System.

Rockoon: Balloon-Based Rocket High-Altitude Launch Platform

Disadvantages:

1. Drift Problem --- Ram-Air Parachute

Precision Landing System

1. Stability of Platform --- Gimbal

System

1. Cost of lifting Gas --- Solar Balloon &

Lightweight Design

Advantages:

1. Significantly reduce launch cost

• Traditional Launch: $4,500 / kg

• Rockoon Launch: $900 / kg

(Mesosphere)

2. Reach higher altitude

• Rockoon system lifts rocket up to 65,000 ft

before rocket ignition.

• Prototype 2 Rocket sea level launch: 3,000 ft

• Prototype 2 Rocket high altitude launch:

8,200 ft

Objectives for UCIRP 2015-2016

• Rockoon prototype 2 high altitude test (65,000ft)

Test structure and avionics system at high altitude

• Hybrid engine static fire test

Verify engine performance for future orbital launch

• Develop prototype of precision landing system

• Develop prototype of gimbaled thrust active stabilization system

• Design hybrid engine rocket capable of active thrust vector control and stabilization

Team Structure

Project Overview

Balloon Launch Hybrid Rocket Subsystems

Balloon Launch

Proof Concept: Prototype 1 Test

Prototype 1 Design Prototype 2 Design

Passive Gimbal Stabilized Launcher:

●Solution of stability problem

Truss Structure● Reduce the bending moment in balloon holding arms

● Limit the maximum rotation angle of gimbal

Rockoon Platform Prototype 2

Gimbal for prototype 2 Prototype 2 rocket

Solar Balloon VersionSolution of high cost of helium

Hybrid Rocket

Hybrid Rocket

• Engine Assembly (High Density Polyethylene and

Liquid Oxygen)

• Isp = 286s at launch

• Ablatively cooled, 4-engine configuration

• Sounding Rocket: 270 km (ΔV = 2.21 km/s, Dry Mass =

47.8%)

• Orbital Launch: ~150 km circular orbit (ΔV = 7.91 km/s, Dry

Mass = 7.1%)

• Design improvements for mass reduction and cost savings

• Liquid Oxygen vs. Nitrous Oxide (volume of oxidizer tank

required)

• Carbon composite oxidizer tank

• Carbon composite combustion chamber and nozzle

• Pressurization system- Gaseous Oxygen vs. Helium

Hybrid Engine Systems

• Liquid Oxygen Injector

• Fuel Grain

• High Density Polyethylene

• Pattern designed for maximum surface area and

minimal wasted fuel at burn out

• Composite Combustion Chamber and Nozzle

• Carbon/graphite insulation and ablative liner

Hybrid Engine Systems

Combustion Chamber and Nozzle MoldLiquid Oxygen Injector

Plumbing Systems

• Liquid Oxygen Tanks

• Low mass (liner-less carbon overwrapped

pressure vessel)

• Gaseous Oxygen Pressurization System

• Replace high pressure helium system (safety and

mass considerations)

• Complications:

• Gathering necessary data to actively control

engines and protect hardware

Flight Propellant System

Static Test Stand Systems

• Propellant System

• Maximize utilization of every component in

both systems

• Minimize long term costs

• Considerations:

• Capable of handling different engine sizes

and thrust levels

• Data Acquisition:

• Gather data on engine performance in order

to optimize the design for increased Isp

Static Test Stand

Propellant System

Static Test Stand

Subsystems

Precision Landing SystemSolution of drift problem

• Ram-air parachute to steer

• Using PID control theory

• First testing with RC car

• Starting with APM 2.6

• Ardurover (open source)

• Switching to Arduino

Precision Landing System

• Steerable Ram-Air Parachute

• Wireless camera with on screen display of real time flight data

Rockoon System Prototype 2 Avionics

• Fail-Safe Algorithms

• XTend 900 S1 RF Module: 40 miles communication range

• IMU: Measures the orientation of the platform

• TMP36 Temperature Sensor: Thermal management

• GSM Module: Send GPS coordinates through text message.

• GPS: Speed, heading, altitude, location

Avionics system prototype Recovery system

Gimbaled Thrust(Active stabilization system for rocket)• Using PID control theory

• Based on calculated model of rocket

• Two servos to control gimbal

Recent High Altitude Test

Flight Predictions

Cambridge University

University of

Michigan

Our Flight

Prediction

Project Phase Start End

Research/UROP Proposal 09/24/2015 11/02/2015

Design 09/24/2015 12/11/2015

Purchase 12/11/2015 01/04/2016

Fabrication 01/04/2016 03/18/2016

Avionics High Altitude Test 04/17/2016 05/08/2016

Report/Optimization 03/23/2016 06/10/2016

Rockoon System Prototype 2

Test

06/04/2016 06/04/2016

Hybrid Engine Static Fire Test 06/10/2016 06/20/2016

Project Timeline:

Questions?