Turbo-Rocket R A brand new class of hybrid rocket Rene Nardi and - - PowerPoint PPT Presentation

Turbo-Rocket

A brand new class of hybrid rocket

Rene Nardi and Eduardo Mautone

53rd AIAA/SAE/ASEE Joint Propulsion Conference –July 10–12, 2017 - Atlanta, Georgia

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Rumo ao Espaço

• UFC Team

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Background

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• Using liquid propellants rockets for educational purpose

has proven elusive for a very long time.

• Academic rocketry relies mostly on solid propellants, in

part to avoid the complexity of liquid propellants rockets.

• As long as the operation is restricted to the lower limits of

the atmosphere, airbreathing is an option worthing further investigation.

Atmosphere Layers

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5 km National Center for Atmospheric Research

Turbo Rocket

Why a liquid-gas hybrid ?

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The rocket should fly high enough to justify the efforts, but it may not have to leave the atmosphere. High subsonic speed is desirable, however, this rocket may not necessarily go supersonic. Jet engines are far simpler, safer and less expensive to operate than rockets.

 No cryogenic system to deal with: no liquid oxygen, no helium, no high pressure vessels.

Why a liquid-gas hybrid ?

LRE System TurboRocket System

The TurboRocket is a brand new class of flying machine

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It does not operate as a jet aircraft,

neither does it like a regular rocket.

JET AIRCRAFT TURBO-ROCKET Horizontal take off Near vertical take off Flies at the horizontal position Flies on the vertical At the same altitude Always changing altitude At constant speed Always changing velocity Engine power set to idle (cruise) Engine at full power

The TurboRocket is a brand new class of flying machine

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It does not operate as a jet aircraft,

neither does it like a regular rocket.

ROCKET TURBO-ROCKET Carries its working fluid in the form of fuel and oxidizer. Carries its own fuel, but relies on the surrounding atmosphere as the source of oxygen. It is capable of operating within or

• utside the atmosphere.

Operation limited to the confines

• f the lower atmosphere.

Thrust is not affected, much, by an increase in altitude. Noticeable thrust reduction as function of altitude. High propellant mass fraction ( 80 %) Low propellant mass fraction ( 5 % )

The TurboRocket is a brand new class of flying machine

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High Level Requirements

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• Design, build and launch a flying machine,
• To carry a 1 kg payload to 5 km ASL,
• Using a comerciall off-the-shelf turbojet engine,
• COTS electronics and sensors,
• With a composite structure (carbon fiber).

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Turbo-Rocket – overview

Turbo-Rocket in Details

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Nose Cone

Parachute Payload Flight Computer

Fins Fuselage

Fuel Tank Electronic Engine Control Unit Engine

Engine Cowling

A Turbojet Engine

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➢Total Weight of 2,6 kg for a Maximum Thrust of 300 N,

➢Nice thrust to weight ratio of 11:1

➢Liquid Rocket Engine at 30:1

➢Burning kerosene at a mass rate of 13 g/sec,

➢Specific Fuel Consumption of 1.6 lb/lbf.s

➢Liquid Rocket Engine at 10 lb/lbf.s.

A Turbojet Engine

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Jet-Cat 300

Engine Installation in Details

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Engine Installation Fuel Tank Installation

Performance simulations: Methodology

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➢Flight path divided into 3 portions 1 - Powered flight; 2 – Coasting; 3 - Descent

Performance simulations - Euler’s Method

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➢1 - Powered flight; ➢ Find the theoretical velocity and altitude increment, without drag, over a small interval of time. ➢ Add this theoretical increment to the velocity in the last interval and determine the drag. ➢ The drag is them substituted back into the original force equation and the actual velocity increment computed from the equation thus generated.

Performance simulations - restrictions

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Performance simulations: Equations

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Performance with 1 kg payload

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40 80 120 160 200 240 5 10 15 20 25 30 35 40 45 1000 2000 3000 4000 5000 6000

Speed ( m/s ) Fligth time (sec) Altitude ( m ) Altitude (m) Speed (m/s)

Performance simulations - results

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Specific Requirements I

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Altitude: 10,000 ft ( 3 km) Payload: 8.8 lb ( 4 kg ) Class: COTS Hybrid (liquid – gas)

20 40 60 80 100 120 140 160 500 1000 1500 2000 2500 3000 3500 4000 5 10 15 20 25 30 35

Altitude (m) Flight Time ( s ) Y(t) Altitude (m) V (t) Speed (m/s)

Spaceport America and IREC

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150 m/s

Powered Flight Coasting

What’s next ?

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• Incremental steps designed to improve the

concept and to, eventually, enhance performance.

• 1. Aerospike for a supersonic nozzle
• 2. Air intake design optimization to reduce drag
• 3. Afterburning, for higher speed and altitude
• 4. Thrust vectoring
• 5. Vertical landing

QUESTIONS ? Thank you.

Rene Nardi renenardi@hotmail.com +1 912 405 6453 +55 12 98251 8864