Green rocket propulsion system

Green Rocket Propulsion System

Descoberta Ofuscante LDA

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Market Opportunity for an Eco-Friendly Propulsion System

Rapidly growing access to space market:

2021

2030

Small Sat launches exponential growth:

launched in 2011-2020

planned to be launched by 2030

There is a strong demand for reliable and cost-efficient engines to enhance orbital placement capabilities of light launcher developers (launchers’ main and kick-stages) and LEO mission integrators, while meeting the ever more stringent space debris mitigation requirements: ESA (ISO 24113:2010) and NASA (2009, NPR 8715.6A).

Innovative Space Technology Capitalizing on the Heritage R&D

Use of standard devices and modular control systems.

Fuel-supply with gas pressure without the turbopump.

The simple chemistry of the propellant components and lower engine temperatures ensure more reliable use than with traditional ones, minimising the time& expense to operations.

Re-profiled for use in orbit transport systems (versatile on-orbit uses).

Heritage issues preventing hydrogen peroxide-powered launchers from achieving orbit are solved (2 patents).

Disruptive, Green Space Launch Capability +

Our propulsion system:

Uses non-explosive fuel components, enabling rockets to be stored fully fuelled at spaceports, ready to go.
Uses non-toxic propellants (50% less carbon-emission than typical launch systems).
Is at least 60% cheaper in re-use than incumbents.
Is simple and reliable (few working parts) - less delayed launches.

The motivated core team

Сomprises rocketry designers, operators and business developers that worked together for years on orbital transport systems and the reusable rocket-space complex (Green Space)

Unique, protected IP and know-how

Enable the company to be the 1st globally to use hydrogen-based fuel launch technology to reach LEO; ready to enhance the IP protection.

GS-10H: Optimal Parameters

Thrust, F, kN	98
Specific impulse in vacuum, I∞p, s	338,4
Specific impulse at sea level, Ip, s	291,3
Maximum weight, М, kg	100
Engine total length, LΣ_к, m	1,62
Maximum engine width, m	0,86
Fuel components (highly concentrated water solutions)	Н₂О₂ (98%) + С₂Н₅ОН (99,9%)
Fuel consumption by weight, G, kg/s	37,1
Temperature in the combustion chamber, T, °K	2238-2580
Temperature at the exit of the nozzle, T, °K	464,4
Combustion chamber pressure, P, Mpa	19,61
High-altitude Laval split nozzle with automatic quality control	depending on the altitude

Key Milestones to be Achieved Through the Incubation in Portugal

Enhancing the unique technologies’ IP protection - evaluate the technology and protect it globally.

Developing the engine mock-up - modern laboratory and testing equipment needed.

Preparing the development of the complex program of experimental trials - technical advice on ESA standards needed

Mapping the potential suppliers, subcontractors, strategic partners and customers in Portugal and globally - ”reaching out of the box”.

Developing the investor pitch-deck - access to investors in Portugal in connection with the Azores spaceport program and globally.

Our Business Strategy

;

Immediate

(2022-2023)

Pre-Seed - Soft landing in Portugal, locate proper R&D and office base with an incubator; develop the Laboratory Model and overall construction design, issue technical documentation, etc.

;

Short-term

(2023-2024)

Seed (up to 1ME) - build the Qualification Model; locate industrial partners; A-Series Round (2ME) - Demonstration Mission; Go public after the 1st successful fire trial (we have investment funds interest) to maintain momentum to the 1st launch.

;

Mid-term

(2025-2026)

B-Series Round - establish the JV to serially produce the engines.develop next generation of engines for orbital transport.

;

Long-term

(2027-2028)

C-Series Round - Integrate with a rocket-space complex, set up a mission integrator, enabled with own orbital fleet and mission control center.