Conceptual design of a nanolauncher based aerospike nozzle to send CubeSats from Mexico.

Paper number

IAC-19,D2,7,4,x51521

Author

Mr. Irving Enrique Gomez Fernandez, Mexico

Coauthor

Mr. Julio Alberto Ramos Meza, Mexico

Coauthor

Mr. J.Antonio Carmona Carlos, Mexico, Space Generation Advisory Council (SGAC)

Coauthor

Mr. Manuel Alejandro Arteaga Aleman, Mexico

Coauthor

Mr. Victor Flores, Mexico

Year

2019

Abstract

The low cost, the simple design and the ease to build a CubeSat nanosatellite represents for scholars, scientists and even enthusiasts, a great opportunity to reach outer space. However, the costs to place a nanosatellite in orbit are expensive because they are carried as piggyback into bigger satellites (more than 1000 kg), which is a limitation. The required budget to launch a satellite of that dimensions start from 50 to 500 million dollars. The cost depends on the satellite mass. The launch per kg to LEO requires an estimated investment of \$10,000 dollars.\\

Nowadays in Mexico, through its space research agency, AEM (Mexican Space Agency) in collaboration with other research institutions, such as CENTA (National Centre for Aeronautical Technologies), want to build and send CubeSats for earth observation and analysis from space, by creating small rockets to launch nanosatellites; with the purpose of a medium term to have the infrastructure to make launches in Mexico. This implies a considerable difference in budget, being able to allocate funding to  research, production and trade of nanosatellites, to be destined to make the nanolauncher in  our country. \\

This paper proposes a conceptual design of a two stage microrocket based on an aerospike nozzle capable of transporting up to three CubeSats of 1U or other configurations in LEO (Low Earth Orbit), contained in a P-POD (Poly-Picosatellite Orbital Deployer) device whose maximum payload mass is 5 kg. The structural design of the rocket is being done with CAD software assigning geometrical and aerodynamic parameters. For the RLC (Rhumb Line Control) a LQG (Gaussian Quadratic Linear) controller is proposed using a gimbal, control simulations will be integrated with the structural design. The development of a recovery system for the reuse of the rocket model is also desired. \\

The conceptual design was made based on the technical specifications of the SS- 520-5 and the Electron rockets. The main characteristics of these rockets are: 

\begin{itemize}
\item The SS-520-5 rocket with a length of 9.54 m developed by JAXA (Japan Aerospace Exploration Agency), is the smallest rocket that has sent a payload, a 3U CubeSat with a mass of 3 kg, in an orbit of 190 x 2000 km in height. 
\item The Electron rocket, developed by Rock Lab from USA and New Zealand, with a length of 17 m and payload capacity from 150 to 250 kg. 
\end{itemize}

Abstract document

IAC-19,D2,7,4,x51521.brief.pdf

Manuscript document

IAC-19,D2,7,4,x51521.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.