High-fidelity trajectory design to flyby near-earth asteroids using cubesats
| Autor: | Gerard Gómez, Joan Pau Sánchez, Josep J. Masdemont, Pablo Machuca |
|---|---|
| Přispěvatelé: | Universitat Politècnica de Catalunya. Departament de Matemàtiques, Universitat Politècnica de Catalunya. SD - Sistemes Dinàmics de la UPC, Cranfield University, European Commission |
| Jazyk: | angličtina |
| Rok vydání: | 2020 |
| Předmět: |
Asteroides
CubeSats Computer science Aerospace Engineering Lagrangian point Thrust 02 engineering and technology Ephemeris 01 natural sciences 0203 mechanical engineering Interplanetary CubeSats 0103 physical sciences Three-body problem Lagrange points CubeSat Sun-Earth Lagrange points Aerospace engineering 010303 astronomy & astrophysics Sun-Earth 020301 aerospace & aeronautics Problema dels tres cossos Near-Earth object business.industry Artificial satellites Matemàtiques i estadística [Àrees temàtiques de la UPC] Low-thrust trajectories Interplanetary Near-Earth asteroids Dynamics Satèl·lits artificials Asteroid Dinàmica Trajectory Interplanetary spaceflight business Trajectory design |
| Zdroj: | Digital.CSIC. Repositorio Institucional del CSIC instname UPCommons. Portal del coneixement obert de la UPC Universitat Politècnica de Catalunya (UPC) |
| Popis: | Fast development of CubeSat technology now enables the first interplanetary missions. The potential application of CubeSats to flyby near-Earth asteroids is explored in this paper in consideration of CubeSats' limited propulsive capabilities and systems constraints. Low-energy asteroid flyby trajectories are designed assuming a CubeSat is initially parked around to the Sun-Earth Lagrange points. High-impulse and low-thrust trajectories with realistic thrusting models are computed first in the Circular Restricted Three-Body Problem (CR3BP), and then in a high-fidelity ephemeris model. Analysis in the ephemeris model is used to confirm that trajectories computed in the CR3BP model also exist in a more realistic dynamical model, and to verify the validity of the results obtained in CR3BP analysis. A catalogue of asteroid flyby opportunities between years 2019 and 2030 is provided, with 80 m/s of available ΔV and departure from halo orbits around the first and second Sun-Earth Lagrange points (of similar size to those typically used by scientific missions). Results show that the CR3BP model can serve as an effective tool to identify reachable asteroids and can provide an initial estimation of the ΔV cost in the ephemeris model (with ±15 m/s accuracy). An impulsive maneuver model can also provide an accurate estimation of the ΔV requirement for a CubeSat equipped with a high-impulse thruster (with 4 m/s accuracy), even if its thrust magnitude is small and requires duty cycling; low-thrust ΔV requirements, however, may differ significantly from the impulsive results (±15 m/s). Funding was provided by Cranfield University’s European Partnership Programme (2016–2017, United Kingdom). |
| Databáze: | OpenAIRE |
| Externí odkaz: |
|