Analytical results for solar sail optimal missions with modulated radial thrust

Quarta, Alessandro A.; Mengali, Giovanni

doi:10.1007/s10569-010-9319-x

Cited by 12 publications

(10 citation statements)

References 30 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As far as photonic solar sails are concerned, such a methodology of trajectory control is usually referred to as ''b-control", and its effectiveness has been studied in several missions scenarios, including orbital transfers (McInnes, 2003;Yamakawa, 2006;Quarta and Mengali, 2011) as well as for generation and control of artificial equilibrium points (Biggs and McInnes, 2010;Aliasi et al, 2012;Aliasi et al, 2014). The main drawback of such a control means is due to the purely radial nature of the propulsive acceleration, which is therefore unable to change the spacecraft orbital plane, nor the SD angular momentum.…”

Section: Smart Dust Heliocentric Dynamicsmentioning

confidence: 99%

“…The mirror counterpart of the previous control law should instead be used in order to minimize the time-variation of semimajor axis, which corresponds to turning the electrochromic system on when the SD is approaching the Sun. It is worth noting that, as is discussed by Quarta and Mengali, 2011, the control strategy of Eq. (32), when applied to a Sun-facing photonic solar sail, is also globally (not only locally) optimal, as it maximizes the time variation of the mechanical energy in a given time interval.…”

Section: Periodic B-controlmentioning

confidence: 99%

See 1 more Smart Citation

Heliocentric trajectory analysis of Sun-pointing smart dust with electrochromic control

Mengali

Quarta

2016

Advances in Space Research

Self Cite

View full text Add to dashboard Cite

Section: Smart Dust Heliocentric Dynamicsmentioning

confidence: 99%

Section: Periodic B-controlmentioning

confidence: 99%

Heliocentric trajectory analysis of Sun-pointing smart dust with electrochromic control

Mengali

Quarta

2016

Advances in Space Research

Self Cite

View full text Add to dashboard Cite

“…The maneuvering time was extremely short, and the thrust direction remained relatively stable, making these scenarios practically achievable in space operation. For a continuous variable thrust, Quarta and Mengali 10 analyzed the optimal trajectories of a spacecraft subjected to a modulated radial thrust, with a magnitude inversely proportional to the square of the distance from the primary body. When the thrust is constant in magnitude and directed radially, some interesting mathematical results can be obtained.…”

Section: Introductionmentioning

confidence: 99%

Optimal control of rapid cooperative spacecraft rendezvous with multiple specific-direction thrusts

Feng

Yang

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Focusing on the long-distance rapid cooperative rendezvous of two spacecraft under finite continuous thrust, this paper proposes a practical strategy for space operation using multiple specific-direction thrusts. Based on the orbital dynamic theory and Pontryagin’s maximum principle, the dynamic equations and optimal control equations for radial, circumferential, and normal thrust are determined. The optimization method is a hybrid algorithm. The initial costate variables for the fuel-optimal rapid cooperative rendezvous problem are obtained using quantum particle swarm optimization and subsequently set as the initial values in the sequence quadratic programming to search for the exact convergent solution. The elliptical and near-circular mission orbital rendezvous for spacecraft with multiple specific-direction thrusts are simulated and optimized. Numerical examples verifying the proposed method are provided. The results facilitate easier realization of rapid spacecraft maneuvering under continuous thrust conditions.

show abstract

“…Interestingly, whatever formats the potentials are, and despite the differences in mathematical expressions, analogous rosette-shaped bounded orbits always rise under the specific conditions. Moreover, potentials in some special cases are also equivalent to be spherically symmetric, among which are the radial acceleration problems for orbital transfers in spacecrafts mission design [3][4][5][6][7][8][9][10][11][12][13][14], and the problems of a particle in equatorial orbits considering the 2 term studied by some researchers recently [15][16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Fourier Series Approximations toJ2-Bounded Equatorial Orbits

Wang

Yuan

Zhao

et al. 2014

Mathematical Problems in Engineering

View full text Add to dashboard Cite

The current paper offers a comprehensive dynamical analysis and Fourier series approximations ofJ2-bounded equatorial orbits. The initial conditions of heterogeneous families ofJ2-perturbed equatorial orbits are determined first. Then the characteristics of two types ofJ2-bounded orbits, namely, pseudo-elliptic orbit and critical circular orbit, are studied. Due to the ambiguity of the closed-form solutions which comprise the elliptic integrals and Jacobian elliptic functions, showing little physical insight into the problem, a new scheme, termed Fourier series expansion, is adopted for approximation herein. Based on least-squares fitting to the coefficients, the solutions are expressed with arbitrary high-order Fourier series, since the radius and the flight time vary periodically as a function of the polar angle. As a consequence, the solutions can be written in terms of elementary functions such as cosines, rather than complex mathematical functions. Simulations enhance the proposed approximation method, showing bounded and negligible deviations. The approximation results show a promising prospect in preliminary orbits design, determination, and transfers for low-altitude spacecrafts.

show abstract

Analytical results for solar sail optimal missions with modulated radial thrust

Cited by 12 publications

References 30 publications

Heliocentric trajectory analysis of Sun-pointing smart dust with electrochromic control

Heliocentric trajectory analysis of Sun-pointing smart dust with electrochromic control

Optimal control of rapid cooperative spacecraft rendezvous with multiple specific-direction thrusts

Fourier Series Approximations toJ2-Bounded Equatorial Orbits

Contact Info

Product

Resources

About