Advanced solar sailing has been an increasingly attractive propulsion system for highly non-Keplerian orbits.Three new applications of the orbital angular momentum reversal(H-reversal) trajectories using solar sails are presented:space observation,heliocentric orbit transfer and collision orbits with asteroids.A theoretical proof for the existence of double H-reversal trajectories(referred to as‘H2RTs’) is given,and the characteristics of the H2RTs are introduced before a discussion of the mission applications.A new family of H2RTs was obtained using a 3D dynamic model of the two-body frame.In a time-optimal control model,the minimum period H2RTs both inside and outside the ecliptic plane were examined using an ideal solar sail.Due to the quasi-heliostationary property at its two symmetrical aphelia,the H2RTs were deemed suitable for space observation.For the second application,the heliocentric transfer orbit was able to function as the time-optimal H-reversal trajectory,since its perihelion velocity is a circular or elliptic velocity.Such a transfer orbit can place the sailcraft into a clockwise orbit in the ecliptic plane,with a high inclination or displacement above or below the Sun.The third application of the H-reversal trajectory was simulated impacting an asteroid passing near Earth in a head-on collision.The collision point can be designed through selecting different perihelia or different launch windows.Sample orbits of each application were presented through numerical simulation.The results can serve as a reference for theoretical research and engineering design. Advanced solar sailing has been an attractive for propulsion system for highly non-Keplerian orbits. New applications of the orbital angular momentum reversal (H-reversal) trajectories using solar sails are presented: space observation, heliocentric orbit transfer and collision orbits with asteroids. A theoretical proof for the existence of double H-reversal trajectories (referred to as 'H2RTs') is given, and the characteristics of the H2RTs are introduced before a discussion of the mission applications. A new family of H2RTs was obtained using a 3D dynamic model of the two-body frame. In a time-optimal control model, the minimum period H2RTs both inside and outside the ecliptic plane were examined using an ideal solar sail. Due to the quasi-heliostationary property at its two symmetrical aphelia, the H2RTs were deemed suitable for space observation. For the second application, the heliocentric transfer orbit was able to function as the time-optimal H-reversal trajectory, since its perihelion velocity is a circular or elliptic velocity. Such a transfer orbit can place the sailcraft into a clockwise orbit in the ecliptic plane, with a high inclination or displacement above or below the sun. third of the H-reversal trajectory was simulated impacting an asteroid passing near Earth in a head-on collision. The collision can be designed by selecting different perihelia or different launch windows. Sample orbits of each application were presented through numerical simulation. The results can serve as a reference for theoretical research and engineering design.