The increasing the mass of Mars landing probes requires enlarging the parachute area to ensure stable deceleration performance while controlling the parachute opening force to avoid excessive structural weight penalties on the probe. One of the effective ways to meet the above needs is the reefing disk-gap-band parachute. In this article, the functional link between the reefing ratio and the resistance coefficient ratio, projection area ratio, and reefing rope load is obtained using fluid-structure coupling simulation analysis based on the Mars environment. The stability characteristics of the reefing disk-gap-band parachute were studied by computational fluid dynamics simulation. The research of this paper shows that the disk-gap-band parachute can achieve the controlled change of resistance performance, and can provide stable performance to meet the engineering application.

With the development of aerospace engineering, the demand for the application of high-performance supersonic parachute with large area, high strength, low opening shock, and low weight and volume is becoming more and more prominent. Supersonic reefing technology is a possible way to meet the future demand, but research in this field remains limited both domestically and internationally. This paper studies the aerodynamic characteristics of supersonic disk-gap-band parachute in different reefing ways and different reefing ratios using the fluid-structure interaction method. The results show that when the mid-gore reefing parachute breaths, the disk keeps full and the band part expands and contracts irregularly. However, for the skirt reefing parachute, the band and disk part expand and contract together. For the aerodynamic characteristics of the parachute reefing, the drag coefficient and the projected area of the mid-gore reefing grow with the increase of reefing ratio, but the skirt reefing shows no obvious change.