2 results about "Atmospheric entry" patented technology

This invention discloses a civilian rocket capsule recovery device with prefabricated slotted skin and convection deceleration and attitude stabilization, belonging to the field of civilian rocket recovery technology. The rocket's ascent phase is completed in a high-altitude vacuum environment. After separation, the rocket body immediately deploys its forward-facing, trumpet-shaped cross-shaped parachute in the vacuum environment and stabilizes, preventing damage from strong airflow upon atmospheric entry. The parachute slots create four straight airflow paths, constraining the descent trajectory and achieving a vertical, straight, and stable descent. This invention employs a top-priority unlocking and progressive, step-by-step separation structure, utilizing airflow thrust and the propulsion module's tail weight for natural attitude adjustment. The fuel tank's inner wall has guide holes to allow for opposing airflows inside and outside the capsule, offsetting descent kinetic energy and reducing drift speed. The propulsion module contains a dedicated recovery ring drive mechanism and an extendable propeller, enabling active attitude adjustment and speed control; in clear weather, the propeller facilitates slow descent, while in severe weather, the rocket's main engine assists in stabilizing speed and deceleration. This invention solves the shortcomings of traditional parachute wings, such as easy damage, lack of guidance, loss of attitude control, and poor deceleration effect. It is adaptable to multiple weather conditions, and the recovery is stable and safe, providing a brand-new technical solution for low-cost and controllable recovery of civilian rockets.

The application discloses a preset time trajectory tracking control method for a planetary probe under input saturation. The method comprises the following steps: establishing an initial dynamic model of the planetary probe in an atmospheric entry section; setting a reference radial distance of the planetary probe; determining an initial height tracking compensation error and a first-order height tracking compensation error of the planetary probe based on an actual radial distance in the initial dynamic model and the reference radial distance; obtaining a second-order height tracking compensation error based on the initial dynamic model, the initial height tracking compensation error and the first-order height tracking compensation error; and setting an initial sliding mode variable, processing the initial sliding mode variable, and obtaining a first-order sliding mode variable. The application solves the technical problem that the planetary probe cannot achieve high-precision landing within a preset time in a complex space environment.