Fully-protected flexible unfolding re-entry aeroshell

Abstract

The invention discloses a fully-protected flexible unfolding re-entry aeroshell comprising a load capsule main body. A rigid thermal protection blunt nose is connected to the lower end of the load capsule main body. A sliding connecting frame is installed at the upper end of the load capsule main body. A head cover is arranged at the top of the sliding connecting frame. Hinged seats and threaded hole bearings are arranged at the connection between the load capsule main body and the rigid thermal protection blunt nose. The hinged seats are connected with the lower parts of lower support bars. The upper parts of the lower support bars are connected with the lower parts of upper support bars. The upper parts of the upper support bars is connected with the sliding connecting frame. A leeward side flexible thermal protection structure and a windward side flexible thermal protection structure are respectively connected to the upper support bars and the lower support bars. The fully-protected flexible unfolding reentry aeroshell uses a connecting-bar unfolding mechanism and adds the leeward side flexible thermal protection structure, thereby not only reducing the requirement of the fairing envelope of a launch vehicle and avoiding the impact of the inflow/shock wave on the rear-end of the aeroshell, but also improving the flight environment and increasing the loading volume to provide a technological path for the entrance, deceleration and landing of future load extraterrestrial asters.

Description

technical field [0001] The invention belongs to the technical field of spacecraft entry and return, and in particular relates to a full-protection flexible deployable reentry reducer. Background technique [0002] At present, the reducer structures with ballistic or semi-ballistic re-entry capabilities in the world mainly include the traditional rigid fixed type and the new flexible expansion type. For the traditional rigid fixed reducer, the advantage is that the heat-proof structure is attached to the entire outer surface to fully protect the reducer. Under the premise of this full-protection structure, the center of mass of the reducer can be deviated from the central axis design , to generate a trim angle of attack greater than 0°, so that the reducer has a certain lift, so as to improve the aerodynamic environment and realize the purpose of semi-ballistic re-entry flight; the disadvantage is that because the whole reducer is a rigid fixed structure, Constrained by the ...

AI Technical Summary

Problems solved by technology

In addition, even at 0° angle of attack, in order to prevent the impact of the shoulder shock wave on the rear end of the reducer, the axial dimension of the flexible deployable reducer is significantly smaller than the diameter of the aerodynamic surface, which also limits the deceleration to a certain extent. container volume and load carrying capacity

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