Semi-rigid mechanical deployment into deceleration landing gear

Abstract

The invention discloses a semi-rigid mechanically-unfolded deceleration entering landing device and belongs to the field of spacecraft entrance and return. The semi-rigid mechanically-unfolded entering decelerated landing device comprises a body, a control ring, a rigid head cone, a semi-rigid heat insulation cover, a semi-rigid heat insulation cover control mechanism and a flexible heat insulation cover mechanism. The body is fixedly connected with the control ring. A drive mechanism is connected between the control ring and the rigid head cone and controls the control ring and the rigid head cone to move relatively. The semi-rigid heat insulation cover control mechanism is covered with the semi-rigid heat insulation cover and hinged to the body and the rigid head cone and controls the semi-rigid heat insulation cover to be unfolded or folded. The flexible heat insulation cover mechanism capable of being unfolded outwards secondarily is arranged on the outer side of the semi-rigid heat insulation cover. The total area of the unfolded device is larger than the primarily-unfolded area, the size is kept small in a folded transmission state, the storage ratio of the device is increased, the deceleration effect of a pneumatic face is improved, the system complexity is lowered, and two-stage deceleration and landing buffering are organically unified.

Description

technical field [0001] The invention relates to a deceleration landing device, in particular to a semi-rigid mechanical deployment and entry deceleration landing device, which belongs to the technical field of spacecraft entry and return. Background technique [0002] With the continuous deepening of deep space exploration, effective deceleration is required when large payloads enter stars with atmospheric environments. The existing design of semi-rigid mechanical deployment and re-entry deceleration landing structure can provide a large aerodynamic deceleration surface, which can well solve the problems of large load entry, deceleration, and landing. At the same time, there are some disadvantages: first, the storage ratio limited. The larger the area of ​​the expanded aerodynamic deceleration surface, the larger the volume of the retracted state, and the higher the demand for the envelope of the rocket fairing. Therefore, from the perspective of engineering application, t...

AI Technical Summary

Problems solved by technology

The existing design of semi-rigid mechanical deployment and re-entry deceleration landing structure can provide a large aerodynamic deceleration surface, which can well solve the problems of large load entry, deceleration, and landing. At the same time, there are some disadvantages: first, the storage ratio limited

Therefore, from the perspective of engineering application, the expansion area of ​​the aerodynamic deceleration surface of this structure cannot be "infinitely" large, the deceleration effect is limited, and other methods such as parachutes are still needed for secondary deceleration; second, the structure does not have buffer after reverse reconstruction The landing stage mainly relies on the thrust reverser engine for buffering, and the system is heavy and complex

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