An integrated device for aerodynamic deceleration, soft landing and protection of a space probe

Abstract

The invention discloses an integrated device for aerodynamic deceleration, soft landing and protection of a space probe, comprising a mounting frame, a petal structure, a main landing leg, an auxiliary landing leg, and a hydraulic system; the mounting frame is fixed on the space probe body, and the petal structure Installed at the lower end of the installation frame, the main landing leg and the auxiliary landing leg are fixedly connected to the installation frame respectively, the other end of the main landing leg is connected to the central rotating shaft of the petal structure, and the other end of the auxiliary landing leg is connected to the main landing leg. A hydraulic buffer system and a partial hydraulic retractable system are placed in the main landing leg and the auxiliary landing leg to maintain a stable attitude during landing and long-term support after landing; through the device, the function of space probes landing on planets with thin atmospheres can be realized ; At the same time, it can perform soft landing on the surface of the planet; the ratio of the aerodynamic deceleration area of ​​the space probe to the maximum cross-sectional area is large, the aerodynamic deceleration efficiency is high, and the aerodynamic deceleration device does not need to be discarded; it is especially suitable for space probes.

Description

technical field [0001] The invention relates to a spacecraft landing device, in particular to an integrated device for aerodynamic deceleration, soft landing and protection of a space probe. Background technique [0002] Documents "Study on Landing Dynamics Modeling and Simulation of Multi-legged Lunar Exploration Soft Lander" (Nanchang University Master's Degree Thesis, 2008) and "Study on Energy Absorption Characteristics of Leg-type Landing Buffer and Dynamics Simulation of Soft Landing Process" ( Harbin Institute of Technology doctoral dissertation, 2013) described that soft landing landers mostly use leg-type soft landing mechanisms, and the landing legs are evenly distributed around the central axis of the lander. According to the configuration of a single landing leg, the landing leg can be divided into "inverted triangle" and "cantilever beam" landing legs. The buffer is installed in the main pillar and auxiliary pillar of the landing leg. Aluminum honeycomb structur...

AI Technical Summary

Problems solved by technology

[0003] Invention patent CN102438906A discloses a "landing device for a space probe and a landing method for a probe equipped with the device". The landing legs can be retracted when landing, but the aerodynamic cabin still needs to be thrown away.

In the prior art, the aerodynamic capsule has been thrown away when it descends to the surface of Mars, and the lander body is directly exposed to the Martian atmosphere; according to existing studies, there is a lot of dust in the Martian atmosphere, especially during Martian storms, when the Martian environment is even harsher. Bare space probes are highly vulnerable to the Martian environment

In summary, the aerodynamic deceleration efficiency of existing Mars landers is low, and the structural utilization rate needs to be improved

Images