Soft landing device with terrain self-adaptive capacity and landing buffering method of soft landing device
A self-adaptive, soft landing technology, applied in the direction of the landing device of the aerospace vehicle, the guidance device of the aerospace vehicle, the system of the aerospace vehicle returning to the earth's atmosphere, etc. Small occupancy, adaptability, and the effect of ensuring safe deployment
Active Publication Date: 2020-12-04
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
[0005] In order to solve the above-mentioned technical defects that the traditional lander cannot safely and reliably realize the landing buffer in the complex terrain area of the star surface, and cannot adjust the attitude after the landing buffer is completed, the present invention proposes a lander with terrain self-adaptive and attitude self-recovery capabilities. landing device, and completed the design of its landing process
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[0039] In order to make the object, technical solution and effect of the present invention clearer and clearer, the following examples are given to further describe the present invention in detail. It should be pointed out that the specific implementations described here are only used to explain the present invention, not to limit the present invention.
[0040] Such as Figure 1~2 As shown, the present invention is a soft landing device with terrain adaptive capability, which mainly includes a lander body frame 100, an explosive bolt assembly 200, a two-way buffer assembly 300 with a driving function, an intermediate telescopic strut assembly 400, and an integrated buffer drive assembly. Strut 500, upper bracket assembly 600 and cushioning foot pad 700; wherein the explosive bolt assembly 200 is directly connected to the lander body frame 100 and the integrated cushioning and driving pillar 500, and the upper bracket assembly 600 is connected to the body frame 100 and the int...
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The invention discloses a soft landing device with terrain adaptive capacity and a landing buffer method thereof, and belongs to the technical field of spacecraft structures and mechanisms. The soft landing device comprises a landing device body frame, an explosive bolt assembly, a two-way buffer assembly with a driving function, a middle telescopic supporting column assembly, a buffering and driving integrated supporting column, an upper support assembly and a buffering foot pad. A locking and unlocking assembly is used for realizing the unfolding of the landing leg assembly; the buffering and driving integrated main supporting column assembly can achieve self-adaption to the star catalogue terrain. The two-way buffer assembly with the driving function can achieve the adaptive capacity ofthe lander to the ground touching moment transverse speed. The middle telescopic supporting column assembly improves the rigidity of the truss between the unfolded landing leg and the lander body. The soft landing device is reasonable in structural design and reliable in performance, the lander can have the self-adaptive capacity to the nondeterministic star catalogue terrain and the star catalogue attitude adjusting capacity of the lander body after buffering, the safety of the star catalogue landing process is obviously improved, and then the task success rate is increased.
Description
technical field [0001] The invention belongs to the technical field of spacecraft structures and mechanisms, and relates to a soft landing device with terrain self-adaptive and attitude self-restoring capabilities and a landing process design, in particular to a soft landing device with terrain self-adaptive capabilities and a landing buffer method thereof . Background technique [0002] The landing buffer device of the extraterrestrial object star probe is mainly used to absorb the impact energy of the lander and realize the support for the body after the buffer is completed. Traditional landing buffer mechanisms mainly include inverted triangle type and cantilever type, both of which use aluminum honeycomb as the buffer crushing material. For example: the famous Apollo 11 and Chang'e series lunar landers have a cantilever beam structure; Luna 16 in the Soviet Union has an inverted triangle structure. The cantilever type and inverted triangle type landing buffer devices a...
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Login to View More IPC IPC(8): B64G1/24B64G1/62
CPCB64G1/244B64G1/62
Inventor 贾山赵建华陈金宝聂宏周向华张胜
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS