A Wind Correction Method for Multi-working Modes of Spacecraft Deceleration and Landing
A working mode and technology of spacecraft, applied to the landing device of aerospace vehicles, the system of spacecraft returning to the earth's atmosphere, etc., to achieve the effects of improving reliability, improving the control of landing point deviation, and simple and easy calculation methods
Active Publication Date: 2016-08-24
BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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Problems solved by technology
[0005] The technical problem solved by the present invention is: to overcome the deficiencies in the prior art, to provide a wind correction method for multi-working modes in the deceleration and landing section of the spacecraft, to solve the wind correction technology for the multi-working modes in the deceleration and landing section of the spacecraft, that is, to improve the multi-working mode. The multi-working stages of the working mode lead to the accuracy requirements of wind correction and improve the control of the accuracy of the landing point
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[0025] Such as figure 1 Shown is the flow chart of the present invention, and the method of the present invention is further described below.
[0026] (1) According to the deceleration and landing system of the spacecraft, the parachute aiming point h 0 , the landing field elevation value h 1, determine the height range of wind correction for the task to be analyzed, and obtain the meteorological parameter values of the landing site by measurement, including the elevation value h, wind direction angle α, and wind speed w;
[0027] (2) Obtain the return and reentry parameters of the spacecraft return module of the mission to be analyzed, including the initial velocity u 0 , initial azimuth A, ballistic inclination θ, earth radius r and theoretical landing point longitude λ 0 , latitude φ 0 , and according to the telemetry parameters of the deceleration landing system of the spacecraft return module, including the deceleration landing system switch parameters and parachute...
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The invention relates to a wind correction method for multiple working modes in the deceleration landing phase of a spacecraft. Through the method, landing point deviation caused by drifting of a re-entry capsule descending by taking a parachute due to a wind field can be acquired, a deviation value is injected into a manned spacecraft in a parameter form, and landing accuracy of the spacecraft is unaffected by the wind field. According to the method, an algorithm solving process is divided by taking the working modes as bases, the process is composed of multiple feature calculation modules, all the modules use a resistance feature parameter and working phase matching method, and solving control of working modules is detailed. By execution of the solving process integrated with the multiple feature calculation modules, accurate wind drift deviation of the deceleration landing phase is acquired, and the problem of deviation in landing accuracy due to wind field changes, the working modes and the like after the spacecraft opens the parachute is solved. The method can be applied to wind correction control on the landing accuracy in the working phase of a spacecraft deceleration landing system.
Description
technical field [0001] This patent belongs to the field of spacecraft system design, and relates to a wind correction method for multi-working modes of a spacecraft deceleration and landing section, which is suitable for accurate wind correction calculation of a spacecraft deceleration and landing system. Background technique [0002] For manned spacecraft, the requirements for the landing point of the return capsule are higher than those of other unmanned spacecraft. The precision control of the landing point involves a series of issues such as the selection of the landing area, the search and rescue of astronauts, and the ground support after landing. [0003] The use of a parachute flexible structure as a deceleration device is greatly affected by the local wind field during its working phase, which requires wind correction on the working section of the parachute system when the manned spacecraft returns to the capsule. Moreover, due to the various working modes of the re...
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IPC IPC(8): B64G1/62
Inventor 贾贺高树义荣伟吴世通雷江利卢齐跃
Owner BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH