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An optimization design method based on a round hybrid parafoil

An optimized design and parafoil technology, which is applied to the system of the spacecraft returning to the earth's atmosphere, the landing device of the spacecraft, etc., can solve the problems of difficult to guarantee the landing point, limited deceleration effect of the parafoil, and large area of ​​the parafoil. Good deceleration effect

Inactive Publication Date: 2019-09-13
XIANYANG NORMAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The main parachute chooses a single stamping parafoil. Due to the heavy weight of the recyclables, the area of ​​the parafoil is very large. If the area is too large, it will lead to a series of problems such as parachute opening mode, incision mode, and limited deceleration in the initial stage of parafoil work.
Using a round umbrella or a combined round umbrella, the system decelerates more obviously, but it cannot control the glide, and it is difficult to guarantee the landing point

Method used

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  • An optimization design method based on a round hybrid parafoil
  • An optimization design method based on a round hybrid parafoil
  • An optimization design method based on a round hybrid parafoil

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Embodiment

[0083] Step 1) Select the reference airfoil of the parafoil as the Clark-Y airfoil, and determine the network model of the parafoil according to the reference airfoil:

[0084] Such as figure 1 Shown is the wing section of the airfoil. The characteristic parameters of the airfoil include thickness 1, camber 2 and chord length 3. The reference airfoil of the selected parafoil is the Clark-Y airfoil. The Clark-Y airfoil is simple in shape and easy to process. Good aerodynamic characteristics, select the typical Clark-Y airfoil model in the airfoil library, change the number of nodes on the airfoil surface, establish different network models, calculate the simulated aerodynamic parameters of different network models, and select the lift coefficient after subtracting the error The network model with the highest and lowest drag coefficient is that of the parafoil.

[0085] By evaluating the influence of the number of grids on the calculation accuracy of numerical simulation aerody...

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Abstract

The invention discloses an optimization design method based on a round hybrid parafoil. The method comprises the steps of selecting a reference airfoil, calculating parafoil characteristic parameters,designing a parafoil hanging system, selecting a main body round umbrella, combining the main body round umbrella and parafoils and finally optimizing the main body round umbrella to complete the optimization design based on the round hybrid parafoil. The method of the invention combines the traditional round umbrella and the parafoils in a planned mode and optimizes the combination. The round hybrid parafoil designed by the method has high controllability, excellent gliding performance and a good deceleration effect, thereby fully meeting the requirements for umbrella systems in a spacecraftbooster recycling process.

Description

technical field [0001] The invention belongs to the technical field of aerospace landing aids, and in particular relates to an optimal design method based on a circular hybrid parafoil. Background technique [0002] During the recovery process of the spacecraft, due to the heavy weight of the booster or the first-stage rocket itself, the speed of movement is greater than 1 when the Mach number is greater than 1, and the flight speed is required to be reduced when the flight altitude is several thousand meters, resulting in a large dynamic pressure load. At present, the main recycling method is to use a multi-stage umbrella system for recycling. The multi-stage parachute system consists of a guide parachute, a drogue parachute and a main parachute. The drogue parachute is a high-strength circular parachute. Its main function is to decelerate and drop altitude at high Mach numbers. When the descending speed reaches a certain range of subsonic speed, it will open The main para...

Claims

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Application Information

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IPC IPC(8): B64G1/62
CPCB64G1/62
Inventor 李艳红
Owner XIANYANG NORMAL UNIV