Composite material integrated control surface structure with progressive decrease in rigidity and processing method thereof

A composite material and rudder surface technology, which is applied to space navigation equipment, space navigation aircraft, space navigation equipment, etc., can solve the problem of insufficient structural design optimization, and achieve the purpose of reducing the weight of the rudder surface structure, improving quality characteristics, and reducing The effect of structural weight

Active Publication Date: 2015-11-11
CHINA ACAD OF LAUNCH VEHICLE TECH
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Problems solved by technology

[0004] For the existing composite material rudder surface, the traditional structural design method adopts the equal stiffness design method, that is, the thickness dimension of the

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  • Composite material integrated control surface structure with progressive decrease in rigidity and processing method thereof
  • Composite material integrated control surface structure with progressive decrease in rigidity and processing method thereof
  • Composite material integrated control surface structure with progressive decrease in rigidity and processing method thereof

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Embodiment Construction

[0039] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0040] Such as figure 1 Shown is a schematic diagram of the structure of the spacecraft rudder surface and a cross-sectional view, where (a) is a schematic diagram of the structure of the spacecraft rudder surface, and (b) is a cross-sectional view of the spacecraft rudder surface structure; figure 2 A schematic diagram of the structure of the rudder surface; Figure 4 Schematic diagram and axonometric diagram of the internal skeleton structure of the rudder surface, where (a) is a schematic diagram of the external skeleton structure of the rudder surface, and (b) is the axonometric diagram of the internal skeleton structure of the rudder surface; from figure 1 , figure 2 and Figure 4 It can be seen that a composite material integrated rudder surface structure with decreasing stiffness proposed by the present invention includes: ...

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Abstract

The invention discloses a composite material integrated control surface structure with progressive decrease in rigidity and a processing method thereof, wherein a design solution of a carbon fiber composite material integrated control surface structure is adopted; besides a control shaft and accessories thereof, the rest of the structure is carbon fiber reinforcedcomposite material; advanced optimization design technology is adopted; through several iterative calculations, the structure size design is optimized; the weight of the control surfacestructure is lightest; the rigidity of the optimized control surface structure is on the decrease progressively along an axial direction, that is, the thickness size of an internal skeleton web is on the decrease progressively towardswing tips and two sides; and the skin thickness is not the same and is on the decrease progressively towards the wing tips, thus the structure weight is further reduced; the control surface modal frequency is increased; and the control surface vibration property is improved.

Description

technical field [0001] The invention relates to a composite material integrally formed rudder surface structure and a processing method, in particular to a composite material integrally formed rudder surface structure and processing method with decreasing stiffness, which is suitable for the technical field of aircraft composite material structure design and forming, especially for small Integrated molding design technology of rudder surface and airfoil. Background technique [0002] Traditional aerospace vehicle rudder structures generally use high-density high-temperature-resistant metal materials, and the structural quality is too large; traditional aerospace vehicle rudder structures generally use all-metal materials for machining. Large, the structural strength and stiffness margin is too large, and the structure has a large space for weight reduction optimization. [0003] The new type of trans-atmospheric flying spacecraft puts forward higher requirements for the lig...

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Application Information

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IPC IPC(8): B64G1/22B29C70/30
Inventor 田甜李晓乐顾春辉许健唐青春张沥崔深山崔占东吴迪张帆李丹圆陈亦冬
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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