An integrated structure of airfoil and trailing edge rudder
A trailing edge rudder and airfoil technology, applied in the field of aircraft structure, can solve the problems of increasing manufacturing cost and time consuming
Active Publication Date: 2018-05-04
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology
[0003] However, the current common airfoil installation structure is that the stabilizer and the rudder surface are directly installed on the cabin body. The disadvantages of this structure are: the requirements for the installation of the cabin body are relatively high, and the joints of the cabin body are required to be able to bear force, and The positioning and installation of the left and right airfoils are required, which not only increases the manufacturing cost, but also takes more time
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[0018] In order to make the technical means, creative features, goals and effects achieved by the present invention easy to understand, the present invention will be further described below in conjunction with specific illustrations.
[0019] see Figure 1~Figure 4 An integrated structure of an airfoil and a trailing edge rudder, including a left body and a right body, and the left body and the right body have the same structure and are symmetrical about the longitudinal centerline 9 of the cabin connecting surface 3, the cabin connecting surface 3 is used to connect the left structure and the right structure; wherein, the left structure includes the main joint 1, the shaft hole boss 2, the airfoil stabilizer 4, the airfoil rudder surface 5, the rudder surface shaft 6, the cabin body 7, and the chord plane 8. Longitudinal centerline 9 and installation angle 10; airfoil stabilizer 4 is installed on the main joint 1, rudder surface rotating shaft 6 is installed in the shaft hole...
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An integrated structure of airfoil and trailing edge rudder, the left body and the right body have the same structure and are symmetrical about the longitudinal centerline of the cabin connecting surface used to connect the left body and the right body; the left body includes a main joint and the shaft hole boss, the airfoil stabilizer is installed on the main joint, the rudder surface shaft is installed in the shaft hole boss, the wing rudder surface is connected to the rudder surface shaft and then connected to the shaft hole boss, and the shaft hole boss is set on Inside the connecting surface of the cabin body, the connecting surface of the cabin body is connected with the cabin body; and the airfoil stabilizer and the rudder surface of the wing surface are in the same chord plane, and the chord plane and the connecting surface of the cabin body form a certain installation angle at the same time. In the present invention, the airfoil stabilizer and the airfoil rudder surface are always in the same chord plane, and at the same time, the chord plane is positioned by the installation angle, which reacts on the main joint and the shaft hole boss to locate the chord plane to form an integrated structure, thereby avoiding the use of tooling for positioning. At the same time, it also reduces the production cycle and reduces the production cost.
Description
technical field [0001] The invention relates to the technical field of aircraft structures, in particular to an integrated structure of an airfoil and a trailing edge rudder. Background technique [0002] With the rapid development of weapon systems, the Air Force has put forward clear requirements for the integration, miniaturization, and low cost of airborne weapons, especially for the overall development outline of domestic and foreign miniaturized tactical missiles, and the integration of all bombs and missiles. Comprehensive design is the only way to develop miniaturized tactical missiles in the future. [0003] However, the current common airfoil installation structure is that the stabilizer and the rudder surface are directly installed on the cabin body. The disadvantages of this structure are: the requirements for the installation of the cabin body are relatively high, and the joints of the cabin body are required to be able to bear force, and the The positioning an...
Claims
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IPC IPC(8): B64C9/02
CPCB64C9/02
Inventor 邓进陈雷陈逸云王再玉毛端华王艳丽张耀庆王韬张维姚雅琳
Owner JIANGXI HONGDU AVIATION IND GRP