Method for determining stroke design value of landing gear buffer structure of flying wing-configured aircraft
A technology for aircraft landing gear and determination methods, which is applied in the fields of instruments, calculations, and special data processing applications, etc., can solve problems that cannot be solidified and finalized, and achieve the effect of simple calculation methods and clear calculation principles
Active Publication Date: 2018-05-29
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology
[0003] The previous methods for determining the structural stroke design value of the landing gear buffer usually involve many overall layout parameters and structural performance parameters, and these parameters are often unresolved or cannot be solidified and finalized in the initial design stage of the flying wing layout aircraft
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[0017] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention.
[0018] figure 2 As shown, Table 1 shows the design parameters of a certain type of flying wing layout aircraft:
[0019] Table 1
[0020]
[0021] Such as figure 2 , according to the method for determining the stroke design value of the present invention and according to the corresponding assignment of each parameter in the table above, the design value S of the landing gear structure stroke of the flying wing layout aircraft can be calculated as:
[0022]
[0023] In the formula, S is the stroke of the landing gear buffer structure (unit is m), H is the height of the aircraft landing and flaring (H=2m), V x is the landing horizontal speed of the aircraft (V x =70m / s), K is ...
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The invention relates to a method for determining the stroke design value of a landing gear buffer structure of a flying wing-configured aircraft and belongs to the technical field of aircraft landinggear design. The method comprises the steps of: 1, establishing a relational expression of stroke S of the landing gear structure of the flying wing-configured aircraft and sinking speed Vy of the aircraft; 2, establishing a calculation formula of the design landing sinking speed Vy of the flying wing-configured aircraft; and 3, obtaining a calculation formula of the stroke S of the landing gearstructure of the aircraft and the sinking speed Vy of the aircraft according to the relational expression established in the step 1 and the calculation formula established in the step 2. The method for determining the stroke design value, which is provided by the invention, has the advantages that only a small number of design parameters which are already determined in an overall developing schemein the initial design stage of the flying wing-configured aircraft are utilized; the calculation method is simple; the calculation principle is clear; and the stroke design value of the landing gearstructure of the flying wing-configured aircraft can be quickly obtained.
Description
technical field [0001] The invention belongs to the technical field of aircraft landing gear design, and in particular relates to a method for determining the stroke design value of a landing gear buffer structure of a flying wing layout aircraft. Background technique [0002] Flying wing layout aircraft (if attached figure 1 ) has become a key development direction in the aviation field due to its good aerodynamic efficiency and stealth performance. Due to its own aerodynamic force and take-off and landing performance characteristics, there are some differences in the landing gear design of flying-wing layout aircraft compared with conventional layout aircraft. According to the development requirements of the overall plan of the flying wing layout aircraft, the landing buffer system should have sufficient capacity to absorb and dissipate the landing energy of the aircraft. The landing energy is absorbed and dissipated by the landing gear buffer, which requires the landing...
Claims
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IPC IPC(8): G06F17/50
CPCG06F30/15
Inventor 姚念奎曹奇凯洪海明王佳莹
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA