Method for calculating asymmetric gushing wind dynamic load of transport aircrafts
A technology for transport aircraft and calculation method, applied in the field of asymmetric gust dynamic load calculation of transport aircraft, can solve the problem of not considering the influence of unsteady aerodynamic characteristics and elastic body motion, not conforming to the actual situation, affecting the safety and safety of the aircraft. reliability and other issues to achieve the effect of improving work efficiency
Pending Publication Date: 2021-03-30
中航通飞华南飞机工业有限公司
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Problems solved by technology
[0004] In the past, the empirical method was mainly used to calculate the static load of a rigid-body aircraft when it encountered an asymmetrical gust, and to design the strength of the body structure, without considering the influence of unsteady aerodynamic characteristics and elastic body motion, which did not conform to the actual situation and seriously affected the safety of the aircraft. sex and reliability
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[0045] All the features disclosed in this specification, or all the methods disclosed, or the steps in the process, except the mutually exclusive features and / or steps, can be combined in any way.
[0046] The method and equipment for calculating the asymmetric gust dynamic load of a transport aircraft provided by the present invention take a typical transport aircraft as an example, and its encounters are as follows: figure 1 Analyze the response characteristics of the shown asymmetrical gust, and calculate the limited dynamic load of the aircraft. The specific implementation process is as follows:
[0047] Step 1, parameter preparation, including the flight speed, flight altitude, and aircraft weight of the aircraft;
[0048]Step 2. Combine aircraft parameters and gust design requirements to generate a parameterized gust field. The parameters include design gust speed, gust gradient, gust shape, flight profile mitigation coefficient, etc.;
[0049] Step 3. Adjust the gust d...
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The invention belongs to the technical field of aircraft structure dynamic response analysis, and particularly relates to a method and equipment for calculating the asymmetric gushing wind dynamic load of a transportation aircraft. The method comprises the following steps: respectively generating dynamic response analysis models of vertical gust and horizontal gust according to a parameterized gust model of an aircraft and a structural model and an aerodynamic model adopted by flutter analysis; solving the response characteristics of the model under the action of gust by utilizing a modal superposition method, and quickly obtaining the incremental load of each part of the model based on the model nodes and a coordinate definition method formulated by the invention; and superposing incremental loads generated by the vertical gust and the horizontal gust, adding 1g of level flight load, and quickly calculating asymmetric limiting loads of shearing force, bending moment and torque of eachpart of the model. By the adoption of the calculation method and device, while flutter analysis is carried out, the limited load of the transport aircraft under the action of asymmetric gust can be quickly solved, a basis is provided for structural strength design of the transport aircraft, and meanwhile the working efficiency is greatly improved.
Description
technical field [0001] The invention belongs to the technical field of dynamic response analysis of aircraft structures, and in particular relates to a calculation method for asymmetric gust dynamic loads of transport aircraft. Background technique [0002] When designing transport aircraft, it is necessary to consider the loads generated by the airframe when the aircraft encounters atmospheric gusts, including CAAC, FAA, EASA, etc., have proposed requirements for transport aircraft to be designed according to dynamic gust loads, mainly including: Wind, discrete gusts are generally divided into three components: longitudinal, vertical and lateral; asymmetrical gusts, CCAR-25.427 (c) stipulates that for horizontal tails with dihedral angles greater than ±10° or for empennage layouts where the horizontal tails are supported on the vertical tails, Each airfoil and its supporting structure must be as specified in §25.341(a) for gusts acting in any direction at right angles to th...
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Login to View More IPC IPC(8): G06F30/15G06F30/28G06F119/14
CPCG06F30/15G06F30/28G06F2119/14Y02T90/00
Inventor 吕继航杨荣罗琳胤
Owner 中航通飞华南飞机工业有限公司