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Flight mechanics modeling method for wingtip hinge combined type flight platform

A technology of flight platform and mechanics modeling, applied in the field of flight dynamics modeling and analysis

Active Publication Date: 2020-11-13
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the deficiency that the existing flight mechanics analysis method cannot be directly applied to the wingtip articulated combined flying platform, the present invention provides a wingtip articulated combined flying platform flight mechanics modeling method based on multibody dynamics theory, the modeling method Intuitive and accurate, the established dynamic model can be used to analyze the trim and stability characteristics of the flight platform

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  • Flight mechanics modeling method for wingtip hinge combined type flight platform
  • Flight mechanics modeling method for wingtip hinge combined type flight platform
  • Flight mechanics modeling method for wingtip hinge combined type flight platform

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Embodiment Construction

[0068] Such as figure 1 The wingtip articulated combined flying platform shown is an example of the combination of two sub-aircraft, and each sub-aircraft is regarded as a rigid body. Each sub-aircraft structure is as follows figure 2 shown. Sub-aircraft structure includes: fuselage 1, right wing 2, right wing aileron 3, full-motion vertical tail 4 (can be used as rudder), full-motion horizontal tail 5 (can be used as elevator), left wing 6, left wing Aileron 7, middle wing 8. The two airframes are connected by a one-way hinge, which can freely rotate along the chord direction.

[0069] According to an embodiment of the present invention, a flight mechanics modeling and analysis method of a wingtip articulated combined flight platform includes:

[0070] Step 1: Calculation initialization

[0071] Information about each sub-aircraft in a given computational model;

[0072] The design parameters are as follows:

[0073] Design Parameters value Design Parame...

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Abstract

The invention relates to a flight dynamics modeling and analysis method for a wingtip hinge combined type flight platform, and belongs to the technical field of aircraft flight mechanics modeling andsimulation analysis. According to the method disclosed in the invention, the sub-aircrafts in the wingtip hinged combined type flying platform are treated as rigid bodies; the degree of freedom of motion is expressed in the form of absolute coordinates relative to an inertial coordinate system, a multi-body dynamics theoretical analysis method is introduced, a constraint equation is established incombination with a Lagrange multiplier method to express an articulation relationship, and a Newton-Euler equation is utilized to establish a flight mechanical equation of the flight platform. The invention provides a method and process for analyzing the flight mechanical characteristics of the wingtip hinge combined type flight platform. Aircraft trimming and flight mechanical stability analysiscan be carried out.

Description

technical field [0001] The invention belongs to the technical field of aircraft flight mechanics modeling and simulation analysis. Specifically, the invention relates to a flight dynamics modeling and analysis method for a wingtip articulated combined flight platform. Background technique [0002] When designing an aircraft, it is the goal that aircraft designers have been pursuing to fully improve the flight performance of the aircraft to meet the requirements of flight missions and combat missions. Endurance performance is the core component of flight performance, which directly determines factors such as the range of activities of the aircraft, long-lasting flight capability and economy. Specifically, the endurance performance of an aircraft includes two aspects: range and flight time. Range and flight time relate to how far and how long an aircraft can fly. Improving range and flight time has always been the core and purpose of research on aircraft endurance performance...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F119/14
CPCG06F30/15G06F2119/14
Inventor 安朝谢长川孟杨刘晨宇
Owner BEIHANG UNIV
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