A Modeling Method of Flight Mechanics of Wingtip Articulated Combined Flying Platform

A technology of flight platform and mechanical modeling, applied in the field of flight dynamics modeling and analysis, to achieve the effect of easy engineering simulation

Active Publication Date: 2022-05-03
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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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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  • A Modeling Method of Flight Mechanics of Wingtip Articulated Combined Flying Platform
  • A Modeling Method of Flight Mechanics of Wingtip Articulated Combined Flying Platform
  • A Modeling Method of Flight Mechanics of Wingtip Articulated Combined Flying 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 articulated combined flight platform, belonging to the technical field of aircraft flight mechanics modeling and simulation analysis. The invention treats the sub-aircraft in the wingtip articulated combined flight platform as a rigid body, expresses the degree of freedom of motion in the form of absolute coordinates relative to the inertial coordinate system, introduces a multi-body dynamics theoretical analysis method, and combines Lagrangian multipliers Constraint equations are established to express the hinge relationship, and Newton-Euler equations are used to establish the flight mechanics equations of the flight platform. The invention provides a method and flow for analyzing the flight mechanics characteristics of a wingtip articulated combined flight platform, and can carry out aircraft trimming and flight mechanics stability analysis.

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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Patent Type & Authority Patents(China)
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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