CN104298804A - Flight load design method - Google Patents

Abstract

The invention belongs to the field of flight load design, and relates to a flight load design method. The method is characterized in that firstly, maneuvering process simulation is carried out, and time history data of operation parameter change in the flight process are obtained; secondly, a severe load calculation state is screened, a load calculation point is obtained according to the maneuvering process, a part load envelope line is drawn, and points on the envelope line are selected to serve as severe load calculation states; thirdly, flight load computing is carried out, an aerodynamic computation model is built, a quality model is built, a pneumatic and structure coupling model is built, and flight load calculation is carried out according to the severe load calculation states by means of theoretical aerodynamic data or calculation of hydromechanics data (CFD data) or wind tunnel tests. The method has the advantage that flight load standardization and precise design are achieved.

Description

A kind of flight load method for designing

Technical field

The invention belongs to Aircraft Load design field, relate to a kind of proposition of flight load method for designing.

Background technology

Aerodynamic arrangement is for realizing advanced aeroperformance and tactical and technical norms requirement, carrying out comprehensive selection and specification to major parameter in aircraft pneumatic design.The research object of aerodynamic arrangement is the relation of main aerodynamic parameter (as lift, resistance, moment coefficient and other aerodynamic derivative) and main aerodynamic parameter and aircraft configuration parameter.

Aircraft flight load refers to that aircraft is in flight course, acts on the general name of aerodynamic force, elastic force and the inertial force on each position of aircraft.The flight load design of aircraft is closely related with security, reliability and economy.Flight load designs accurately, can not only reduce construction weight, meets reliability and security requirement, can also improve economy.Flight load design relates to the multiple-discipline comprehensive research project of the subjects such as aerodynamics, flight mechanics, weight, aeroelasticity, structural strength, its determination more complicated, needs to be determined by methods such as theory calculate, wind tunnel test and load actual measurements.Correctly determine that aircraft flight load is the important content of airplane design, being by bridge that is overall, pneumatic design steering structure Intensity Design, is the foundation of structural design, strength check, very important.

The main flow way of current flight load design carries out mobile process emulation according to specification, screening severe load computing mode (or specifying LOAD FOR state), set up LOAD FOR model, use theoretical aerodynamic data (Fluid Mechanics Computation data (CFD data) or wind tunnel test data) to carry out flight load calculating.By finding the research of domestic and international flight load design data of literatures, there is no now flight load design cycle that is complete, specification.

Summary of the invention

The object of the invention is: according to flight load integrated design thought, propose flight load design cycle, realize the object of flight load standardization, minute design.

Technical scheme of the present invention is: a kind of flight load method for designing, is characterized in that, comprise the steps:

The first, carry out mobile process emulation, obtain the time history data of kinematic parameter change in flight course.

The second, screening severe load computing mode, emulate the LOAD FOR point obtained according to mobile process, drafting components ' load envelope, chooses point on envelope as severe load computing mode.

3rd, carry out flight load calculating: set up aerodynamics evaluation model; Set up quality model; Set up pneumatic/structure Coupling model; According to severe load computing mode, theoretical aerodynamic data or Fluid Mechanics Computation data (CFD data) or wind tunnel test data is used to carry out flight load calculating.

Advantage of the present invention is: propose flight load design cycle, realizes the object of flight load standardization, minute design.

Accompanying drawing explanation

Accompanying drawing 1 is maneuvering flight example

Accompanying drawing 2 is reliving plate examples

Accompanying drawing 3 is severe load design conditions examples

Accompanying drawing 4 is aerodynamics evaluation models

Accompanying drawing 5 is quality models

Accompanying drawing 6 is pneumatic/structure Coupling models

Accompanying drawing 7 is flight load result of calculation examples

Embodiment

Below by specific embodiment, also the present invention is described in further detail by reference to the accompanying drawings.

The present invention studies for certain seating plane.

One, mobile process emulation is carried out according to specification.Mobile process emulation is one of basis of LOAD FOR.Maneuver simulation calculates needs the simulation mathematical model setting up airplane motion, on the basis of airplane motion Development of Simulation Software, the mode of optimized handling input quantity is adopted to make aircraft require flight according to maneuver, calculate the time history data of kinematic parameter change in flight course, for the LOAD FOR of each parts.

Two, severe load computing mode is screened.Aircraft can do various maneuver (as shown in Figure 1) aloft, and from the angle of intensive analysis, pays close attention to the aircraft action situation that stand under load is the most serious often awing, therefore needs screening severe load computing mode.The LOAD FOR point obtained is emulated according to mobile process, selected monitoring section on each parts, the load value of monitoring section is calculated according to LOAD FOR point, draw out shearing-moment curve and shearing-torque diagram respectively according to the load value of each block supervises section, then the outer rim point often opening figure is coupled together formation reliving plate.Reliving plate example as shown in Figure 2.According to the reliving plate drawn, select the point on envelope curve, namely these points are load design points, and the parameter of its correspondence is load design state.By these point retrievals out, merge the state removing repetition, obtain final severe load design conditions, as shown in Figure 3.

Three, flight load computational analysis is carried out.The feature of foundation aircraft configuration and control surface, sets up aerodynamics evaluation model, as shown in Figure 4; Quality model is set up, as shown in Figure 5 according to mass distribution; Set up pneumatic/structure Coupling model, as shown in Figure 6.According to severe load computing mode, wind tunnel test data are used to carry out flight load calculating.Flight load result of calculation example as shown in Figure 7.

Claims (1)

1. a flight load method for designing, is characterized in that, comprises the steps:

The first, carry out mobile process emulation, obtain the time history data of kinematic parameter change in flight course;

The second, screening severe load computing mode, emulate the LOAD FOR point obtained according to mobile process, drafting components ' load envelope, chooses point on envelope as severe load computing mode;

3rd, carry out flight load calculating: set up aerodynamics evaluation model; Set up quality model; Set up pneumatic/structure Coupling model; According to severe load computing mode, theoretical aerodynamic data or Fluid Mechanics Computation data (CFD data) or wind tunnel test data is used to carry out flight load calculating.