CN109573098B - Full-size fatigue test high vertical tail load loading design method - Google Patents

Full-size fatigue test high vertical tail load loading design method Download PDF

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CN109573098B
CN109573098B CN201811476917.3A CN201811476917A CN109573098B CN 109573098 B CN109573098 B CN 109573098B CN 201811476917 A CN201811476917 A CN 201811476917A CN 109573098 B CN109573098 B CN 109573098B
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load
vertical
vertical tail
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tail
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CN109573098A (en
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王亚芳
王新波
闵强
秦剑波
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AVIC First Aircraft Institute
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]

Abstract

The invention belongs to the field of aviation fatigue damage tolerance tests, and particularly relates to a design method for loading of a high vertical tail vertical load in a full-size fatigue test. Firstly, establishing a full-machine finite element model, determining a load loading form according to the magnitude and magnitude of vertical load of a vertical tail, determining a loading form, carrying out full-machine load calculation, and converting joint load to an adjacent machine body frame according to an equivalent principle; and finally, performing durability analysis and calculation on the key part of the connection of the vertical tail of the fuselage. By adopting the method provided by the invention, the problems that a vertical load loading system of the vertical tail is complex and is not easy to design are solved.

Description

Full-size fatigue test high vertical tail load loading design method
Technical Field
The invention belongs to the field of aviation fatigue damage tolerance tests, and particularly relates to a design method for loading of a high vertical tail vertical load in a full-size fatigue test.
Background
The full-scale fatigue test of the airplane is an important means for verifying whether the service life of the structure of the airplane can meet the use requirement, and the application mode of the test load determines the implementation scale of the test to a certain extent. Before a designer formulates a test implementation scheme, a large amount of theoretical analysis calculation needs to be carried out, so that the test loading design can be ensured to truly simulate all load states, and the test implementation scale, the test period and the like need to be considered.
Aiming at the layout of a high vertical fin structure, the vertical fin is positioned at the upper part of a rear machine body frame, and the vertical load is mainly the self inertial load. Due to the structural characteristics of the vertical tails, vertical loads are not easy to apply, additional lateral force or lateral internal force is generated by stretching the adhesive tape along the inclined direction, extra damage is caused to the knot structure, and the test loading period can be prolonged.
The key assessment part for the connection of the vertical tails of the airframe comprises an airframe vertical tail connecting joint, an adjacent frame, a stringer and a skin. On the basis of ensuring that the part is accurately checked and other parts are not damaged in advance, the vertical load of the vertical tail sinks to the frame of the machine body for applying, so that the load applying mode is simplified, the test progress is accelerated, and the test period is shortened.
Disclosure of Invention
The purpose of the invention is: a design method for loading high vertical load of vertical tails in full-scale fatigue test is provided.
The technical scheme of the invention is as follows: a full-size fatigue test high vertical tail load loading design method comprises the following steps:
step one, establishing a full-machine finite element model, and solving full-machine load to obtain vertical load F of drooping tail under each load working conditionjzj＝1、2、3…N；
Determining a load loading form according to the magnitude and magnitude of vertical load of the vertical tail, analyzing the structural forms of a vertical tail connecting joint, a nearby frame, a skin and a stringer of the fuselage, and determining a loading scheme;
thirdly, according to the connection characteristics of the vertical tail of the machine body, the vertical load of the vertical tail is sunk onto the frame of the machine body for applying, and according to the strength of the connection joint structure of the vertical tail of the machine body, the vertical load F of the vertical tail is combinedzPitching moment MYSize, carrying out full-aircraft load calculation solution, and preliminarily calculating to obtain the load F 'of each fuselage vertical tail joint under each working condition'izi＝1、2、3…M；
Step four, converting the joint load to an adjacent frame of the airplane body according to the equivalent principle according to the joint load under each working condition obtained in the step three;
and step five, carrying out finite element solution under the full-machine load implementation state with other loads of the machine body structure according to the machine body frame load obtained in the step four, and carrying out durability analysis calculation on the key part of the vertical tail connection of the machine body.
Further, the finite element solving method comprises the following steps: finite element modeling is carried out on the fuselage, the frame, the skin and the stringer, loads are applied to unit nodes, and solving calculation is carried out to obtain stress and load results of each unit.
Further, the durability analysis and calculation method comprises the following steps: and calculating the service lives of the key joint and the key part through the recalculated stress and load solving result, and giving the fatigue margin of the key part.
The invention has the advantages that: the invention provides a full-size fatigue test high vertical loading design method for a vertical load of a vertical fin. Based on the characteristics of difficulty in vertical load application of the vertical tail and heavy lever system, the invention provides finite element solution calculation under the full-machine load implementation state, and durability analysis calculation is carried out on the key connection part of the vertical tail of the machine body by adopting an application mode that the vertical load of the vertical tail sinks on the frame of the machine body. The method has the advantages of correct theoretical basis, novel design, clear and simple analysis steps and clear engineering concept. The invention solves the problems of complex vertical load loading system and difficult design.
Drawings
FIG. 1 is a schematic illustration of a vertical tail load in a fuselage vertical tail configuration;
FIG. 2 is a schematic illustration of vertical fin load calculations onto a fuselage vertical fin joint;
FIG. 3 is a schematic illustration of vertical load calculations for a vertical tail to a fuselage frame.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings, referring to fig. 1 to 3.
As shown in fig. 1, a schematic view of the vertical fin load in the vertical fin structure of the fuselage, wherein the vertical fin is connected with the fuselage through 4 pairs of joints, and the vertical load of the vertical fin acts at the rear position;
as shown in fig. 2, a schematic diagram of calculating the vertical load of the vertical fin to the vertical fin joint of the body is shown, and finite element solution is performed to obtain the load of the vertical fin joint of the body;
as shown in fig. 3, the vertical load of the vertical tail is calculated on the frame of the fuselage, and the equivalent of the joint load is calculated on the frame of the fuselage and is applied together with other loads.
A full-size fatigue test high vertical tail load loading design method comprises the following steps:
step one, establishing a full-machine finite element model, and solving full-machine load to obtain vertical load F of drooping tail under each load working conditionzj，j＝1、2、3…N；
Determining a load loading form according to the magnitude and magnitude of vertical load of the vertical tail, analyzing the structural forms of a vertical tail connecting joint, a nearby frame, a skin and a stringer of the fuselage, and determining a loading scheme;
thirdly, according to the connection characteristics of the vertical tail of the machine body, the vertical load of the vertical tail is sunk onto the frame of the machine body for applying, and according to the strength of the connection joint structure of the vertical tail of the machine body, the vertical load F of the vertical tail is combinedzPitching moment MYSize, carrying out full-aircraft load calculation solution, and preliminarily calculating to obtain the load F 'of each fuselage vertical tail joint under each working condition'zi，i＝1、2、3…M；
Step four, converting the joint load to an adjacent frame of the airplane body according to the equivalent principle according to the joint load under each working condition obtained in the step three;
and step five, carrying out finite element solution under the full-machine load implementation state with other loads of the machine body structure according to the machine body frame load obtained in the step four, and carrying out durability analysis calculation on the key part of the vertical tail connection of the machine body.
Example (c):
the present invention will be described in further detail with reference to a specific example.
A full-size fatigue test high vertical tail load loading design method comprises the following steps:
it is known that:
and the load condition M is 1.
Step one, establishing a full-machine finite element model, and solving full-machine load to obtain a vertical load F of a vertical tail under 1 working conditionz-30000N (vertically down);
determining a mode for sinking the vertical load of the vertical fin to the frame of the machine body to apply according to the size and magnitude of the vertical load of the vertical fin;
thirdly, according to the strength of the connecting joint structure of the vertical tail of the fuselage, combining the vertical load of the vertical tail, carrying out calculation and solving of the load of the whole machine, and preliminarily calculating to obtain the load F of the vertical tail joint of each fuselage under each working conditionzi＝9000N/7000N/-20000N/-26000N；i＝1、2、3、4；
Step four, obtaining each joint load under the working condition of 1 according to the step three, converting the joint load to an adjacent machine body frame according to a static force equivalent principle, and obtaining frame loads of Fzj＝7500N/5000N/-6500N/-23000N/-13000N；j＝1、2、3、4、5；
Step five, according to the frame load of the fuselage obtained in the step four, carrying out finite element solution under the full-machine load implementation state with other loads of the fuselage structure, and analyzing and calculating the fatigue margin influence of the key part of the vertical tail connection of the fuselage;
the invention has the advantages that: the invention provides a full-size fatigue test high vertical loading design method for a vertical load of a vertical fin. Based on the characteristics of difficulty in vertical load application of the vertical tail and heavy lever system, the invention provides finite element solution calculation under the full-machine load implementation state, and durability analysis calculation is carried out on the key connection part of the vertical tail of the machine body by adopting an application mode that the vertical load of the vertical tail sinks on the frame of the machine body. The method has the advantages of correct theoretical basis, novel design, clear and simple analysis steps and clear engineering concept. The invention solves the problems of complex vertical load loading system and difficult design.

Claims (3)

1. A full-size fatigue test high vertical tail load loading design method is characterized by comprising the following steps: the method comprises the following steps:
step one, establishing a full-machine finite element model, and solving full-machine load to obtain vertical load F of drooping tail under each load working conditionzj；j＝1、2、3…N；
Determining a load loading form according to the magnitude and magnitude of vertical load of the vertical tail, analyzing the structural forms of a vertical tail connecting joint, a nearby frame, a skin and a stringer of the fuselage, and determining a loading scheme;
thirdly, according to the connection characteristics of the vertical tail of the machine body, the vertical load of the vertical tail is sunk onto the frame of the machine body for applying, and according to the strength of the connection joint structure of the vertical tail of the machine body, the vertical load F of the vertical tail is combinedzPitching moment MYSize, carrying out full-aircraft load calculation solution, and preliminarily calculating to obtain the load F 'of each fuselage vertical tail joint under each working condition'zi；i＝1、2、3…M；
Step four, converting the joint load to an adjacent frame of the airplane body according to the equivalent principle according to the joint load under each working condition obtained in the step three;
and step five, carrying out finite element solution under the full-machine load implementation state with other loads of the machine body structure according to the machine body frame load obtained in the step four, and carrying out durability analysis calculation on the key part of the vertical tail connection of the machine body.
2. The full-scale fatigue test high vertical tail load loading design method according to claim 1, characterized in that: the finite element solving method comprises the following steps: finite element modeling is carried out on the fuselage, the frame, the skin and the stringer, loads are applied to unit nodes, and solving calculation is carried out to obtain stress and load results of each unit.
3. The full-scale fatigue test high vertical tail load loading design method according to claim 1 or 2, characterized in that: the durability analysis and calculation method comprises the following steps: and calculating the service lives of the key joint and the key part through the recalculated stress and load solving result, and giving the fatigue margin of the key part.
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CN111301713A (en) * 2020-04-09 2020-06-19 中国飞机强度研究所 Double-beam type wing adhesive tape load sharing method
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