KR101310201B1 - Load analysis system and load analysis method to design the internal weapon bay of fifth generation aircraft - Google Patents

Abstract

PURPOSE: A load analysis system and a load analysis method for designing the internal weapon bay (IWB) of fifth generation aircraft are provided to calculate a load necessary for the IWB, the system for carrying arms equipment, the system for launching and releasing the arms equipment, and the opening and shutting of the cover of the IWB. CONSTITUTION: A base data extraction module (100) sets up the predetermined demanding and designing standards and extracts base data for IWB design. A data generation module (200) generates weight data based on the base data. A calculation module (300) calculates a load for IWB design using the weight data. A result output module (400) outputs a load value for IWB design.

Description

LOAD ANALYSIS SYSTEM AND LOAD ANALYSIS METHOD TO DESIGN THE INTERNAL WEAPON BAY OF FIFTH GENERATION AIRCRAFT}

The present invention relates to a load analysis system and load analysis method for the design of the internal armed window of the fifth generation fighter, and more specifically, the internal armed window, cover door, missile carrying and launching system, and armed necessary for the design of the inner armed window. The present invention relates to a load analysis system and a load analysis method for the design of an internal armed window of a fifth generation fighter jet for the design of a drop system.

Recently developed fighters are increasingly important for stealth performance to increase pilot survivability. Considering stealth performance, fifth-generation fighters must use an internal armed window to prevent detection by enemy radars.

Stealth refers to the ability to cover up against all detection functions by considering structural, material, electromagnetic, and shape characteristics from the design stage. Say. Due to the nature of fighters, it is necessary to equip fighters to suppress enemy aircraft or to attack ground targets, but when equipped with an external weapon such as an arm, it is easy to be captured by enemy detection equipment. In the case of the aircraft, an internal armored window is installed on the aircraft to improve stealth function.

Here, the internal armed window must be able to equip as much weapons as possible while overcoming spatial constraints, and in order to avoid enemy detection even during high-speed maneuvers, armed firing and dropping missions must be carried out in a very short time. There is a problem that is needed.

Accordingly, the present invention provides an internal armed window for the internal armed window design of a fifth generation fighter, a system capable of carrying an armed system, a system for launching and discharging an armed arm, and a 5 It is an object of the present invention to provide a load analysis system and load analysis method for the design of internal armored windows of generation fighters.

In order to achieve the above object, the load analysis system for the internal armed window design of the fifth generation fighter according to the present invention sets requirements and design criteria for the internal armed window design, based on the requirements and the design criteria Data generation for generating a weight data based on the basic data extraction module 100 for extracting the basic data for the internal armed window design, and the basic data for the internal armed window design extracted from the basic data extraction module 100 Module 200, the calculation module 300 for calculating the load for armed window design using the weight data generated in the data generation module 200 and the armed window design calculated in the calculation module 300 It characterized in that it comprises a result output module 400 for outputting a load value for.

In addition, the load analysis system for the design of the internal armed window of the fifth generation fighter according to the present invention, in the data extraction module 100, the requirement and the design criteria are maneuvering area and emergency landing according to the flight shape and mission It is characterized by the situation, the firing time, the spin, and the firing load.

In addition, the load analysis system for the internal armed window design of the fifth generation fighter according to the present invention, in the data extraction module 100, the basic data is the aircraft shape, the armed mounting shape, aircraft maneuvering parameters, aerodynamic data And a weight data, a firing profile, and a friction coefficient.

In addition, the load analysis system for the internal armed window design of the fifth generation fighter according to the present invention, in the data generation module 200, the weight data is armed window aerodynamic load, cover door aerodynamic load, armed aerodynamic load It is characterized by.

In addition, the load analysis system for the design of the internal armed window of the fifth generation fighter according to the present invention, the cover door aerodynamic load is characterized in that the cover door to the closed shape, the cover door to extract the results of the open shape, respectively .

In addition, the load analysis system for the internal armed window design of the fifth generation fighter according to the present invention, in order to extract the cover door aerodynamic load,

식(1)

Equation (1)

Where P _i is the pressure acting on the i ^th panel, q _∞ is the dynamic pressure under the analysis conditions, C _{p_i} is the pressure coefficient of the i ^th panel, F _i is the load acting on the panel in each direction, and A _i is i ^th The panel area, n _i is characterized in that the cover door aerodynamic load is extracted through the normal direction vector of the i ^th panel.

In addition, the load analysis system for the internal armed window design of the fifth generation fighter according to the present invention, when calculating the load for armed window design in the calculation module 300, armed window aerodynamic load, cover door aerodynamic load and In addition, the armed aerodynamic load, the inertial load and the missile carrying system is characterized by including the load.

In addition, the load analysis system for the internal armed window design of the fifth generation fighter according to the present invention, in the result output module 400, the load value for armed window design is characterized in that to output using a load coordinate system.

In addition, the load analysis method for the internal armed window design of the fifth generation fighter according to the present invention, to set the requirements and design criteria for the internal armed window design, the internal armed window design based on the requirements and the design criteria Basic data extraction step (S100) for extracting the basic data for the data generation step (S200) for generating a weight data based on the basic data for the internal armed window design extracted in the basic data extraction step (S100) And a calculation step (S300) of calculating a load for armed window design using the weight data generated in the data generation step (S200), and a load value for armed window design calculated in the calculation step (S300). And outputting the result output step (S400).

According to the present invention, an internal armed window necessary for designing an internal armed window of a fifth generation fighter, a system capable of carrying an armed system, a system for launching and discharging an armed arm, and a 5 necessary to open and close a cover door of an internal armed window It has the effect of providing a load analysis system and load analysis method for the design of internal armored windows of generation fighters.

1 shows a load analysis system for internal armed window design.
2 shows an example of aerodynamic analysis.
3 shows an area ratio formula;
4 is a diagram illustrating a load analysis step for armed window design according to the present invention.
5 is a view showing a limit load drainage during emergency landing.
6 shows a Trapeze system for carrying missiles.
7 shows a basic analysis of the Trapeze system.
8 shows a store / actuator suppository.
9 shows the armed window design cover door coordinates.
10 shows load analysis results for missile system design.
11 is a view showing a load analysis result for Bomb system design.
Fig. 12 shows load analysis results for cover door design and cover door operating actuator design in stealth shape;

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings and the following description. However, the present invention is not limited to the embodiments described herein but may be embodied in other forms. Rather, the embodiments disclosed herein are provided so that the disclosure can be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Like reference numerals designate like elements throughout the specification. It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. In the present specification, the singular form includes plural forms unless otherwise specified in the specification. &Quot; comprises "and / or" comprising ", as used herein, unless the recited element, step, operation, and / Or additions.

-Requirements and design criteria

The basic requirements for internal armed window design are defined to include maneuvering area, emergency landing situation, firing time, spin and firing load according to flight geometry / mission as shown in Table 1. The design criteria mainly apply to MIL-STA-8591, which defines the armament, buffers, and connections to aircraft, and other general aircraft design criteria.

Basic data

Many basic data are needed for load analysis of internal armored windows, especially aircraft shape, armed shape, aircraft maneuvering parameters, aerodynamic data, weight data, launch profile, and friction coefficient. The basic data used for static load analysis can be shown in Table 2.

-Armed Spear

There are many ways to generate aerodynamic loads, but considering the number of analysis conditions and the convenience of calculation, panel methods are generally used in the field of load analysis. Previous methods used the DLM (Doublet Lattice Method) based on the 2D analysis model, but there are many limitations in performing aerodynamic analysis of three-dimensional structures such as internal armored windows. Therefore, in the present invention, as shown in FIG. 2, ZONAIR, a commercial software for 3D panel analysis, is used, and the aerodynamic coefficient value at the electric field level is compared with the CFD analysis result to ensure reliability of the aerodynamic analysis result.

-Aero cover door

As shown in FIG. 2, the aerodynamics of the cover door are extracted from the results of the closed and open shapes through 3D panel modeling, and the load applied to the door hinge is calculated through Equation (1).

식 (1)

Formula (1)

Where P _i is the pressure acting on the i ^th panel, q _∞ is the dynamic pressure under the analysis conditions, C _{p_i} is the pressure coefficient of the i ^th panel, F _i is the load acting on the panels in each direction, and A _i is the i ^th panel The area, n _i, is the normal direction vector of the i ^th panel.

Armed Aerodynamics

In the case of missiles, the cover doors open, and when the armed system comes out, a large aerodynamic load is applied. This aerodynamic force is derived from the flight test measurement data of similar missiles, and the aerodynamic coefficient function for the analysis conditions is extracted as shown in Table 3, and the final aerodynamic force is calculated by applying the area ratio formula shown in FIG.

When the armed window is opened, a pressure change occurs inside the armed window. At this time, the aerodynamic force acting on the arming system and the arming has a significant influence on the aerodynamic characteristics of the arming during arming release, but it is not critical from the point of view of the design load, so the initial pressure state in the armed window only considers the inertia load. However, the pressure of the rear structure inside the armed window cannot be ignored, so the drag coefficient and the projected area of the plate are taken into account.

-Weight data generation

The weight data for calculating the inertial load is divided from the CATIA model by the weight of the center, the center of gravity, and the mass of the continuum structure, which is divided into slices and the mass of masses that can be expressed as a single mass, such as armed or system parts. Generate rotational inertia (MOI) data.

-Load analysis

-Load analysis program

Using the MATLAB program for the analysis of the internal armored window, the program SELA that can calculate the load for each part required for the internal armored window design as shown in FIG. This program consists of basic data extraction module, data generation module, calculation module and result output module. The results from this program are sufficient to be used as initial design loads, but additional dynamic load analysis should be performed for missile transport systems, missile launches, and bomb release analyzes to generate the final load.

-Aerodynamic / Inertial force calculation

The aerodynamic load of the cover door and IWB is accumulated at the load reference point (LRP) after the panel pressure is converted to each panel load using equation (1). The inertial load is calculated by the weight item weight, and then converted to the equivalent load at the armed CG and LRP positions. The limit load multiple during emergency landings applies to FIG. 5.

-Missile system calculation

The missile transport system uses the Trapeze method as shown in FIG. 6. The basic structure of the system is two links connected to the mistletoe launcher and an actuating actuator on the rear link.

The actuating actuator design load is assumed to be a 2D plane as shown in FIG. 7, and only the Fx, Fy, and Mz loads that have an important effect on the system are added as external forces, and the maneuvering load according to the opening angle and the hang fire condition or tip-off state of the missile. Determine the final load taking into account static conditions at. Actuator load and supporting load are verified by dynamic load analysis and FEM analysis using ADAMS.

- Analysis result

-Load coordinate system

For the convenience of analysis, a load coordinate system is used, and mountings such as arming are defined as shown in FIG. 8 in consideration of aerodynamic characteristics. In the case of the cover door, as shown in FIG. 9, the direction in which the door is to be opened is defined in the + direction, and the hinge moment generated by this force is defined in the positive direction.

Armed load

10 is a load analysis result for the missile system design. Hang fire condition and emergency landing condition are important for X direction load, and emergency landing condition and maneuver condition are important for Y direction load.

For the load in the Z direction, tip-off and maneuvering loads are important. 11 is a load analysis result for Bomb system design. In the case of bomb loads, due to the large armed weight effect, emergency landing conditions are most important in most cases.

-Cover door load

Fig. 12 shows load analysis results for cover door design and cover door operating actuator design in stealth shape. In the case of cover doors, both the directional pressure in the closed state and the directional pressure in the open state are to be considered, and the appropriate actuator position and the design load are to be calculated by calculating the load acting on each section. Of particular note is that the position of the IWB is located in the center of the fuselage, it can be seen that a sudden pressure change, which is considered a shock wave occurs.

- conclusion

Through the present invention, the load analysis required for the design of the internal armored window was performed. To this end, a number of basic data were generated, especially for aerodynamic loads, using the 3D panel method to obtain satisfactory results.

We also developed a program for armed window load analysis for ease of analysis. Finally, load analysis was performed to design cover doors, armed hauling, launching and dropping systems to create the optimum conditions for the design.

The methods and analysis techniques obtained through the present invention will be successfully used for the development of armed systems and fifth generation aircraft to be developed in the future.

Although the embodiments of the present invention have been described above, various modifications may be made by those skilled in the art. Therefore, it should be understood that the present invention should not be construed as being limited to the above embodiments, but should be construed in accordance with the following claims.

100: keynote data generation module
200: data generation module
300: calculation module
400: result output module

Claims (9)

Basic data extraction module 100 for setting a predetermined requirement and design criteria for the interior armed window design and extracting the basic data for the interior armed window design based on the predetermined requirements and the design criteria. and,
A data generation module 200 generating weight data based on the basic data for designing the internal armed window extracted by the basic data extraction module 100;
Calculation module 300 for calculating the load for armed window design using the weight data generated by the data generation module 200,
Including a result output module 400 for outputting the load value for the armed window design calculated in the calculation module 300,
In the data extraction module 100,
The requirements and the design criteria are maneuvering area according to flight shape and mission, emergency landing situation, launch time, spin, launch load,
The basic data are aircraft shape, armed shape, aircraft maneuvering parameters, aerodynamic data, weight data, launch profile, friction coefficient,
In the data generation module 200,
The weight data are armed window aerodynamic load, cover door aerodynamic load, armed aerodynamic load,
The cover door aerodynamic load extracts the results of the cover door closed shape and the cover door open shape, respectively,
To extract the cover door aerodynamic load,

Equation (1)
Where P _i is the pressure acting on the i ^th panel, q _∞ is the dynamic pressure under the analysis conditions, C _{p_i} is the pressure coefficient of the i ^th panel, F _i is the load acting on the panel in each direction, and A _i is i ^th Panel area, n _i is the normal direction vector of i ^th panel)
Through the cover door aerodynamic load,
In the calculation module 300,
When calculating the load for armed window design, the armed window aerodynamic load, cover door aerodynamic load, armed aerodynamic load, including inertial load and missile carrying system load are included. Load analysis system for window design. delete delete delete delete delete delete The method of claim 1,
In the result output module 400,
A load analysis system for designing an internal armed window of a fifth generation fighter, characterized by outputting a load value for armed window design using a load coordinate system. delete

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