Rapid design method for airplane profile

Abstract

The invention belongs to the field of overall design shapes of aircrafts, and relates to a rapid design method for an airplane shape. The method comprises the following steps: creating a shape design module based on CATIA software, constructing a theoretical shape of the whole aircraft, carrying out parametric modeling on each part of the aircraft, carrying out associated design, and realizing the quick and synchronous updating capability of the shape of the whole aircraft after the shape parameters of the parts are changed. The method is simple in tool, simplified in step and convenient to operate, and improves the working efficiency of shape selection design.

Description

Technical Field

[0001] The invention belongs to the field of overall design appearance of aircraft and relates to a method for rapid design of aircraft appearance. Background Art

[0002] As a key step in the overall design of an aircraft, shape design directly affects the aircraft's aerodynamic characteristics and performance indicators. The quality of shape design is crucial to the successful development of a new aircraft. Therefore, it is inevitable to carry out a variety of shape selection and design work during the design process, which requires multiple shape design schemes, bringing a huge workload for shape design.

[0003] At present, appearance design mostly adopts an independent design form. When it involves the appearance design of multiple components, multiple designers are required to design at the same time, and the parametric association method is not used in the design process. When the appearance of a component needs to be changed, not only the appearance of the component needs to be redrawn, but also its related components need to be redrawn, which requires multiple people to carry out appearance design work. Summary of the invention

[0004] Purpose of the invention: To provide a method for rapid design of aircraft shape, so as to solve the problem of low efficiency in modifying shape parameters during the aircraft shape design process.

[0005] Technical solution:

[0006] A method for rapid design of aircraft shape is provided, including:

[0007] Based on the generative appearance design module of CATIA software, the theoretical appearance of the entire aircraft is constructed. Through parametric modeling of various aircraft components and associative design, the ability to quickly and synchronously update the appearance of the entire aircraft is achieved when the appearance parameters of the components are changed.

[0008] Furthermore, based on the generative shape design module and assembly module of CATIA software, the theoretical shape of the whole aircraft is constructed. By parametric modeling of each aircraft component and associative design, the whole aircraft shape can be quickly and synchronously updated after the shape parameters of the components are changed, including:

[0009] Step 1: Design the parameters of each aircraft component in a related manner; the components include: fuselage, wing, wing-body fairing, engine nacelle, and landing gear nacelle;

[0010] Step 2: Based on the above-mentioned associative design, the generative shape design module of CATIA software is used to construct the parametric theoretical shape skeleton of the whole aircraft of each component, thereby creating the parametric theoretical shape of the whole aircraft of each component;

[0011] Step 3: Quickly update and check the theoretical appearance of the entire machine by changing the parameters of each component.

[0012] Furthermore, the method further comprises:

[0013] Step 4: By adjusting the parameters of any component, the theoretical appearance of the entire machine can be quickly updated.

[0014] Furthermore, the associations among the various aircraft components include:

[0015] The fuselage is the parent component, unidirectionally associated with the wing, aerofoil, wing-body fairing, engine nacelle, and landing gear nacelle;

[0016] The wing is the parent component, unidirectionally linked to the wing-body fairing and the engine nacelle.

[0017] Further, the component also includes a radome;

[0018] The relationships between the various parts of the aircraft also include:

[0019] The radome is a sub-component and is associated with the fuselage or wing-body fairing as required.

[0020] Furthermore, the parametric design of step 2 must meet the following rules:

[0021] Only the key publishing elements and basic coordinate systems of associated components are allowed to be referenced; external reference elements are minimized; key control dimensions are set as parameters, and mathematical formulas are used to reference parameters for design process dimensions; avoid using curve design methods such as pasting by results, circular references, sketch references to surfaces, unconstrained sketches, and uncontrollable tangent directions.

[0022] Furthermore, by adjusting the parameters of any component, the theoretical shape of the entire machine can be quickly updated, including:

[0023] The component parameters to be adjusted are obtained based on the CFD simulation calculation results and the selected wind tunnel test results, thereby updating the corresponding components and / or the theoretical shape of the entire aircraft.

[0024] Beneficial Effects

[0025] This method uses parametric associative design to obtain a three-dimensional digital model of the parametric associative theoretical appearance of the entire aircraft, which can realize adjustable component control parameters - synchronous update of component design results - synchronous update of associated component appearances, and finally quickly obtain a new overall aircraft appearance capability, which can improve workload efficiency and reduce the workload of appearance selection design. At the same time, the associated model update can automatically check for errors, avoid incoordination errors between component interfaces, improve design quality, and reduce design change costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a logical diagram of the relationship between the various parts of the aircraft;

[0027] Figure 2It is a schematic diagram of the creation of parameterized shape components. DETAILED DESCRIPTION

[0028] The present invention provides a method for quickly modifying the appearance. Based on the generative appearance design module of CATIA software, the theoretical appearance of the entire aircraft is constructed. By parametrically modeling the aircraft components (fuselage, wings, wing-body fairings, engine nacelles, landing gear nacelles, antenna covers, etc.), and performing associated design, the ability to quickly and synchronously update the appearance of the entire aircraft is achieved after the appearance parameters of the components are changed. This reduces the workload of appearance selection design in the scheme stage and improves work efficiency. The method comprises the following steps:

[0029] Step 1: Design the correlation between the main parameters of each aircraft component;

[0030] Step 2: construct the parametric shape skeleton of each component based on the generative shape design module of CATIA software;

[0031] Step 3: Create the parametric theoretical shape of each component and perform a quick update check;

[0032] Step 4: Rapidly update the appearance of the entire machine by adjusting the design parameters of the component appearance.

[0033] Combination Figure 1 , Figure 2 , provides a method for rapid design of aircraft shape, based on CATIA software generative shape design module and assembly module, to construct the theoretical shape of the whole aircraft, through parametric modeling of aircraft components (fuselage, wing, wing-body fairing, engine nacelle, landing gear nacelle, radome, etc.), and associative design, to achieve the ability to quickly and synchronously update the shape of the whole aircraft after the shape parameters of the components are changed. This method includes the following steps:

[0034] Step 1: Design the association of the main parameters of each aircraft component, associate the parameters of the six major components of fuselage, wing, tail, wing-body fairing, engine nacelle, and landing gear nacelle, and realize the ability to update the associated components of a single component synchronously, reducing the workload caused by the change of other components when a single component is changed. The fuselage is associated with the wing through the wing front beam frame and the middle section shape elements; the fuselage is associated with the landing gear nacelle through the landing gear main load-bearing frame and the middle section shape elements; the fuselage is associated with the tail through the tail front beam frame and the tail section shape elements; the wing-body fairing is associated with the fuselage shape, wing front beam plane, wing rear beam plane, central wing shape, wing leading edge, and wing trailing edge elements; the wing is associated with the engine nacelle through the wing leading edge, wing shape, engine suspension rib plane, and wing front beam plane elements. The association relationship is unidirectional. When the parent component is changed, the child level is updated synchronously. Reverse references and cross-level references are strictly prohibited.

[0035] Step 2: Based on the generative shape design module of CATIA software, the parametric shape skeleton of each component is constructed, and the parametric design method is used to parametrically model the various aircraft components (fuselage, wings, tail, wing-body fairing, engine nacelle, landing gear nacelle). The parametric design process only allows the reference of key release elements and basic coordinate systems of associated components; external reference elements are minimized; key control dimensions are set as parameters, and the design process dimensions use mathematical formulas to reference parameters; standardize the design process, and avoid the use of design methods such as pasting by results, circular references, sketch reference surfaces, unconstrained sketches, and curves with uncontrollable tangent directions.

[0036] Step 3: Create parametric theoretical shapes for each component based on the surface function of the generative shape design module of CATIA software. After the design is completed, perform parametric checks and surface quality checks on the design results to ensure that key control parameters can be adjusted and the shape can be updated. After completion, the design results will be published to facilitate the reference of sub-component parameters.

[0037] Step 4: Optimize the overall shape of the aircraft based on the CFD simulation calculation results and the selected wind tunnel test results, and quickly update the overall shape of the aircraft by adjusting the design parameters of the component shapes.

[0038] In summary, after constructing the parametric associated shape of the aircraft, the new shape of the entire aircraft can be quickly obtained by adjusting the shape parameters, thereby reducing the workload of shape selection and design in the scheme stage and improving work efficiency.

Claims

1. A method for rapid design of aircraft shape, characterized in that: include: Based on the generative appearance design module of CATIA software, the theoretical appearance of the entire aircraft is constructed. Through parametric modeling of various aircraft components and associative design, the ability to quickly and synchronously update the appearance of the entire aircraft is achieved when the appearance parameters of the components are changed.

2. The method according to claim 1, characterized in that Based on the generative shape design module and assembly module of CATIA software, the theoretical shape of the whole aircraft is constructed. By parametric modeling of each aircraft component and associative design, the whole aircraft shape can be quickly and synchronously updated after the shape parameters of the components are changed, including: Step 1: Design the parameters of each aircraft component in a related manner; the components include: fuselage, wing, wing-body fairing, engine nacelle, and landing gear nacelle; Step 2: Based on the above-mentioned associative design, the generative shape design module of CATIA software is used to construct the parametric theoretical shape skeleton of the whole aircraft of each component, thereby creating the parametric theoretical shape of the whole aircraft of each component; Step 3: Quickly update and check the theoretical appearance of the entire machine by changing the parameters of each component.

3. The method according to claim 2, characterized in that The method further comprises: Step 4: By adjusting the parameters of any component, the theoretical appearance of the entire machine can be quickly updated.

4. The method according to claim 2, characterized in that: The relationships between the various parts of the aircraft include: The fuselage is the parent component, unidirectionally associated with the wing, aerofoil, wing-body fairing, engine nacelle, and landing gear nacelle; The wing is the parent component, unidirectionally linked to the wing-body fairing and the engine nacelle.

5. The method according to claim 4, characterized in that Parts also include a radome; The relationships between the various parts of the aircraft also include: The radome is a sub-component and is associated with the fuselage or wing-body fairing as required.

6. The method according to claim 2, characterized in that The parametric design of step 2 must meet the following rules: Only the key publishing elements and basic coordinate systems of associated components are allowed to be referenced; external reference elements are minimized; key control dimensions are set as parameters, and mathematical formulas are used to reference parameters for design process dimensions; avoid using curve design methods such as pasting by results, circular references, sketch references to surfaces, unconstrained sketches, and uncontrollable tangent directions.

7. The method according to claim 3, characterized in that By adjusting the parameters of any component, the theoretical shape of the entire machine can be quickly updated, including: The component parameters to be adjusted are obtained based on the CFD simulation calculation results and the selected wind tunnel test results, thereby updating the corresponding components and / or the theoretical shape of the entire aircraft.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the method according to any one of claims 1 to 7 is implemented.

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