CN116738572B - Aircraft configuration modularized assembly method and system - Google Patents
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Abstract
The embodiment of the invention provides an aircraft configuration modularized assembly method, and belongs to the technical field of aircraft modeling. The method comprises the following steps: acquiring component selection information triggered by a user based on the bottom layer geometric engine, and determining a component set based on the component selection information; performing component assembly based on a pre-constructed component assembly model and the component set to obtain a module set; based on a pre-constructed module assembly model and the module set, performing module assembly to obtain an assembly model; wherein, a module is assembled from a plurality of corresponding components. The method solves the problems of low modeling efficiency, low accuracy and inconsistent design standards of the existing aircraft modeling scheme.
Description
Technical Field
The invention relates to the technical field of aircraft modeling, in particular to a modular assembly method and a modular assembly system for an aircraft configuration.
Background
The development of the aerospace craft is a complex system engineering, the scheme design of the aerospace craft is a multi-professional and multi-disciplinary collaborative design process, and the following working situations exist in the overall scheme design stage of the aerospace craft at present:
1) The general scheme design stage has no three-dimensional model, and the main submissions are two-dimensional graphs and general scheme data files. The traditional CAD software is not suitable for the design stage of the aircraft scheme, firstly, the modeling workload by using the CAD software is large and takes a long time, secondly, the overall scheme design stage does not need a very detailed aircraft structure, the fineness of the model is less complex than that of a digital prototype stage, and only the model is required to express the layout structure.
2) The design of an aircraft is entirely dependent on the personal experience of the designer. Empirical data is critical in aircraft design, and if the designer designs more accurately, the number of design iterations is small. If the designer gives a large inaccuracy in the design values, the number of design iterations increases significantly.
3) The design mode is different due to different models and different personal experience levels, and the design tools adopted by the overall scheme data are inconsistent. The formula calculation is carried out in Excel through a formula or a MATLAB program is compiled, and each model adopts a single set of calculation formula according to different structures of various models.
4) The modular design is not available, although the single-model design has preliminarily provided the idea of module design, the modular design cannot be realized because the module division methods of the models are inconsistent, data barriers exist between the models and cannot be used for reference, and the rule of module division of the models is not unified. This is not conducive to product serialization and modular planning, and cannot achieve multi-scheme parallel design.
It can be seen that in the existing aircraft modeling schemes, there are problems of low modeling efficiency, low accuracy and inconsistent design standards, and a new modularized assembly method for a vehicle configuration needs to be created for the problems.
Disclosure of Invention
The embodiment of the invention aims to provide a modularized assembly method and a modularized assembly system for a vehicle configuration, which at least solve the problems of low modeling efficiency, low accuracy and inconsistent design standards of the existing aircraft modeling scheme.
To achieve the above object, a first aspect of the present invention provides a modular assembly method of an aircraft configuration, the method comprising: acquiring component selection information triggered by a user based on the bottom layer geometric engine, and determining a component set based on the component selection information; performing component assembly based on a pre-constructed component assembly model and the component set to obtain a module set; based on a pre-constructed module assembly model and the module set, performing module assembly to obtain an assembly model; wherein, a module is assembled from a plurality of corresponding components.
Optionally, the method further comprises: constructing the underlying geometry engine, comprising: based on a geometric engine angcad, a basic engine is constructed by combining with the SysML standard; coupling a preset engineering algorithm on the basic engine to obtain a bottom layer geometric engine; wherein, the preset engineering algorithm comprises: one or more of flight timing, mass substation, and mass characteristics.
Optionally, the acquiring the component selection information triggered by the user based on the underlying geometry engine, determining the component set based on the component selection information, includes: determining a target component based on the component selection information triggered by the user; in a pre-constructed component library, searching the target component, positioning and extracting the target component; and each time one component selection information is triggered, a target component is correspondingly extracted, and the extracted target component is stored in the component set.
Optionally, the building rule of the component library includes: carrying out parameterization expression on each component based on the component type, and obtaining a parameterized component based on a parameterized expression result; the parameterized expression is expressed on the type of the component, the structure of the component and the geometric topological structure of the aircraft where the component is located; the component types include: one or more of a storage tank class, nose cone class, class of engines, class of airfoils, and special class.
Optionally, the method further comprises: building a component assembly model, comprising: acquiring a component assembly knowledge graph, and taking the component assembly knowledge graph as first training sample data; model training is carried out based on the first training sample data, and a component assembly model is obtained; building a module assembly model, comprising: acquiring a module assembly knowledge graph, wherein the module assembly knowledge graph is used as second training sample data; and performing model training based on the second training sample data to obtain a module assembly model.
Optionally, the assembling of the components based on the pre-constructed component assembling model and the component set to obtain a module set includes: traversing the component set, and identifying component assembly coordinates of the components one by one and reference coordinates of assembled modules corresponding to the components; obtaining a one-to-one correspondence between assembly coordinates of each component and reference coordinates of an assembled module; and when a certain component is identified as a split component of the module, executing the component assembly based on the corresponding relation, and completing all component assembly.
Optionally, the module assembling is performed based on the pre-constructed module assembling model and the module set, so as to obtain an assembling model, which includes: taking the origin of the module as the module assembly coordinate, and taking the reference coordinate of the last assembled module for the component in the module as the assembled coordinate of the module; and executing module assembly based on the module assembly coordinates and the assembled coordinates of the modules to complete assembly of all the modules.
Optionally, the method further comprises: in the process of executing component assembly and module assembly, if the assembly position is reported to be wrong, opening a modification function; and recovering the adjustment assembly parameters and/or the coordinate shift parameters of the user, and executing secondary assembly.
A second aspect of the invention provides an aircraft configuration modular assembly system, the system comprising: the acquisition unit is used for acquiring component selection information triggered by a user based on the bottom layer geometric engine and determining a component set based on the component selection information; the component assembly unit is used for assembling the components based on the pre-constructed component assembly model and the component set to obtain a module set; the module assembling unit is used for assembling the modules based on the pre-constructed module assembling model and the module set to obtain an assembling model; wherein, a module is assembled from a plurality of corresponding components.
In another aspect, the present invention provides a computer readable storage medium having instructions stored thereon that when run on a computer cause the computer to perform the aircraft configuration modular assembly method described above.
Through the technical scheme, the aircraft configuration is subjected to modularized design, when a user has initial modeling requirements, only a target component needs to be triggered in a construction library, and then the component and the module are automatically assembled, so that the automatic assembly in the whole modeling process is realized. The three-dimensional solid model is not needed in the design stage of the overall scheme of the aircraft, the assembly efficiency is greatly improved, the assembly precision is ensured through the modularized design, and the product serialization design is also realized.
Additional features and advantages of embodiments of the invention will be set forth in the detailed description which follows.
Drawings
The accompanying drawings are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain, without limitation, the embodiments of the invention. In the drawings:
FIG. 1 is a flow chart of steps of a modular assembly method for an aircraft configuration provided in accordance with one embodiment of the present invention;
FIG. 2 is a system block diagram of an aircraft configuration modular assembly system provided in one embodiment of the invention.
Detailed Description
The following describes specific embodiments of the present invention in detail with reference to the drawings. It should be understood that the detailed description and specific examples, while indicating and illustrating the invention, are not intended to limit the invention.
The development of the aerospace craft is a complex system engineering, the scheme design of the aerospace craft is a multi-professional and multi-disciplinary collaborative design process, and the following working situations exist in the overall scheme design stage of the aerospace craft at present:
1) The general scheme design stage has no three-dimensional model, and the main submissions are two-dimensional graphs and general scheme data files. The traditional CAD software is not suitable for the design stage of the aircraft scheme, firstly, the modeling workload by using the CAD software is large and takes a long time, secondly, the overall scheme design stage does not need a very detailed aircraft structure, the fineness of the model is less complex than that of a digital prototype stage, and only the model is required to express the layout structure.
2) The design of an aircraft is entirely dependent on the personal experience of the designer. Empirical data is critical in aircraft design, and if the designer designs more accurately, the number of design iterations is small. If the designer gives a large inaccuracy in the design values, the number of design iterations increases significantly.
3) The design mode is different due to different models and different personal experience levels, and the design tools adopted by the overall scheme data are inconsistent. The formula calculation is carried out in Excel through a formula or a MATLAB program is compiled, and each model adopts a single set of calculation formula according to different structures of various models.
4) The modular design is not available, although the single-model design has preliminarily provided the idea of module design, the modular design cannot be realized because the module division methods of the models are inconsistent, data barriers exist between the models and cannot be used for reference, and the rule of module division of the models is not unified. This is not conducive to product serialization and modular planning, and cannot achieve multi-scheme parallel design.
Therefore, in the existing aircraft modeling scheme, the problems of low modeling efficiency, low accuracy and inconsistent design standards generally exist, and the novel aircraft configuration modularized modeling method is provided according to the scheme. According to the scheme, the aircraft configuration is subjected to modularized design, when a user has initial modeling requirements, only a target component needs to be triggered in a construction library, and then the component and the module are automatically assembled, so that automatic assembly in the whole modeling process is realized. The three-dimensional solid model is not needed in the design stage of the overall scheme of the aircraft, the assembly efficiency is greatly improved, the assembly precision is ensured through the modularized design, and the product serialization design is also realized.
FIG. 1 is a flow chart of a method for modular assembly of an aircraft configuration according to one embodiment of the present invention. As shown in fig. 1, an embodiment of the present invention provides a modular assembly method for an aircraft configuration, the method comprising:
step S10: the user-triggered component selection information is collected based on the underlying geometry engine, and a component set is determined based on the selection information.
Specifically, constructing the underlying geometry engine includes: based on a geometric engine angcad, a basic engine is constructed by combining with the SysML standard; coupling a preset engineering algorithm on the basic engine to obtain a bottom layer geometric engine; wherein, the preset engineering algorithm comprises: one or more of flight timing, mass substation, mass characteristics.
In the embodiment of the invention, the aircraft system composition logic architecture is composition logic defining an aircraft configuration structure, describing how many main body modules an aircraft configuration is composed of, why the aircraft structure layout is a hierarchical structure tree. In the scheme of the invention, in order to realize the logical architecture of the aircraft system composition, a light geometric engine based on an angcad (geometric engine) is provided, and the engineering algorithms such as a flight sequence, a mass substation, a mass characteristic and the like are combined with the standard modeling language of SysML (Systems Modeling Language, system modeling language) and related data format specifications to form the bottom foundation of the modular intelligent design of the aircraft configuration.
On the basis of the bottom geometrical engine, the design of the aircraft system composition logic architecture is developed and realized. Mainly comprises the following three layers:
1) Typical components for expressing the minimum structure constituting an aircraft are developed based on the underlying architecture.
2) Each body module expressing the aircraft configuration is realized through different component parameterized design assembly modeling.
3) The three-dimensional structure of the aircraft is quickly built through the modular combination design of the main bodies.
In the embodiment of the invention, the scheme is intended to realize modularized construction, and a corresponding construction platform is required to be constructed so as to quickly construct a model without detailed modeling data when the front end is designed for solving the technical problem of the scheme. Therefore, to implement this fast and standard unified model building scheme, a corresponding platform set-up is necessary. On the built platform, component selection and subsequent assembly processes can be rapidly realized, user operation steps are reduced, and subjective interference is avoided.
Preferably, the method for determining the component set based on the selection information includes the steps of: determining a target component based on the component selection information triggered by the user; in a pre-constructed component library, carrying out the target construction search, positioning and extracting the target component; and each time a component selection message is triggered, a target component is correspondingly extracted, and the extracted target component is stored in the component set.
In the embodiment of the invention, when the model is built, because the model is only the initial conception imaging, a user can make building selection based on requirements. Preferably, in order to avoid the problem that the selected components are not matched with each other, after triggering one component selection, the user can select the subsequent component selection, only the matched component of the selected component, and other components which cannot be matched with the current component can prevent the user from selecting, so that the problem of component misselection caused by insufficient experience of the user is avoided. The model construction threshold is lowered, and the assembly model is prevented from deviating from expectations.
Preferably, the building rule of the component library includes: carrying out parameterization expression on each component based on the component type, and obtaining a parametric component based on a parameterization expression result; the parameterized expression is expressed on the construction type, the component structure and the geometric topological structure of the aircraft where the construction is located; the component types include: one or more of a storage tank class, nose cone class, class of engines, class of airfoils, and special class.
In the embodiment of the invention, the aircraft configuration design requires rich engineering design experience and rule knowledge of a designer, and knowledge engineering technology is adopted to integrate the aircraft industry knowledge, specification and experience into a three-dimensional modeling algorithm to form a parameterized modeling technology based on the aircraft knowledge rule. The method is characterized in that the knowledge abstraction expression is carried out on the aircraft components aiming at the structural characteristics of the aircraft, and the aircraft structural design model in the overall scheme design stage is simplified through parameterized component modeling, so that the purpose of no three-dimensional modeling in the overall scheme design stage is realized. Parameterized components are parameterized representations of the geometric topology of an aircraft structure, describing how a component is defined, how it is expressed by parameters, and how it is classified. At present, the components based on knowledge rules comprise six major components of storage tanks, nose cones, cabin sections, engines, wing surfaces and special types, and the components comprise 28 components. The method specifically comprises the following steps:
1) Class of cabin: in the aircraft structure, the physical structures such as an instrument cabin, a box section, an interstage section, a transition section, a load bracket and the like are complex, and most of the structures are grid reinforcement and skin. The design stage of the overall scheme does not need a geometric model with detailed characteristic details, so that the structure of the physical model is required to be simplified, the structure of a real model is expressed by a light cylinder section with a certain wall thickness, and the design of three deformation structures of a front cone, a back cone and a column section is realized by parameterized adjustment of the diameters and the heights of the upper end and the lower end of the model.
2) Storage tanks: the structure of the aircraft is provided with oxygen and fuel tanks for storing propellant, and the structure layout design is different according to different task demands, and the common structure comprises a serial structure with equal diameters of the oxygen fuel tanks, a serial structure with equal diameters of the oxygen fuel tanks and common bottoms, a serial structure with unequal diameters of the oxygen fuel tanks, an oxygen fuel tank parallel structure and the like. By parameterizing the structure of the storage tank, the rapid modeling of different structures of the storage tank is realized.
3) Nose cone: the common nose cone types in aircraft design comprise three types of parameterized designs of von karman nose cone, bulb truncated cone and oblique nose cone due to different aerodynamic performance requirements. Wherein the beveled nose cone is used only for the design of the booster module.
4) Engines are as follows: different engines are adopted for designing an aircraft due to different requirements of flight tasks, and the aircraft mainly comprises two types of liquid engines and solid engines at present. The software realizes geometric modeling and performance calculation of the engine through parameterized description of engine layout and performance data.
5) Airfoil class: in the design of an aircraft, different airfoils need to be designed for stabilizing the flight path. And the wing is parameterized and expressed by combining design knowledge, so that the rapid modeling of the wing surface structure is realized.
Step S20: and performing component assembly based on the pre-constructed component assembly model and the component set to obtain a module set.
Specifically, traversing the component set, and identifying component assembly coordinates of each component one by one and reference coordinates of an assembled module corresponding to the component; obtaining a one-to-one correspondence between assembly coordinates of each component and reference coordinates of an assembled module; and when a certain component is identified as a split component of the module, executing the component assembly based on the corresponding relation, and completing all component assembly.
In one possible embodiment, the component automated assembly technique is to software assembly knowledge commonly used in aircraft assembly designs, and package assembly coordinates and assembled reference coordinates of the component into a component model. The software performs a one-to-one match by automatically identifying the assembly coordinates of the subject component with the assembled reference coordinates of all the components previously assembled to the subject component. And automatically assembled to the structural member that constitutes the aircraft structure when identified as such. The components of the non-aircraft structure are not assembled as assembly components. When the assembly position is not reasonable, the position of the component can be adjusted by adjusting the assembly parameters and the coordinate offset.
Step S30: and performing module assembly based on the pre-constructed module assembly model and the module set to obtain an assembly model.
Specifically, the automated assembly technology of each main body module of the aircraft is to integrate the assembly design knowledge of the aircraft into the configuration design. When designing the module, the origin of coordinates of the module is taken as assembly coordinates, and the assembled parameter coordinates of the last component used for expressing the structure of the module are the assembled reference coordinates of the module. In the process of designing the configuration of the aircraft, the assembly coordinates of the program automatic identification module and the assembled reference coordinates are subjected to rapid assembly design. When the assembly position is unreasonable, the position of the whole arrow can be adjusted by adjusting the assembly parameters and the coordinate offset.
Preferably, the method further comprises: building a component assembly model, comprising: acquiring a component assembly knowledge graph, and taking the component assembly knowledge graph as first training sample data; model training is carried out based on the first training sample data, and a component assembly model is obtained; building a module assembly model, comprising: acquiring a module assembly knowledge graph, wherein the module assembly knowledge graph is used as second training sample data; and performing model training based on the second training sample data to obtain a module assembly model.
In the embodiment of the invention, aiming at the trend that the aircraft design model cannot be quickly serialized from a single model to a model product and the model product modularized design mode is converted, the whole modeling concept of the software is developed based on the modularized design concept. In order to meet the application requirements of aircraft modularization and rapid product serialization, the local and server storage and reuse technologies of an aircraft fairing module, a core-level module, a booster module, a payload module and an escape tower module are provided, and the modularized reuse, modularized sharing and modularized combination design of the aircraft cross-model products are realized. The specific modularization implementation scheme comprises the following steps:
1) Module instance saving techniques are provided in module design and configuration design to store currently designed module instances to a module library for reuse.
2) The configuration design provides a module replacement technique to replace the module currently being designed with a stored mature module.
3) The configuration design provides a module inserting technology, so that a module instance is inserted before an existing module, and the structural increment of the aircraft is quickly realized.
4) During configuration design, a replication boosting module technology is provided, so that the rapid replication of the design state of the boosting module instance is realized, and the layout design of the booster is rapidly realized.
In the embodiment of the invention, the scheme adopts a modularized design idea and a parameterized driving idea, integrates the aircraft configuration design and geometric modeling process, and forms a set of flexible, convenient and lightweight initial configuration modeling tool. The effect that this scheme reaches in aircraft overall scheme configuration design process is as follows:
1) The configuration of the aircraft is converted from a formula, a numerical calculation design, a two-dimensional sketch model design mode to a full three-dimensional model visual design mode of the aircraft in the overall scheme design stage.
2) The three-dimensional physical model of the aircraft is omitted in the overall scheme design stage, and the situation that a designer does not have visual and stereoscopic sense impression on the aircraft is broken through.
3) The design based on the full three-dimensional model and full parameterization is realized, and the overall scheme design efficiency is greatly improved.
4) The modularized design mode is realized, knowledge accumulation of the aircraft component and main body module model is facilitated, and the module reuse and the product serialization design between the same model and different models are satisfied.
FIG. 2 is a system block diagram of an aircraft configuration modular assembly system provided in one embodiment of the invention. As shown in fig. 2, an embodiment of the present invention provides an aircraft configuration modular assembly system, the system comprising: the acquisition unit is used for acquiring component selection information triggered by a user based on the bottom layer geometric engine and determining a component set based on the selection information; the component assembly unit is used for assembling the components based on the pre-constructed component assembly model and the component set to obtain a module set; the module assembling unit is used for assembling the modules based on the pre-constructed module assembling model and the module set to obtain an assembling model; wherein, a module is assembled from a plurality of corresponding components.
Embodiments of the present invention also provide a computer readable storage medium having instructions stored thereon, which when run on a computer cause the computer to perform the above-described modular assembly method of an aircraft configuration.
Those skilled in the art will appreciate that all or part of the steps in a method for implementing the above embodiments may be implemented by a program stored in a storage medium, where the program includes several instructions for causing a single-chip microcomputer, chip or processor (processor) to perform all or part of the steps in a method according to the embodiments of the invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or other various media capable of storing program codes.
The alternative embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the embodiments of the present invention are not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solutions of the embodiments of the present invention within the scope of the technical concept of the embodiments of the present invention, and all the simple modifications belong to the protection scope of the embodiments of the present invention. In addition, the specific features described in the above embodiments may be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, the various possible combinations of embodiments of the invention are not described in detail.
In addition, any combination of the various embodiments of the present invention may be made, so long as it does not deviate from the idea of the embodiments of the present invention, and it should also be regarded as what is disclosed in the embodiments of the present invention.
Claims (8)
1. A method of modular assembly of an aircraft configuration, the method comprising:
acquiring component selection information triggered by a user based on the bottom layer geometric engine, and determining a component set based on the component selection information;
based on the pre-constructed component assembly model and the component set, performing component assembly to obtain a module set, including:
traversing the component set, and identifying component assembly coordinates of the components one by one and reference coordinates of assembled modules corresponding to the components;
obtaining a one-to-one correspondence between assembly coordinates of each component and reference coordinates of an assembled module;
when a certain component is identified as a split component of the module, executing the component assembly based on the corresponding relation to complete all component assembly;
based on a pre-constructed module assembly model and the module set, performing module assembly to obtain an assembly model; wherein, a module is assembled by a plurality of corresponding components;
the module assembling is performed based on the pre-constructed module assembling model and the module set to obtain an assembling model, and the method comprises the following steps:
taking the origin of the module as the module assembly coordinate, and taking the reference coordinate of the last assembled module for the component in the module as the assembled coordinate of the module;
and executing module assembly based on the module assembly coordinates and the assembled coordinates of the modules to complete assembly of all the modules.
2. The method according to claim 1, wherein the method further comprises:
constructing the underlying geometry engine, comprising:
based on a geometric engine angcad, a basic engine is constructed by combining with the SysML standard;
coupling a preset engineering algorithm on the basic engine to obtain a bottom layer geometric engine; wherein,
the preset engineering algorithm comprises the following steps: one or more of flight timing, mass substation, and mass characteristics.
3. The method of claim 1, wherein the capturing user-triggered component selection information based on the underlying geometry engine, determining a set of components based on the component selection information, comprises:
determining a target component based on the component selection information triggered by the user;
in a pre-constructed component library, searching the target component, positioning and extracting the target component;
and each time one component selection information is triggered, a target component is correspondingly extracted, and the extracted target component is stored in the component set.
4. A method according to claim 3, wherein the building rules of the component library comprise:
carrying out parameterization expression on each component based on the component type, and obtaining a parameterized component based on a parameterized expression result; wherein,
the parameterized expression is expressed on the type of the component, the structure of the component and the geometric topological structure of the aircraft where the component is located;
the component types include:
one or more of a storage tank class, nose cone class, class of engines, class of airfoils, and special class.
5. The method according to claim 1, wherein the method further comprises:
building a component assembly model, comprising:
acquiring a component assembly knowledge graph, and taking the component assembly knowledge graph as first training sample data;
model training is carried out based on the first training sample data, and a component assembly model is obtained;
building a module assembly model, comprising:
acquiring a module assembly knowledge graph, wherein the module assembly knowledge graph is used as second training sample data;
and performing model training based on the second training sample data to obtain a module assembly model.
6. The method according to claim 1, wherein the method further comprises:
in the process of executing component assembly and module assembly, if the assembly position is reported to be wrong, opening a modification function;
and recovering the adjustment assembly parameters and/or the coordinate shift parameters of the user, and executing secondary assembly.
7. An aircraft configuration modular assembly system, the system comprising:
the acquisition unit is used for acquiring component selection information triggered by a user based on the bottom layer geometric engine and determining a component set based on the component selection information;
a component assembling unit for performing component assembly based on a pre-constructed component assembly model and the component set to obtain a module set, comprising:
traversing the component set, and identifying component assembly coordinates of the components one by one and reference coordinates of assembled modules corresponding to the components;
obtaining a one-to-one correspondence between assembly coordinates of each component and reference coordinates of an assembled module;
when a certain component is identified as a split component of the module, executing the component assembly based on the corresponding relation to complete all component assembly;
the module assembling unit is used for assembling the modules based on the pre-constructed module assembling model and the module set to obtain an assembling model; wherein, a module is assembled by a plurality of corresponding components;
the module assembling is performed based on the pre-constructed module assembling model and the module set to obtain an assembling model, and the method comprises the following steps:
taking the origin of the module as the module assembly coordinate, and taking the reference coordinate of the last assembled module for the component in the module as the assembled coordinate of the module;
and executing module assembly based on the module assembly coordinates and the assembled coordinates of the modules to complete assembly of all the modules.
8. A computer readable storage medium having instructions stored thereon, which when run on a computer causes the computer to perform the aircraft configuration modular assembly method of any of claims 1-6.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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