CN113704878B - Method for applying load of landing gear by using aircraft structure full-aircraft finite element model - Google Patents
Method for applying load of landing gear by using aircraft structure full-aircraft finite element model Download PDFInfo
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- CN113704878B CN113704878B CN202110896055.5A CN202110896055A CN113704878B CN 113704878 B CN113704878 B CN 113704878B CN 202110896055 A CN202110896055 A CN 202110896055A CN 113704878 B CN113704878 B CN 113704878B
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- 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
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Abstract
The application belongs to the field of aircraft structure design, and particularly relates to a method for applying a landing gear load by a full-aircraft finite element model of an aircraft structure. Comprising the following steps: step one, balancing the load of the whole machine under the load of the lifting device; step two, adding a finite element model of a landing gear under the loading state of the landing gear in a finite element model of the whole aircraft structure, and adjusting the posture of the finite element model of the whole aircraft structure to the loading state of the corresponding landing gear; thirdly, applying airplane distribution load in the airplane structure full-airplane finite element model; step four, applying airplane concentrated force load in the airplane structure full-airplane finite element model; step five, applying displacement constraint in the aircraft structure full-aircraft finite element model; and step six, checking the loading result of the aircraft structure full-aircraft finite element model. The application can more accurately simulate the real loading condition of the aircraft structure under the load of the landing gear, and can realize the fine design of the loading of the aircraft structure so as to reduce the weight of the structure.
Description
Technical Field
The application belongs to the field of aircraft structure design, and particularly relates to a method for applying a landing gear load by a full-aircraft finite element model of an aircraft structure.
Background
In the design of an aircraft structure, the influence of the load of a landing gear on the aircraft structure is generally considered to be limited to the aircraft structure near the corresponding landing gear, and the stress analysis and the structural design of the aircraft structure are performed by applying the load concentrated by the landing gear and restraining the load at a far end. The method omits the force transmission process of balancing the landing gear with the inertial load and other concentrated forces of the airplane, so that the analysis of the force transmission route of the airplane structure has deviation, which is not beneficial to the fine design of the airplane structure and may cause weight gain of the airplane structure.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a method for applying a lifting device load to a full-aircraft finite element model of an aircraft structure, which aims to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
a method of applying landing gear loads to a full aircraft finite element model of an aircraft structure, comprising:
step one, balancing the load of the whole machine under the load of the lifting device;
step two, adding a finite element model of a landing gear under the loading state of the landing gear in a finite element model of the whole aircraft structure, and adjusting the posture of the finite element model of the whole aircraft structure to the loading state of the corresponding landing gear;
thirdly, applying airplane distribution load in the airplane structure full-airplane finite element model;
step four, applying airplane concentrated force load in the airplane structure full-airplane finite element model;
step five, applying displacement constraint in the aircraft structure full-aircraft finite element model;
and step six, checking the loading result of the aircraft structure full-aircraft finite element model.
In at least one embodiment of the present application, in step one, the full-aircraft load balancing under the load of the landing gear includes:
force balance is achieved by adjusting overload in all directions;
moment balance is achieved by adjusting the angular acceleration in each direction.
In at least one embodiment of the present application, in step three, the applying the aircraft distribution load in the aircraft structural whole-aircraft finite element model includes:
aerodynamic loads and distributed inertial loads are equivalently applied to the interfaces of the frameworks and/or the wall panels of the aircraft structural whole-aircraft finite element model according to the loads.
In at least one embodiment of the application, the distributed inertial load comprises a fuel tank inertial load.
In at least one embodiment of the present application,
the course component of the inertial load of the fuel tank is applied to the junction of the fuel tank end structure and the wallboard or the framework;
the vertical component of the inertial load of the fuel tank is applied to the junction of the bottom structure of the fuel tank and the wallboard or the framework;
the lateral component of the inertial load of the tank is applied at the interface of the tank side structure and the wall plate or skeleton.
In at least one embodiment of the present application, in step four, the applying the aircraft concentrated force load in the aircraft structural whole-aircraft finite element model comprises:
the aircraft concentrated force load is applied to the corresponding joint intersection point according to the actual stress state.
In at least one embodiment of the present application, in step five, the applying displacement constraints in the aircraft structural full-aircraft finite element model includes:
setting the vertical displacement and the lateral displacement of the grounding point of the front landing frame to 0;
setting the course displacement and the vertical displacement of the grounding point of the left main lifting frame to 0;
the heading displacement and vertical displacement of the right main landing gear ground point are set to 0.
In at least one embodiment of the present application, in step six, the checking the loading result of the aircraft structural whole-aircraft finite element model includes:
judging whether the resultant force and the resultant force acting point of the airplane distribution load applied to the airplane structure full-airplane finite element model are consistent with the resultant force and the resultant force acting point of the actual airplane distribution load, and if not, adjusting the third step;
judging whether the airplane concentrated force load and the coordinates applied to the airplane structure full-airplane finite element model are consistent with the actual airplane concentrated force load and the coordinates, and if not, adjusting the fourth step;
and (3) calculating the whole finite element model of the aircraft structure, judging whether constraint counter forces are 0, and if the constraint counter forces are not 0, adjusting the fifth step.
The application has at least the following beneficial technical effects:
according to the method for applying the loading of the landing gear by the aircraft structure full-aircraft finite element model, in the aircraft structure full-aircraft finite element model, the real loading condition of the aircraft structure under the loading of the landing gear can be more accurately simulated, and the fine design of loading of the aircraft structure can be realized, so that the structure weight is reduced.
Drawings
FIG. 1 is a flow chart of a method of applying a landing gear load to a full aircraft finite element model of an aircraft structure in accordance with one embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1.
The application provides a method for applying a lifting device load by a full-aircraft finite element model of an aircraft structure, which comprises the following steps:
s100, balancing the load of the whole machine under the load of the lifting device;
s200, adding a finite element model of a landing gear under the loading state of the landing gear in a finite element model of the whole aircraft structure, and adjusting the posture of the finite element model of the whole aircraft structure to the loading state of the corresponding landing gear;
s300, applying airplane distribution load in an airplane structure all-airplane finite element model;
s400, applying airplane concentrated force load in the airplane structure full-airplane finite element model;
s500, applying displacement constraint in the aircraft structure full-aircraft finite element model;
s600, checking a loading result of the aircraft structure full-aircraft finite element model.
In the method for applying the load of the landing gear by the aircraft structure full-aircraft finite element model, in S100, the full-aircraft load balancing under the load of the landing gear comprises the following steps:
force balance is achieved by adjusting overload in all directions;
moment balance is achieved by adjusting the angular acceleration in each direction.
And carrying out full-aircraft load balancing according to the load unbalance of the landing gear under the load state, firstly adjusting the force balance in all directions, and then adjusting the moment balance in all directions. Specifically, the force imbalance is achieved by adjusting the overload in the corresponding direction, for example, the imbalance Fx in the x direction is achieved by increasing the overload:
dnx＝Fx/mg
force balance in the direction is achieved;
wherein m is the aircraft mass and g is the gravitational acceleration.
The moment imbalance realizes moment balance by adjusting the angular acceleration in the corresponding direction, for example, the unbalance amount Mx in the x direction is increased by overload:
dwx＝Mx/Ixx
the moment balance in the direction is realized;
where Ixx is the inertia of an aircraft about the x-axis.
According to the method for applying the loading of the landing gear on the aircraft structure full-aircraft finite element model, after the posture of the aircraft structure full-aircraft finite element model is adjusted to the corresponding loading state of the landing gear, the aircraft distribution load, the aircraft concentrated force load and the displacement constraint are applied to the aircraft structure full-aircraft finite element model.
In particular, in a preferred embodiment of the application, the aircraft distributed load includes aerodynamic load as well as distributed inertial load. Applying the aircraft distribution load in the aircraft structural whole-aircraft finite element model includes:
aerodynamic loads and distributed inertial loads are applied to the interfaces of the frameworks and/or the wall panels of the aircraft structural full-aircraft finite element model according to load equivalent.
In this embodiment, the distributed inertial load includes a fuel tank inertial load. Wherein a heading component of the inertial load of the fuel tank is applied at the junction of the fuel tank end structure and the wall plate or skeleton; the vertical component of the inertial load of the fuel tank is applied to the junction of the bottom structure of the fuel tank and the wall plate or skeleton; lateral components of the inertial load of the fuel tank are applied at the interface of the side structure of the fuel tank and the wall plate or skeleton.
In a preferred embodiment of the present application, applying aircraft concentrated force loads in an aircraft structural whole-aircraft finite element model comprises:
the aircraft concentrated force load is applied to the corresponding joint intersection point according to the actual stress state. The concentrated force load is directly applied to the corresponding joint, and the concentrated inertial force load is distributed to the corresponding joint intersection point according to the actual stress state.
In a preferred embodiment of the application, applying displacement constraints in a full aircraft finite element model of an aircraft structure comprises:
setting the vertical displacement and the lateral displacement of the grounding point of the front landing frame to 0;
setting the course displacement and the vertical displacement of the grounding point of the left main lifting frame to 0;
the heading displacement and vertical displacement of the right main landing gear ground point are set to 0.
In a preferred embodiment of the present application, in S600, checking the loading result of the aircraft structure full aircraft finite element model includes:
judging whether the resultant force and the resultant force acting point of the airplane distribution load applied to the airplane structure full-airplane finite element model are consistent with the resultant force and the resultant force acting point of the actual airplane distribution load, and if not, adjusting S300;
judging whether the aircraft concentrated force load and the coordinates applied to the aircraft structure full aircraft finite element model are consistent with the actual aircraft concentrated force load and the coordinates, and if not, adjusting S400;
and calculating the whole finite element model of the aircraft structure, judging whether constraint counter forces are 0, and if the constraint counter forces are not 0, adjusting S500.
The method for applying the load of the landing gear by the aircraft structure full-aircraft finite element model can more accurately simulate the actual loading condition of the aircraft structure under the load of the landing gear, and can realize the fine design of the loading of the aircraft structure so as to reduce the weight of the structure.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (3)
1. A method of applying landing gear loading to a full aircraft finite element model of an aircraft structure, comprising:
step one, balancing the load of the whole machine under the load of the lifting device;
step two, adding a finite element model of a landing gear under the loading state of the landing gear in a finite element model of the whole aircraft structure, and adjusting the posture of the finite element model of the whole aircraft structure to the loading state of the corresponding landing gear;
and thirdly, applying airplane distribution load to the airplane structure full-airplane finite element model, wherein the method comprises the following steps of:
pneumatic load and distributed inertial load are equivalently applied to the junction of the framework and/or the wallboard of the aircraft structure full-aircraft finite element model according to the load;
the distributed inertial load comprises a fuel tank inertial load;
the course component of the inertial load of the fuel tank is applied to the junction of the fuel tank end structure and the wallboard or the framework;
the vertical component of the inertial load of the fuel tank is applied to the junction of the bottom structure of the fuel tank and the wallboard or the framework;
the lateral component of the inertial load of the fuel tank is applied to the junction of the side structure of the fuel tank and the wallboard or the framework;
and step four, applying an airplane concentrated force load in the airplane structure all-airplane finite element model, wherein the method comprises the following steps of:
the aircraft concentrated force load is applied to the corresponding joint intersection point according to the actual stress state;
step five, applying displacement constraint in the aircraft structure full-aircraft finite element model, which comprises the following steps:
setting the vertical displacement and the lateral displacement of the grounding point of the front landing frame to 0;
setting the course displacement and the vertical displacement of the grounding point of the left main lifting frame to 0;
setting the course displacement and the vertical displacement of the grounding point of the right main landing gear to 0;
and step six, checking the loading result of the aircraft structure full-aircraft finite element model.
2. The method of applying a landing gear load to a full aircraft finite element model of an aircraft structure according to claim 1, wherein in step one, the full aircraft load balancing under the landing gear load comprises:
force balance is achieved by adjusting overload in all directions;
moment balance is achieved by adjusting the angular acceleration in each direction.
3. The method of applying a landing gear load to an aircraft structural whole-aircraft finite element model according to claim 2, wherein in step six, the checking the loading result of the aircraft structural whole-aircraft finite element model comprises:
judging whether the resultant force and the resultant force acting point of the airplane distribution load applied to the airplane structure full-airplane finite element model are consistent with the resultant force and the resultant force acting point of the actual airplane distribution load, and if not, adjusting the third step;
judging whether the airplane concentrated force load and the coordinates applied to the airplane structure full-airplane finite element model are consistent with the actual airplane concentrated force load and the coordinates, and if not, adjusting the fourth step;
and (3) calculating the whole finite element model of the aircraft structure, judging whether constraint counter forces are 0, and if the constraint counter forces are not 0, adjusting the fifth step.
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