CN112417600A - Method for rapidly calculating static strength of helicopter oil tank cabin - Google Patents
Method for rapidly calculating static strength of helicopter oil tank cabin Download PDFInfo
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- CN112417600A CN112417600A CN202011326434.2A CN202011326434A CN112417600A CN 112417600 A CN112417600 A CN 112417600A CN 202011326434 A CN202011326434 A CN 202011326434A CN 112417600 A CN112417600 A CN 112417600A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/04—Constraint-based CAD
Abstract
The invention belongs to the technical field of helicopter structure static strength design, and particularly relates to a method for rapidly calculating static strength of a helicopter oil tank cabin. The method comprises the following steps: s1: establishing a finite element simulation model of the oil tank cabin, and applying constraint according to actual conditions; s2: determining the working condition of the oil tank cabin and screening out the serious working condition of the oil tank cabin; s3: simulating the self inertial load distribution of the oil tank cabin body; s4: simulating the loading of fuel oil; s5: creating a working condition that the overload of the oil tank cabin is 1g in the front and back direction, the left and right direction and the up and down direction, and submitting a software calculation static strength result; s6: and (4) calculating the static strength of the actual oil tank cabin under each overload condition in a combined manner. The method not only comprehensively analyzes the static strength of the helicopter oil tank cabin under each helicopter mission profile, but also saves time; providing modeling key points and an analysis method of finite element simulation of the oil tank cabin; meanwhile, the method is suitable for analyzing the oil tank cabins in various shapes.
Description
Technical Field
The invention belongs to the technical field of helicopter structure static strength design, and particularly relates to a method for rapidly calculating static strength of a helicopter oil tank cabin.
Background
The main function of a helicopter fuel tank is to store the fuel required for the mission profile of the helicopter. The first requirement is that the safety of the helicopter is improved, and the mounting structure of the helicopter fuel tank meets the strength design. Because the helicopter has numerous mission profiles and requires that the structure of the helicopter oil tank cabin meets all mission requirements, severe working conditions need to be selected and loading calculation is carried out, and therefore, how to effectively and quickly carry out static strength calculation on the oil tank cabin is very critical.
At present, the static strength calculation method mainly used for helicopter fuel tanks at home and abroad has the following defects: firstly, the simplified calculation method only applies pressure loads in all directions to the oil tank cabin, and the pressure loads are inconsistent with actual loads, so that the load loss is easily caused; secondly, part of the calculation methods are complicated to load, difficult to operate and prone to errors.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the defects of the prior art, the invention provides a calculation method for rapidly analyzing the static strength of a helicopter oil tank cabin, which meets the rapid design requirement of the static strength.
The technical scheme of the invention is as follows: in order to achieve the purpose, the method for rapidly calculating the static strength of the helicopter oil tank cabin comprises the following steps:
S1: establishing a finite element simulation model of the oil tank cabin, and applying constraint according to actual conditions;
s2: determining the working condition of the oil tank cabin and screening out the serious working condition of the oil tank cabin;
s3: simulating the self inertial load distribution of the oil tank cabin body;
s4: simulating the loading of fuel oil;
s5: creating a working condition that the overload of the oil tank cabin is 1g in the front and back direction, the left and right direction and the up and down direction, and submitting a software calculation static strength result;
s6: and (4) calculating the static strength of the actual oil tank cabin under each overload condition in a combined manner.
In one possible embodiment, in step S1, the finite element simulation model of the tank compartment is created by using msc.
In a possible embodiment, in step S2, the operating conditions of the tank cabin include a full-aircraft inertia balance load operating condition, an emergency landing (ship) operating condition, and an emergency refueling fault operating condition.
In a possible embodiment, the step S2 of screening the severe operating condition of the tank compartment specifically includes the following steps:
s201: determining the weight G1 of the cabin body of the oil tank cabin, the weight G2 of fuel oil in the full oil state and the barycentric coordinates Xg, Yg and Zg of the oil tank cabin in the full oil state;
s202: obtaining the severe working condition and the overload nx, ny and nz of the tank body of the oil tank cabin under the working condition of the full-engine inertia balance load through the gravity center coordinates Xg, Yg and Zg of the oil tank cabin in the full-oil state;
S203: and comparing the overload nx, ny and nz under the working condition of the full-aircraft inertia balance load in the second step with the overload under the working condition of emergency landing (ship) and the working condition of emergency refueling fault obtained according to the standard, and screening out the serious working condition with the maximum overload in a single direction and/or the maximum synthesized overload.
In one possible embodiment, in step S3, the tank compartment body inertia load distribution itself is simulated by a rigid unit (MPC).
In one possible embodiment, the step S3 includes loading the tank body G1 at the center of gravity of the tank body, and loading 1G of unit overload load in the positive and negative directions x, y, and z, respectively.
In a possible embodiment, the step S4 specifically includes the following steps:
s401: loading the load of fuel under the weight of G2 under the overload of each 1G unit in the positive and negative directions of x, y and z by an evenly distributed loading method;
s402: respectively establishing 1g unit cross in positive and negative directions of x, y and z by a compressive stress field function loading methodOil pressure distribution of the loaded fuel, wherein the pressure field function is Pk ═ PghiRho is fuel density, g is gravity acceleration, HiThe maximum travel of the fuel in each direction.
In a possible embodiment, in step S6, the combination result is used to calculate the static strength of the tank module under each overload condition.
The invention has the beneficial effects that: the invention has the advantages that: firstly, the static strength of the helicopter oil tank cabin under each helicopter mission profile is comprehensively analyzed, and the time is saved; secondly, providing modeling key points and an analysis method of finite element simulation of the oil tank cabin; and thirdly, the method is suitable for analyzing the fuel tank cabins in various shapes.
Drawings
FIG. 1 is a flow chart of the method of the present invention
FIG. 2 is a schematic diagram of the distribution of the inertial load of the tank body of the oil tank cabin according to the embodiment of the invention
FIG. 3 is a schematic diagram of applying uniform load 1g ahead in the embodiment of the present invention
FIG. 4 is a schematic view of the oil pressure field load of 1g ahead in the embodiment of the present invention
Wherein:
g1-weight of the tank body of the oil tank; g2-weight of fuel at full oil; xg, Yg, Zg-fuel tank cabin body gravity center
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the flowchart of the method of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1-4, a method for rapidly calculating the static strength of a helicopter fuel tank cabin comprises the following steps:
s1: establishing a finite element simulation model of the oil tank cabin by adopting MSC.Patran finite element simulation software, and applying constraint according to actual conditions;
s2: determining working conditions of the oil tank cabin, including a full-aircraft inertia balance load working condition L1, an emergency landing (ship) working condition L2 and an emergency refueling fault working condition L3; the method for screening the severe working conditions of the oil tank cabin specifically comprises the following steps:
s201: determining the weight G1 of the cabin body of the oil tank cabin, the weight G2 of fuel oil in an oil-full state and the barycentric coordinates Xg, Yg and Zg of the oil tank cabin in the oil-full state;
s202: obtaining the severe working condition and overload nx, ny and nz of the fuel tank cabin body under the working condition L1 of the full-aircraft inertia balance load through the gravity center coordinate;
s203: comparing the overload nx, ny and nz under the full-aircraft inertia balance load working condition L1 in the step S202 with the overload under the emergency landing (ship) working condition L2 and the emergency refueling fault working condition L3 obtained according to the standard, and screening out the serious working condition with the maximum overload in a single direction and/or the maximum synthesized overload;
s3: simulating the self inertial load distribution of the oil tank cabin body; simulating the distribution of the inertial load of the tank body of the oil tank cabin by a rigid unit (MPC), loading the weight G1 of the tank body at the gravity center of the tank body of the oil tank cabin, and loading 1G of unit overload load in the positive and negative directions of x, y and z respectively, wherein the total load is 6 load j (j is 1,2, … … 6);
S4: simulating the loading of fuel oil; the method specifically comprises the following steps:
s401: by a uniform loading method, the fuel oil is loaded with the load under the weight of G2 under the overload of 1G of units in the positive and negative directions of x, y and z respectively, and the total load k is 6 (k is 1,2, … … 6); as shown in fig. 3, load 1g forward;
s402: through a pressure stress field function loading method, oil pressure distribution of fuel oil under the condition that units of 1g in the positive and negative directions of x, y and z are overloaded is respectively established, and 6 loads l (l is 1,2 and … … 6) are totally loaded, wherein the pressure field function is Pk is rho gHiRho is fuel density, g is gravity acceleration, HiThe maximum travel of the fuel in each direction; as shown in FIG. 4, the oil pressure profile 1g forward;
s5: creating a working condition that the overload of the fuel tank cabin is 1g in the front-back direction, the left-right direction and the up-down direction, respectively establishing a working condition loadcase n (n is 1,2, … … 6) that the overload of the fuel tank cabin is 1g in each direction, wherein loadcase 1 is the load when j, k and l are all 1, and so on, wherein loadcase 1 represents forward 1g, loadcase2 represents backward 1g, loadcase 3 represents rightward 1g, loadcase4 represents leftward 1g, loadcase 5 represents upward 1g, and loadcase6 represents downward 1g, and submitting software to calculate a fuel tank cabin static strength result (n is 1,2, … … 6) under loadcase n (n is 1,2, … … 6);
S6: the static strength of the actual oil tank cabins under all overloads is calculated in a combined mode; and (3) calculating the static strength of the fuel tank cabin under each overload by combining a combination result method, wherein the actual overload is nx ═ 0.6, ny ═ 1, and nz ═ 3.5, and then the calculation result can be set to 0.6 ═ result2+1 ═ result 4+3.5 ═ result 6, so that the strength result under the corresponding overload can be obtained.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A method for rapidly calculating the static strength of a helicopter oil tank cabin is characterized by comprising the following steps:
s1: establishing a finite element simulation model of the oil tank cabin, and applying constraint according to actual conditions;
s2: determining the working condition of the oil tank cabin and screening out the serious working condition of the oil tank cabin;
s3: simulating the self inertial load distribution of the oil tank cabin body;
s4: simulating the loading of fuel oil;
S5: creating a working condition that the overload of the oil tank cabin is 1g in the front and back direction, the left and right direction and the up and down direction, and submitting a software calculation static strength result;
s6: and (4) calculating the static strength of the actual oil tank cabin under each overload condition in a combined manner.
2. The method for rapidly calculating the static strength of the fuel tank cabin of the helicopter according to claim 1, wherein in step S1, a finite element simulation model of the fuel tank cabin is established by using msc.
3. The method for rapidly calculating the static strength of the fuel tank cabin of the helicopter in the claim 2, wherein in the step S2, the working conditions of the fuel tank cabin are determined to include the working conditions of the full-aircraft inertia balance load, the emergency landing/ship and the emergency refueling fault.
4. The method for rapidly calculating the static strength of the fuel tank cabin of the helicopter according to claim 3, wherein the step S2 of screening the severe working condition of the fuel tank cabin specifically comprises the following steps:
s201: determining the weight G1 of the cabin body of the oil tank cabin, the weight G2 of fuel oil in the full oil state and the barycentric coordinates Xg, Yg and Zg of the oil tank cabin in the full oil state;
s202: obtaining the severe working condition and overload nx, ny and nz of the fuel tank cabin body under the working condition of the full-machine inertia balance load through the gravity center coordinate;
S203: and (3) comparing the overload nx, ny and nz under the working condition of the full-aircraft inertia balance load in the S202 with the overload under the working condition of emergency landing (ship) and the working condition of emergency refueling fault obtained according to the standard, and screening out the serious working condition with the maximum overload in a single direction and/or the maximum synthesized overload.
5. The method for rapidly calculating the static strength of the fuel tank cabin of the helicopter in accordance with claim 4, wherein in the step S3, the distribution of the inertial load of the fuel tank cabin body itself is simulated by a rigid unit (MPC).
6. The method for rapidly calculating the static strength of the fuel tank compartment of a helicopter in accordance with claim 5, wherein said step S3 comprises loading the tank body G1 at the center of gravity of the fuel tank compartment body, and loading 1G of unit overload load in the positive and negative directions x, y and z, respectively.
7. The method for rapidly calculating the static strength of the fuel tank compartment of the helicopter according to claim 6, wherein said step S4 specifically comprises the steps of:
s401: loading the load of fuel under the weight of G2 under the overload of each 1G unit in the positive and negative directions of x, y and z by an evenly distributed loading method;
s402: respectively establishing oil pressure distribution of fuel oil under the condition that units of 1g in the positive and negative directions of x, y and z are overloaded by a pressure stress field function loading method, wherein the pressure field function is Pk (p) ═ gH iRho is fuel density, g is gravity acceleration, HiThe maximum travel of the fuel in each direction.
8. The method for rapidly calculating the static strength of the fuel tank cabin of a helicopter according to claim 7, wherein in step S6, the static strength of the fuel tank cabin under each overload condition is calculated by combining the bin result method.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113086243A (en) * | 2021-04-20 | 2021-07-09 | 中国直升机设计研究所 | Distribution method for inertial load of full-aircraft mass body of helicopter |
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| Publication number | Priority date | Publication date | Assignee | Title |
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