CN107958119A - A kind of load calculation method for external aircraft accessory casing mounting structure - Google Patents
A kind of load calculation method for external aircraft accessory casing mounting structure Download PDFInfo
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- CN107958119A CN107958119A CN201711231135.9A CN201711231135A CN107958119A CN 107958119 A CN107958119 A CN 107958119A CN 201711231135 A CN201711231135 A CN 201711231135A CN 107958119 A CN107958119 A CN 107958119A
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- external aircraft
- mounting structure
- aircraft accessory
- load
- accessory casing
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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
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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Abstract
The present invention relates to field of airplane design, more particularly to a kind of load calculation method for external aircraft accessory casing mounting structure, include the following steps：According to the service condition of aircraft and external aircraft accessory casing, the LOAD FOR operating mode of external aircraft accessory casing mounting structure is determined；According to definite LOAD FOR operating mode, with reference to the operation principle of external aircraft accessory casing, the load factor under each operating mode is analyzed, determines the load of external aircraft accessory casing mounting structure center of gravity under each operating mode；According to external aircraft accessory casing mounting structure force-transfer characteristic, the external aircraft accessory casing mounting structure load of each operating mode is calculated using finite element method；Determine the external aircraft accessory casing mounting structure load for instructing structure design.The load calculation method for external aircraft accessory casing mounting structure of the present invention, load input is provided for external aircraft accessory casing mounting structure design.
Description
Technical field
The present invention relates to field of airplane design, more particularly to a kind of load for external aircraft accessory casing mounting structure
Computational methods.
Background technology
External aircraft accessory casing is used for installation, fastening aircraft annex, is provided with hydraulic pump, fuel pump, power generation thereon
Machine, gas turbine starter.When engines ground starts, the power of gas turbine starter is passed into engine accessory power rating machine
Casket, when engine works, aircraft accessory is passed to by engine power.External aircraft accessory casing provides second for aircraft and moves
Power source, its function is particularly significant, and the installed load of external aircraft accessory casing calculates, then for accessory drive gearbox mounting structure and
Aircraft dependency structure provides design input.At present, still it is used to instruct external aircraft accessory casing without specification and design manual
The LOAD FOR of mounting structure.
The content of the invention
The object of the present invention is to provide a kind of load calculation method for external aircraft accessory casing mounting structure.
The technical scheme is that：
A kind of load calculation method for external aircraft accessory casing mounting structure, includes the following steps：
Step 1: according to the service condition of aircraft and external aircraft accessory casing, external aircraft accessory casing installation is determined
The LOAD FOR operating mode of structure；
Step 2: according to definite LOAD FOR operating mode, it is each with reference to the operation principle of external aircraft accessory casing, analysis
Load factor under operating mode, determines the load of external aircraft accessory casing mounting structure center of gravity under each operating mode；
Step 3: according to external aircraft accessory casing mounting structure force-transfer characteristic, each work is calculated using finite element method
The external aircraft accessory casing mounting structure load of condition；
Step 4: determine the external aircraft accessory casing mounting structure load for instructing structure design.
Optionally, in the step 1, the aircraft includes symmetrical motor-driven positive g flight, symmetrical motor-driven minusg flies
Row and three kinds of service conditions of yawed flight；
The external aircraft accessory casing includes airflight situation.
Optionally, in the step 1, the LOAD FOR operating mode of the external aircraft accessory casing mounting structure includes：
Symmetrical motor-driven positive g flight；
Symmetrical motor-driven negative-g flight；
Yawed flight.
Optionally, the load factor of external aircraft accessory casing includes three kinds under each operating mode, is respectively：
Moment of torsion, the external aircraft accessory machine of the active force of hydraulic pump, the active force of fuel pump, Flexible Rotating to accessory drive gearbox
The inertia force that the normal direction positive g of casket and thereon annex produces；
Moment of torsion, the external aircraft accessory machine of the active force of hydraulic pump, the active force of fuel pump, Flexible Rotating to accessory drive gearbox
The inertia force that the normal direction minusg of casket and thereon annex produces；
Moment of torsion, the external aircraft accessory machine of the active force of hydraulic pump, the active force of fuel pump, Flexible Rotating to accessory drive gearbox
The lateral inertia force of casket and thereon annex.
Optionally, in the step 3, the external aircraft accessory casing mounting structure force-transfer characteristic includes：
External aircraft accessory casing mounting structure is made of 6 non-coplanar leverages of space, and each pull rod is external aircraft
Accessory drive gearbox provides a fixed free degree, is statically determinate structure.
Optionally, in the step 3, calculate the external aircraft accessory casing of each operating mode using finite element method and install
Structural loads include：
External aircraft accessory casing is reduced to shell member, pull rod is using bar member simulation, then by external aircraft under each operating mode
The load of accessory drive gearbox mounting structure center of gravity puts on external aircraft accessory casing center of gravity, by FEM calculation, obtains
The load of external aircraft accessory casing installation pull rod.
Invention effect：
The load calculation method for external aircraft accessory casing mounting structure of the present invention, is external aircraft accessory casing
Mounting structure design provides load input.
Brief description of the drawings
Fig. 1 is the load calculation method flow chart that the present invention is used for external aircraft accessory casing mounting structure；
Fig. 2 is the external aircraft accessory casing mounting structure LOAD FOR finite element model signal of the present invention.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
1 and Fig. 2 is used for the present invention load calculation method of external aircraft accessory casing mounting structure below in conjunction with the accompanying drawings
It is described in further details.
The present invention provides a kind of load calculation method for external aircraft accessory casing mounting structure, including following step
Suddenly：
Step 1: according to the service condition of aircraft and external aircraft accessory casing, external aircraft accessory casing installation is determined
The LOAD FOR operating mode of structure.
Overload parameters influence the load of external aircraft accessory casing mounting structure in flight parameter, and overload is divided into normal direction mistake
Carry and lateral overload, therefore by the service condition of aircraft, choose symmetrical motor-driven positive g flight, symmetrical motor-driven negative-g flight and
Three kinds of situations of yawed flight are as external aircraft accessory casing mounting structure LOAD FOR situation；On external aircraft accessory casing
Hydraulic pump, fuel pump, Flexible Rotating work when engine is driven, due to aircraft normal g-load parameter when ground uses
For 1, the inertia force on accessory drive gearbox is less than load value during flight, therefore chooses airflight situation as LOAD FOR work
Condition.
Accessory drive gearbox mounting structure load amounts to 3 kinds of load working conditions, and operating mode 1 is for symmetrical motor-driven positive g flight, operating mode 2
Symmetrical motor-driven negative-g flight, operating mode 3 are yawed flight.
Step 2: according to definite LOAD FOR operating mode, it is each with reference to the operation principle of external aircraft accessory casing, analysis
Load factor under operating mode, determines the load of external aircraft accessory casing mounting structure center of gravity under each operating mode.
External aircraft accessory casing operation principle drives the liquid on accessory drive gearbox to be connected by Flexible Rotating with engine
Press pump, fuel pump, generator operation, realize the power output of engine.With reference to operation principle, external aircraft accessory casing load
Active force, engine when when factor including hydraulic pump works to active force, the fuel oil pump work of accessory drive gearbox to accessory drive gearbox
The Flexible Rotating inertia force of annex to the active force of accessory drive gearbox and external aircraft accessory casing and thereon is connected with accessory drive gearbox.
The load factor of 1 accessory drive gearbox of operating mode is the active force of hydraulic pump, the active force of fuel pump, Flexible Rotating are to annex
The moment of torsion of casing, external aircraft accessory casing and thereon annex normal direction positive g produce inertia force；2 accessory drive gearbox of operating mode
Load factor is moment of torsion, the external aircraft accessory of the active force of hydraulic pump, the active force of fuel pump, Flexible Rotating to accessory drive gearbox
The inertia force that the normal direction minusg of casing and thereon annex produces；The load factor of 3 accessory drive gearbox of operating mode is the effect of hydraulic pump
Power, the active force of fuel pump, Flexible Rotating is to the moment of torsion of accessory drive gearbox, external aircraft accessory casing and the lateral of annex is used to thereon
Property power.
Step 3: according to external aircraft accessory casing mounting structure force-transfer characteristic, each work is calculated using finite element method
The external aircraft accessory casing mounting structure load of condition.
External aircraft accessory casing mounting structure is made of 6 non-coplanar leverages of space, and each pull rod is external aircraft
Accessory drive gearbox provides a fixed free degree, is statically determinate structure.
Mounting structure load is calculated using finite element method.Accessory drive gearbox is reduced to shell member, pull rod is using bar member simulation.
The load of external aircraft accessory casing mounting structure center of gravity under each operating mode is put on into external aircraft accessory casing center of gravity again
Place, by FEM calculation, obtains the load of external aircraft accessory casing installation pull rod.
Step 4: by screening the external aircraft accessory casing mounting structure load under each operating mode, determine to be used to instruct
The external aircraft accessory casing mounting structure load of structure design.
The load calculation method for external aircraft accessory casing mounting structure of the present invention, is external aircraft accessory casing
Mounting structure design provides load input, to aircraft dependency structure great significance for design.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can readily occur in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (6)
1. a kind of load calculation method for external aircraft accessory casing mounting structure, it is characterised in that include the following steps：
Step 1: according to the service condition of aircraft and external aircraft accessory casing, external aircraft accessory casing mounting structure is determined
LOAD FOR operating mode；
Step 2: according to definite LOAD FOR operating mode, with reference to the operation principle of external aircraft accessory casing, each operating mode is analyzed
Under load factor, determine the load of external aircraft accessory casing mounting structure center of gravity under each operating mode；
Step 3: according to external aircraft accessory casing mounting structure force-transfer characteristic, calculated using finite element method outside each operating mode
Put aircraft accessory casing mounting structure load；
Step 4: determine the external aircraft accessory casing mounting structure load for instructing structure design.
2. the load calculation method according to claim 1 for external aircraft accessory casing mounting structure, its feature exists
In in the step 1, the aircraft includes symmetrical motor-driven positive g flight, symmetrical motor-driven negative-g flight and yaw and flies
Three kinds of service conditions of row；
The external aircraft accessory casing includes airflight situation.
3. the load calculation method according to claim 2 for external aircraft accessory casing mounting structure, its feature exists
In in the step 1, the LOAD FOR operating mode of the external aircraft accessory casing mounting structure includes：
Symmetrical motor-driven positive g flight；
Symmetrical motor-driven negative-g flight；
Yawed flight.
4. the load calculation method according to claim 3 for external aircraft accessory casing mounting structure, its feature exists
In the load factor of external aircraft accessory casing includes three kinds under each operating mode, is respectively：
The active force of hydraulic pump, the active force of fuel pump, Flexible Rotating to the moment of torsion of accessory drive gearbox, external aircraft accessory casing and
The inertia force that the normal direction positive g of annex produces thereon；
The active force of hydraulic pump, the active force of fuel pump, Flexible Rotating to the moment of torsion of accessory drive gearbox, external aircraft accessory casing and
The inertia force that the normal direction minusg of annex produces thereon；
The active force of hydraulic pump, the active force of fuel pump, Flexible Rotating to the moment of torsion of accessory drive gearbox, external aircraft accessory casing and
The lateral inertia force of annex thereon.
5. the load calculation method according to claim 4 for external aircraft accessory casing mounting structure, its feature exists
In in the step 3, the external aircraft accessory casing mounting structure force-transfer characteristic includes：
External aircraft accessory casing mounting structure is made of 6 non-coplanar leverages of space, and each pull rod is external aircraft accessory
Casing provides a fixed free degree, is statically determinate structure.
6. the load calculation method according to claim 5 for external aircraft accessory casing mounting structure, its feature exists
In in the step 3, calculating the external aircraft accessory casing mounting structure load of each operating mode using finite element method includes：
External aircraft accessory casing is reduced to shell member, pull rod is using bar member simulation, then by external aircraft accessory under each operating mode
The load of casing mounting structure center of gravity puts on external aircraft accessory casing center of gravity, by FEM calculation, obtains external
Aircraft accessory casing installs the load of pull rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711231135.9A CN107958119A (en) | 2017-11-29 | 2017-11-29 | A kind of load calculation method for external aircraft accessory casing mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711231135.9A CN107958119A (en) | 2017-11-29 | 2017-11-29 | A kind of load calculation method for external aircraft accessory casing mounting structure |
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| CN107958119A true CN107958119A (en) | 2018-04-24 |
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| CN201711231135.9A Pending CN107958119A (en) | 2017-11-29 | 2017-11-29 | A kind of load calculation method for external aircraft accessory casing mounting structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108897959A (en) * | 2018-07-04 | 2018-11-27 | 北京航空航天大学 | A kind of seaworthiness airworthiness compliance method of combustion box |
| CN110705141A (en) * | 2019-08-30 | 2020-01-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Fatigue load spectrum determination method for external airplane accessory casing fixing device |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108897959A (en) * | 2018-07-04 | 2018-11-27 | 北京航空航天大学 | A kind of seaworthiness airworthiness compliance method of combustion box |
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| CN110705141A (en) * | 2019-08-30 | 2020-01-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Fatigue load spectrum determination method for external airplane accessory casing fixing device |
| CN110705141B (en) * | 2019-08-30 | 2023-06-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Fatigue load spectrum determining method for external aircraft accessory case fixing device |
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Application publication date: 20180424 |
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