CN107944161A - A kind of load calculation method for thrust vectoring engine mount - Google Patents
A kind of load calculation method for thrust vectoring engine mount Download PDFInfo
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- CN107944161A CN107944161A CN201711231163.0A CN201711231163A CN107944161A CN 107944161 A CN107944161 A CN 107944161A CN 201711231163 A CN201711231163 A CN 201711231163A CN 107944161 A CN107944161 A CN 107944161A
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- G—PHYSICS
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- 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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- 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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Abstract
The present invention relates to field of airplane design, more particularly to a kind of load calculation method for thrust vectoring engine mount, include the following steps：According to the service condition of aircraft and engine, the LOAD FOR operating mode of thrust vectoring engine mount is determined；According to definite LOAD FOR operating mode, with reference to the work characteristics of engine, the load factor under each operating mode is analyzed, determines the load of each operating mode lower thrust vector engine center of gravity；According to engine mount force-transfer characteristic, engine mount load under each operating mode is calculated using finite element method；According to engine mount load under various LOAD FOR operating modes, the engine mount load for instructing structure design is determined.The load calculation method for thrust vectoring engine mount of the present invention, to provide load input using the aeroplane structure design and intensive analysis of thrust vectoring engine, is of great significance the airplane design of installed thrust vector engine.
Description
Technical field
The present invention relates to field of airplane design, more particularly to a kind of loadometer for thrust vectoring engine mount
Calculation method.
Background technology
Thrust Vectoring Technology is each needed for operating aircraft to generate by varying the size and Orientation of engine thrust output
The technology of axial force/torque, its application target is the crosslinking Comprehensive Control deflected by vector spray deflection with aircraft rudder surface, real
Existing High Angle of Attack trim is controllable and post stall maneuver dynamic is controllable, improves aircraft low-speed performance, strengthens supersonic speed sustained turn ability,
Extended flight envelope curve, improves air maneuver, manipulation characteristic, provides stronger Comprehensive Control ability to improve flying quality.Push away
Force vector technology with behind its side to body Combined design after stealthy income, flattening, control it is simple efficiently the advantages that obtained for four generations
Machine, casement unmanned plane processed and the contour stealthy, high-performance cruise of New-Generation Fighter, the favor of high power-driven plane.
It is related to the jet pipe deflection of engine during thrust vectoring engine use, engine uses envelope curve, work
The aircraft of the more conventional jet pipe layout of situation differs, and is used to instruct thrust vectoring engine there is presently no corresponding specification
Fixing device LOAD FOR, with reference to the work characteristics of engine, is established thrust vectoring and is started, it is necessary to the service condition of analysis of aircraft
The load calculation method of machine fixing device.
The content of the invention
The object of the present invention is to provide a kind of load calculation method for thrust vectoring engine mount.
The technical scheme is that：
A kind of load calculation method for thrust vectoring engine mount, includes the following steps：
Step 1: according to the service condition of aircraft and engine, the loadometer of thrust vectoring engine mount is determined
Calculate operating mode；
Step 2: according to definite LOAD FOR operating mode, with reference to the work characteristics of engine, the load under each operating mode is analyzed
Lotus factor, determines the load of each operating mode lower thrust vector engine center of gravity；
Step 3: according to engine mount force-transfer characteristic, engine under each operating mode is calculated using finite element method
Fixing device load；
Step 4: according to engine mount load under various LOAD FOR operating modes, determine to be used to instruct structure design
Engine mount load.
Optionally, in the step 1, the service condition of the aircraft includes symmetrical maneuvering flight, rolling flight of spiraling
And spin flight；
The service condition of the engine includes nozzle deflection and nozzle does not deflect.
Optionally, in the step 1, the LOAD FOR operating mode includes following six kinds：
Aircraft carries out symmetrical maneuvering flight, nozzle deflection；
Aircraft carries out symmetrical maneuvering flight, and nozzle does not deflect；
Aircraft carries out rolling flight of spiraling, nozzle deflection；
Aircraft carries out rolling flight of spiraling, and nozzle does not deflect；
Aircraft carries out spin flight, nozzle deflection；
Aircraft carries out spin flight, and nozzle does not deflect.
Optionally, the load of the thrust vectoring engine center of gravity includes：
The maneuvering load of thrust vectoring engine center of gravity is thrust, the deflection production of normal inertial force, gyroscopic couple, jet pipe
Raw additional moment, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, normal inertial force, gyroscopic couple, nozzle
Aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, lateral inertia force, jet pipe deflect the additional of generation
Torque, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is that thrust, lateral inertia force, nozzle pneumatically carry
Lotus；
The maneuvering load of thrust vectoring engine center of gravity is thrust, the deflection production of normal inertial force, gyroscopic couple, jet pipe
Raw additional moment, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, normal inertial force, gyroscopic couple, nozzle
Aerodynamic loading.
Optionally, in the step 3, the engine mount force-transfer characteristic includes：
Thrust vectoring starts owner's stationary plane to be fixed by the topology layout mode of two thrust pin assemblies, on the outside of main stationary plane
Thrust pin bears the power of X, Y both direction, and main stationary plane inboard thrust pin bears the power in tri- directions of X, Y, Z；
Thrust vectoring engine auxiliary stationary plane is fixed by the topology layout mode of two rod assemblies, and pull rod bears axial direction
Power, be a redundant structure.
Optionally, in the step 3, calculating fixing device load using finite element method includes：
It is volume elements by motor simpler, thrust pin passes through finite element meter using beam member simulation, pull rod using bar member simulation
Calculate, obtain engine mount load under each operating mode.
Invention effect：
The load calculation method for thrust vectoring engine mount of the present invention, to use thrust vectoring engine
Aeroplane structure design and intensive analysis provide load input, have to the airplane design of installed thrust vector engine important
Meaning.
Brief description of the drawings
Fig. 1 is the load calculation method flow chart that the present invention is used for thrust vectoring engine mount；
Fig. 2 is the load calculation method flow chart that the present invention is used for thrust vectoring engine mount.
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 the present invention for the load calculation method of thrust vectoring engine mount below in conjunction with the accompanying drawings
It is further described.
The present invention provides a kind of load calculation method for thrust vectoring engine mount, including following step
Suddenly：
Step 1: according to the service condition of aircraft and engine, the loadometer of thrust vectoring engine mount is determined
Calculate operating mode.
Overload, angular speed, angular acceleration, height, speed parameter influence the fixing device load of engine in flight parameter
Lotus, overload are divided into normal g-load and lateral overload, therefore by the service condition of aircraft；It is therefore preferred that the service condition of aircraft
Including symmetrical maneuvering flight, spiral rolling flight and spin flight；It is inclined that the service condition of engine includes nozzle
Turn and nozzle does not deflect.
Specifically, the service condition of the flight progress of aircraft and engine is superimposed, LOAD FOR operating mode is divided into as follows
Six kinds：
Aircraft carries out symmetrical maneuvering flight, nozzle deflection；
Aircraft carries out symmetrical maneuvering flight, and nozzle does not deflect；
Aircraft carries out rolling flight of spiraling, nozzle deflection；
Aircraft carries out rolling flight of spiraling, and nozzle does not deflect；
Aircraft carries out spin flight, nozzle deflection；
Aircraft carries out spin flight, and nozzle does not deflect.
Step 2: according to definite LOAD FOR operating mode, with reference to the work characteristics of engine, the load under each operating mode is analyzed
Lotus factor, determines the load of each operating mode lower thrust vector engine center of gravity.
Specifically, the load of thrust vectoring engine center of gravity includes：
The maneuvering load of thrust vectoring engine center of gravity is thrust, the deflection production of normal inertial force, gyroscopic couple, jet pipe
Raw additional moment, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, normal inertial force, gyroscopic couple, nozzle
Aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, lateral inertia force, jet pipe deflect the additional of generation
Torque, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is that thrust, lateral inertia force, nozzle pneumatically carry
Lotus；
The maneuvering load of thrust vectoring engine center of gravity is thrust, the deflection production of normal inertial force, gyroscopic couple, jet pipe
Raw additional moment, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, normal inertial force, gyroscopic couple, nozzle
Aerodynamic loading.
Step 3: according to engine mount force-transfer characteristic, engine under each operating mode is calculated using finite element method
Fixing device load.
Specifically, engine mount force-transfer characteristic includes：
Thrust vectoring starts owner's stationary plane to be fixed by the topology layout mode of two thrust pin assemblies, on the outside of main stationary plane
Thrust pin bears the power of X, Y both direction, and main stationary plane inboard thrust pin bears the power in tri- directions of X, Y, Z；
Thrust vectoring engine auxiliary stationary plane is fixed by the topology layout mode of two rod assemblies, and pull rod bears axial direction
Power, be a redundant structure.
Further, calculating fixing device load using finite element method includes：
It is volume elements by motor simpler, thrust pin passes through finite element meter using beam member simulation, pull rod using bar member simulation
Calculate, obtain engine mount load under each operating mode.
Step 4: according to engine mount load under 6 kinds of LOAD FOR operating modes, determine for instructing structure design
Engine mount load.
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 thrust vectoring engine mount, it is characterised in that include the following steps：
Step 1: according to the service condition of aircraft and engine, the LOAD FOR work of thrust vectoring engine mount is determined
Condition；
Step 2: according to definite LOAD FOR operating mode, with reference to the work characteristics of engine, analyze load under each operating mode because
Element, determines the load of each operating mode lower thrust vector engine center of gravity；
Step 3: according to engine mount force-transfer characteristic, calculate engine under each operating mode using finite element method and fix
Device load；
Step 4: according to engine mount load under various LOAD FOR operating modes, the hair for instructing structure design is determined
Motivation fixing device load.
2. the load calculation method according to claim 1 for thrust vectoring engine mount, it is characterised in that
In the step 1, the service condition of the aircraft includes symmetrical maneuvering flight, spiral rolling flight and spin flight；
The service condition of the engine includes nozzle deflection and nozzle does not deflect.
3. the load calculation method according to claim 2 for thrust vectoring engine mount, it is characterised in that
In the step 1, the LOAD FOR operating mode includes following six kinds：
Aircraft carries out symmetrical maneuvering flight, nozzle deflection；
Aircraft carries out symmetrical maneuvering flight, and nozzle does not deflect；
Aircraft carries out rolling flight of spiraling, nozzle deflection；
Aircraft carries out rolling flight of spiraling, and nozzle does not deflect；
Aircraft carries out spin flight, nozzle deflection；
Aircraft carries out spin flight, and nozzle does not deflect.
4. the load calculation method according to claim 3 for thrust vectoring engine mount, it is characterised in that
The load of the thrust vectoring engine center of gravity includes：
The maneuvering load of thrust vectoring engine center of gravity is thrust, the deflection of normal inertial force, gyroscopic couple, jet pipe produces
Additional moment, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, normal inertial force, gyroscopic couple, nozzle are pneumatic
Load；
The maneuvering load of thrust vectoring engine center of gravity for thrust, lateral inertia force, jet pipe deflection produce additional moment,
Nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, lateral inertia force, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, the deflection of normal inertial force, gyroscopic couple, jet pipe produces
Additional moment, nozzle aerodynamic loading；
The maneuvering load of thrust vectoring engine center of gravity is thrust, normal inertial force, gyroscopic couple, nozzle are pneumatic
Load.
5. the load calculation method according to claim 3 for thrust vectoring engine mount, it is characterised in that
In the step 3, the engine mount force-transfer characteristic includes：
Thrust vectoring starts owner's stationary plane to be fixed by the topology layout mode of two thrust pin assemblies, main stationary plane outboard thrust
Pin bears the power of X, Y both direction, and main stationary plane inboard thrust pin bears the power in tri- directions of X, Y, Z；
Thrust vectoring engine auxiliary stationary plane is fixed by the topology layout mode of two rod assemblies, and pull rod bears axial
Power, is a redundant structure.
6. the load calculation method according to claim 5 for thrust vectoring engine mount, it is characterised in that
In the step 3, calculating fixing device load using finite element method includes：
It is volume elements by motor simpler, thrust pin, by FEM calculation, is obtained using beam member simulation, pull rod using bar member simulation
Engine mount load under to each operating mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711231163.0A CN107944161A (en) | 2017-11-29 | 2017-11-29 | A kind of load calculation method for thrust vectoring engine mount |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711231163.0A CN107944161A (en) | 2017-11-29 | 2017-11-29 | A kind of load calculation method for thrust vectoring engine mount |
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| Publication Number | Publication Date |
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| CN107944161A true CN107944161A (en) | 2018-04-20 |
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| CN201711231163.0A Pending CN107944161A (en) | 2017-11-29 | 2017-11-29 | A kind of load calculation method for thrust vectoring engine mount |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113177276A (en) * | 2021-04-27 | 2021-07-27 | 中国航发沈阳发动机研究所 | Load determination method for high-pressure shaft thrust bearing of aircraft engine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043608A (en) * | 2015-07-13 | 2015-11-11 | 大连理工大学 | High thrust and variable thrust vector measuring device |
| CN106428623A (en) * | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
-
2017
- 2017-11-29 CN CN201711231163.0A patent/CN107944161A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043608A (en) * | 2015-07-13 | 2015-11-11 | 大连理工大学 | High thrust and variable thrust vector measuring device |
| CN106428623A (en) * | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
Non-Patent Citations (1)
| Title |
|---|
| 罗金亮: "飞机发动机固定装置的载荷计算方法", 《洪都科技》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113177276A (en) * | 2021-04-27 | 2021-07-27 | 中国航发沈阳发动机研究所 | Load determination method for high-pressure shaft thrust bearing of aircraft engine |
| CN113177276B (en) * | 2021-04-27 | 2022-08-19 | 中国航发沈阳发动机研究所 | Load determination method for high-pressure shaft thrust bearing of aircraft engine |
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Application publication date: 20180420 |
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