CN104408231A - Small airplane full-airplane load balancing method - Google Patents
Small airplane full-airplane load balancing method Download PDFInfo
- Publication number
- CN104408231A CN104408231A CN201410608888.7A CN201410608888A CN104408231A CN 104408231 A CN104408231 A CN 104408231A CN 201410608888 A CN201410608888 A CN 201410608888A CN 104408231 A CN104408231 A CN 104408231A
- Authority
- CN
- China
- Prior art keywords
- airplane
- load
- single discrete
- center
- gravity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title abstract description 7
- 230000005484 gravity Effects 0.000 claims abstract description 12
- 230000001133 acceleration Effects 0.000 claims abstract description 7
- 240000002853 Nelumbo nucifera Species 0.000 claims description 8
- 235000006508 Nelumbo nucifera Nutrition 0.000 claims description 8
- 235000006510 Nelumbo pentapetala Nutrition 0.000 claims description 8
- 238000012795 verification Methods 0.000 abstract description 5
- 238000013461 design Methods 0.000 abstract description 4
- 238000012360 testing method Methods 0.000 description 5
- 238000004364 calculation method Methods 0.000 description 4
- 230000003340 mental effect Effects 0.000 description 4
- 238000011161 development Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to a small airplane full-airplane load balancing method, and belongs to the technical field of airplane intensity design. According to the method, after the angular acceleration is corrected, the gravity center moment realizes self balance through inertial load and pneumatic load, so the full-airplane load balance is reached. The method adopted by the invention has the advantages that simplicity and reliability are realized, and in addition, through the developing and the use of various models of airplanes in the company, the requirements of experimental verification and airworthiness review are met.
Description
Technical field
The present invention relates to the complete airborne lotus Calculate Ways of a kind of flivver, belong to the technical field of strength of aircraft design.
Background technology
At present, global general-use aviation develops rapidly, the market demand of Small General Aircraft is increasing, therefore, increasing aircratfsman add general-purpose aircraft manufacture field, can fast, low cost develop the huge challenge that the aircraft product of meeting the need of market becomes aircratfsman.
But be limited to the mandatory requirement of general-purpose aircraft air worthiness regulation, airplane design must be carried out full machine balancing load and be calculated, and in order to obtain rudder face trim load, needs extra a lot of wind tunnel test that increases, and needs longer lead time and expensive testing expenses.Therefore, solve the complete airborne lotus trim problem of flivver when Intensity Design works, quickening lead time, reduction testing expenses are extremely important.Invention is a kind of practical for this reason, and the complete airborne lotus Calculate Ways meeting engineering calculation accuracy requirement is necessary.
Summary of the invention
In order to overcome above-mentioned defect, the object of the present invention is to provide the complete airborne lotus Calculate Ways of a kind of flivver.The present invention under the condition of not carrying out a large amount of wind tunnel test and CFD computing, provide a kind of fast, meet engineering calculation accuracy requirement, and can by the flivver complete airborne lotus Calculate Ways of verification experimental verification.
To achieve these goals, the present invention adopts following technical scheme:
The complete airborne lotus Calculate Ways of a kind of flivver:
Aircraft is subject to the aerodynamic moment of pneumatic outer year and the moment of self inertia load balances at center of gravity place,
, ensure pneumatic total moment preserving now, angular acceleration calculates:
Single discrete mass point inertial load:
---single discrete point quality
---single discrete point locality overload
---the center of gravity of airplane is transshipped
---single discrete point is apart from the distance of the center of gravity of airplane
Due to
ratio
little by less than 2%, therefore computational accuracy meets 5% Engineering Error.
When carrying out inertial load and calculating, angular acceleration is revised, thus utilizes the self-equilibrating principle of full machine aerodynamic loading counterweight mental and physical efforts square and inertial load counterweight mental and physical efforts square to carry out load trim.
Major advantage of the present invention:
The present invention can not carry out under the prerequisite that a large amount of wind tunnel test and CFD calculate, and provides a kind of and meets national military standard and air worthiness regulation to the computing method of full machine unbalanced moments trim requirement.
Due in aircraft development process, intensity specialty needs when carrying out finite element analysis to carry out discrete to operating mass unloden, but adopt discrete after the full machine moment of inertia that calculates of the full machine moment of inertia phase weight/power ratio specialty that obtains of Mass Calculation less than normal, and Pneumatic Professional adopts when calculating Aircraft Load is the full machine moment of inertia that provides of weight specialty, therefore intensity specialty can produce a unbalanced moments when carrying out full machine LOAD FOR, national military standard and air worthiness regulation all require to adopt suitable method to give trim to this unbalanced moments, the present invention is by after correction angle acceleration, make inertial load counterweight mental and physical efforts square and aerodynamic loading counterweight mental and physical efforts square self-equilibrating, thus reach full machine counterweight balance, the method that the present invention adopts is simple and reliable, and use through the development of the many types of aircraft of our company, meet verification experimental verification and Airworthiness Examination requirement.
Accompanying drawing explanation
Fig. 1 is the structural representation of flivver in the present invention.
Embodiment
Describe the present invention below in conjunction with accompanying drawing 1:
In Fig. 1:
1---aircraft aerodynamic loading is to the moment of center of gravity
2---full machine aerodynamic loading P;
3---the aerodynamic loading pressure heart is to the distance L of the center of gravity of airplane;
4---wing;
5---fuselage:
6---empennage.
As shown in the figure, aircraft is subject to the aerodynamic moment of pneumatic outer year and the moment of self inertia load balances at center of gravity place, but due to
if the angular acceleration values therefore directly adopting Pneumatic Professional to provide, calculates
, a unbalanced moments will be produced
.The pneumatic total moment preserving of present guarantee, angular acceleration is revised:
Single discrete mass point inertial load:
---single discrete point quality
---single discrete point locality overload
---the center of gravity of airplane is transshipped
---single discrete point is apart from the distance of the center of gravity of airplane
Due to usually
ratio
little by less than 2%, therefore computational accuracy meets 5% Engineering Error.
Claims (1)
1. the complete airborne lotus Calculate Ways of flivver, is characterized in that:
Aircraft is subject to the aerodynamic moment of pneumatic outer year and the moment of self inertia load balances at center of gravity place,
, ensure pneumatic total moment preserving now, angular acceleration calculates:
Single discrete mass point inertial load:
---single discrete point quality
---single discrete point locality overload
---the center of gravity of airplane is transshipped
---single discrete point is apart from the distance of the center of gravity of airplane
Due to
ratio
little by less than 2%, therefore computational accuracy meets 5% Engineering Error.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410608888.7A CN104408231A (en) | 2014-11-04 | 2014-11-04 | Small airplane full-airplane load balancing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410608888.7A CN104408231A (en) | 2014-11-04 | 2014-11-04 | Small airplane full-airplane load balancing method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104408231A true CN104408231A (en) | 2015-03-11 |
Family
ID=52645862
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410608888.7A Pending CN104408231A (en) | 2014-11-04 | 2014-11-04 | Small airplane full-airplane load balancing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104408231A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105447269A (en) * | 2015-12-15 | 2016-03-30 | 西北工业大学 | Non-structural mass trimming method for airplane in steady overload state |
| CN108090302A (en) * | 2018-01-04 | 2018-05-29 | 北京中航智科技有限公司 | A kind of helicopter flight mechanical simulation method and system |
| 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 |
| CN113830326A (en) * | 2021-11-01 | 2021-12-24 | 中国商用飞机有限责任公司 | Static aeroelasticity ground simulation system and method for airplane |
| CN117550093A (en) * | 2023-11-16 | 2024-02-13 | 中国飞机强度研究所 | An aircraft whole-machine static test attitude perception and its adjustment method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6671590B1 (en) * | 2001-04-30 | 2003-12-30 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method and system for active noise control of tiltrotor aircraft |
| CN102789527A (en) * | 2012-07-11 | 2012-11-21 | 南京航空航天大学 | Particle swarm optimization method for airplane trim |
-
2014
- 2014-11-04 CN CN201410608888.7A patent/CN104408231A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6671590B1 (en) * | 2001-04-30 | 2003-12-30 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method and system for active noise control of tiltrotor aircraft |
| CN102789527A (en) * | 2012-07-11 | 2012-11-21 | 南京航空航天大学 | Particle swarm optimization method for airplane trim |
Non-Patent Citations (1)
| Title |
|---|
| 李友和: "机身载荷计算方法和程序", 《洪都科技》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105447269A (en) * | 2015-12-15 | 2016-03-30 | 西北工业大学 | Non-structural mass trimming method for airplane in steady overload state |
| CN105447269B (en) * | 2015-12-15 | 2019-01-11 | 西北工业大学 | A kind of non-structural mass Calculate Ways of aircraft under permanent overload |
| CN108090302A (en) * | 2018-01-04 | 2018-05-29 | 北京中航智科技有限公司 | A kind of helicopter flight mechanical simulation method and system |
| CN108090302B (en) * | 2018-01-04 | 2021-11-30 | 北京中航智科技有限公司 | Helicopter flight mechanics simulation method and system |
| 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 |
| CN113086243B (en) * | 2021-04-20 | 2022-08-02 | 中国直升机设计研究所 | Distribution method for inertial load of full-aircraft mass body of helicopter |
| CN113830326A (en) * | 2021-11-01 | 2021-12-24 | 中国商用飞机有限责任公司 | Static aeroelasticity ground simulation system and method for airplane |
| CN113830326B (en) * | 2021-11-01 | 2024-06-04 | 中国商用飞机有限责任公司 | Aircraft static aeroelastic ground simulation system and method |
| CN117550093A (en) * | 2023-11-16 | 2024-02-13 | 中国飞机强度研究所 | An aircraft whole-machine static test attitude perception and its adjustment method |
| CN117550093B (en) * | 2023-11-16 | 2025-07-22 | 中国飞机强度研究所 | Method for adjusting static test attitude of aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104408231A (en) | Small airplane full-airplane load balancing method | |
| US11126758B2 (en) | Automatic airfoil and wing design based on dynamic modeling of structural and aerodynamic performance | |
| CN107391858B (en) | A method to obtain the influence of the static aeroelastic deformation of the wind tunnel model | |
| Mantari et al. | Static and dynamic analysis of laminated composite and sandwich plates and shells by using a new higher-order shear deformation theory | |
| CN104776970B (en) | A kind of anti-bird of Helicopter Main blade pitch-change-link hits performance verification method | |
| EP3543108A1 (en) | Automatic airfoil and wing design based on dynamic modeling of structural and aerodynamic performance | |
| CN104133926B (en) | A kind of elastic pneumatic force characteristic comprehensive analysis method | |
| JP2010195392A5 (en) | ||
| CN110702364B (en) | Correction method of high-altitude propeller wind tunnel test data for the influence of tip Mach number | |
| CN104298804A (en) | Flight load design method | |
| CN104648688B (en) | A kind of blade foil gauge is arranged and decoupling method | |
| CN204286756U (en) | A kind of missile wing aerodynamic loading analog loading test device | |
| CN103693203B (en) | Small-sized self-balance formula weathercock | |
| CN109299579B (en) | Method for correcting wind tunnel force test data of large-aspect-ratio aircraft | |
| CN103196666A (en) | Static test method of horizontal shaft wind turbine vane scale model based on equal strength principle | |
| Mavriplis et al. | Supersonic Configurations at Low Speeds (SCALOS): CFD Aided Wind Tunnel Data Corrections | |
| CN106800095A (en) | Telescopic landing gear calibration load based on buffer compression travel determines method | |
| CN106096089A (en) | A kind of aircraft dynamics scale model undercarriage buffer spring | |
| CN203758689U (en) | Helicopter standard blade parameter calibrating device | |
| CN105628333B (en) | A kind of pneumatic error under the conditions of high-altitude High Mach number determines method | |
| CN103577649B (en) | The defining method of cargo hold floor load when transport class aircraft cargo drops | |
| CN102736618A (en) | Diagnosability determining method of satellite control system based on transfer functions | |
| CN105334032B (en) | A kind of calculation method in model structure service life | |
| Prasad et al. | Finite state inflow models for a coaxial rotor in hover | |
| CN109323841B (en) | Coordination method for total load and distributed load of wing based on grid |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150311 |
|
| RJ01 | Rejection of invention patent application after publication |