CN105138828B - A kind of double-strand chain control surface hinge moment derivative evaluation method - Google Patents
A kind of double-strand chain control surface hinge moment derivative evaluation method Download PDFInfo
- Publication number
- CN105138828B CN105138828B CN201510496438.8A CN201510496438A CN105138828B CN 105138828 B CN105138828 B CN 105138828B CN 201510496438 A CN201510496438 A CN 201510496438A CN 105138828 B CN105138828 B CN 105138828B
- Authority
- CN
- China
- Prior art keywords
- derivative
- control surface
- rudder
- angle
- double
- 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.)
- Active
Links
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
A kind of double-strand chain control surface hinge moment derivative evaluation method, it is related to aerodynamic characteristics of vehicle estimating techniques, for estimating double-strand chain control surface hinge moment, preceding rudder face, rear control surface hinge moment are individually calculated with the derivative and hinge moment of yaw angle or the angle of attack with angle of rudder reflection derivative with simple chain evaluation method；Assume that than parameter, new hinge axis location is calculated in compensation according to rear rudder face feature profile parameter；It will be moved after new hinge axis location, obtain new compensation and compare parameter；Correct residual quantity in the head for obtaining rear rudder face；Preceding rudder face is calculated with angle of rudder reflection derivative, rear rudder face with angle of rudder reflection derivative.Double-strand chain control surface hinge moment derivative evaluation method provided by the invention can carry out double-strand chain control surface hinge moment derivative estimation, inference process rationally, clear principle, estimate suitable for double-strand chain control surface hinge moment derivative, result of calculation rationally, it is quick, accurate.
Description
Technical field
The present invention relates to aerodynamic characteristics of vehicle estimating techniques, in particular to a kind of double-strand chain control surface hinge moment
Derivative evaluation method.
Background technology
Existing aircraft rudder surface hinge moment evaluation method system has《ESDU》、DATACOM、《Airplane Design》、
《Airplane design handbook》、《Aviation aerodynamic force engineering calculation handbook》Deng, still, existing aircraft rudder surface hinge moment evaluation method
System is only capable of pro form bill hinge control surface hinge moment.Existing aircraft control surface, especially rudder, on a large scale using double-strand chain
Rudder face, original aircraft rudder surface hinge moment evaluation method system can not meet existing airplane design and use.
So based on insufficient existing for above-mentioned existing aircraft rudder surface hinge moment evaluation method system, there is an urgent need for solutions now
Certainly the technical issues of is how to design a kind of evaluation method of aircraft rudder surface hinge moment, aircraft rudder surface hinge moment estimation
Method can realize the estimation of the double-strand chain control surface hinge moment of existing aircraft control surface, and adapting to, meet the design of aircraft makes
With.
Invention content
It is an object of the invention to solve above-mentioned deficiency of the prior art, a kind of advantages of simple is provided, can be to existing
Aircraft control surface the double-strand chain control surface hinge moment derivative evaluation method estimated of double-strand chain torque.
The purpose of the present invention is achieved through the following technical solutions：A kind of double-strand chain control surface hinge moment derivative evaluation method,
For estimating double-strand chain control surface hinge moment, include the following steps：
S1:With simple chain evaluation method individually calculate front rudder, rear rudder hinge moment with yaw angle or the angle of attack derivative and
Hinge moment is with angle of rudder reflection derivative；
S2：Assume that parameter is compared in compensation according to rear rudder face feature profile parameter using ESDU Controls 04.01.03 algorithms
It is 0.2, new hinge axis location is calculated；
S3：5% will be moved after new hinge axis location, obtain new compensation and compare parameter
Wherein, CbFor chord length C before axisfFor chord length after axis, thFor thickness at hinge axis, shifting amount after a hinge axis；
S4：According to new compensation than parameter with assume compensation than parameter and consult calculate head compensation obtain rear rudder face with figure
Head correct residual quantity △ l；
S5：Control surface hinge moment is corrected with angle of rudder reflection derivative and head after the normal force of rudder face is with angle of rudder reflection derivative afterwards
Shifting amount and the product reciprocal of total chord ratio, i.e. CN δ ' after residual quantity and hinge axis2=Ch δ '2×△l/0.05；
S6：Rudder face is with angle of rudder reflection derivative Ch δ before being calculated according to the following formula1, rear rudder face is with angle of rudder reflection derivative Ch δ2：
Chδ2=Ch δ '2×(δ1+δ2)/δ2。
In said program preferably, in S1 after independent calculate during control surface deflection, need to be calculated its normal force with
Angle of rudder reflection derivative, i.e. CN δ '2。
In any of the above-described scheme preferably, according to the total chord length of 1/2 and control surface of thickness at existing hinge axis, if compensation
Than parameter △=0.2, a new hinge axis location is calculated, wherein, the total chord length of control surface is chord length and string after axis before axis
It is the sum of long.
In any of the above-described scheme preferably, control surface hinge moment is with side before individually being calculated with simple chain evaluation method in S1
The derivative and hinge moment of sliding angle or the angle of attack are not deflected with the relatively preceding rudder face of rudder face after assuming during angle of rudder reflection derivative.
A kind of advantageous effect of double-strand chain control surface hinge moment derivative evaluation method provided by the present invention is, by this
Evaluation method can to double-strand chain control surface hinge moment carry out derivative estimation, inference process rationally, clear principle, suitable for double-strand chain
Control surface hinge moment derivative estimates that result of calculation is rationally, fast, accurately.
Description of the drawings
Fig. 1 is a kind of meter of a preferred embodiment of double-strand chain control surface hinge moment derivative evaluation method according to the invention
Calculate head access figure；
Fig. 2 is a kind of embodiment illustrated in fig. 1 of double-strand chain control surface hinge moment derivative evaluation method according to the invention
Calculate head datum-correction graph；
Fig. 3 is a kind of embodiment illustrated in fig. 1 Fig. 1 of double-strand chain control surface hinge moment derivative evaluation method according to the invention
Rudder face diagrammatic cross-section afterwards.
Specific embodiment
In order to better understand according to a kind of double-strand chain control surface hinge moment derivative evaluation method of the present invention program, below
A kind of one preferred embodiment of double-strand chain control surface hinge moment derivative evaluation method of the present invention is further explained with reference to attached drawing
It states bright.
As shown in Figure 1-Figure 3, a kind of double-strand chain control surface hinge moment derivative evaluation method provided by the invention, for estimating
Double-strand chain control surface hinge moment, includes the following steps：
S1:With simple chain evaluation method individually calculate front rudder, rear rudder hinge moment with yaw angle or the angle of attack derivative and
Hinge moment is with angle of rudder reflection derivative；
S2：Assume that parameter is compared in compensation according to rear rudder face feature profile parameter using ESDU Controls 04.01.03 algorithms
It is 0.2, new hinge axis location is calculated；
S3：5% will be moved after new hinge axis location, obtain new compensation and compare parameter
Wherein, CbFor chord length before axis, CfFor chord length after axis, thFor thickness at hinge axis, shifting amount after a hinge axis；
S4：According to new compensation than parameter with assume compensation than parameter and consult calculate head compensation obtain rear rudder face with figure
Head correct residual quantity △ l；
S5：Control surface hinge moment is corrected with angle of rudder reflection derivative and head after the normal force of rudder face is with angle of rudder reflection derivative afterwards
Shifting amount and the product reciprocal of total chord ratio, i.e. CN δ ' after residual quantity and hinge axis2=Ch δ '2×△l/0.05；
S6：Rudder face is with angle of rudder reflection derivative Ch δ before being calculated according to the following formula1, rear rudder face is with angle of rudder reflection derivative Ch δ2：
Chδ2=Ch δ '2×(δ1+δ2)/δ2。
Wherein, during control surface deflection, need to be calculated its normal force with angle of rudder reflection derivative, i.e. CN after independent calculate in S1
δ2'.According to the total chord length of 1/2 and control surface of thickness (th) at existing hinge axis, if compensation is calculated than parameter △=0.2
One new hinge axis location, wherein, the total chord length of control surface is the sum of chord length and chord length after axis before axis.
Control surface hinge moment is with yaw angle or the derivative and hinge of the angle of attack before individually being calculated with simple chain evaluation method in S1
Chain torque is not deflected with the relatively preceding rudder face of rudder face after assuming during angle of rudder reflection derivative.
Using double-strand chain control surface hinge moment derivative evaluation method provided by the invention to certain model feeder liner double-strand chain
The control surface hinge moment of rudder is estimated, takes its result of the test such as following table：
Product see the table below behind chord length and axis after front and rear control surface deflection angle, axis：
| Angle of rudder reflection | Chord length (m) after axis | Product (m behind axis2) | |
| Preceding rudder face | δ1 | 0.504 | 1.063 |
| Rudder face afterwards | δ 2=δ 1 | 0.2925 | 0.6175 |
S1：By front and rear rudder face by simple chain mode, knot is calculated by ESDU simple chain control surface hinge moment evaluation methods
Fruit is as follows：
| Hinge moment is with sideslip angular derivative | Hinge moment is with angle of rudder reflection derivative | |
| Preceding rudder face | -0.00271 | -0.00668 |
| Rudder face afterwards | -0.00124 | -0.00605 |
S2：By rear rudder face sectional parameter, hinge axis location when acquiring compensation than being 0.2 is 20%, as shown in Figure 3.
S3：5% will be moved after hinge axis and obtain new hinge axis location 25%, rear shifting amount a=0.05*592.3=29.615,
Preceding rudder face chord length Cb=116.5, rear rudder face chord length Cf=465.9, thickness th=139.2 at former hinge axis, calculate new compensation
Compare parameter：
S4：It looks into ESDU Controls 04.01.03 Fig. 2 and obtains head corrected parameter △ l=0.164.
S5：Calculate CN δ=- 0.00605*0.164/0.05=0.0198.
S6：Preceding rudder face, rear control surface hinge moment are calculated with angle of rudder reflection derivative.
Fig. 3 is illustrated that the schematic cross-sectional view of rear rudder face, wherein line on the basis of dotted line, and the intersection position of datum line is direction
The position of the hinge axis of rudder, hinge axis rudder is divided into axis before, two parts, wherein C after axisbFor chord length C before axisfFor string after axis
It is long, thFor thickness at hinge axis.
It has been done in detail above in association with a kind of double-strand chain control surface hinge moment derivative evaluation method specific embodiment of the present invention
Description, but be not limitation of the present invention, any letter made to the above embodiment of every technical spirit according to the present invention
Single modification belongs to the technical scope of the present invention, it is also necessary to explanation, a kind of double-strand chain rudder face hinge power according to the invention
The scope of square derivative evaluation method technical solution includes the arbitrary combination between each part mentioned above.
Claims (4)
1. a kind of double-strand chain control surface hinge moment derivative evaluation method, for estimating double-strand chain control surface hinge moment, feature exists
In including the following steps：
S1:Front rudder, rear rudder hinge moment are individually calculated with yaw angle or the derivative and hinge of the angle of attack with simple chain evaluation method
Torque is with angle of rudder reflection derivative；
S2：Assume that compensation is than parameter according to rear rudder face feature profile parameter using ESDU Controls 04.01.03 algorithms
0.2, new hinge axis location is calculated；
S3：5% will be moved after new hinge axis location, obtain new compensation and compare parameter
Wherein, CbFor chord length before hinge axis, CfFor chord length after hinge axis, thFor thickness at hinge axis, shifting amount after a hinge axis；
S4：According to new compensation than parameter with assume compensation than parameter and consult calculate head compensation obtain the head of rear rudder face with figure
Correct residual quantity △ l in portion；
S5：Control surface hinge moment corrects residual quantity with angle of rudder reflection derivative and head after the normal force of rudder face is with angle of rudder reflection derivative afterwards
And shifting amount and the product reciprocal of total chord ratio, i.e. CN δ ' after hinge axis2=Ch δ '2×△l/0.05；
S6：Rudder face is with angle of rudder reflection derivative Ch δ before being calculated according to the following formula1, rear rudder face is with angle of rudder reflection derivative Ch δ2：
Chδ2=Ch δ '2×(δ1+δ2)/δ2。
2. double-strand chain control surface hinge moment derivative evaluation method as described in claim 1, it is characterised in that：It is individually being counted in S1
After calculation during control surface deflection, need to be calculated its normal force with angle of rudder reflection derivative, i.e. CN δ '2。
3. double-strand chain control surface hinge moment derivative evaluation method as claimed in claim 2, it is characterised in that：According to existing hinge
If compensating than parameter △=0.2, a new hinge axis location is calculated in the total chord length of 1/2 and control surface of thickness at axis,
In, the total chord length of control surface is the sum of chord length and chord length after axis before axis.
4. double-strand chain control surface hinge moment derivative evaluation method as described in claim 1, it is characterised in that：Simple chain is used in S1
Evaluation method individually calculate before control surface hinge moment with the derivative and hinge moment of yaw angle or the angle of attack with angle of rudder reflection derivative when
The relatively preceding rudder face of rudder face does not deflect after assuming that.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510496438.8A CN105138828B (en) | 2015-08-13 | 2015-08-13 | A kind of double-strand chain control surface hinge moment derivative evaluation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510496438.8A CN105138828B (en) | 2015-08-13 | 2015-08-13 | A kind of double-strand chain control surface hinge moment derivative evaluation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105138828A CN105138828A (en) | 2015-12-09 |
| CN105138828B true CN105138828B (en) | 2018-06-29 |
Family
ID=54724174
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510496438.8A Active CN105138828B (en) | 2015-08-13 | 2015-08-13 | A kind of double-strand chain control surface hinge moment derivative evaluation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105138828B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105574257B (en) * | 2015-12-12 | 2019-02-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft double-strand chain rudder efficiency calculation method |
| CN106777689B (en) * | 2016-12-15 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Airplane double-hinge control surface deflection method based on finite element model |
| CN108444626B (en) * | 2018-06-26 | 2023-08-11 | 中电科芜湖钻石飞机制造有限公司 | Measuring device for aircraft control surface hinge moment |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103577701A (en) * | 2013-11-13 | 2014-02-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for computing control surface hinge moment coefficient when airplane incidence angle, sideslip angle and rudder deflection angle are all zero degree |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130345910A1 (en) * | 2011-02-11 | 2013-12-26 | The Board Of Trustees Of The University Of Illinois | Detector function and system for predicting airfoil stall from control surface measurements |
-
2015
- 2015-08-13 CN CN201510496438.8A patent/CN105138828B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103577701A (en) * | 2013-11-13 | 2014-02-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for computing control surface hinge moment coefficient when airplane incidence angle, sideslip angle and rudder deflection angle are all zero degree |
Non-Patent Citations (4)
| Title |
|---|
| Coning motion instability of spinning missiles induced by hinge moment;Wei Zhou et al;《Aerospace Science and Technology》;20130829;第30卷(第1期);239-245页 * |
| Hardware-in-the-loop simulator for research on fault tolerant control of electrohydraulic actuators in a flight control application;Mark Karpenko et al;《Mechatronics》;20091031;第19卷(第7期);1067-1077页 * |
| 舵面铰链力矩及其缝隙效应研究;黄宗波等;《实验流体力学》;20071231;第21卷(第4期);1-6页 * |
| 舵面铰链力矩的估算;孔德永等;《空气动力学学报》;20050630;第23卷(第2期);263-266页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105138828A (en) | 2015-12-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105138828B (en) | A kind of double-strand chain control surface hinge moment derivative evaluation method | |
| EP2466288B1 (en) | Method of designing natural laminar flow wing for reynolds numbers equivalent to actual supersonic aircraft | |
| US9821903B2 (en) | Closed loop control of aircraft control surfaces | |
| CN108984862B (en) | Pneumatic characteristic CFD calculation result correction method | |
| CN105466660B (en) | A kind of aircraft aerodynamic parameter subregion step identification method using acceleration observer | |
| JP2010195392A5 (en) | ||
| CN107145677B (en) | Improved geometric parameter airfoil design method | |
| CN106650095B (en) | Correction method of unmanned aerial vehicle control matrix based on wind tunnel test data and CFD calculation | |
| WO2012141770A3 (en) | Laminar flow wing optimized for transonic and supersonic cruise aircraft | |
| CN104133926A (en) | Comprehensive analysis method of elastic aerodynamic force characteristic | |
| JP2010243400A (en) | Building berth support interference correcting method in subsonic half model wind tunnel test | |
| CN105109705A (en) | Method for calculating rigidity of aircraft airfoil surface structure | |
| CN104331084A (en) | Pneumatic rudder deflection range calculation method based on direction rudder roll control strategy | |
| CN106864770B (en) | A method of assessment unmanned plane manufactures the pneumatic deviation of shape | |
| CN105936334B (en) | A kind of drag reduction pin passive control methods controlled for wing shock wave and device | |
| CN104374541A (en) | Static pressure calculation method for L-shaped pressure sensor | |
| CN202304693U (en) | Device for testing outline dimensions of battery | |
| CN106995037B (en) | Ship hull surface outside plate indulges the arrangement method of bone | |
| CN104627388B (en) | A kind of self adaptation ballistic prediction method of reentry vehicle | |
| Lawson et al. | Development of experimental techniques for hybrid laminar flow control in the ARA transonic wind tunnel | |
| CN117171894A (en) | Aircraft layout pneumatic optimization design method considering static margin constraint | |
| Smith | An Assessment of CREATE-AV Kestrel for F-35 Aero/Performance Applications | |
| CN105205127A (en) | Adaptive-step database establishment method and system of liquid mass/volume characteristic database | |
| CN104155983B (en) | Crosslinking impact assessment method for aerodynamic coupling property between aircraft attitude movement channels | |
| CN106168529B (en) | A kind of wind tunnel test methods for correcting aircraft rigid body lift coefficient |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |