CN105138828A - Double-hinge control surface hinge moment derivative estimation method - Google Patents

Abstract

The invention discloses a double-hinge control surface hinge moment derivative estimation method, which relates to the aircraft aerodynamic characteristics estimation technology. The method is used for estimating double-hinge control surface hinge moment, separately calculating derivatives of hinge moments of front and back control surfaces with sideslip angle/angle of incidence and derivatives of the hinge moments with deflection angles of control surfaces through a single hinge estimation method, supposing a compensation ratio parameter according to a back control surface characteristic section parameter, calculating out a new hinge shaft position, moving the new hinge shaft position backward to obtain a new compensation ratio parameter, obtaining nose allowance of the back control surface, and calculating out the derivative of deflection angle of control surface of the front control surface and the derivative of deflection angle of control surface of the back control surface. The double-hinge control surface hinge moment derivative estimation method, provided by the invention, can perform derivative estimation on double-hinge control surface hinge moment, has the advantages of rational deduction process and clear principles, is suitable for double-hinge control surface hinge moment derivative estimation, and obtains rational and accurate calculation result quickly.

Description

A kind of double-strand chain control surface hinge moment derivative evaluation method

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, " AirplaneDesign ", " airplane design handbook ", " aviation aerodynamic force engineering calculation handbook " etc., but existing aircraft rudder surface hinge moment evaluation method system only can pro form bill hinge control surface hinge moment.Existing aircraft control surface, especially yaw rudder, adopt double-strand chain rudder face on a large scale, and original aircraft rudder surface hinge moment evaluation method system cannot meet existing airplane design and use.

So, based on the deficiency that above-mentioned existing aircraft rudder surface hinge moment evaluation method system exists, the technical matters needing now solution badly how to design a kind of evaluation method of aircraft rudder surface hinge moment, this aircraft rudder surface hinge moment evaluation method can realize the estimation of the double-strand chain control surface hinge moment of existing aircraft control surface, and the design adapting to, meet aircraft uses.

Summary of the invention

The object of the invention is to solve above-mentioned deficiency of the prior art, the double-strand chain control surface hinge moment derivative evaluation method provide a kind of advantages of simple, can estimating to the double-strand chain moment of existing aircraft control surface.

Object 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, comprises the steps:

S1: calculate separately front rudder, rear rudder hinge moment with the derivative of yaw angle/angle of attack and hinge moment with angle of rudder reflection derivative with simple chain evaluation method;

S2: utilizing ESDUControls04.01.03 algorithm to compensate than parameter according to rear rudder face feature profile parameter supposition is 0.2, calculates the hinge axis location made new advances;

S3: move 5% by after new hinge axis location, obtains new compensation and compares parameter

wherein, C _bfor chord length C before axle _ffor chord length after axle, t _hfor hinge axis place thickness, the amount of moving after a hinge axis;

S4: new compensation compensates than parameter and supposition and consults FIGURE2 than parameter and calculate the head correction residual quantity △ 1 that head compensation figure obtains rear rudder face;

S5: total the normal force of rear rudder face is rear control surface hinge moment with the product of the amount of moving after angle of rudder reflection derivative and head correction residual quantity and hinge axis with the inverse of chord ratio with angle of rudder reflection derivative, i.e. CN δ ' ₂=Ch δ ' ₂× Δ 1/0.05.

S6: calculate front rudder face with angle of rudder reflection derivative Ch δ according to following formula ₁, rear rudder face with angle of rudder reflection derivative, Ch δ ₂

${\mathrm{Ch\δ}}_1={{\mathrm{Ch\δ}}_1}^{\′}+\frac{{{\mathrm{Ch\δ}}_2}^{\′}\×S2\×C2\×\mathrm{\δ}2}{S1\×C1\×\mathrm{\δ}1}-\frac{{\mathrm{CN\δ}}_2^{\′}\×S2\×\mathrm{\δ}2\×(C1-C2)}{S1\×\mathrm{\δ}1\×C1}$

Chδ ₂＝Chδ′ ₂×(δ1+δ2)/δ2

In such scheme preferably, during control surface deflection, need to calculate its normal force with angle of rudder reflection derivative, i.e. CN δ ' in S1 after calculating separately ₂.

In above-mentioned either a program preferably, according to existing hinge axis place thickness 1/2th and the total chord length of control surface, if compensate than parameter △=0.2, calculate a new hinge axis location, wherein, the total chord length of control surface is chord length sum after chord length and axle before axle.

In above-mentioned either a program preferably, in S1 with simple chain evaluation method calculate separately front control surface hinge moment with the derivative of yaw angle/angle of attack and hinge moment with rudder face after hypothesis during angle of rudder reflection derivative relatively before rudder face do not deflect.

The beneficial effect of a kind of double-strand chain control surface hinge moment derivative evaluation method provided by the present invention is, derivative estimation can be carried out to double-strand chain control surface hinge moment by this evaluation method, inference process rationally, clear principle, be applicable to the estimation of double-strand chain control surface hinge moment derivative, result of calculation rationally, quick, accurately.

Accompanying drawing explanation

Fig. 1 calculates head according to the FIGURE2 of a preferred embodiment of a kind of double-strand chain control surface hinge moment derivative evaluation method of the present invention to consult with figure;

Fig. 2 calculates head datum-correction graph according to the FIGURE2 embodiment illustrated in fig. 1 of a kind of double-strand chain control surface hinge moment derivative evaluation method of the present invention;

Fig. 3 is rudder face diagrammatic cross-section after the Fig. 1 embodiment illustrated in fig. 1 according to a kind of double-strand chain control surface hinge moment derivative evaluation method of the present invention.

Embodiment

In order to understand a kind of double-strand chain control surface hinge moment derivative evaluation method according to the present invention program better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to a kind of double-strand chain control surface hinge moment derivative evaluation method of the present invention.

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, comprises the steps:

S1: calculate separately front rudder, rear rudder hinge moment with the derivative of yaw angle/angle of attack and hinge moment with angle of rudder reflection derivative with simple chain evaluation method;

S2: utilizing ESDUControls04.01.03 algorithm to compensate than parameter according to rear rudder face feature profile parameter supposition is 0.2, calculates the hinge axis location made new advances;

S3: move 5% by after new hinge axis location, obtains new compensation and compares parameter

wherein, C _bfor chord length C before axle _ffor chord length after axle, t _hfor hinge axis place thickness, the amount of moving after a hinge axis;

S4: new compensation compensates than parameter and supposition and consults FIGURE2 than parameter and calculate the head correction residual quantity △ 1 that head compensation figure obtains rear rudder face;

S5: total the normal force of rear rudder face is rear control surface hinge moment with the product of the amount of moving after angle of rudder reflection derivative and head correction residual quantity and hinge axis with the inverse of chord ratio with angle of rudder reflection derivative, i.e. CN δ ' ₂=Ch δ ' ₂× Δ 1/0.05.

S6: calculate front rudder face with angle of rudder reflection derivative Ch δ according to following formula ₁, rear rudder face is with angle of rudder reflection derivative Ch δ: ₂

${\mathrm{Ch\δ}}_1={{\mathrm{Ch\δ}}_1}^{\′}+\frac{{{\mathrm{Ch\δ}}_2}^{\′}\×S2\×C2\×\mathrm{\δ}2}{S1\×C1\×\mathrm{\δ}1}-\frac{{\mathrm{CN\δ}}_2^{\′}\×S2\×\mathrm{\δ}2\×(C1-C2)}{S1\×\mathrm{\δ}1\×C1}$

Chδ ₂＝Chδ′ ₂×(δ1+δ2)/δ2。

Wherein, during control surface deflection, need to calculate its normal force with angle of rudder reflection derivative, i.e. CN δ ' in S1 after calculating separately ₂.According to existing hinge axis place thickness 1/2th and the total chord length of control surface, if compensate than parameter △=0.2, calculate a new hinge axis location, wherein, the total chord length of control surface is chord length sum after chord length and axle before axle.

In S1 with simple chain evaluation method calculate separately front control surface hinge moment with the derivative of yaw angle/angle of attack and hinge moment with rudder face after hypothesis during angle of rudder reflection derivative relatively before rudder face do not deflect.

Apply the control surface hinge moment of double-strand chain control surface hinge moment derivative evaluation method provided by the invention to certain model feeder liner double-strand chain yaw rudder to estimate, get its test findings as following table:

Before and after control surface deflection angle, long-pendingly after chord length and axle after axle to see the following form:

	Angle of rudder reflection	Chord length (m) after axle	Long-pending (m after axle 2)
				Front rudder face	δ1	0.504	1.063
Rear rudder face	δ2＝δ1	0.2925	0.6175

S1: front and back rudder face is pressed simple chain mode, calculates result by ESDU simple chain control surface hinge moment evaluation method as follows:

	Hinge moment is with yaw angle derivative	Hinge moment is with angle of rudder reflection derivative
			Front rudder face	-0.00271	-0.00668
Rear rudder face	-0.00124	-0.00605

S2: by rear rudder face sectional parameter, trying to achieve the hinge axis location compensated than when being 0.2 is 20%, as shown in Figure 3.

S3: obtain new hinge axis location 25% by moving 5% after hinge axis, after the amount of moving a=0.05*592.3=29.615, front rudder face chord length Cb=116.5, rear rudder face chord length Cf=465.9, former hinge axis place thickness th=139.2, calculates new compensation than parameter:

$\mathrm{\Δ}={\[{\left(\frac{116.5+29.615}{465.8-29.615}\right)}^2-{\left(\frac{0.5\×139.2}{465.8-29.615}\right)}^2\]}^{0.5}=0.293$

S4: look into ESDUControls04.01.03 Fig. 2 and obtain head corrected parameter △ 1=0.164.

S5: calculate CN δ=-0.00605*0.164/0.05=0.0198.

S6: calculate front rudder face, rear control surface hinge moment with angle of rudder reflection derivative.

Shown in Fig. 3 is the cross-sectional schematic of rear rudder face, and wherein dotted line is datum line, and the position of intersecting point of datum line is the position of the hinge axis of yaw rudder, two parts, wherein C before yaw rudder is divided into axle by hinge axis, after axle _bfor chord length C before axle _ffor chord length after axle, t _hfor hinge axis place thickness.

More than be described in detail in conjunction with a kind of double-strand chain control surface hinge moment derivative evaluation method specific embodiment of the present invention, but be not limitation of the present invention, everyly according to technical spirit of the present invention, technical scope of the present invention is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of a kind of double-strand chain control surface hinge moment derivative evaluation method technical scheme of the present invention.

Claims (4)

1. a double-strand chain control surface hinge moment derivative evaluation method, for estimating double-strand chain control surface hinge moment, is characterized in that, comprising the steps:

S1: calculate separately front rudder, rear rudder hinge moment with the derivative of yaw angle/angle of attack and hinge moment with angle of rudder reflection derivative with simple chain evaluation method;

S2: utilizing ESDUControls04.01.03 algorithm to compensate than parameter according to rear rudder face feature profile parameter supposition is 0.2, calculates the hinge axis location made new advances;

S3: move 5% by after new hinge axis location, obtains new compensation and compares parameter

wherein, C _bfor chord length C before hinge axis _ffor chord length after hinge axis, t _hfor hinge axis place thickness, the amount of moving after a hinge axis;

S4: new compensation compensates than parameter and supposition and consults FIGURE2 than parameter and calculate the head correction residual quantity △ 1 that head compensation figure obtains rear rudder face;

S5: total the normal force of rear rudder face is rear control surface hinge moment with the product of the amount of moving after angle of rudder reflection derivative and head correction residual quantity and hinge axis with the inverse of chord ratio with angle of rudder reflection derivative, i.e. CN δ ' ₂=Ch δ ' ₂× Δ 1/0.05.

S6: calculate front rudder face with angle of rudder reflection derivative Ch δ according to following formula ₁, rear rudder face is with angle of rudder reflection derivative Ch δ ₂:

${\mathrm{Ch\δ}}_1={{\mathrm{Ch\δ}}_1}^{\′}+\frac{{{\mathrm{Ch\δ}}_2}^{\′}\×S2\×C2\×\mathrm{\δ}2}{S1\×C1\×\mathrm{\δ}1}-\frac{{\mathrm{CN\δ}}_2^{\′}\×S2\×\mathrm{\δ}2\×(C1-C2)}{S1\×\mathrm{\δ}1\×C1}$

Chδ ₂＝Chδ ₂′×(δ ₁+δ ₂)/δ ₂。

2. double-strand chain control surface hinge moment derivative evaluation method as claimed in claim 1, is characterized in that: during control surface deflection, need to calculate its normal force with angle of rudder reflection derivative, i.e. CN δ ' in S1 after calculating separately ₂.

3. double-strand chain control surface hinge moment derivative evaluation method as claimed in claim 2, it is characterized in that: according to existing hinge axis place thickness 1/2th and the total chord length of control surface, if compensate than parameter △=0.2, calculate a new hinge axis location, wherein, the total chord length of control surface is chord length sum after chord length and axle before axle.

4. double-strand chain control surface hinge moment derivative evaluation method as claimed in claim 1, is characterized in that: calculate separately front control surface hinge moment with simple chain evaluation method in S1 and do not deflect with the relatively front rudder face of rudder face after hypothesis during angle of rudder reflection derivative with the derivative of yaw angle/angle of attack and hinge moment.