CN106528915A - Method for determining minimum deflection rate critical value of maneuvering control surface of civil transport plane - Google Patents
Method for determining minimum deflection rate critical value of maneuvering control surface of civil transport plane Download PDFInfo
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Abstract
The invention discloses a method for determining a minimum deflection rate critical value of a maneuvering control surface of a civil transport plane. The method comprises the steps that (1) a roll angle rate pi_inf, a pitch angle rate qi_inf and a yaw angle rate ri_inf of the plane at a random moment under a flight state are computed; (2) the roll angle rate, the pitch angle rate and the yaw angle rate at the random moment are computed respectively; (3) a maximum euler angle rate generated when k delta=inf and a maximum euler angle rate generated when k delta=Lim are computed; (4) the period t1 and the period tj which needed by the roll angle rate, the pitch angle rate and the yaw angle rate to reach maximum values are recorded respectively, and a time different dtj is determined by the t1 and the tj; and (5) the minimum deflection rate critical value of the maneuvering control surface is determined. The method for determining the minimum deflection rate critical value of the maneuvering control surface of the civil transport plane disclosed by the invention provides a complete set of method for determining the minimum deflection rate critical value of the maneuvering control surface of the civil transport plane; and a new approach is provided for design of the deflection rate of the maneuvering control surface.
Description
Technical field
The present invention relates to aircraft grasps steady design field, more particularly to a kind of civil transport manoeuvre face is minimum
Deflection speed critical value determines method.
Background technology
Air maneuver control surface minimum deflection speed critical value determines maneuverability and the flight safety that can ensure that aircraft,
If deflection speed is too small, it is possible to can not guarantee maneuverability expected from aircraft, or even flight safety is constituted a threat to；If
Deflection speed is excessive, it is possible to propose too high requirement to actuator design, and needs pay bigger cost, so minimum inclined
The determination of rotational speed rate critical value is particularly important.Fig. 1 is the principle that air maneuver control surface minimum deflection speed critical value determines
Figure.
That in Fig. 1, solid line is represented is KδEulerian angles rate curve during=inf；That dotted line is represented is KδEuler during=Lim
Angular speed curve；t1That what is represented is KδThe time required during maximum Euler's angular speed is reached during=inf；tjThat what is represented is Kδ=Lim
When reach the time required during maximum Euler's angular speed；dtjThat what is represented is time difference (tj-t1)。
At present, it is for the determination of civil transport manoeuvre face minimum deflection speed critical value, also no a set of applicable
Method, depending on major part is both referred to the motor-driven face minimum deflection speed of domestic and international similar aircraft, but minimum deflection speed
Why it is so fixed, why fixed so big, lack theories technique support, or even some are in order to meet minimum deflection rate requirement
And considerably increase aircraft development cost.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
It is an object of the invention to provide a kind of civil transport manoeuvre face minimum deflection speed critical value determination side
Method come overcome or at least mitigate prior art at least one drawbacks described above.
For achieving the above object, a kind of civil transport manoeuvre face minimum deflection speed critical value of present invention offer is true
Determine method, the civil transport manoeuvre face minimum deflection speed critical value determines that method comprises the steps：
Step 1：In manoeuvre face KδDuring=inf, the rolling angular speed of flight status lower any time is calculated
pi_inf, pitch rate qi_inf, yawrate ri_inf；
Step 2：As the K in manoeuvre faceδFor a series of finite values (Lim) when, respectively calculate any time roll angle
Speed (pi_Lim)j, pitch rate (qi_Lim)j, yawrate (ri_Lim)j；
Step 3：Calculate KδMaximum Euler angular speed (p during=infmax_inf, qmax_inf, rmax_inf) and calculate Kδ=LimWhen most
Big Euler angle speed ((pmax_Lim)j, (qmax_Lim)j, (rmax_Lim)j)；
Step 4：K is recorded respectively by computer sim- ulation modeδFor inf and Lim when, rolling angular speed, pitch rate and
Yawrate reaches time t required during maximum1And tj, and pass through t1And tjDetermine time difference dtj；
Step 5：Determine manoeuvre face minimum deflection speed critical value (Kδ_min)L。
Preferably, the rolling angular speed p in the step 1i_inf, pitch rate qi_inf, yawrate ri _ i n fSpecifically
It is to be obtained by equation below：
；Wherein,
Ix,Iy,IzIt is around aircraft x, the moment of inertia (kg.m of tri- axle of y, z3), pi-1_inf,qi-1_inf,ri-1_infIt was a upper moment
Euler's angular speed (°/s),Be respectively a upper moment Euler's angular acceleration (°/s2), Δ t is meter
Evaluation time step-length (s), value are 0.001,It was the ram compression (kg/m.s at a upper moment2),It is upper one respectively
The rolling at moment, pitching and yawing moment coefficient, S are wing area of reference (m2), bA,cAIt is length and the Average aerodynamic of wing
Chord length (m).
Preferably, rolling angular speed (p in the step 2i_Lim)j, pitch rate (qi_Lim)j, yawrate
(ri_Lim)jObtain specifically by equation below：；Its
In,
Ix,Iy,IzIt is around aircraft x, the moment of inertia (kg.m of tri- axle of y, z3), pi-1_inf, qi-1_inf, ri-1_inf are
Euler's angular speed (°/s) at a upper moment,Be respectively a upper moment Euler's angular acceleration (°/s2),
Δ t is to calculate time step (s), and value is 0.001,It was the ram compression (kg/m.s at a upper moment2),Point
It was not rolling, pitching and the yawing moment coefficient at a upper moment, S is wing area of reference (m2), bA,cABe wing length and
Mean aerodynamic chord (m).
Preferably, the K in the step 3δMaximum Euler angular speed (p during=infmax_inf, qmax_inf, rmax_inf) pass through
Equation below is calculated：
pmax_inf=max (pi_inf),qmax_inf=max (qi_inf),rmax_inf=max (ri_inf)；Wherein, j is KδValue
Number.
Preferably, the K in the step 3δMaximum Euler angular speed ((p during=Limmax_Lim)j, (qmax_Lim)j,
(rmax_Lim)j) calculated by equation below：
(pmax_Lim)j=max ((pi_Lim)j),(qmax_Lim)j=max ((qi_Lim)j),(rmax_Lim)j=max
((ri_Lim)j)；Wherein, j is KδValue number.
Preferably, the time difference dtjFor dtj=tj-t1。
Preferably, the step 5 is：Judge dtjIn have several time differences to meet following condition：First pre-conditioned≤
dtj≤ the second is pre-conditioned；
If only one of which time difference meets condition, current control surface is recorded by the time difference computer sim- ulation inclined
Turn value, it is manoeuvre face minimum deflection speed critical value (K to deserve front control deflecting facet valueδ_min)L；
If multiple time differences meet condition, then in taking multiple time differences, numerical value is pre-conditioned closest to first
Time difference, records current control surface tilt value by the time difference computer sim- ulation, and it is motor-driven to deserve front control deflecting facet value
Control surface minimum deflection speed critical value (Kδ_min)L。
Preferably, described first it is pre-conditioned be 0.075 second；Described second it is pre-conditioned be 0.08 second.
Preferably, a series of finite values (Lim) in the step 1 include 5 °/s, 10 °/s, 15 °/s, 20 °/s, 25 °/
S, 30 °/s.
Preferably, j values in the span of 20 °/s to 70 °/s.
It is a set of complete that civil transport manoeuvre face minimum deflection speed critical value in the present invention determines that method is provided
Whole civil transport manoeuvre face minimum deflection speed critical value determines method；Carry for manoeuvre deflecting facet rated design
For a kind of new tool, while preferably serving following type design.
Description of the drawings
Fig. 1 is the schematic diagram that air maneuver control surface minimum deflection speed critical value of the prior art determines.
Fig. 2 is that the civil transport manoeuvre face minimum deflection speed critical value in one embodiment of the invention determines method
Schematic flow sheet.
Specific embodiment
For making purpose, technical scheme and the advantage of present invention enforcement clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than the embodiment of whole.It is exemplary below with reference to the embodiment of Description of Drawings, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment obtained under the premise of creative work is not made by member, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " or position relationship are based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than indicate or imply the dress of indication
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The restriction of scope.
Fig. 1 is the schematic diagram that air maneuver control surface minimum deflection speed critical value of the prior art determines.Fig. 2 is this
Invent the schematic flow sheet that the civil transport manoeuvre face minimum deflection speed critical value in an embodiment determines method.
Civil transport manoeuvre face minimum deflection speed critical value as shown in Figure 1 determines that method includes following step
Suddenly：Step 1：In manoeuvre face KδDuring=inf, the rolling angular speed p of flight status lower any time is calculatedi_inf, bow
Elevation angle speed qi_inf, yawrate ri_inf；
Step 2：As the K in manoeuvre faceδFor a series of finite values (Lim) when, respectively calculate any time roll angle
Speed (pi_Lim)j, pitch rate (qi_Lim)j, yawrate (ri_Lim)j；
Step 3：Calculate KδMaximum Euler angular speed (p during=infmax_inf, qmax_inf, rmax_inf) and calculate Kδ=LimWhen most
Big Euler angle speed ((pmax_Lim)j, (qmax_Lim)j, (rmax_Lim)j)；
Step 4：K is recorded respectively by computer sim- ulation modeδFor inf and Lim when, rolling angular speed, pitch rate and
Yawrate reaches time t required during maximum1And tj, and pass through t1And tjDetermine time difference dtj；
Step 5：Determine manoeuvre face minimum deflection speed critical value (Kδ_min)L。
In the present embodiment, the rolling angular speed p in step 1i_inf, pitch rate qi_inf, yawrate ri_infTool
Body is to be obtained by equation below：
；Wherein,
Ix,Iy,IzIt is around aircraft x, the moment of inertia (kg.m of tri- axle of y, z3)(xCorrespondence x-axis,yCorrespondence y-axis,zCorrespondence z-axis),
pi-1_inf,qi-1_inf,ri-1_infIt was Euler's angular speed (unit for °/s) at a upper moment,On being respectively
One moment Euler's angular acceleration (unit for °/s2), Δ t is to calculate time step (unit is s), and value is 0.001,
It was that (unit is kg/m.s for the ram compression at a upper moment2), Cli-1Be a upper moment rolling coefficient,It was the pitching at a upper moment
Coefficient,It was the yawing moment coefficient at a upper moment, S is that (unit is m to wing area of reference2), bAIt is the length (unit of wing
For m), cAMean aerodynamic chord (unit is m).
In the present embodiment, rolling angular speed (p in step 2i_Lim)j, pitch rate (qi_Lim)j, yawrate
(ri_Lim)jObtain specifically by equation below：
；Wherein,
Ix,Iy,IzIt is around aircraft x, the moment of inertia (kg.m of tri- axle of y, z3)(xCorrespondence x-axis,yCorrespondence y-axis,zCorrespondence z-axis),
pi-1_inf,qi-1_inf,ri-1_infIt was Euler's angular speed (°/s) at a upper moment,It is upper a period of time respectively
Quarter Euler's angular acceleration (°/s2), Δ t is to calculate time step (s), and value is 0.001,It was the ram compression at a upper moment
(kg/m.s2),Be a upper moment rolling coefficient,Be a upper moment pitching coefficient,It was the inclined of a upper moment
Boat moment coefficient, S is wing area of reference (m2), bAIt is length (unit is m), the c of wingA(unit is mean aerodynamic chord
m)。
In the present embodiment, the K in step 3δMaximum Euler angular speed (p during=infmax_inf, qmax_inf, rmax_inf) logical
Cross equation below to be calculated：
pmax_inf=max (pi_inf),qmax_inf=max (qi_inf),rmax_inf=max (ri_inf)；Wherein,
J is KδValue number.Advantageously, j values in the span of 20 °/s to 70 °/s.Take within the range
Value, can save the computer sim- ulation time.
In the present embodiment, the K in step 3δ=LimWhen maximum Euler angular speed ((pmax_Lim)j, (qmax_Lim)j,
(rmax_Lim)j) calculated by equation below：
(pmax_Lim)j=max ((pi_Lim)j),(qmax_Lim)j=max ((qi_Lim)j),(rmax_Lim)j=max
((ri_Lim)j)；Wherein,
J is KδValue number.Advantageously, j values in the span of 20 °/s to 70 °/s.Take within the range
Value, can save the computer sim- ulation time.
In the present embodiment, time difference dtjFor dtj=tj-t1。
In the present embodiment, step 5 is：Judge dtjIn have several time differences to meet following condition：
First pre-conditioned≤dtj≤ the second is pre-conditioned；
If only one of which time difference meets condition, current control surface is recorded by the time difference computer sim- ulation inclined
Turn value, it is manoeuvre face minimum deflection speed critical value (K to deserve front control deflecting facet valueδ_min)L；
If multiple time differences meet condition, then in taking multiple time differences, numerical value is pre-conditioned closest to first
Time difference, records current control surface tilt value by the time difference computer sim- ulation, and it is motor-driven to deserve front control deflecting facet value
Control surface minimum deflection speed critical value (Kδ_min)L。
In the present embodiment, first it is pre-conditioned be 0.075 second；Second it is pre-conditioned be 0.08 second.
In the present embodiment, a series of finite values (Lim) in the step 1 include 5 °/s, 10 °/s, 15 °/s, 20 °/
S, 25 °/s, 30 °/s.It is understood that a series of finite value (Lim) arbitrarily can choose.
Below with illustrate be that mode is further elaborated on to the application, it is to be understood that the citing is not
Constitute any restriction to the application.
The aircraft of known a certain embodiment calculates state, such as table 1 below：
Method is determined by the civil transport manoeuvre face minimum deflection speed critical value of the application, is obtained as follows
Result of calculation：
2 manoeuvre face (elevator) minimum deflection speed critical value of table
3 manoeuvre face (rudder) minimum deflection speed critical value of table
4 manoeuvre face (aileron) minimum deflection speed critical value of table
It is last it is to be noted that：Above example only to illustrate technical scheme, rather than a limitation.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：Which is still
Technical scheme described in foregoing embodiments can be modified, or equivalent is carried out to which part technical characteristic and replace
Change；And these modifications or replacement, do not make the essence of appropriate technical solution depart from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (10)
1. a kind of civil transport manoeuvre face minimum deflection speed critical value determines method, it is characterised in that described civilian
Transporter manoeuvre face minimum deflection speed critical value determines that method comprises the steps：
Step 1：In manoeuvre face KδDuring=inf, the rolling angular speed of flight status lower any time is calculated by formula
pi_inf, pitch rate qi_inf, yawrate ri_inf；
Step 2：As the K in manoeuvre faceδFor a series of finite values (Lim) when, the rolling of any time is calculated respectively by formula
Angular speed (pi_Lim)j, pitch rate (qi_Lim)j, yawrate (ri_Lim)j；
Step 3：Calculate KδMaximum Euler angular speed (p during=infmax_inf, qmax_inf, rmax_inf) and calculate KδIt is maximum during=Lim
Euler angular speed ((pmax_Lim)j, (qmax_Lim)j, (rmax_Lim)j)；
Step 4：K is recorded respectively by computer sim- ulation modeδFor inf and Lim when, rolling angular speed, pitch rate and yaw angle
Speed reaches time t required during maximum1And tj, and pass through t1And tjDetermine time difference dtj；
Step 5：Determine manoeuvre face minimum deflection speed critical value (Kδ_min)L。
2. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 1 determines method, its feature
It is, the rolling angular speed p in the step 1i_inf, pitch rate qi_inf, yawrate ri_infSpecifically by as follows
Formula is obtained：
Wherein,
Ix,Iy,IzIt is around aircraft x, the moment of inertia (kg.m of tri- axle of y, z3), pi-1_inf,qi-1_inf,ri-1_infIt was the Europe at a upper moment
Drawing angular speed (°/s),Be respectively a upper moment Euler's angular acceleration (°/s2), when Δ t is to calculate
Between step-length (s), value is 0.001,It was the ram compression (kg/m.s at a upper moment2),It was a upper moment respectively
Rolling, pitching and yawing moment coefficient, S is wing area of reference (m2), bA,cAIt is length and the mean aerodynamic chord of wing
(m)。
3. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 2 determines method, its feature
It is, rolling angular speed (p in the step 2i_Lim)j, pitch rate (qi_Lim)j, yawrate (ri_Lim)jSpecially lead to
Cross equation below acquisition：
Wherein,
Ix,Iy,IzIt is around aircraft x, the moment of inertia (kg.m of tri- axle of y, z3), pi-1_inf,qi-1_inf,ri-1_infIt was the Europe at a upper moment
Drawing angular speed (°/s),Be respectively a upper moment Euler's angular acceleration (°/s2), when Δ t is to calculate
Between step-length (s), value is 0.001,It was the ram compression (kg/m.s at a upper moment2),It was a upper moment respectively
Rolling, pitching and yawing moment coefficient, S is wing area of reference (m2), bA,cAIt is length and the mean aerodynamic chord of wing
(m)。
4. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 3 determines method, its feature
It is, the K in the step 3δMaximum Euler angular speed (p during=infmax_inf, qmax_inf, rmax_inf) entered by equation below
Row is calculated：
pmax_inf=max (pi_inf),qmax_inf=max (qi_inf),rmax_inf=max (ri_inf)；Wherein,
J is KδValue number.
5. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 4 determines method, its feature
It is, the K in the step 3δMaximum Euler angular speed ((p during=Limmax_Lim)j, (qmax_Lim)j, (rmax_Lim)j) by such as
Lower formula is calculated：(pmax_Lim)j=max ((pi_Lim)j),(qmax_Lim)j=max ((qi_Lim)j),(rmax_Lim)j=max
((ri_Lim)j)；Wherein, j is KδValue number.
6. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 5 determines method, its feature
It is, the time difference dtjFor dtj=tj-t1。
7. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 6 determines method, its feature
It is that the step 5 is：Judge dtjIn have several time differences to meet following condition：First pre-conditioned≤dtj≤ the second is pre-
If condition；
If only one of which time difference meets condition, by the current manipulation deflecting facet of time difference computer sim- ulation record
Value, it is manoeuvre face minimum deflection speed critical value (K to deserve front control deflecting facet valueδ_min)L；
If multiple time differences meet condition, then in taking multiple time differences, numerical value is closest to the first pre-conditioned time
Difference, records current control surface tilt value by the time difference computer sim- ulation, and it is manoeuvre to deserve front control deflecting facet value
Face minimum deflection speed critical value (Kδ_min)L。
8. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 7 determines method, its feature
Be, described first it is pre-conditioned be 0.075 second；Described second it is pre-conditioned be 0.08 second.
9. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 1 determines method, its feature
Be, a series of finite values (Lim) in the step 1 include 5 °/s, 10 °/s, 15 °/s, 20 °/s, 25 °/s, 30 °/s.
10. minimum deflection speed critical value in civil transport manoeuvre face as claimed in claim 4 determines method, its feature
It is, j values in the span of 20 °/s to 70 °/s.
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Cited By (1)
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| CN110598345A (en) * | 2019-09-19 | 2019-12-20 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating and analyzing rolling characteristics of fuel in oil tank of oiling machine during transverse movement |
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| CN110598345A (en) * | 2019-09-19 | 2019-12-20 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating and analyzing rolling characteristics of fuel in oil tank of oiling machine during transverse movement |
| CN110598345B (en) * | 2019-09-19 | 2022-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating and analyzing rolling characteristics of fuel in oil tank of oiling machine during transverse movement |
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