CN110239737A - The calculation method of wing flap adjustment amount when multiple whirlpool paddle aircraft yaw, sideslip - Google Patents

The calculation method of wing flap adjustment amount when multiple whirlpool paddle aircraft yaw, sideslip Download PDF

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Publication number
CN110239737A
CN110239737A CN201910456936.8A CN201910456936A CN110239737A CN 110239737 A CN110239737 A CN 110239737A CN 201910456936 A CN201910456936 A CN 201910456936A CN 110239737 A CN110239737 A CN 110239737A
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China
Prior art keywords
wing flap
sideslip
adjustment amount
calculation method
control wheel
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CN201910456936.8A
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CN110239737B (en
Inventor
唐永红
陈军
韩金辰
李颢
游晓恒
唐蕃
蔡晓飞
陈正明
轩晓楠
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AVIC Shaanxi Aircraft Industry Group Corp Ltd
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AVIC Shaanxi Aircraft Industry Group Corp Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • 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

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Supercharger (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)
  • Toys (AREA)

Abstract

The invention belongs to technical field of aerospace, to solve the problems, such as multiple whirlpool paddle aircraft yaw, sideslip, the calculation method of wing flap adjustment amount when proposing a kind of multiple whirlpool paddle aircraft yaw, breakking away, comprising: step 1 obtains control wheel deflection angle θ and deflection direction；Step 2, according to formulaIt is wing flap regulation coefficient that wing flap adjustment numerical quantity L, the K, which is calculated,；Step 3, the deflection direction according to control wheel, obtain wing flap adjustment amount L and adjustment direction.

Description

The calculation method of wing flap adjustment amount when multiple whirlpool paddle aircraft yaw, sideslip
Technical field
The invention belongs to technical field of aerospace, are related to multiple whirlpool paddle aircraft, when appearance of taking a flight test before factory is yawed, is breakked away, A kind of double slit retrusive wing flap adjustment amount calculation method.
Background technique
The process of aircraft assembly is assembled into component at component, assembly staking for component assembly, component is butted into aircraft, aircraft It not can avoid part manufacturing tolerance, component assembling deviation, component riveting rigging error equal error in manufacture assembling process to accumulate and ask Topic, especially multi engines airplane power factor (PF) difference, the accumulation of fuel consumption difference, may aggravate aircraft appearance yaw, sideslip etc. is Column problem.
The above problem is difficult to debug stage discovery on ground and solve, can only be by multiple at present without the algorithm of adjustment amount Adjustment is taken a flight test, and is improved or is corrected aircraft and break away and yaw problem, adjusts during taking a flight test, waste a large amount of aviation kerosine, increase Add carbon dioxide isothermal chamber gas emissions, the rudder faces such as pilot guidance aileron, rudder are needed in taking a flight test, increases control Amount processed increases the satisfaction of user, so there is an urgent need to the wing flaps of a kind of amendment aircraft yaw, sideslip to adjust quantity algorithm.
Summary of the invention
The technical issues of solution
To solve the problems, such as multiple whirlpool paddle aircraft yaw, sideslip, the present invention proposes a kind of multiple whirlpool paddle aircraft yaw, breaks away When wing flap adjustment amount calculation method, it is simple, efficiently, it is quick, to solve the problems, such as yaw, sideslip.
Technical solution
A kind of multiple whirlpool paddle aircraft yaw, when breakking away wing flap adjustment amount calculation method, comprising:
Step 1 obtains control wheel deflection angle θ and deflection direction；
Step 2, according to formulaWing flap adjustment numerical quantity L, the K is calculated as wing flap adjustment Coefficient；
Step 3, the deflection direction according to control wheel, obtain wing flap adjustment amount L and adjustment direction.
In step 1, when control wheel deflection angle θ and deflection direction are according to breakking away, yawing, pilot is to guarantee that aircraft is flat Fly, by the way that manipulation control wheel amendment is breakked away, yaw angle obtains.
K is 1430.66.
The K passes through the wing section lift coefficient and the flap of control wheel deflection angle, the area of aileron and wing flap, aileron and wing flap The length of the wing obtains.
Step 3 specifically:
When driving, which is faced left, plays disk, left side wing flap shortens L/2 and right side wing flap along course and extends L/2 against course, when driving When sailing the disk right side and beating, left side wing flap against course extends L/2 and right side wing flap along course shortens L/2.
Alternatively, step 3 specifically:
When driving, which is faced left, plays disk, left side wing flap shortens L along course, and when the control wheel right side is beaten, right side wing flap contracts along course Short L.
Alternatively, step 3 specifically:
When driving, which is faced left, plays disk, right side wing flap extends L against course, and when the control wheel right side is beaten, left side wing flap is stretched against course Long L.
Further include:
Step 4 is adjusted wing flap by calculated value.
Beneficial effect
The present invention provides one kind to break away for calculating aircraft, yaw when, simple, the efficiently algorithm of wing flap adjustment amount, It can rapidly and efficiently instruct that aircraft yaw, the adjustment of wing flap changes left and right wing area by adjusting wing flap in sideslip, improve left Starboard wing lift, making up aerofoil profile, span manufacture build-up tolerance, deviation, error accumulation and multi engines airplane engine, there are power The series of problems such as aircraft yaw, sideslip caused by factor difference, fuel consumption difference etc..The application that the present invention passes through a large amount of aircrafts It confirms, which does not need to iterate and multiple flight validation, reach the consistent purpose of aircraft or so airfoil lift, Have the characteristics that simple, quick, efficient.Reduce successive ignition adjustment and flight validation process simultaneously, it is satisfied to increase user Degree, the achievement can be applied in various aircrafts, have extensive society generalization and application value.
Detailed description of the invention
Fig. 1 is that control wheel deflects θ angle schematic diagram
Fig. 2 is aircraft flap adjustment amount schematic diagram
Wherein: 1. control wheels deflect θ angle, 2. wing flap adjustment amount L, 3. ailerons (wing flap adjustment reference data), 4. wing flaps.
Specific embodiment
It elaborates with reference to the accompanying drawing to the present invention:
A kind of multiple whirlpool paddle aircraft yaw, when breakking away wing flap adjustment amount calculation method, comprising:
Step 1 obtains control wheel deflection angle θ and deflection direction；
When control wheel deflection angle θ and deflection direction are according to breakking away, yawing, pilot is to guarantee that aircraft is flat to fly, and passes through behaviour Vertical control wheel amendment is breakked away, yaw angle obtains.
Step 2, according to formulaWing flap adjustment numerical quantity L, the K is calculated as wing flap adjustment Coefficient；
The K passes through the wing section lift coefficient and the flap of control wheel deflection angle, the area of aileron and wing flap, aileron and wing flap The length of the wing obtains.Preferably, 1430.66 K.
Step 3, the deflection direction according to control wheel, obtain wing flap adjustment amount L and adjustment direction.
There are three types of the implementations of step 3:
First way:
When driving, which is faced left, plays disk, left side wing flap shortens L/2 and right side wing flap along course and extends L/2 against course, when driving When sailing the disk right side and beating, left side wing flap against course extends L/2 and right side wing flap along course shortens L/2.
The second way:
When driving, which is faced left, plays disk, left side wing flap shortens L along course, and when the control wheel right side is beaten, right side wing flap contracts along course Short L.
The third mode:
When driving, which is faced left, plays disk, right side wing flap extends L against course, and when the control wheel right side is beaten, left side wing flap is stretched against course Long L.
Step 4 is adjusted wing flap by calculated value.
Embodiment
As shown in Figure 1, 2, a kind of multiple whirlpool paddle aircraft yaw, break away when wing flap adjustment amount algorithm, the side comprising aircraft Sliding angle 1, wing flap adjustment amount 2, aileron (wing flap adjustment reference data) 3, wing flap 4.
A kind of multiple whirlpool paddle aircraft yaw, the algorithm of aileron adjustment amount includes control wheel deflection angle θ and deflection when breakking away The judgement in direction 1, wing flap adjustment amount L numerical value 2, aileron (wing flap adjustment reference data) 3, wing flap 4, wing flap adjustment direction.
When the first step is according to breakking away, yawing, after pilot is by deflecting 6 ° of control wheel θ angle to the left, guarantee that aircraft is flat winged.
Second step is according to formulaIt is 2 ㎜ that wing flap adjustment numerical quantity L, which is calculated,.
Third step turns control wheel according to left avertence, and determining that left side wing flap shortens the numerical value of L is 2 ㎜ or right side wing flap elongation L Numerical value is 2 ㎜.

Claims (8)

1. the calculation method of wing flap adjustment amount when a kind of multiple whirlpool paddle aircraft yaw, sideslip characterized by comprising
Step 1 obtains control wheel deflection angle θ and deflection direction；
Step 2, according to formulaIt is wing flap adjustment system that wing flap adjustment numerical quantity L, the K, which is calculated, Number；
Step 3, the deflection direction according to control wheel, obtain wing flap adjustment amount L and adjustment direction.
2. the calculation method of wing flap adjustment amount, feature when a kind of multiple whirlpool paddle aircraft yaw as described in claim 1, sideslip It is, in step 1, when control wheel deflection angle θ and deflection direction are according to breakking away, yawing, pilot is to guarantee that aircraft is flat to fly, logical Cross manipulation control wheel amendment sideslip, yaw angle obtains.
3. the calculation method of wing flap adjustment amount, feature when a kind of multiple whirlpool paddle aircraft yaw as described in claim 1, sideslip It is, K 1430.66.
4. the calculation method of wing flap adjustment amount, feature when a kind of multiple whirlpool paddle aircraft yaw as claimed in claim 3, sideslip It is, the K passes through the wing section lift coefficient and wing flap of control wheel deflection angle, the area of aileron and wing flap, aileron and wing flap Length obtain.
5. the calculation method of wing flap adjustment amount, feature when a kind of multiple whirlpool paddle aircraft yaw as described in claim 1, sideslip It is, step 3 specifically:
When driving, which is faced left, plays disk, left side wing flap shortens L/2 along course and right side wing flap is against course elongation L/2, works as control wheel When the right side is beaten, left side wing flap extends L/2 against course and right side wing flap is along course shortening L/2.
6. the calculation method of wing flap adjustment amount, feature when a kind of multiple whirlpool paddle aircraft yaw as described in claim 1, sideslip It is, step 3 specifically:
When driving, which is faced left, plays disk, left side wing flap shortens L along course, and when the control wheel right side is beaten, right side wing flap shortens L along course.
7. the calculation method of wing flap adjustment amount, feature when a kind of multiple whirlpool paddle aircraft yaw as described in claim 1, sideslip It is, step 3 specifically:
When driving, which is faced left, plays disk, right side wing flap extends L against course, and when the control wheel right side is beaten, left side wing flap extends L against course.
8. the calculation method of wing flap adjustment amount, feature when a kind of multiple whirlpool paddle aircraft yaw as described in claim 1, sideslip It is, further includes:
Step 4 is adjusted wing flap by calculated value.
CN201910456936.8A 2019-05-29 2019-05-29 Method for calculating flap adjustment amount of multi-engine turboprop aircraft during yawing and sideslip Active CN110239737B (en)

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CN201910456936.8A CN110239737B (en) 2019-05-29 2019-05-29 Method for calculating flap adjustment amount of multi-engine turboprop aircraft during yawing and sideslip

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH246879A (en) * 1943-01-07 1947-01-31 Air Equipement Device for controlling the correction aileron on board aerodynes.
WO1989006411A1 (en) * 1988-01-11 1989-07-13 Sundstrand Data Control, Inc. Wind shear detection system
RU1839845C (en) * 1965-12-27 2006-05-27 Федеральное государственное унитарное предпри тие"Центральный аэрогидродинамический институт им.проф. Н.Е.Жуковского" (ФГУП "ЦАГИ") Device for enhancing controllability and stability of winged and finned flying vehicles at high flying speed
CN102365202A (en) * 2009-03-27 2012-02-29 空中客车营运有限公司 Aerofoil comprising a high lift flap
CN103332288A (en) * 2013-06-13 2013-10-02 西北工业大学 Edge strip at trailing edge of airplane and design method thereof
CN105676853A (en) * 2016-01-15 2016-06-15 中国人民解放军国防科学技术大学 Flight control method automatically adjusting neutral position of unmanned aerial vehicle
CN109515737A (en) * 2018-03-16 2019-03-26 陕西飞机工业（集团）有限公司 A kind of plane airfoil balancing device

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH246879A (en) * 1943-01-07 1947-01-31 Air Equipement Device for controlling the correction aileron on board aerodynes.
RU1839845C (en) * 1965-12-27 2006-05-27 Федеральное государственное унитарное предпри тие"Центральный аэрогидродинамический институт им.проф. Н.Е.Жуковского" (ФГУП "ЦАГИ") Device for enhancing controllability and stability of winged and finned flying vehicles at high flying speed
WO1989006411A1 (en) * 1988-01-11 1989-07-13 Sundstrand Data Control, Inc. Wind shear detection system
CN102365202A (en) * 2009-03-27 2012-02-29 空中客车营运有限公司 Aerofoil comprising a high lift flap
CN103332288A (en) * 2013-06-13 2013-10-02 西北工业大学 Edge strip at trailing edge of airplane and design method thereof
CN105676853A (en) * 2016-01-15 2016-06-15 中国人民解放军国防科学技术大学 Flight control method automatically adjusting neutral position of unmanned aerial vehicle
CN109515737A (en) * 2018-03-16 2019-03-26 陕西飞机工业（集团）有限公司 A kind of plane airfoil balancing device

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