CN103593515B - A kind of load design method of pylon of aircraft - Google Patents
A kind of load design method of pylon of aircraft Download PDFInfo
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- CN103593515B CN103593515B CN201310526789.XA CN201310526789A CN103593515B CN 103593515 B CN103593515 B CN 103593515B CN 201310526789 A CN201310526789 A CN 201310526789A CN 103593515 B CN103593515 B CN 103593515B
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Abstract
A kind of load design method of pylon of aircraft (1) determines hanger loads typical operating mode, calculates the aerodynamic loading of aircraft under each operating mode, and obtains the inertial load of aircraft under each operating mode according to the flight characteristics of helicopter；(2) stabilising arrangement and the maneuvering load of connection member thereof are calculated；(3) set up hanger integral finite element analysis model, calculate the maneuvering load of each ingredient of hanger；(4) maneuvering load of anti-sway retainer and hanger is calculated；(5) the bigger maneuvering load of anti-sway retainer and hanger is taken in step (3), (4) respectively as anti-sway retainer and the maneuvering load of hanger；(6) 0.1 0.3 times of preloading as anti-sway retainer of the anti-sway retainer maneuvering load that upper step is determined；This preloads with anti-sway retainer maneuvering load sum as the full payload of anti-sway retainer；(7) using the pulling force that determines in hanger maneuvering load as the maneuvering load of blasting bolt, surplus load is as the maneuvering load of hanger box.
Description
Technical field
Take helicopter high-speed flight for aircraft by special hanger and carry out relevant flight test, this
The bright a kind of load design method providing hanger.
Background technology
At present, the carrier aircraft platform flying to use hung by domestic air-supported vehicle is all fixed-wing carrier aircraft, and hanging rack structure can
By standard application, load design method can be according to Airborne suspension equipment junction universal design criterion.Go straight up to
When carrying transport heavy goods outside machine fuselage, typically with relatively low velocity low altitude flight, usual code requirement is specified
Single-point or Mulit-point Connection, this connection scheme power transmission is clear, load is prone to analyze and design.With the former two
Difference, aircraft select helicopter as carrier aircraft platform, obtain after certain flight speed and flying height with
Helicopter separates, and the hanger used is a kind of new construction scheme, as it is shown in figure 1, include universal joint 6,5
Root cable wire 1, main steel frame 2, hanger (being made up of hanger box and blasting bolt), anti-sway retainer and stable dress
Put in 3(figure 301 for stabilising arrangement junction point) etc. assembly, 5 cable wire one end universal-joints respectively are not
With suspension ring hole, the other end is connected on main steel frame difference pole；Again by a central steel with certain length
Universal joint is connected by rope 12 with helicopter 11；Below by 2 hangers and 4 anti-sway retainers and flight
Device 13 is connected；Main steel frame rear one stabilising arrangement of connection is to ensure aircraft course stability, when going straight up to
When machine flight is to specified window, detonate blasting bolt, and aircraft separates with hanger.
The load design of this hanger standard, specification and literature supply at home there is no clear stipulaties bar
Civilian and referential method for designing, also lacks correlation test data, therefore, Bracket loading because hanger is novel
The correctness of method for designing is to hanging rack structure design and to ensure that aircraft safe and reliable has suitable important
Property.
Summary of the invention
The technology of the present invention solves problem: overcome the deficiencies in the prior art, for different zero of different operating modes
Part, effectively integrated element method, engineering calculating method and experimental study consider reliability requirement, shape
Become a kind of load design method of pylon of aircraft, for the load of hanger main parts size in accurate design objective section
Lotus situation provides analysis means.
The technical solution of the present invention is: a kind of load design method of pylon of aircraft, adaptation of methods ring
Border is to carry aircraft by hanger below helicopter, described hanger include cable wire, main steel frame, anti-sway only
Dynamic device, hanger and universal joint；Wherein hanger includes hanger box and is arranged on the blasting bolt within hanger box；
The stabilising arrangement attitude with stabilized flight device is installed at main steel frame rear；Step is as follows:
(1) determine hanger loads typical operating mode, calculate the aerodynamic loading of aircraft under each operating mode, and according to
The flight characteristics of helicopter obtains the inertial load of aircraft under each operating mode；
(2) the loads typical operating mode determined according to (1st) step and stabilising arrangement characteristic, calculate stabilising arrangement
And the maneuvering load of connection member；
(3) hanger integral finite element analysis model is set up, the loads typical operating mode determined according to step (1),
Under corresponding operating mode, the maneuvering load that step (2) calculates is applied to the junction of hanger and stabilising arrangement,
The aerodynamic loading that step (1) calculated, inertial load are carried in the centroid position of aircraft；Each according to hanger
The stressing conditions of ingredient and the transmission characteristic of power, calculate the maneuvering load of each ingredient of hanger；
(4) according to engineering calculation formulas, the maneuvering load of anti-sway retainer and hanger is calculated；
(5) the bigger maneuvering load of anti-sway retainer and hanger is taken in step (3), (4) respectively as anti-sway
Retainer and the maneuvering load of hanger；
(6) 0.1-0.3 times of the anti-sway retainer maneuvering load determined in step (5) is stopped as anti-sway
Preloading of dynamic device；This preloads with the anti-sway retainer maneuvering load sum that determines in step (5) as anti-
The full payload of pendulum retainer；
(7) step (5) will determine the maneuvering load as blasting bolt of the pulling force in hanger maneuvering load,
Surplus load is as the maneuvering load of hanger box.
The maneuvering load of described cable wire improves 0.5-1 times on the basis of step (3) value of calculation；Universal joint
Maneuvering load takes the maneuvering load of cable wire.
The maneuvering load of described main steel frame is on the basis of step (3) value of calculation, after improving according to cable wire
In maneuvering load and step (6), in the full payload of anti-sway retainer, step (7), the use of hanger box carries
Lotus re-starts force analysis and determines maneuvering load.
The present invention compared with prior art has the beneficial effect that
(1) present invention overcomes helicopter extension to fly in the design of aircraft Bracket loading without design standard, specification and ginseng
The difficult problem examined, for the hanger being made up of cable wire, blasting bolt formula Novel lifting lugs structure and anti-sway retainer etc.,
Integrated element method, engineering calculating method and experimental study consider reliability requirement effectively, forms one
Plant load design method of pylon of aircraft, for the load feelings of hanger main parts size in accurate design objective section
Condition provides analysis means.
(2) present invention describes suspension hanger bearing mechanism from system-level and structural detail different aspects, overcomes
Finite element modeling difficult point, uses Coupled Rigid-flexible modeling analysis technology, establishes system-level analysis model.And
Design and control problem for preloading of " only putting device-main steel frame-hanger " complicated Path of Force Transfer, propose pre-
The solution that load preset value and experimental study combine, provides thinking for analog structure load design.
Accompanying drawing explanation
Fig. 1 helicopter is hung and is flown the signal of aircraft hanger；
Fig. 2 is flow chart of the present invention；
Fig. 3 is hanging rack structure of the present invention and main parts size；
Fig. 4 is hanger of the present invention and aircraft FEM (finite element) model.
Detailed description of the invention
A kind of aircraft Bracket loading design cycle as shown in Figure 2, below according to this design process to this
Bright realization is described in detail.
(1) determine hanger loads typical operating mode, calculate the aerodynamic loading of aircraft under each operating mode, and according to
The flight characteristics of helicopter obtains the inertial load of aircraft under each operating mode；
Climb for helicopter/hanger/aircraft assembly in lifting, acceleration, turn, throw in window, mooring
The different situations such as return, determine lifting, accelerate to climb and three typical conditions of high speed straight and level flight.Each operating mode
Aerodynamic load of aerobat at present conventional CFD numerical algorithm can be used to calculate；The inertia of each operating mode
Determine according to Helicopter flight performance, as when helicopter lifts by crane, normal g-load coefficient is 2.0-2.5, accelerate to climb
Time, normal g-load coefficient is 1.1-1.5, course overload factor 0.3 etc., and inertial load is overload factor and fly
Row thinks highly of the product of power, typically takes higher value.
(2) the loads typical operating mode determined according to (1st) step and stabilising arrangement characteristic, calculate stabilising arrangement
And the maneuvering load of connection member；
By (1st) step load working condition, select differing heights, friction speed parameter, stabilising arrangement and connection thereof
The load of parts is given by,
In formula: S is the drag area of stabilising arrangement, v is flight speed, and ρ is atmospheric density.
During lifting, flight speed is 0, stabilising arrangement no-load, selects acceleration to climb and high speed straight and level flight two
Under individual operating mode, maximum load is the maneuvering load of stabilising arrangement and connection member thereof.
(3) hanger integral finite element analysis model is set up, the loads typical operating mode determined according to step (1),
Under corresponding operating mode, the maneuvering load that step (2) calculates is applied to the junction of hanger and stabilising arrangement,
The aerodynamic loading that step (1) calculated, inertial load are carried in the centroid position of aircraft；Each according to hanger
The stressing conditions of ingredient and the transmission characteristic of power, calculate the maneuvering load of each ingredient of hanger；
Hanger integral finite element analysis model belongs to Rigid-flexible Coupling Dynamics Analysis model, and its foundation to consider to hang
Ear 5, anti-sway retainer 4, main steel frame 2, the mechanical characteristic of cable wire 1 and Path of Force Transfer, such as Fig. 3, including:
Blasting bolt is subjected only to pulling force, and hanger box bears two-way shearing and pressure, cable wire tension not pressurized, anti-sway only
Dynamic device pressurized not tension, main steel frame rod member bears space three-dimensional power and moment etc..Finite element analysis can use business
Industry software part, such as ABAQUS, ANSYS, the model of foundation is as shown in Figure 4.
Method for solving may select static method, dynamic solving method, and different method for solving are it needs to be determined that suitably
Boundary condition or initial condition.By three kinds of load working conditions of (1st) step and inertial load thereof and aerodynamic loading conduct
The initial conditions of finite element analysis model, solves and can obtain cable wire, hanger, blasting bolt, anti-sway stop
The effect to main steel frame of the parts such as device.
(4) according to engineering calculation formulas, the maneuvering load of anti-sway retainer and hanger is calculated；
Above-mentioned engineering calculation formulas can refer to document, such as " MIL-A-8591E ".Give with (1st) step
The aerodynamic loading and the inertial load that go out three kinds of operating modes are initial conditions, calculate hanger and the use of anti-sway retainer
Load.
(5) maximum load situation is selected, as hanger according to the result of calculation of (3rd) step and (4th) step
Maneuvering load with anti-sway retainer.
(6) 0.1-0.3 times of the anti-sway retainer maneuvering load determined in step (5) is stopped as anti-sway
Preloading of dynamic device；This preloads with the anti-sway retainer maneuvering load sum that determines in step (5) as anti-
The full payload of pendulum retainer；
For ensureing hanger and the integral rigidity of aircraft in-flight, reduce anti-sway stopping in flight test and put device and fly
The clearance impact of row device, improves hanger and the mechanical environment of aircraft instrument and equipment, the blasting bolt of hanger with
Anti-sway retainer is intended to apply certain pretightning force.Preloading requirement is: under normal flight operating mode, anti-sway only
Dynamic device is not kept completely separate with the contact surface of body parts with aircraft surface, hanger hanger box.Preload
The technological difficulties of design are that pretightning force size is closely related with factors, such as hanger, flight with lax control
The rigidity of the rigidity of structure of device and intensity, hanger and anti-sway retainer and intensity, mounting process etc..
At the beginning of preloading design, the initial conditions of hanging rack structure rigidity information does not possesses, and needs certain warp
Test and determine, 0.1-0.3 times of preloading as anti-sway retainer of desirable anti-sway retainer maneuvering load, after
After phase product first sample possesses, need to use experimental study to carry out load and hanging rack structure correction.
(7) step (5) will determine the maneuvering load as blasting bolt of the pulling force in hanger maneuvering load,
Can be selected for blasting bolt model according to maneuvering load, remaining sharing part of the load is as the maneuvering load of hanger box.
Consider that part cable wire lost efficacy or only part cable wire of a certain power moment bears the situation of load, making of cable wire
Can improve 0.5-1 times on the basis of step (3) value of calculation by load, namely cable wire maneuvering load takes
1.5-2 times of step (3) value of calculation；Cable wire retroaction is universal joint load, the maneuvering load of universal joint
Value takes the maneuvering load value of cable wire.
The maneuvering load of main steel frame is corrected due to the maneuvering load of above-mentioned parts, it is therefore desirable to again enter
Row analyze, namely on the basis of step (3) value of calculation, according to cable wire improve after maneuvering load and
In step (6), in the full payload of anti-sway retainer, step (7), the maneuvering load of hanger box re-starts and is subject to
Power analysis determines the maneuvering load of the local rod member being connected on main steel frame with cable wire, anti-sway retainer.
Embodiment
Take as a example by helicopter makes a flight test by certain aircraft, the connection side of aircraft-hanger-helicopter
Formula is as it is shown in figure 1, its hanging rack structure scheme is as in figure 2 it is shown, application the inventive method carries out Bracket loading and sets
Meter.
1. determine load working condition, calculate the aerodynamic loading under each operating mode and inertial load.
According to overall plan, mission profile, control requirement, the ability of stabilising arrangement (umbrella), go straight up to function
The input file such as power and flight envelope, it is determined that 3 kinds of typical conditions.
Table 1 helicopter is hung and is flown to throw in the description of certain aircraft operating mode
| Operating mode is numbered | Operating mode describes |
| 1 | Lifting, normal g-load 2.5g, transverse acceleration 1.0g, course overload 1.0g |
| 2 | Acceleration is climbed, normal g-load 1.5g, course overload 0.3g, transverse acceleration 0.8g |
| 3 | High speed straight and level flight, normal g-load 1.1g |
For operating mode 3, by CFD numerical computations can obtain aerodynamic force at aircraft barycenter, aerodynamic moment and
Coefficient, is shown in Table 2, and in table, Fx, Fy, Fz, Mx, My and Mz are full flight vehicle aerodynamic power and moment phase
Power and moment for aircraft barycenter.The aerodynamic loading of operating mode 2 calculates process with operating mode 3.
Aerodynamic force, moment and coefficient thereof under certain state of flight of table 2
| Aerodynamic Coefficient | cx | cy | cz | cmx | cmy | cmz |
| Numerical value | 0.093454 | -0.05502471 | 0.67068975 | 0.00938299 | 0.024479724 | 0.077703538 |
| Aerodynamic force, moment | Fx/N | Fy/N | Fz/N | Mx/Nm | My/Nm | Mz/Nm |
| Numerical value | 554.7 | -326.6 | 3981.2 | 534.7 | 1394.9 | 4427.7 |
Inertial load is the product of helicopter overload factor and aircraft gravity, and as a example by operating mode 1, three-dimensional is used to
Property load is respectively as follows: course ± 32.4kN, normal direction 82.2kN, transverse load ± 32.4kN.Positive negative indication
Forward and backward and left and right.
2. stabilising arrangement and connection load design thereof
When surface temperature is 15 degree, atmospheric density is about 0.78kg/m3, the speed of a ship or plane is 45～50m/s, it is considered to
Flexible characteristic to wind speed and stabilising arrangement affects, and the drag area of stabilising arrangement is about 5.18～5.86m2,
The then resistance of drogue:
V=45m/s, 4091N≤F≤4628N ... ... ... ... (2)
V=50m/s, 5051N≤F≤5714N ... ... ... ... (3)
To sum up, stabilising arrangement range of resistance:
4091N≤F≤5714N ... ... ... ... ... ... (4)
Stabilising arrangement and the load of connection thereof, also need to consider the dynamic load effect of 1.2.
3. hanger modeling and loading analysis
Hanging rack structure models, and ignores each component junction point detail characteristic, and component builds beam element with axis, pipe with
Pipe directly intersects.Anti-sway retainer use bar unit and this unit material performance can only pressurized can not tension.Quick-fried
Fried bolt strut and tie unit；Hanger course shear behavior, by arranging that along course bar unit is simulated, laterally resists
Cutting performance to pass through respectively to arrange that a bar unit is simulated along z to the hanger front and back, bar unit is connected to install
Little quality steel arm in steelframe.Cable wire selects only to bear the cable elements of power, and cable wire unit converges (should
Point represents universal joint).The finite element analysis model of whole system is as shown in Figure 4.
The situation of operating mode 1 is the most serious, is analyzed it.Inertial load is applied at aircraft barycenter,
Do static analysis.By analysis, cable wire load can be obtained, as shown in the table:
Table 3 operating mode 3 cable wire load condition
| Title | Model load situation |
| Cable wire 1 pulling force | 21.85kN, universal joint junction point is pointed to from junction point 1 in direction |
| Cable wire 2 pulling force | 21.85kN, universal joint junction point is pointed to from junction point 2 in direction |
| Cable wire 3 pulling force | 30.25kN, universal joint junction point is pointed to from junction point 3 in direction |
| Cable wire 4 pulling force | 30.25kN, universal joint junction point is pointed to from junction point 4 in direction |
| Cable wire 5 pulling force | 3.8kN, universal joint junction point is pointed to from junction point 5 in direction |
Hanger load is 47.3kN；Because of rigid motion, under final poised state, anti-sway retainer does not stresses.
4 follow-up hangers and anti-sway retainer, universal joint, cable wire, blasting bolt, the load of main steel frame set
Meter calculates according to the step of above-mentioned introduction, may finally form aircraft Bracket loading file, and utilizing should
File is follow-up just can carry out structure detailed design and strength check to hanger.Empirical tests the inventive method can expire
Foot aerial mission requirement.
The present invention is unspecified partly belongs to general knowledge as well known to those skilled in the art.
Claims (3)
1. a load design method of pylon of aircraft, adaptation of methods environment is to pass through hanger below helicopter
Carrying aircraft, described hanger includes cable wire, main steel frame, anti-sway retainer, hanger and universal joint；Its
Middle hanger includes hanger box and is arranged on the blasting bolt within hanger box；Stable dress is installed at main steel frame rear
Put with the attitude of stabilized flight device；It is characterized in that method step is as follows:
(1) determine hanger loads typical operating mode, calculate the aerodynamic loading of aircraft under each operating mode, and according to
The flight characteristics of helicopter obtains the inertial load of aircraft under each operating mode；Described loads typical operating mode includes
Lifting, acceleration are climbed and high speed straight and level flight；
(2) the loads typical operating mode determined according to (1st) step and stabilising arrangement characteristic, calculate stabilising arrangement
And the maneuvering load of connection member；
(3) hanger integral finite element analysis model is set up, the loads typical operating mode determined according to step (1),
Under corresponding operating mode, the maneuvering load that step (2) calculates is applied to the junction of hanger and stabilising arrangement,
The aerodynamic loading that step (1) calculated, inertial load are carried in the centroid position of aircraft；Each according to hanger
The stressing conditions of ingredient and the transmission characteristic of power, calculate the maneuvering load of each ingredient of hanger；
(4) according to engineering calculation formulas, the maneuvering load of anti-sway retainer and hanger is calculated；
(5) higher value of anti-sway retainer and hanger maneuvering load is taken in step (3), (4) respectively as anti-
Pendulum retainer and the maneuvering load of hanger；
(6) 0.1-0.3 times of the anti-sway retainer maneuvering load determined in step (5) is stopped as anti-sway
Preloading of dynamic device；This preloads with the anti-sway retainer maneuvering load sum that determines in step (5) as anti-
The full payload of pendulum retainer；
(7) step (5) will determine the maneuvering load as blasting bolt of the pulling force in hanger maneuvering load,
Surplus load is as the maneuvering load of hanger box.
A kind of load design method of pylon of aircraft the most according to claim 1, it is characterised in that: institute
The maneuvering load stating cable wire improves 0.5-1 times on the basis of step (3) value of calculation；The use of universal joint carries
Lotus takes the maneuvering load of cable wire.
A kind of load design method of pylon of aircraft the most according to claim 2, it is characterised in that: institute
The maneuvering load of the main steel frame stated is on the basis of step (3) value of calculation, and the use after improving according to cable wire carries
In lotus and step (6), in the full payload of anti-sway retainer, step (7), the maneuvering load of hanger box is again
Carry out force analysis and determine maneuvering load.
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| CN103995955B (en) * | 2014-04-17 | 2017-03-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of analysis method of the plug-in attachment structure bearing capacity of aircraft |
| CN104075868B (en) * | 2014-05-30 | 2017-02-22 | 西北工业大学 | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system |
| CN107679267B (en) * | 2017-08-22 | 2021-02-02 | 合科软件（北京）有限责任公司 | Helicopter mooring load determining method and device and electronic equipment |
| CN110543687A (en) * | 2019-08-02 | 2019-12-06 | 西安飞机工业（集团）有限责任公司 | airplane load design method |
| CN112364494B (en) * | 2020-10-30 | 2024-04-09 | 中国运载火箭技术研究院 | Method for calculating hanging load and checking strength of plane-symmetric aircraft |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103324778A (en) * | 2013-01-05 | 2013-09-25 | 中国航空工业集团公司西安飞机设计研究所 | Ground load determination method of multi-fulcrum airplane |
| CN103350754A (en) * | 2013-07-12 | 2013-10-16 | 大连理工大学 | Pneumatic feeding device for externally-hung load |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2009130690A2 (en) * | 2008-04-23 | 2009-10-29 | Cyclone Aviation Products Ltd. | Ejectable pylon for airborne payloads |
-
2013
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103324778A (en) * | 2013-01-05 | 2013-09-25 | 中国航空工业集团公司西安飞机设计研究所 | Ground load determination method of multi-fulcrum airplane |
| CN103350754A (en) * | 2013-07-12 | 2013-10-16 | 大连理工大学 | Pneumatic feeding device for externally-hung load |
Non-Patent Citations (1)
| Title |
|---|
| 导弹挂架载荷标定试验与模型求解;周福强等;《机械强度》;20090415;第221-224页 * |
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