CN109387357A - A kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings and method - Google Patents
A kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings and method Download PDFInfo
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- CN109387357A CN109387357A CN201811301503.7A CN201811301503A CN109387357A CN 109387357 A CN109387357 A CN 109387357A CN 201811301503 A CN201811301503 A CN 201811301503A CN 109387357 A CN109387357 A CN 109387357A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0041—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining deflection or stress
- G01M5/005—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining deflection or stress by means of external apparatus, e.g. test benches or portable test systems
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Abstract
The invention discloses a kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings and methods, are related to field of aerospace technology.The device includes the first stationary plane, the second stationary plane, crossbeam, load screw rod, the load lever system formed by multi-grade lever and loading blocks；First stationary plane and the second stationary plane are oppositely arranged, and crossbeam is fixedly connected between two stationary planes；The first fixed block and the second fixed block are provided on first stationary plane, for missile wing to be fixed on the first stationary plane；It loads screw rod and runs through crossbeam, load primary lever of the lower end of screw rod into load lever system and apply full payload, the both ends for loading each final stage lever in lever system are located at each load in loading blocks and apply at the position of point；Loading blocks are located at the top of missile wing, and match with the shape of missile wing.The device applies load by simple screw-rod structure, can continuously be loaded, and structure is simple, and loading method simulation quality is high.
Description
Technical field
The present invention relates to field of aerospace technology, in particular to a kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings
And method.
Background technique
Missile wing provides lift for missile flight, and in flight course, missile wing will receive aerodynamic loading effect.To guarantee flight peace
It is complete and stable, there are corresponding requirements to missile wing strength and stiffness, missile wing slow test is vital verifying means, passes through fixation
Faying face applies respective loads on aerofoil to obtain the strength and stiffness characteristic of missile wing, determines whether to meet flight and requires.
In existing research technique, aerodynamic loading suffered by missile wing is obtained according to wind tunnel test or software for calculation, in conjunction with
Simple power and torque equivalent relation obtain the load at load(ing) point and load(ing) point, in order to slow test load, this kind of mode
There may be bigger differences for the aerodynamic loading that the load distribution of acquisition is obtained with wind tunnel test or software for calculation, generate to missile wing
Deformation effect is different；Also, from experimental rig, existing loading method is usually that hydraulic loaded or suspension load, the former
Structure is complicated, and equipment is expensive, and professional person is needed to operate, and the latter loads and unloads trouble, is difficult continuously to load, and be easy to produce
Impact, causes equipment damage, and existing loading method is usually local loading, generated aerodynamic loading is in flight course
Face power, the two have bigger difference.
Summary of the invention
The purpose of the present invention is to provide a kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings and method, load distribution is more quasi-
Really, loading method simulation quality is higher, and the deformation of missile wing is more nearly live flying state, and can continuously be loaded.
In a first aspect, the present invention provides a kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings, including it is the first stationary plane, second solid
Determine face, crossbeam, load screw rod, the load lever system formed by multi-grade lever and loading blocks；First stationary plane and described
Second stationary plane is oppositely arranged, and the crossbeam is fixedly connected between two stationary planes and the beam vertical is in the first stationary plane
With the second stationary plane；The first fixed block and the second fixed block in same horizontal line are provided on first stationary plane,
First fixed block and second fixed block are used to missile wing being fixed on first stationary plane；The load screw rod passes through
The crossbeam is worn, primary lever of the lower end of the load screw rod into load lever system applies full payload, the load thick stick
The both ends of each final stage lever are located at each load in loading blocks and apply at the position of point in lever system；The loading blocks are located at institute
The top of missile wing is stated, and is matched with the shape of the missile wing.
Optionally, the crossbeam is two I-beams, and the edge of a wing of two I-beams is located in same level, and two works
The distance that the load screw rod may pass through is reserved between word beam.
Optionally, be further fixedly arranged on load seat on the top flange of two I-beams, the load seat offer with it is described
Load the compatible threaded hole of screw flight；The load screw rod runs through the load seat.
Optionally, rubber pad is equipped between the loading blocks and the missile wing, for keeping the power transmission of loading blocks more uniform.
Optionally, it is equipped with sensor in the lower end of the load screw rod, is applied to level-one for measuring the load screw rod
Full payload on lever.
Optionally, it is additionally provided with force transfer ball in the lower end of the load screw rod, the force transfer ball is located at the lower end of load screw rod
Between sensor, the force transfer ball is round shape.
Optionally, the upper end of the load screw rod is rectangular or hexagon.
Second aspect, the present invention provides a kind of missile wing aerodynamic loading simulation loading method, applied to described in first aspect
Device, comprising:
Determine that the aerodynamic loading distribution of missile wing, the aerodynamic loading distribution include the pressure of each face element in missile wing surface
Power；
According to the pressure of each face element in missile wing surface, aerofoil lift and the aerofoil pressure heart position of the missile wing are obtained；
The aerofoil of the missile wing is divided into several piecemeals, is determined according to the centroid of each piecemeal to loading blocks and applies load
Load lever system in each load where each final stage lever both ends apply the position of point；
According to the aerofoil lift, aerofoil pressure heart position and least strain energy principle, determine that each load applies point
Load.
Optionally, described according to the aerofoil lift, aerofoil pressure heart position and least strain energy principle, it determines each
Load applies the load of point, comprising:
The first equation group is obtained according to the equilibrium relation of power and torque, first equation group is
Wherein, L is aerofoil lift, xL、yLThe coordinate of heart position is pressed for aerofoil, n is the quantity that load applies point, LiIt is each
Load applies the load of point, xi、yiApply the coordinate of point, i=1,2,3 ..., n for each load；And
Virtual beam deformation between pressing heart position and each load to apply point according to the aerofoil can U and Lagrange multiplier
Method establishes extremal function F (λ, λx,λy),
Wherein, EI is the bending stiffness of virtual beam, liApply the virtual beam that point presses heart position to be formed with aerofoil for each load
Length；And second equation group is obtained, the second equation group is
The load L for obtaining each load and applying point is calculated according to first equation group and the second equation groupi。
Optionally, the aerodynamic loading distribution of the determining missile wing, comprising: it is every that the missile wing surface is obtained by wind tunnel test
The pressure of one face element.
Compared with the prior art, a kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings provided by the invention, passes through simple screw rod
Structure applies load, can continuously be loaded and be unloaded, and structure is simple, also, passes through simulation missile wing and rocket body or arrow completely
The connection type of body, preferably missile wing deformation under reaction time of day, also, each load is applied into point by loading blocks
Concentrated force is separated into face power, makes missile wing force-bearing situation further to time of day, therefore the device has load distribution accurate,
Loading method simulation quality is high, and missile wing connection type simulation quality is high, the simple advantage of structure.Further, become using based on minimum
The distributed load calculated or wind tunnel test obtains is converted default load by the missile wing aerodynamic loading simulation loading method of shape energy principle
Load at lotus application makes load when test closer to practical flight load.
To enable the above objects, features and advantages of the present invention to be clearer and more comprehensible, alternative embodiment is cited below particularly, and cooperate
Appended attached drawing, is described in detail below.
Detailed description of the invention
It, below will be to use required in embodiment in order to illustrate more clearly of the technical solution of embodiment of the present invention
Attached drawing be briefly described, it should be understood that the following drawings illustrates only certain embodiments of the present invention, therefore is not to be seen as
It is the restriction to range, it for those of ordinary skill in the art, without creative efforts, can be with root
Other relevant attached drawings are obtained according to these attached drawings.
Fig. 1 shows On The Simulation Load Device For Aerodynamic Loads of Missile Wings main view provided by the present invention；
Fig. 2 shows On The Simulation Load Device For Aerodynamic Loads of Missile Wings axis side views provided by the present invention；
Fig. 3 shows the schematic diagram of loading blocks in On The Simulation Load Device For Aerodynamic Loads of Missile Wings of the present invention；
Fig. 4 shows the top view of On The Simulation Load Device For Aerodynamic Loads of Missile Wings provided by the present invention；
Fig. 5 is the schematic illustration that lever is loaded in On The Simulation Load Device For Aerodynamic Loads of Missile Wings of the present invention；
Fig. 6 is the flow chart of missile wing aerodynamic loading simulation loading method of the present invention.
Icon: the first stationary plane of 1-；The first fixed block of 2-；The second fixed block of 3-；4- crossbeam；5- loads seat；6- loads spiral shell
Bar；7- force transfer ball；8- sensor；9- loads lever system；10- loading blocks；The second stationary plane of 11-；12- rubber pad；13- bullet
The wing；901- first loads lever；902- second loads lever；903- third loads lever；904- the 4th loads lever；905-
Five load levers；906- the 6th loads lever；907- the 7th loads lever.
Specific embodiment
Below in conjunction with attached drawing in the embodiment of the present invention, technical solution in the embodiment of the present invention carries out clear, complete
Ground description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.Usually exist
The component of the embodiment of the present invention described and illustrated in attached drawing can be arranged and be designed with a variety of different configurations herein.Cause
This, is not intended to limit claimed invention to the detailed description of the embodiment of the present invention provided in the accompanying drawings below
Range, but it is merely representative of selected embodiment of the invention.Based on the embodiment of the present invention, those skilled in the art are not doing
Every other embodiment obtained under the premise of creative work out, shall fall within the protection scope of the present invention.
It should also be noted that similar label and letter indicate similar terms in following attached drawing, therefore, once a certain Xiang Yi
It is defined in a attached drawing, does not then need that it is further defined and explained in subsequent attached drawing.
In the description of the present invention, it should be noted that the instruction such as term " on ", "lower", "left", "right", "inner", "outside"
Orientation or positional relationship be based on the orientation or positional relationship shown in the drawings or the invention product using when usually put
Orientation or positional relationship, be merely for convenience of description of the present invention and simplification of the description, rather than the device of indication or suggestion meaning
Or element must have a particular orientation, be constructed and operated in a specific orientation, therefore be not considered as limiting the invention.
In the description of the present invention, it is also necessary to which explanation is unless specifically defined or limited otherwise, term " setting ",
" installation ", " connected ", " connection " shall be understood in a broad sense, for example, it may be fixedly connected, may be a detachable connection or one
Connect to body；It can be mechanical connection, be also possible to be electrically connected；It can be directly connected, it can also be indirect by intermediary
It is connected, can be the connection inside two elements.
In the description of the present invention, it is also necessary to explanation, herein, such as first and second or the like relationship art
Language is only used to distinguish one entity or operation from another entity or operation, without necessarily requiring or implying this
There are any actual relationship or orders between a little entities or operation.The terms such as term "horizontal", "vertical", " pendency "
It is not offered as requiring component abswolute level or pendency, but can be slightly tilted.As "horizontal" only refers to that its direction is opposite " perpendicular
It is more horizontal for directly ", it is not to indicate that the structure is had to fully horizontally, but can be slightly tilted.Term " includes ",
"comprising" or any other variant thereof is intended to cover non-exclusive inclusion so that include a series of elements process,
Method, article or equipment not only include those elements, but also including other elements that are not explicitly listed, or are also wrapped
It includes as elements inherent to such a process, method, article, or device.In the absence of more restrictions, by sentence " including
One ... " limit element, it is not excluded that there is also another in the process, method, article or apparatus that includes the element
Outer identical element.For the ordinary skill in the art, above-mentioned term can be understood in the present invention with concrete condition
Concrete meaning.
With reference to the accompanying drawing, it elaborates to some embodiments of the present invention.In the absence of conflict, following
Feature in embodiment and embodiment can be combined with each other.
First embodiment
Missile wing is to provide lift for missile flight, and in flight course, missile wing will receive aerodynamic loading effect, to guarantee to fly
Row is safe and stablizes, therefore has corresponding requirements to apply on aerofoil generally by fixed combinating surface the strength and stiffness of missile wing
Respective loads obtain the strength and stiffness characteristic of missile wing, determine whether missile wing meets flight and require.
Fig. 1 and Fig. 2 are please referred to, a kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings is present embodiments provided, which includes
First stationary plane 1, crossbeam 4, loads screw rod 6, the load lever system 9 formed by multi-grade lever and loads second stationary plane 11
Block 10.First stationary plane 1 and the second stationary plane 11 are oppositely arranged, and perpendicular to the ground, and it is fixed that crossbeam 4 is fixedly connected on first
Between face 1 and the second stationary plane 11, and perpendicular to the first stationary plane 1 and the second stationary plane 11；It is provided on the first stationary plane
The first fixed block 2 and the second fixed block 3 in same horizontal line, the first fixed block 2 and the second fixed block 3 can be by missile wings 13
It is fixed on the first stationary plane 1；Load lever system 9 is made of multi-grade lever, and load screw rod 6 runs through crossbeam 4, loads screw rod 6
Primary lever of the lower end into load lever system 9 apply full payload, load the both ends point of each final stage lever in lever system 9
Each load it Wei Yu not apply at the position of point in loading blocks 10；Loading blocks 10 are located at the top of missile wing 13, and the shape with missile wing 13
Shape matches.The axis side view of the analog loading device is shown in Fig. 2, and it is fixed to omit second in order to facilitate observation of, in Fig. 2
Face.
Specifically, the first stationary plane 1 and the second stationary plane 11 being oppositely arranged provide support for entire analog loading device,
In realistic simulation load test, the column being usually fixedly connected with the ground or the steel plate being fixedly connected with the column.Load
The full payload that 6 lower end of screw rod is transmitted carries out multistage transmitting by the multi-grade lever in load lever system, and multi-grade lever is by several
Lever composition is loaded, load distribution is carried out to full payload, each load where realizing each final stage lever both ends applies point to load
Block 10 applies load.Loading blocks 10 are located at 13 top of missile wing, and the concentrated force that each load in final stage lever both ends can be applied to point is converted
For uniform surface power, it is applied to missile wing, the shape of loading blocks 10 need to agree with completely with the shape of 13 aerofoil of missile wing.First stationary plane 1
It is equipped with the first fixed block 2 and the second fixed block 3, the first fixed block 2 is fixedly connected with the root of missile wing 13 with the second fixed block 3,
To which missile wing 13 is fixedly connected on the first stationary plane 1, it should be noted that missile wing root and the first fixed block 2, second are solid
The connection type of the connection type and practical missile wing and rocket body or body of determining block 3 is completely the same.
In the present embodiment, loading blocks 10 have greater stiffness, are made of, are illustrated in figure 3 wherein muti-piece independent metal block
A kind of composition form can convert uniform surface power for the concentrated force at each load distribution point, with 13 surface shape one of missile wing
It causes；The settable rubber pad 12 between loading blocks 10 and missile wing 13, for eliminating 10 He of loading blocks as caused by mismachining tolerance
The phenomenon that 13 surface of missile wing is not agreed with, so that power transmission is more uniform.
In the present embodiment, above-mentioned crossbeam 4 is made of two I-beams, and the web of two I-beams is oppositely arranged, and two
The edge of a wing of I-beam is located in same level, and a certain distance is reserved between two I-beams, and preset space should be big
In the diameter of load screw rod 6, load screw rod 6 is passed through among two I-beams.
In the present embodiment, it is fixedly installed load seat 5 on the top flange of two I-beams, loads and is equipped with outside screw rod 6
Screw thread, load seat 5 are equipped with threaded hole compatible with load screw rod 6；Screw rod 6 is loaded through load seat 5, and from two I-shapeds
The distance reserved between beam passes through.Optionally, the upper end for loading screw rod 6 is rectangular or hexagon, can be suitable by load spanner
Hour hands turn load screw rod 6 counterclockwise, and load screw rod 6 is moved under the action of loading the threaded hole of seat 5, to realize
Load or unload.
In the present embodiment, into load lever system 9, a certain location point transmits full payload to load screw rod 6 on primary lever,
The point of application in load screw rod lower end is provided with sensor 8, due to that need to be wanted according to predetermined load in aerodynamic loading simulation process
Setting is asked to be applied to the load of 13 aerofoil of missile wing, sensor 8 is located between load screw rod 6 and load lever system 9, can be real-time
Accurate measurement load screw rod is applied to the full payload on missile wing 13, can be according to sensing when continuously being loaded to load screw rod
The full payload adjustment load screw rod 6 that device 8 obtains reaches predetermined load and wants in the movement in downward direction or in upward direction
It asks.It is additionally provided with force transfer ball 7 in load screw rod lower end, is located between load screw rod lower end and sensor, can be a round steel ball,
During loading, there are relative motions between load screw rod and sensor, and therefore, the force transfer ball 7 being arranged between can
Keep load transmission more smooth, also, effectively avoid transmitting loading in have skidded or load be mutated the case where.
Load lever system is illustrated with Fig. 4, in the load lever system, including multiple load levers, specifically
Lever 902, second, which is loaded, for the first load lever 901, second loads lever 902, the third load load thick stick of lever the 903, the 4th
Bar the 904, the 5th loads lever the 905, the 6th and loads lever 906 and the 7th load lever 907, the 7th load formation of lever 907
Primary lever, load screw rod move downward, and act on a certain position between the 7th load 907 both ends of lever, to the 7th load thick stick
Apply full payload at the position of bar 907, the both ends of the 7th load lever 907 are fixedly connected on the 5th load lever the 905, the 6th and add
A certain position between the both ends of lever 906 is carried, the both ends of the 5th load lever 905 are fixedly connected on third load lever 903, the
The both ends of a certain position between the both ends of four load levers 904, the 6th load lever 906 are fixedly connected on the first load lever
901, a certain position between the second load 902 both ends of lever.5th load lever 905 and the 6th load lever 906 form two
Grade lever, the first load lever 901, second load lever 902, third load lever 903 and the 4th load formation of lever 904
Three-level lever, wherein three-level lever adds as the final stage lever in the load lever system, the first load lever 901, second
The both ends for carrying lever 902, third load lever 903 and the 4th load lever 904 are located at each load in loading blocks and apply point
At position, directly apply load to loading blocks.
Specifically, the determination for loading position of the fulcrum on any load lever in lever system can be according to lever principle and gas
The loading demands of dynamic loading simulation, the schematic illustration of load lever is shown in Fig. 5, by taking the 7th load lever 907 as an example, is added
It carries screw rod and is applied with power F in a certain position in the middle, resultant force F is decomposed into F1 and F2, the length of L1 and L2 is adjusted, meets condition
It is as follows:
F=F1+F2；
F1*L1=F2*L2；
When carrying out aerodynamic loading simulation loading, required to determine that each load for applying load to missile wing is applied according to predetermined load
The load added some points, that is, the load at each final stage lever both ends, each load lever loaded in lever system can be according to above-mentioned
Condition rationally determines its ratio L1/L2, so that the load that each load in final stage lever applies point is able to satisfy predetermined load
It is required that.
In conclusion being pulled when carrying out simulation loading by above-mentioned On The Simulation Load Device For Aerodynamic Loads of Missile Wings using load
Hand turns load screw rod, and between load screw rod and load seat under threaded connection effect, load screw rod is moved downward, and passes through biography
Power ball, can be according to the full payload size of sensor real-time display when turning load screw rod to the 7th load lever transmission full payload
Being adjusted to load screw rod makes it meet predetermined load requirement, and the full payload of load screw rod transmitting passes through the 7th load lever point
The both ends of the 7th load lever are fitted on, and are transmitted on the 5th load lever and the 6th load lever step by step, then transmit step by step
Onto the first load lever, the second load lever, third load lever, the 4th load lever, load is completed by multi-grade lever
Distribution, then applied the first load lever, the second load lever, third load lever, the 4th load lever both ends by loading blocks
The concentrated force added is converted into uniform surface power, acts on missile wing surface, completes load.After loading procedure, reversely turns and add
Screw rod is carried, load screw rod is moved upwards, completes unloading.
It is worth noting that, the quantity of several load levers is variable in load lever system, as long as can be realized more
Grade lever construction, will load the full payload that screw rod applies and carry out load distribution is the range that the present embodiment is protected, above-mentioned side
It is only one of which embodiment provided by the present embodiment described in case.
Second embodiment
A kind of missile wing aerodynamic loading simulation loading method is present embodiments provided, which can be applied to first
Device as described in the examples, in device in the first embodiment, the full payload that load screw rod applies passes through multiple load thick sticks
The load distribution of bar applies load from each final stage lever both ends to loading blocks, and concentrated force is converted to uniform surface power and applied by loading blocks
It is added in missile wing surface, completes simulation loading.Method in the present embodiment can be used for determining above-mentioned missile wing aerodynamic loading simulation loading
Load on device where each final stage lever both ends applies the load of point.Referring to Fig. 6, this method comprises:
S101: determine that the aerodynamic loading distribution of missile wing, aerodynamic loading distribution include the pressure of each face element in missile wing surface.
The aerodynamic loading distribution for obtaining missile wing is calculated by wind tunnel test, the distribution of this load is usually the every one side in missile wing surface
The pressure coefficient or pressure of member are needed pressure coefficient if obtaining the pressure coefficient of each face element multiplied by dynamic pressure and face element face
Product is translated into pressure.
S102: according to the pressure of each face element in missile wing surface, aerofoil lift and the aerofoil pressure heart position of missile wing are obtained.
The pressure of all face elements is summed, obtains aerofoil lift, and aerofoil is obtained by the shifting theorem of power and presses the heart
Position.
S103: being divided into several piecemeals for the aerofoil of missile wing, is determined according to the centroid of each piecemeal to loading blocks and applies load
Each load in the load lever system of lotus where each final stage lever both ends applies the position of point.
It should be noted that the location of each final stage lever both ends can freely be determined according to S103.
S104: according to aerofoil lift, aerofoil pressure heart position and least strain energy principle, determine that each load applies the load of point
Lotus.
For step S104, it is specifically based on least strain energy principle, and combines dynamic balance and equalising torque relationship, to count
The load that each load determined in S103 applies point is calculated, calculating process is as follows.
The first step lists the first equation group according to the equilibrium relation of power and torque.
In above-mentioned formula, L is aerofoil lift, xL、yLThe coordinate of heart position is pressed for aerofoil, n is the quantity that load applies point,
LiApply the load of point, x for each loadi、yiApply the coordinate of point, i=1,2,3 ..., n for each load.It is related in the method
To position coordinates be used uniformly the same coordinate system, origin is identical.
Second step, pressing heart position and each load to apply according to aerofoil, the virtual beam between point deforms energy U and Lagrange multiplies
Sub- method establishes extremal function F (λ, λx,λy),
Wherein, EI is the bending stiffness of virtual beam, liApply the virtual beam that point presses heart position to be formed with aerofoil for each load
Length；Make in the case where meeting power and moment equilibrium condition, the deformation of system can be minimum, can list second equation group accordingly
Third step according to n equation in second equation group, and combines above-mentioned 3 power and torque equilibrium equation, can be with
It calculates and obtains λ, λx,λy,L1,…,Ln, to obtain the load point for meeting least strain energy principle, dynamic balance and equalising torque
Cloth, that is, each load apply the load L of pointi。
Least strain energy principle refers to deformation energy possessed by whole system among the above, and it is opposite that perseverance is less than other possible states
The deformation energy answered obtains second equation group accordingly in the present embodiment and solves each load of acquisition according to power and torque equilibrium equation
Apply the load of point.By the panel load distribution method based on least strain energy principle, it is assigned to predetermined load and applies at point, make
The deformation of missile wing is obtained close to its live flying state, simulates better effect.
If the function in the above method is realized in the form of software function module and sells or make as independent product
Used time can store in a computer readable storage medium.Computer software product is stored in a storage medium,
It uses including some instructions so that a computer equipment (can be personal computer, laptop, server or net
Network equipment etc.) execute the above embodiment of the present invention the method all or part of the steps.And storage medium above-mentioned includes: U
Disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access
Memory), the various media that can store program code such as magnetic or disk.
In conclusion On The Simulation Load Device For Aerodynamic Loads of Missile Wings provided by the invention, is applied by simple screw-rod structure
Lotus is loaded, continuously can be loaded and be unloaded, structure is simple, also, passes through the connection of simulation missile wing and rocket body or rocket body completely
Mode, preferably missile wing deformation under reaction time of day, also, pass through the concentrated force minute that each load is applied point by loading blocks
It dissipates for face power, makes missile wing force-bearing situation further to time of day, therefore the device has load distribution accurate, loading method
Simulation quality is high, and missile wing connection type simulation quality is high, the simple advantage of structure.
It further, will calculating or wind using the missile wing aerodynamic loading simulation loading method based on least strain energy principle
The distributed load that hole is tested is converted into the load at predetermined load application, carries load when test closer to practical flight
Lotus.
The foregoing is merely alternative embodiments of the invention, are not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of On The Simulation Load Device For Aerodynamic Loads of Missile Wings, which is characterized in that including the first stationary plane, the second stationary plane, crossbeam,
Load screw rod, the load lever system formed by multi-grade lever and loading blocks；First stationary plane and second stationary plane
It is oppositely arranged, the crossbeam is fixedly connected between two stationary planes and the beam vertical is fixed in the first stationary plane and second
Face；The first fixed block and the second fixed block in same horizontal line are provided on first stationary plane, described first is solid
Determine block and second fixed block is used to missile wing being fixed on first stationary plane；The load screw rod runs through the cross
Beam, primary lever of the lower end of the load screw rod into load lever system applies full payload, in the load lever system
The both ends of each final stage lever are located at each load in loading blocks and apply at the position of point；The loading blocks are located at the missile wing
Top, and match with the shape of the missile wing.
2. the apparatus according to claim 1, which is characterized in that the crossbeam is two I-beams, the wing of two I-beams
Edge is located in same level, and the distance that the load screw rod may pass through is reserved between two I-beams.
3. the apparatus of claim 2, which is characterized in that be further fixedly arranged on load on the top flange of two I-beams
Seat, the load seat offer threaded hole compatible with the load screw flight；The load screw rod adds through described
Carry seat.
4. device according to claim 3, which is characterized in that rubber pad is equipped between the loading blocks and the missile wing,
For keeping the power transmission of loading blocks more uniform.
5. device according to claim 4, which is characterized in that be equipped with sensor in the lower end of the load screw rod, be used for
Measure the full payload that the load screw rod is applied on primary lever.
6. device according to claim 5, which is characterized in that be additionally provided with force transfer ball in the lower end of the load screw rod, institute
It states force transfer ball to be located between the lower end and sensor of load screw rod, the force transfer ball is round shape.
7. device according to claim 1-6, which is characterized in that the upper end of the load screw rod is rectangular or six
It is prismatic.
8. a kind of missile wing aerodynamic loading simulation loading method, which is characterized in that be applied to as claim 1-7 is described in any item
Device, comprising:
Determine that the aerodynamic loading distribution of missile wing, the aerodynamic loading distribution include the pressure of each face element in missile wing surface；
According to the pressure of each face element in missile wing surface, aerofoil lift and the aerofoil pressure heart position of the missile wing are obtained；
The aerofoil of the missile wing is divided into several piecemeals, is determined according to the centroid of each piecemeal to loading blocks and applies adding for load
Carry the position that each load in lever system where each final stage lever both ends applies point；
According to the aerofoil lift, aerofoil pressure heart position and least strain energy principle, determine that each load applies the load of point
Lotus.
9. according to the method described in claim 8, it is characterized in that, described press heart position according to the aerofoil lift, the aerofoil
It sets and least strain energy principle, determines that each load applies the load of point, comprising:
The first equation group is obtained according to the equilibrium relation of power and torque, first equation group is
Wherein, L is aerofoil lift, xL、yLThe coordinate of heart position is pressed for aerofoil, n is the quantity that load applies point, LiFor each load
Apply the load of point, xi、yiApply the coordinate of point, i=1,2,3 ..., n for each load；And
It presses heart position and each load to apply virtual beam deformation energy U and method of Lagrange multipliers between point according to the aerofoil, builds
Vertical extremal function F (λ, λx,λy),
Wherein, EI is the bending stiffness of virtual beam, liApply the virtual beam length that point presses heart position to be formed with aerofoil for each load；
And second equation group is obtained, the second equation group is
The load L for obtaining each load and applying point is calculated according to first equation group and the second equation groupi。
10. according to the method described in claim 9, it is characterized in that, the aerodynamic loading of the determining missile wing is distributed, comprising:
The pressure of each face element in missile wing surface is obtained by wind tunnel test.
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| CN201811301503.7A CN109387357B (en) | 2018-11-02 | 2018-11-02 | A kind of wing aerodynamic load simulation loading device and method |
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| CN201811301503.7A CN109387357B (en) | 2018-11-02 | 2018-11-02 | A kind of wing aerodynamic load simulation loading device and method |
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| CN110954395A (en) * | 2019-11-12 | 2020-04-03 | 航天时代飞鸿技术有限公司 | A kind of elastic loading device and method for performance test of folding elastic wing |
| CN111766051A (en) * | 2020-04-29 | 2020-10-13 | 深圳亚太航空技术有限公司 | Operational performance test device |
| CN112706945A (en) * | 2020-12-11 | 2021-04-27 | 中国特种飞行器研究所 | Pneumatic load loading method |
| CN113911390A (en) * | 2021-09-30 | 2022-01-11 | 上海交通大学 | Dynamic synchronous loading test device and method for deformable wing |
| CN113968357A (en) * | 2021-10-21 | 2022-01-25 | 南京航空航天大学 | Loading device and method for simulating aerodynamic loads in special-shaped cabins |
| CN114323618A (en) * | 2021-12-30 | 2022-04-12 | 中国特种飞行器研究所 | Pneumatic load loading method for flexible airfoil structure |
| CN116256234A (en) * | 2023-05-16 | 2023-06-13 | 北京航天众信科技有限公司 | Static test device for target missile wing |
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| CN113911390A (en) * | 2021-09-30 | 2022-01-11 | 上海交通大学 | Dynamic synchronous loading test device and method for deformable wing |
| CN113911390B (en) * | 2021-09-30 | 2024-02-23 | 上海交通大学 | Dynamic synchronous loading test device and method for deformed wing |
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| CN114323618A (en) * | 2021-12-30 | 2022-04-12 | 中国特种飞行器研究所 | Pneumatic load loading method for flexible airfoil structure |
| CN114323618B (en) * | 2021-12-30 | 2023-10-20 | 中国特种飞行器研究所 | Pneumatic load loading method for flexible airfoil structure |
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| CN116256234B (en) * | 2023-05-16 | 2023-08-29 | 北京航天众信科技有限公司 | Static test device for target missile wing |
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