CN109238622A - One kind being used for short blunt shape aircraft pitch orientation free vibration dynamic derivative testing device - Google Patents
One kind being used for short blunt shape aircraft pitch orientation free vibration dynamic derivative testing device Download PDFInfo
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- CN109238622A CN109238622A CN201810932942.1A CN201810932942A CN109238622A CN 109238622 A CN109238622 A CN 109238622A CN 201810932942 A CN201810932942 A CN 201810932942A CN 109238622 A CN109238622 A CN 109238622A
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- push rod
- pulling needle
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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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
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Abstract
One kind being used for short blunt shape aircraft pitch orientation free vibration dynamic derivative testing device, comprising: pitching hinge (5), motion transfering device, support device, driving device；The motion transfering device includes push rod (6), upper pulling needle (9), lower pulling needle (11), limited block (13)；Driving device is placed on support device inner cavity, and output end is connected with push rod (6) one end for being placed in support device inner cavity, and driving push rod (6) moves forward and backward；Pitching hinge (5) one end is connected support device, and the other end is connected with short blunt shape test model；Limited block (13) is mounted in support device, and limitation push rod (6) only moves forward and backward；Lower pulling needle (11) is mounted on push rod (6), and upper pulling needle (9) is mounted on short blunt shape test model；Test front and back limits the movement of pitching hinge by push rod (6)；It during test, is moved upwards by moving forward and backward for push rod by pulling needle (9) in lower pulling needle (11) driving, and then short blunt contour model (1) is driven to do free vibration campaign around the center of rotation of pitching hinge (5).
Description
Technical field
The present invention relates to one kind to obtain pitching side using free vibration dynamic derivative testing method for short blunt shape aircraft
To the flow tunnel testing device of dynamic derivative.
Background technique
The pneumatic design of aircraft and Control System Design require the dynamic stability for providing aircraft under its flying condition
Derivative data.In the movement for the change that gestures or when by interference in air flow the pitching of statokinetic, partially can occur to deviate for aircraft
Boat or roll oscillation.The purpose of dynamic stability research is to indicate the attenuation trend and rule of these vibrations.Passive type is damped
For the aircraft of control, the dynamic flying quality and reliability requirement of aircraft propose the indication of aerocraft dynamic stability
High requirement.Too low dynamic stability is easy to cause the angular movement of aircraft to dissipate, in this way, will seriously affect flying for aircraft
Row posture.Therefore, the accurate indication of dynamic derivative is particularly important.
Dynamic derivative is also referred to as dynamic stability derivative, for describing pneumatic spy when aircraft carries out maneuvering flight and is disturbed
Property.It is essential aerodynamic parameter in flight vehicle aerodynamic performance design, control system and master-plan.Dynamic stability derivative pair
It is critically important for Flight Vehicle Design teacher, because these derivatives can provide the natural stability of aircraft, control rudder face
Efficiency and mobility, in addition these derivatives but also the geometrical property of aircraft presented during Preliminary design it is especially heavy
The meaning wanted.
Short blunt shape aircraft refers to manned loading aerial vehicle or Manned reentry capsule etc. more, such as the Apollo in the U.S.
Manned return capsule, the Soyuz return capsule of the former Soviet Union, China divine boat's return capsule, Mars probes landing module etc. is big blunt nosed
Feature can satisfy lift required under various flying speeds during being loaded into flight, resistance, be allowed to safety and steady landing.It is short
Main work the first is that research of dynamic stability characteristic in the design of blunt shape flight vehicle aerodynamic.Since this kind of aircraft is close to spherical shape
SShape features, sub-, transonic speed stage, dynamic stability damp very little, it is also possible to dynamic wild effect occur, confirm this kind of fly
Row device has good dynamic stability characteristic, it is ensured that its flight safety is the final purpose of this kind of aircraft dynamic stability characteristic research.
The dynamic stability characteristic of short blunt shape aircraft is studied, a main means are to obtain its dynamic stability derivative, at present
Main method has theory analysis, numerical value calculating and wind tunnel test, and wind tunnel test is most intuitively to obtain short blunt shape dynamic stability
A kind of method of derivative.
It is free vibration test method and forced vibration tests method that wind-tunnel dynamic stability derivative, which tests common method, at present,
By measuring the kinematic parameter of the aerodynamic force acted on model, torque and measurement model, its dynamic stability derivative is found out.Due to strong
Compel vibration testing method and need measurement model aerodynamic force and angular displacement simultaneously, needs model front-rear direction inner space larger, needle
To blunt body shape aircraft, it is difficult to realize using forced vibration tests method.And free vibration test method only needs to carry out
The measurement of angular displacement, may be implemented the measurement to short blunt shape Dynamic Stability Derivatives of The Aircraft, and relatively traditional free vibration test device,
It also needs further to study for the free vibration dynamic derivative testing of this kind of aircraft.Therefore dynamic to obtain short blunt shape aircraft
Stablize derivative, a set of free vibration dynamic derivative testing device is devised, for studying short blunt shape aircraft dynamic stability characteristic.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the deficiencies of the prior art and provide a kind of for short blunt shape aircraft
Pitch orientation free vibration dynamic derivative testing device.
The technical solution of the invention is as follows: one kind is for short blunt shape aircraft pitch orientation free vibration dynamic derivative examination
Experiment device, comprising: pitching hinge, motion transfering device, support device, driving device；The motion transfering device includes pushing away
Bar, upper pulling needle, lower pulling needle, limited block；
Driving device is placed on support device inner cavity, and output end is connected with the push rod one end for being placed in support device inner cavity,
Driving push rod moves forward and backward；Pitching hinge one end is connected support device, and the other end is connected with short blunt shape test model；Limited block
It is mounted in support device, limitation push rod only moves forward and backward；Lower pulling needle is mounted on push rod, and upper pulling needle is mounted on short blunt shape
On test model；Test front and back limits the movement of pitching hinge by push rod；During test, pass through moving forward and backward for push rod
It drives upper pulling needle to move upwards by lower pulling needle, and then short blunt contour model is driven to do free vibration around the center of rotation of pitching hinge
Movement.
Further, the driving device uses and is able to bear the cylinder not less than 5Mpa bleed pressure.
Further, cylinder block thickness is not less than 10mm, and cylinder block front end cylinder head and cylinder block are in sealing contact
Face length is not less than 40mm；Cylinder intake/outlet ozzle is threadedly engaged length not less than 20mm.
Further, cylinder remaining part material selection steel in addition to gasket.
Further, the output speed of the driving device is not less than 2m/s.
Further, the vibration of short blunt shape test model is controlled by adjusting upper pulling needle, the vertex distance difference of lower pulling needle
Width.
Further, the pitching hinge is structure as a whole, including model links cone, strut joint face, crossbeam, movement
Beam；Model link cone sets central bore, passes through the movement of the inner hole and push rod cooperation limitation pitching hinge；Strut joint face sets rank
Terraced inner hole, wherein support device is connect by macropore with strut joint face, and aperture is used to support push rod；Positioned at model link cone with
A pair of beams between strut joint face, the equal consistency of thickness of a pair of of movement beam and symmetrical, a pair of movement beam be placed in crossbeam it
Between, and the gap between adjacent motion beam and crossbeam is not less than 0.5mm；Make model link cone being capable of opposite branch by moving beam
The movement of bar joint face.
Further, change the vibration frequency of short blunt shape test model by adjusting beam thickness.
Further, beam thickness range 0.6mm-2.5mm.
Further, three parts after in front of the movement beam includes, middle section are that thickness and beam thickness are consistent
Straight beam；Front and back two parts are consistent with the angle of middle section, pass through front and back two parts link model link cone and strut joint face
And make straight beam and beam vertical.
Further, 30 ° -60 ° of the angular range.
Further, the support device includes strut, radome fairing, axis；
Hollow strut uses cone match mode, connects chock by front end and positioning key is mounted on axis, axis
It is connect with wind-tunnel attack angle mechanism；Radome fairing is mounted on axis front end.
The advantages of the present invention over the prior art are that:
(1) the small size pitching hinge designed has smaller compared to previous free vibration dynamic derivative testing pitching hinge
Axial dimension, can preferably match short blunt shape dummy vehicle.
(2) pulling needle is all made of fine thread mode with lower pulling needle and connects on, can be simple and fast adjust model obtain
Initial angular displacement.
(3) movement of push rod rolling direction is limited by limited block, it is ensured that driving can effectively be implemented every time.
(4) pitching hinge difference cantilever thickness can satisfy the demand of test model difference free running frequency.
Detailed description of the invention
Fig. 1 is the assembling schematic diagram according to the embodiment of the present invention；
Fig. 2 is the pitching hinge schematic diagram according to the embodiment of the present invention；
Fig. 3 is the strut schematic diagram according to the embodiment of the present invention；
Fig. 4 is the limited block schematic diagram according to the embodiment of the present invention；
Fig. 5 is the high-pressure cylinder schematic diagram according to the embodiment of the present invention；
Fig. 6 is the push rod schematic diagram according to the embodiment of the present invention；
Fig. 7 is the lower pulling needle schematic diagram according to the embodiment of the present invention；
Fig. 8 is the upper pulling needle schematic diagram according to the embodiment of the present invention；
Fig. 9 is the collected pitching angular displacement signal according to the embodiment of the present invention.
Specific embodiment
Detailed description of the present invention embodiment with reference to the accompanying drawing.
As shown in figures 1-8, short blunt shape aircraft pitch orientation free vibration dynamic derivative testing device, including pitching are used for
Hinge 5, motion transfering device, support device, driving device；Following components are specifically included in this example: short blunt contour model
1, pitching hinge tenses cushion block 2, pitching hinge stretching screw 3, pitching hinge and connects tapered sleeve 4, pitching hinge 5, push rod 6, pitching
Hinge connects taper pin 7, pitching hinge attachment screw 8, upper pulling needle 9, upper pulling needle holding screw 10, lower pulling needle 11, strut 12, limit
Block 13, limited block fixing screws 14, cylinder 15, high-pressure cylinder fixing screws 16, radome fairing 17, connection chock 18, positioning key 19,
Axis 20；
As shown in figure 5, cylinder 15 is filled using the high-pressure cylinder not less than 5Mpa bleed pressure is able to bear as the present invention
The driving device set is placed on the inner cavity of support device.Cylinder block thickness be not less than 10mm, cylinder block front end cylinder head with
Cylinder block sealing contact surface length is not less than 40mm；Cylinder intake/outlet ozzle is threadedly engaged length not less than 20mm.Gas
Cylinder remaining part material selection steel in addition to gasket.The output speed of driving device is not less than 2m/s.
Support device mainly includes strut 12, radome fairing 17, axis 20；Hollow strut 12 uses cone match mode,
Chock 18 is connected by front end and positioning key 19 is mounted on axis 20, and axis 20 is connect with wind-tunnel attack angle mechanism；Radome fairing 17
Threadedly it is mounted on 20 front end of axis.
As shown in Fig. 2, pitching hinge 5 is structure as a whole, including model link cone 51, strut joint face 52, crossbeam 53, fortune
Dynamic beam 54；Model link cone 51 sets central bore, passes through the movement of the inner hole and the cooperation limitation pitching hinge of push rod 6；Strut connects
Junction 52 sets ladder inner hole, and wherein support device is connect by macropore with strut joint face, and aperture is used to support push rod；Positioned at mould
A pair of beams 53, a pair of of movement equal consistency of thickness of beam 54 between type link cone 51 and strut joint face 52 and symmetrical, one
Movement beam is placed between crossbeam, and the gap between adjacent motion beam and crossbeam is not less than 0.5mm；Made by moving beam 54
Model link cone 51 can be moved with respect to strut joint face 52.Change the vibration of short blunt shape test model by adjusting beam thickness
Dynamic frequency.Beam thickness range 0.6mm-2.5mm.
Three parts after moving in front of beam 54 includes, middle section are thickness and the consistent straight beam of beam thickness；Front and back two
It is point consistent with the angle of middle section, by front and back two parts link model link cone 51 and strut joint face 52 and make straight beam
With beam vertical.30 ° -60 ° of above-mentioned angular range.
Motion transfering device includes push rod 6, upper pulling needle 9, lower pulling needle 11, limited block 13；Cylinder 15 passes through two high pressure gas
Cylinder fixing screws 16 are mounted on 12 rear end inner cavity of strut, and output end is connected with 6 one end of push rod for being placed in 12 inner cavity of strut, driving
Push rod 6 is moved forward and backward in 12 inner cavity of strut；Pitching hinge 5 connects taper pin 7 by two pitching hinges and two pitching hinges connect
It connects screw 8 and is mounted on 12 front end of strut in 90 ° of angles, short blunt contour model 1 connects tapered sleeve 4 by pitching hinge and is mounted on pitching
5 front end of hinge, the way of contact are cone match, are made by pitching hinge tension cushion block 2 and four pitching hinge stretching screws 3 short
Blunt contour model 1 and pitching hinge 5 are axially fastening connection；Limited block 13 is mounted on strut 12 by limited block fixing screws 14
On, limitation push rod 6 only moves forward and backward；Lower pulling needle 11 is mounted on 6 front position of push rod, drives lower 11 front and back of pulling needle by push rod 6
Movement, upper pulling needle 9 are mounted on short 1 intracavity posterior end of blunt contour model, and upper pulling needle 9 is by upper 10 tightening of pulling needle holding screw；Before test
The movement of pitching hinge is limited by push rod 6 afterwards；During test, pass through moving forward and backward by the driving of lower pulling needle 11 for push rod
Pulling needle 9 moves upwards, and so that pulling needle 9 and short blunt contour model 1 is obtained initial angular displacement, and then short blunt contour model 1 is around pitching
Do free vibration campaign in 5 center of hinge.Short blunt shape examination is controlled by adjusting upper pulling needle 9, the vertex distance difference of lower pulling needle 11
Test the amplitude of model.
Test model is mounted on strut by pitching hinge, drives push rod to move forward and backward by high-pressure cylinder, on push rod
Quickly movement can make test model obtain an initial angle to one starting force of upper pulling needle on test model before and after lower pulling needle
Displacement, under the action of pitching hinge, test model can do free damping campaign, pass through the foil gauge being attached on pitching hinge
The angular displacement time history that model free damping campaign can be measured collects pitching hinge angle position by data collection system
The voltage signal values of shifting signal, and then carry out corresponding data processing and can be obtained by corresponding pitching dynamic stability derivative.
Embodiment
It is tried using of the invention for short blunt shape aircraft pitch orientation free vibration dynamic derivative testing device
When testing, which is mounted on wind-tunnel tulwar, and high-pressure cylinder 15 is mounted on 12 inner cavity of strut, passes through 15 band of high-pressure cylinder
Dynamic 6 front and back of push rod quickly moves, and pulling needle 9 under 11 fast driving of lower pulling needle on push rod 6 gives lower pulling needle 9 and short blunt contour model 1
Initial angular displacement, under the resilient support of pitching hinge 5, short blunt contour model 1 does free vibration fortune around 5 center of pitching hinge
It is dynamic, variation in angular displacement time history can be measured by the foil gauge pasted on pitching hinge 5, just by corresponding data processing
Available pitching dynamic stability derivative.
A whole set of test mechanism size is always about 1000mm, and the point diameter of strut 12 is 22mm, and 5 diameter of pitching hinge is
Pitch vibration angle ± 5 ° may be implemented in 32mm, sleeve mechanism maximum, by changing the cantilever thickness of pitching hinge 5, may be implemented
Vibration frequency 8Hz~20Hz.As shown in figure 9, collected pitch angle time history, initial angular displacement are when to test
2.8 °, vibration frequency 15Hz.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (12)
1. one kind is used for short blunt shape aircraft pitch orientation free vibration dynamic derivative testing device characterized by comprising bow
Face upward hinge (5), motion transfering device, support device, driving device；The motion transfering device includes push rod (6), upper pulling needle
(9), lower pulling needle (11), limited block (13)；
Driving device is placed on support device inner cavity, and output end is connected with push rod (6) one end for being placed in support device inner cavity, drives
Dynamic push rod (6) move forward and backward；Pitching hinge (5) one end is connected support device, and the other end is connected with short blunt shape test model；Limit
Position block (13) is mounted in support device, and limitation push rod (6) only moves forward and backward；Lower pulling needle (11) is mounted on push rod (6), on
Pulling needle (9) is mounted on short blunt shape test model；Test front and back limits the movement of pitching hinge by push rod (6)；Test
In the process, it is moved upwards by moving forward and backward for push rod by pulling needle (9) in lower pulling needle (11) driving, and then drives short blunt epimorph
Type (1) does free vibration campaign around the center of rotation of pitching hinge (5).
2. experimental rig according to claim 1, it is characterised in that: the driving device, which uses to be able to bear, to be not less than
The cylinder of 5Mpa bleed pressure.
3. experimental rig according to claim 2, it is characterised in that: cylinder block thickness is not less than 10mm, cylinder block
Front end cylinder head and cylinder block sealing contact surface length are not less than 40mm；Cylinder intake/outlet ozzle is threadedly engaged length
Not less than 20mm.
4. experimental rig according to claim 2 or 3, it is characterised in that: cylinder remaining part in addition to gasket
Material selection steel.
5. experimental rig according to claim 1, it is characterised in that: the output speed of the driving device is not less than
2m/s。
6. experimental rig according to claim 1, it is characterised in that: by the top for adjusting upper pulling needle (9), lower pulling needle (11)
Range difference is put to control the amplitude of short blunt shape test model.
7. experimental rig according to claim 1, it is characterised in that: the pitching hinge (5) is structure as a whole, including
Model link cone (51), strut joint face (52), crossbeam (53), movement beam (54)；
Model link cone (51) sets central bore, passes through the movement of the inner hole and push rod (6) cooperation limitation pitching hinge；Strut connects
Junction (52) sets ladder inner hole, and wherein support device is connect by macropore with strut joint face, and aperture is used to support push rod；It is located at
A pair of beams (53), the equal consistency of thickness of a pair of of movement beam (54) between model link cone (51) and strut joint face (52) and right
Claim distribution, a pair of movement beam is placed between crossbeam, and the gap between adjacent motion beam and crossbeam is not less than 0.5mm；Pass through fortune
Dynamic beam (54) move model link cone (51) can with respect to strut joint face (52).
8. experimental rig according to claim 7, it is characterised in that: change short blunt shape test by adjusting beam thickness
The vibration frequency of model.
9. experimental rig according to claim 7, it is characterised in that: beam thickness range 0.6mm-2.5mm.
10. the experimental rig according to claim 7 or 9, it is characterised in that: the movement beam (54) include before in after three
Part, middle section are thickness and the consistent straight beam of beam thickness；Front and back two parts are consistent with the angle of middle section, by preceding
The link of two parts link model bores (51) and strut joint face (52) and makes straight beam and beam vertical afterwards.
11. experimental rig according to claim 10, it is characterised in that: 30 ° -60 ° of the angular range.
12. experimental rig according to claim 1, it is characterised in that: the support device includes strut (12), rectification
Cover (17), axis (20)；
Hollow strut (12) uses cone match mode, is mounted on axis by front end connection chock (18) and positioning key (19)
(20) on, axis 20 is connect with wind-tunnel attack angle mechanism；Radome fairing (17) is mounted on axis (20) front end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810932942.1A CN109238622B (en) | 2018-08-16 | 2018-08-16 | Device for testing free vibration dynamic derivative of short and blunt profile aircraft in pitching direction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810932942.1A CN109238622B (en) | 2018-08-16 | 2018-08-16 | Device for testing free vibration dynamic derivative of short and blunt profile aircraft in pitching direction |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109238622A true CN109238622A (en) | 2019-01-18 |
| CN109238622B CN109238622B (en) | 2020-07-14 |
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ID=65070448
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810932942.1A Active CN109238622B (en) | 2018-08-16 | 2018-08-16 | Device for testing free vibration dynamic derivative of short and blunt profile aircraft in pitching direction |
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| CN110940483A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Pitching yawing free vibration dynamic derivative test device for large slenderness ratio aircraft |
| CN110940484A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Rolling forced vibration dynamic derivative test device for high-speed flying wing model under large attack angle |
| CN116818259A (en) * | 2023-08-23 | 2023-09-29 | 中国航空工业集团公司沈阳空气动力研究所 | Vibration damping device and method for dynamic derivative test mechanism |
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| CN109238622B (en) | 2020-07-14 |
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