CN109060291A - For short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative angle measurement and experimental rig - Google Patents
For short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative angle measurement and experimental rig Download PDFInfo
- Publication number
- CN109060291A CN109060291A CN201810932958.2A CN201810932958A CN109060291A CN 109060291 A CN109060291 A CN 109060291A CN 201810932958 A CN201810932958 A CN 201810932958A CN 109060291 A CN109060291 A CN 109060291A
- Authority
- CN
- China
- Prior art keywords
- bearing
- model
- axis
- connecting shaft
- angle measurement
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
-
- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
One kind being used for short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative testing angle measurement and experimental rig, and wherein angle measurement unit includes model connection cone (51), bearing axis (52), bearing jack-post pin (53), strain beam (54), strut connecting shaft (56), bearing (ball) cover (57), bearing nut (58), bearing (510)；Model connection cone (51) front end conical surface is connected with short blunt shape test model；Model connection cone (51) rear end is supported on bearing axis (52) by bearing jack-post pin (53)；Strain beam (54) both ends are separately mounted in model connection cone (51) and strut connecting shaft (56)；Bearing (510) inner ring is mounted on bearing axis (52), fixed axial by bearing nut (58)；Bearing (510) outer ring is mounted on strut connecting shaft (56), fixes its axial direction by bearing (ball) cover (57)；By pasting foil gauge on strain beam (54), when model connects cone (51) and moves with respect to strut connecting shaft (56), angle time history is measured by strain beam (54).
Description
Technical field
The present invention relates to one kind to obtain aircraft by free vibration dynamic derivative testing method for short blunt shape aircraft
The experimental rig of dynamic derivative under low frequency state, low-frequency vibration frequency are 1Hz-3Hz.
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 needs to meet certain similarity criterion when dynamic derivative wind tunnel test, one of them main similar parameter
Movement frequency of the contracting than rear test model is simulated by wind tunnel test that is, according to the motion frequency of practical flight device for reduced frequency
Rate.Due to combine the factors such as support stiffness, intensity, shake for short blunt shape Dynamic Stability Derivatives of The Aircraft wind tunnel test low frequency
Dynamic simulation is always a technological difficulties.
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.Force vibration
Dynamic test method can realize the dynamic derivative testing of lower frequency by adjusting driving source frequency, but due to forced vibration tests
Method need simultaneously measurement model aerodynamic force and angular displacement, need model front-rear direction inner space larger, for blunt body outside
Shape aircraft is difficult to realize using forced vibration tests method.And free vibration test method only needs to carry out the survey of angular displacement
Amount, may be implemented the measurement to short blunt shape Dynamic Stability Derivatives of The Aircraft, and relatively traditional free vibration test device, fly for this kind of
The low frequency free vibration dynamic derivative testing of row device also needs further to study.It therefore is the short blunt shape aircraft low frequency state of acquisition
Dynamic derivative devises a set of low frequency free vibration dynamic derivative testing device, 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 low-frequency vibration dynamic derivative angle measurement and experimental rig.
The technical solution of the invention is as follows: one kind is for short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative examination
Test angle measurement unit, comprising: model connect cone, bearing axis, bearing jack-post pin, strain beam, strut connecting shaft, bearing (ball) cover,
Bearing nut, bearing；
The model connection cone front end conical surface is connected with short blunt shape test model；Model connection cone rear end passes through bearing jack-post pin
It is supported on bearing axis；Strain beam both ends are separately mounted in model connection cone and strut connecting shaft；Bearing inner race is mounted on axis
It holds on axis, it is fixed axial by bearing nut；Bearing outer ring is mounted in strut connecting shaft, fixes its axial direction by bearing (ball) cover；It answers
Become on beam by pasting foil gauge, when opposite strut connecting shaft movement is bored in model connection, when measuring angle by strain beam
Between course.
Further, the strain beam uses two, and relative test device central axis is symmetrical.
Further, the strain beam 4 be V-type beam, 90 ± 8 ° of v-angle.
Further, described to answer side bar with a thickness of 0.1mm-0.25mm.
Further, support connection shaft body is cylindrical body, the front end working motion slot of cylindrical body, model connection
The rear end of cone moves in movement slots, and movement slots both ends of the surface process cylindrical hole, for installing bearing；Cylindrical body rear end processes ladder
Hole.
Further, the gap of model connection cone rear end sides and movement slots is greater than 1mm.
One kind being used for short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative testing device, including above-mentioned angle measurement
Device, motion transfering device, support device, driving device；
Driving device is placed on support device inner cavity, and output end is connected with motion transfering device, driving movement transmitting dress
It sets and moves forward and backward；Strut one end of the connecting shaft is connected support device；Test front and back is measured by motion transfering device limited angular
The movement of device；During test, short blunt contour model is driven to fill around angle measurement by moving forward and backward for motion transfering device
The center of rotation set does low frequency movement.
Further, the motion transfering device includes push rod, upper pulling needle, lower pulling needle, limited block；
Push rod is placed in support device inner cavity and is connected with driving device output end, and limited block is mounted in support device, limit
Push rod processed only moves forward and backward；Lower pulling needle is mounted on push rod, and upper pulling needle is mounted on short blunt shape test model；Test front and back
By push rod pass through strut connecting shaft ladder aperture be arranged in model connect cone rear end hole cooperation, limited angular measure
The movement of device；During test, upper pulling needle is driven to move upwards by lower pulling needle by moving forward and backward for push rod, and then drive short
Blunt contour model does low frequency movement around the center of bearing axis.
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 output speed of driving device is not less than 2m/s.
Further, the driving device uses and is able to bear the cylinder not less than 5Mpa bleed pressure, cylinder block
Thickness is not less than 10mm, and 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.
Further, the support device includes strut, radome fairing, axis；Hollow strut uses cone match side
Formula connects chock by front end and positioning key is mounted on axis, and axis is connect with wind-tunnel attack angle mechanism；During radome fairing is mounted on
Axis front end.
The advantages of the present invention over the prior art are that:
(1) the small-scale model connection cone designed is compared to previous free vibration dynamic derivative testing pitching hinge inner cone, tool
There is smaller axial dimension, can preferably match short blunt shape dummy vehicle.
(2) low-frequency vibration of experimental rig may be implemented by the installation thin torque beam of two panels symmetrical above and below, while acquires two
Piece torque beam signal can reduce measurement error, propose measurement accuracy.
(3) model connection cone is mounted in strut connecting shaft by a pair of bearings 619/8, can be carried in test larger
Axial load, while there is lesser pitch orientation rigidity, it is adapted to the aerodynamic characteristics of short blunt shape aircraft well.
Detailed description of the invention
Fig. 1 is the assembling schematic diagram according to the embodiment of the present invention；
Fig. 2 is that cone schematic diagram is connected according to the model of the embodiment of the present invention；
Fig. 3 is the bearing axis schematic diagram according to the embodiment of the present invention；
Fig. 4 is the strain beam schematic diagram according to the embodiment of the present invention；
Fig. 5 is the bearing (ball) cover schematic diagram according to the embodiment of the present invention；
Fig. 6 is the strut connecting shaft schematic diagram according to the embodiment of the present invention；
Fig. 7 is the general assembly drawing according to the embodiment of the present invention；
Fig. 8 is the strut schematic diagram according to the embodiment of the present invention；
Fig. 9 is the limited block schematic diagram according to the embodiment of the present invention；
Figure 10 is the high-pressure cylinder schematic diagram according to the embodiment of the present invention；
Figure 11 is the push rod schematic diagram according to the embodiment of the present invention；
Figure 12 is the lower pulling needle schematic diagram according to the embodiment of the present invention；
Figure 13 is the upper pulling needle schematic diagram according to the embodiment of the present invention；
Figure 14 is the collected low frequency 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 to 6, it is used for short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative testing device, comprising: mould
Type connection cone 51, bearing axis 52, bearing jack-post pin 53, strain beam 54, strain beam screw 55, strut connecting shaft 56, bearing (ball) cover
57, bearing nut 58, bearing (ball) cover screw 59, bearing 61,9/8 510；
The model connection 51 front end conical surfaces of cone are connected with short blunt shape test model；51 rear ends of model connection cone pass through bearing axis
Pin 53 is supported on bearing axis 52；54 leading portion of strain beam is mounted on model connection cone 51 by strain beam screw 55, rear end
It is mounted in strut connecting shaft 56 by strain beam screw 55；Bearing nut 58 is mounted on strut company by bearing (ball) cover screw 59
In spindle 56, effect is 619/8510 outer ring of fixing bearing；52 middle section of bearing axis connects 51 cooperation of cone, two sides with model
61,9/8 510 inner ring of bearing and bearing nut 58 are installed.510 outer ring of bearing is mounted in strut connecting shaft 56, by bearing (ball) cover
57 fix its axial direction；56 rear end of strut connecting shaft is mounted on strut by taper pin and screw mode, the support installation of front end inner hole
61,9/8 510 outer ring of bearing, the opposite strut connecting shaft 56 of model connection cone 51 can be freely rotated；By pasting on strain beam 54
Foil gauge measures angle time history by strain beam 54 when the opposite strut connecting shaft 56 of model connection cone 51 is moved.When
When opposite strut connecting shaft movement is bored in model connection, relative motion angle can be measured by the foil gauge pasted on strain beam
The time history of displacement is collected the voltage signal values of angular displacement signal by data collection system, and then is counted accordingly
It can be obtained by corresponding low frequency pitching dynamic stability derivative according to processing.
As illustrated in figures 7 to 13, a kind of to be used for short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative testing device, packet
Include above-mentioned angle measurement unit 5, motion transfering device, support device, driving device；Following zero is specifically included in this example
Part: short blunt contour model 1, tense cushion block 2, stretching screw 3, connection tapered sleeve 4, angle measurement unit 5, push rod 6, connection taper pin 7,
Attachment screw 8, upper pulling needle 9, upper pulling needle holding screw 10, lower pulling needle 11, strut 12, limited 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；
Using the high-pressure cylinder not less than 5Mpa bleed pressure is able to bear, the driving as apparatus of the present invention fills cylinder 15
It sets, is placed on the inner cavity of support device.Cylinder block thickness is not less than 10mm, and cylinder block front end cylinder head and cylinder block are close
Sealing-in contacting surface length is not less than 40mm；Cylinder intake/outlet ozzle is threadedly engaged length not less than 20mm.Cylinder removes gasket
Outer remaining part material selection steel.The output speed of driving device is not less than 2m/s.
Driving device is placed on support device inner cavity, and output end is connected with motion transfering device, driving movement transmitting dress
It sets and moves forward and backward；56 one end of strut connecting shaft is connected support device；Test front and back is surveyed by motion transfering device limited angular
Measure the movement of device；During test, drive short blunt contour model 1 around angle measurement by moving forward and backward for motion transfering device
The center of rotation of device does low frequency movement.
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.
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；Angle measurement unit is mounted on 12 front end of strut, and short blunt contour model 1 passes through connection
Tapered sleeve 4 is mounted on 5 front end of angle measurement unit, and the way of contact is cone match, by tensing cushion block 2 and four stretching screws 3
Short blunt contour model 1 and angle measurement unit 5 is set to axially fasten connection；Limited block 13 is installed by limited block fixing screws 14
On strut 12, limitation push rod 6 is only moved forward and backward；Lower pulling needle 11 is mounted on 6 front position of push rod, is set aside by the drive of push rod 6
Needle 11 moves forward and backward, and upper pulling needle 9 is mounted on short 1 intracavity posterior end of blunt contour model, and upper pulling needle 9 is tight by upper pulling needle holding screw 10
It is fixed；Test front and back by push rod 6 pass through strut connecting shaft 56 ladder aperture be arranged in model connect bore 51 rear ends hole
Cooperation, the movement of limited angular measuring device；During test, upper pulling needle is driven by lower pulling needle 11 by moving forward and backward for push rod
9 move upwards, and then short blunt contour model 1 is driven to do low frequency movement around the center of bearing axis 52.By adjust upper pulling needle 9, under
The vertex distance difference of pulling needle 11 controls the amplitude of short blunt shape test model.
Embodiment
It is tried using of the invention for short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative testing device
When testing, which is mounted on strut, front end model connection 51 joint test models of cone, model connection
It is connected between cone 51 and strut connecting shaft 56 by strain beam 54, under the rigidity support of strain beam 54, model connection cone 51 can be with
Opposite strut connecting shaft 56 does free vibration, and a pair of bearings 61,9/8 510 can bear the axial load that model is subject to, by giving
Model applies an initial angular displacement, and model can connect cone 51 with movable model and do free damping fortune around strut connecting shaft 56
It is dynamic, variation in angular displacement time history can be measured by the foil gauge pasted on strain beam 54, pass through corresponding data processing
It can be obtained by low frequency pitching dynamic stability derivative.
Entire experimental rig length is 85mm, diameter 40mm, and when test, entire experimental rig is placed on short blunt shape flight
Device test model inner cavity.Pitch vibration angle ± 10 ° may be implemented in experimental rig maximum, by changing the cantilever thickness of strain beam,
Vibration frequency 1Hz~8Hz may be implemented.Collected pitch angle time history, initial angle position when as shown in figure 14, to test
Moving is 3.8 °, vibration frequency 1.8Hz.
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 low-frequency vibration dynamic derivative testing angle measurement unit, feature exists
In, comprising: model connection cone (51), bearing axis (52), bearing jack-post pin (53), strain beam (54), strut connecting shaft (56), axis
Socket end lid (57), bearing nut (58), bearing (510)；
Model connection cone (51) front end conical surface is connected with short blunt shape test model；Model connection cone (51) rear end passes through bearing axis
Pin (53) is supported on bearing axis (52)；Strain beam (54) both ends are separately mounted to model connection cone (51) and strut connecting shaft
(56) on；Bearing (510) inner ring is mounted on bearing axis (52), fixed axial by bearing nut (58)；Bearing (510) outer ring peace
On strut connecting shaft (56), its axial direction is fixed by bearing (ball) cover (57)；By pasting foil gauge on strain beam (54), in mould
When type connection cone (51) is moved with respect to strut connecting shaft (56), angle time history is measured by strain beam (54).
2. angle measurement unit according to claim 1, it is characterised in that: the strain beam uses two, and opposite
Experimental rig central axis is symmetrical.
3. angle measurement unit according to claim 1 or 2, it is characterised in that: the strain beam 4 is V-type beam, V-type
90 ± 8 ° of angle.
4. angle measurement unit according to claim 1 or 2, it is characterised in that: described answers side bar with a thickness of 0.1mm-
0.25mm。
5. angle measurement unit according to claim 1 or 2, it is characterised in that: the support connection shaft body is circle
The rear end of cylinder, the front end working motion slot of cylindrical body, model connection cone (51) moves in movement slots, and movement slots both ends of the surface add
Work cylindrical hole, for installing bearing；Cylindrical body rear end processing shoulder hole.
6. angle measurement unit according to claim 1 or 2, it is characterised in that: model connection cone (51) rear end sides with
The gap of movement slots is greater than 1mm.
7. one kind is used for short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative testing device, it is characterised in that: including power
Benefit require 1 described in angle measurement unit, motion transfering device, support device, driving device；
Driving device is placed on support device inner cavity, and output end is connected with motion transfering device, before driving motion transfering device
After move；Strut connecting shaft (56) one end is connected support device；Test front and back is measured by motion transfering device limited angular
The movement of device；During test, drive short blunt contour model (1) around angle measurement by moving forward and backward for motion transfering device
The center of rotation of device does low frequency movement.
8. experimental rig according to claim 7, it is characterised in that: the motion transfering device include push rod (6), on
Pulling needle (9), lower pulling needle (11), limited block (13)；
Push rod (6) is placed in support device inner cavity and is connected with driving device output end, and limited block (13) is mounted in support device,
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
On model；The ladder aperture that test front and back passes through strut connecting shaft (56) by push rod (6) connect cone in model with setting
(51) the hole cooperation of rear end, the movement of limited angular measuring device；During test, pass through moving forward and backward by lower pulling needle for push rod
(11) pulling needle (9) moves upwards in driving, and then short blunt contour model (1) is driven to do low frequency fortune around the center of bearing axis (52)
It is dynamic.
9. experimental rig according to claim 8, 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.
10. experimental rig according to claim 7, it is characterised in that: the output speed of driving device is not less than 2m/s.
11. experimental rig according to claim 10, it is characterised in that: the driving device is not low using being able to bear
In the cylinder of 5Mpa bleed pressure, cylinder block thickness is not less than 10mm, and cylinder block front end cylinder head and cylinder block seal
Contact surface length is not less than 40mm；Cylinder intake/outlet ozzle is threadedly engaged length not less than 20mm.
12. experimental rig according to claim 7, 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 |
|---|---|---|---|
| CN201810932958.2A CN109060291B (en) | 2018-08-16 | 2018-08-16 | Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810932958.2A CN109060291B (en) | 2018-08-16 | 2018-08-16 | Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109060291A true CN109060291A (en) | 2018-12-21 |
| CN109060291B CN109060291B (en) | 2021-02-09 |
Family
ID=64686150
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810932958.2A Active CN109060291B (en) | 2018-08-16 | 2018-08-16 | Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109060291B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111289208A (en) * | 2020-03-06 | 2020-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Model tail boom device suitable for fighter plane wind tunnel test |
| CN116046330A (en) * | 2023-03-30 | 2023-05-02 | 中国航空工业集团公司哈尔滨空气动力研究所 | Three-degree-of-freedom virtual flight test device capable of ventilating |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101726401A (en) * | 2009-12-09 | 2010-06-09 | 中国航空工业第一集团公司沈阳空气动力研究所 | Scale measuring device for pitching dynamic derivative experiment |
| CN102818692A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
-
2018
- 2018-08-16 CN CN201810932958.2A patent/CN109060291B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101726401A (en) * | 2009-12-09 | 2010-06-09 | 中国航空工业第一集团公司沈阳空气动力研究所 | Scale measuring device for pitching dynamic derivative experiment |
| CN102818692A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
Non-Patent Citations (1)
| Title |
|---|
| 赵俊波 等: "圆锥标模高超声速俯仰自由振动试验与分析", 《气体物理》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110940484B (en) * | 2019-11-13 | 2021-11-16 | 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 |
| CN111289208A (en) * | 2020-03-06 | 2020-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Model tail boom device suitable for fighter plane wind tunnel test |
| CN116046330A (en) * | 2023-03-30 | 2023-05-02 | 中国航空工业集团公司哈尔滨空气动力研究所 | Three-degree-of-freedom virtual flight test device capable of ventilating |
| CN116046330B (en) * | 2023-03-30 | 2023-06-16 | 中国航空工业集团公司哈尔滨空气动力研究所 | Three-degree-of-freedom virtual flight test device capable of ventilating |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109060291B (en) | 2021-02-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107966264B (en) | One kind being used for hypersonic wind tunnel rolling forced vibration dynamic derivative experimental rig | |
| CN109000881B (en) | Rolling forced vibration dynamic derivative test device suitable for Mach number of 8.0 | |
| CN110940484B (en) | Rolling forced vibration dynamic derivative test device for high-speed flying wing model under large attack angle | |
| CN107238457B (en) | A kind of low thrust measuring device | |
| CN109060291A (en) | For short blunt shape aircraft pitch orientation low-frequency vibration dynamic derivative angle measurement and experimental rig | |
| CN106840574B (en) | A kind of device for wind-tunnel dynamic derivative forced vibration tests | |
| CN102901595B (en) | Method for measuring hinge moment of control surface | |
| CN110940480B (en) | Pitching yawing forced vibration dynamic derivative test device used under high attack angle of high-speed flying wing model | |
| CN107966265B (en) | One kind yawing forced vibration dynamic derivative experimental rig for hypersonic wind tunnel pitching | |
| CN114476122B (en) | Air refueling simulation test device and method based on wind tunnel | |
| CN110793746B (en) | Wind tunnel test device for measuring thrust of oblique cutting spray pipe of hypersonic vehicle | |
| CN103837322A (en) | Hydrodynamic performance testing method of water surface aircraft | |
| CN109506877B (en) | Sub-span super wind tunnel 90-degree large attack angle coupling 360-degree rolling device | |
| CN109238622A (en) | One kind being used for short blunt shape aircraft pitch orientation free vibration dynamic derivative testing device | |
| US4862739A (en) | Wind tunnel model support mechanism | |
| CN109297672B (en) | Pitching yawing forced vibration dynamic derivative test device suitable for Mach number of 8.0 | |
| CN207423487U (en) | A kind of high-precision rolling moment independent measurement device | |
| CN115508038A (en) | Test device for high-speed wind tunnel ultra-large attack angle pitching and rolling double-freedom-degree motion | |
| Shaojun et al. | Application of recurrent neural network in research of intelligent wind tunnel balance | |
| CN112345195B (en) | Test device for high-speed wind tunnel ultra-large attack angle multi-frequency compound motion | |
| CN110940483B (en) | Pitching yawing free vibration dynamic derivative test device for large slenderness ratio aircraft | |
| RU2726564C1 (en) | Aerodynamic model of aircraft with air-jet engine | |
| CN108982041B (en) | Air rudder core excitation testing device | |
| CN114778064B (en) | Supporting device and test system for wind tunnel virtual flight test of gyroplane model | |
| Trollinger | Refined performance and loads of a mach-scale rotor at high advance ratios |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |