CN107271136A - A kind of wind tunnel test system - Google Patents
A kind of wind tunnel test system Download PDFInfo
- Publication number
- CN107271136A CN107271136A CN201710508256.7A CN201710508256A CN107271136A CN 107271136 A CN107271136 A CN 107271136A CN 201710508256 A CN201710508256 A CN 201710508256A CN 107271136 A CN107271136 A CN 107271136A
- Authority
- CN
- China
- Prior art keywords
- vector
- propelling nozzle
- vector propelling
- model aircraft
- wind
- 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
- G01M9/02—Wind tunnels
-
- 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
- G01M9/08—Aerodynamic models
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of wind tunnel test system, for promoting model aircraft that experiment is blowed vector in wind-tunnel, the vector promotes the fuselage interior of model aircraft to be provided with a first vector propelling nozzle and a second vector propelling nozzle, current velocity controller is provided with the first vector propelling nozzle and the second vector propelling nozzle, the wind tunnel test system includes one and is fixedly connected with the floor of the wind-tunnel and top plate and vertically disposed support column and a pole for being used to support the vector propulsion model aircraft.The wind tunnel test system of the present invention discharges to form jet effect to obtain jet power using the pressure-air of compressed air source by pipeline to vector propelling nozzle, the jet state of vector propelling motor is simulated, the defect of aerodynamics situation of model aircraft can not be promoted in tunnel simulation vector by overcoming prior art.
Description
Technical field
Model aircraft is promoted the present invention relates to a kind of aviation aerodynamics testing equipment, more particularly to available for vector
A kind of wind tunnel test system.
Background technology
Wind tunnel test is, according to aerodynamic principle, model aircraft or its part to be fixed on such as fuselage, wing
In wind-tunnel, model aircraft or its part are flowed through by applying artificial airflow, aerial various complicated state of flights are simulated with this, obtained
Take test data.Wind-tunnel is to carry out aerodynamic studies and the most basic testing equipment of aircraft development, each type aircraft
Development be required in wind-tunnel carrying out substantial amounts of experiment.The main purpose of wind tunnel test is the various skies of model aircraft to be obtained
The changing rule of aerodynamic parameter.The flying quality of each aircraft is evaluated, except such as speed, height, aircraft weight and is started
Outside the key elements such as machine thrust, one of most important standard is the aerodynamic quality of aircraft.The full machine wind tunnel test of aircraft needs will be whole
Individual model aircraft is supported in wind-tunnel, and each part of whole model aircraft is measured by pressure test equipment under artificial airflow environment
Pressure distribution data under the conditions of particular flight, the dynamic characteristic of aircraft is obtained with this.
Vector Push Technology refer to thrust component that aircraft engine thrust produced by the deflection of jet pipe or tail jet come
Substitute the control surface of former aircraft or strengthen the operating function of aircraft, the technology that the flight to aircraft is controlled in real time.Vector is pushed away
Entering technology can allow a part for motor power to become steering force, instead of or part replace control surface, so as to greatly reduce thunder
Up to reflective surface area；No matter the angle of attack is much and how low flying speed is, aircraft can all be manipulated using this part steering force, and this just increases
The navigability of aircraft is added.Due to directly producing steering force, and value and direction are variable, also increase the agility of aircraft
Property, thus suitably can reduce or remove vertical fin, it can also substitute some other control surface.This is to the detectivity for reducing aircraft
Favourable, the resistance of aircraft can also reduced, structure mitigates again.Therefore, the use of vector Push Technology is to solve design contradiction
Optimal selection.
But during the full machine wind tunnel test of model aircraft is carried out, due to tunnel size and model aircraft size
Limitation, it is impossible to a real engine is installed inside model aircraft, thus for employing vector Push Technology
For model aircraft, method there is no to simulate the aerodynamics situation that vector promotes model aircraft in wind tunnel test.That is,
In existing wind-tunnel technique, model aircraft is that static support (can also sometimes be adjusted during wind-tunnel flyoff
The posture of whole aircraft, but can not simulate with dynamic situation), model aircraft is in itself without power, when wind tunnel test
Be using air flow with respect to model aircraft speed come simulated flight state.But for employing vector Push Technology
For model aircraft, when the propulsive force size and Orientation of aircraft engine changes, the wind tunnel test under quiescent conditions is only
The aerodynamics situation under a kind of state can be simulated.Existing wind tunnel test system can only be obtained using substantial amounts of static test
Discrete status data, then obtains the approximate dynamic number of continuous adjustment propulsive force size and Orientation by way of interpolation
According to tested number is very huge, and the expensive and result of the test that wastes time and energy is still approximate, and the degree of accuracy is poor.
The content of the invention
It is noted earlier to be reduced or avoided the technical problem to be solved in the present invention is to provide a kind of wind tunnel test system
Problem.
Specifically, the invention provides a kind of wind tunnel test system, for promoting model aircraft to vector in wind-tunnel
It is blowed experiment, the vector promotes the fuselage interior of model aircraft to be provided with a first vector propelling nozzle and one the
The end of two vector propelling nozzles, the first vector propelling nozzle and the second vector propelling nozzle is provided with the stretching vector
First jet pipe and the second jet pipe in the adjustable jet direction of the afterbody of model aircraft are promoted, first vector is promoted
Current velocity controller is provided with jet pipe and the second vector propelling nozzle；The current velocity controller includes：Around described first
The symmetrically arranged multiple bores of madial wall of vector propelling nozzle and the second vector propelling nozzle reduce control panel；Around described
The symmetrically arranged multiple bores of madial wall of one vector propelling nozzle and the second vector propelling nozzle expand control panel；And covering
The bore reduces control panel and the bore expands the elastic covering of control panel；The wind tunnel test system includes one and institute
The floor for stating wind-tunnel is fixedly connected and vertically disposed support column and one are used to support the vector to promote aircraft with top plate
The pole of model；One end of the pole is connected with the support column, and the other end is fixed on the vector and promotes model aircraft
On fuselage between the first vector propelling nozzle and the second vector propelling nozzle.
The wind tunnel test system of the present invention is released using the pressure-air of compressed air source by pipeline to vector propelling nozzle
Put to form jet effect to obtain jet power, simulated the jet state of vector propelling motor, overcome prior art
The defect of the aerodynamics situation of model aircraft can not be promoted in tunnel simulation vector, propulsive force can be carried by simulation
Dynamical state under, greatly reduce the quantity of wind tunnel test, wind tunnel test is closer to real conditions, and result precision is higher.
Also, the present invention additionally uses pipeline and is entered by wing, adjusts that pipeline, electrical heating wire, current velocity controller etc. are various to arrange
Apply and reduce further experimentation cost, improve test accuracy.
Brief description of the drawings
The following drawings is only intended to, in doing schematic illustration and explanation to the present invention, not delimit the scope of the invention.Wherein,
The structural representation that model aircraft is promoted according to the vector of the specific embodiment of the present invention is shown in Fig. 1；
The side view of the wind tunnel test system of a specific embodiment according to the present invention is shown in Fig. 2；
The top view of the wind tunnel test system of another specific embodiment according to the present invention is shown in Fig. 3；
The current velocity controller in the wind tunnel test system according to another specific embodiment of the present invention is shown in Fig. 4
Enlarged diagram；
The A-A sectional views of current velocity controller shown in Fig. 4 are shown in Fig. 5.
Embodiment
In order to which technical characteristic, purpose and effect to the present invention are more clearly understood from, now control illustrates this hair
Bright embodiment.Wherein, identical part uses identical label.
The structural representation that model aircraft is promoted according to the vector of the specific embodiment of the present invention is shown in Fig. 1,
The vector promotes the fuselage interior of model aircraft 10 to be provided with a first vector propelling nozzle 11 and the second vector propulsion
Jet pipe 15, the end of the first vector propelling nozzle 11 and the second vector propelling nozzle 15 is provided with the stretching vector and promoted
First jet pipe 12 and the second jet pipe 16 in the adjustable jet direction of the afterbody of model aircraft 10.That is, in order to
Overcome prior art can not promote the defect of aerodynamics situation of model aircraft in tunnel simulation vector, the present invention is provided
A kind of model aircraft of special construction, the model is with that can simulate the jet state of vector propelling motor, in wind-tunnel
Jet power is produced in process of the test.That is, above-mentioned vector is promoted in model aircraft 10, be provided with two vector propelling nozzles 11,
15, the two vector propelling nozzles 11,15 can produce jet-stream wind, and its jet pipe 12,16 as jet engine
Jet direction be adjustable.Certainly, it will be understood by those skilled in the art that the vector propelling nozzle 11,15 of the present invention
The such jet-stream wind of jet engine can be simply similar to, itself is not real jet hair without rotary part
Motivation, therefore two jet pipes 12,16 are nor the jet pipe in the adjustable jet direction of real structure, the two jet pipes 12,
16 be only the conical pipeline of solid shape, and the conical pipeline is arranged on the tail end of vector propelling nozzle 11,15, can be by normal
The hydraulic pressure or electromagnetically-operated part (not shown) of rule control its deflection angle, so as to control the direction of jet.On tail spray
The control in the jet direction of pipe 12,16 can use routine techniques, be not the emphasis that the present invention is paid close attention to, no longer go to live in the household of one's in-laws on getting married one by one herein
State.
The side view of the wind tunnel test system of a specific embodiment according to the present invention is shown in Fig. 2；As illustrated,
The wind tunnel test system of the present invention can be used for promoting model aircraft 10 to blow the vector of the invention shown in Fig. 1 in wind-tunnel
Wind is tested, and the wind tunnel test system is fixedly connected and vertically disposed branch including one with the floor 200 of wind-tunnel and top plate 300
Dagger 400 and a pole 500 for being used to support the vector propulsion model aircraft 10；One end of pole 500 and support column
400 connections, the other end is fixed on the first vector propelling nozzle 11 and the second vector propelling nozzle that vector promotes model aircraft 10
On fuselage between 15 (Fig. 3).
Further, as shown in figure 3, the wind tunnel test system according to another specific embodiment of the invention is shown in it
The top view of system；Wherein, the wind tunnel test system further comprises the compressed air source 4 for the outside for being arranged at wind-tunnel and used
In be connected the compressed air source 4 with the first vector propelling nozzle 11 and the second vector propelling nozzle 15 respectively first
Pipeline 51 and second pipe 52.That is, injection gas is produced in order to simulate jet engine by two vector propelling nozzles 11,15
Stream, the present invention is provided with compressed air source 4, is promoted and sprayed to vector by pipeline 51,52 using the pressure-air of compressed air source 4
The release of pipe 11,15 forms high velocity air, forms jet effect to obtain jet power.In order to clearly show that in Fig. 3, two are depicted
Individual compressed air source 4, in practical work process, the two compressed air sources 4 can be shared, that is, only need a compressed air
Source 4.Certainly, it will be appreciated by those skilled in the art that when actual wind tunnel test, the pressure on compressed air source 4
Power size, the length of pipeline 51,52 and vector propelling nozzle 11,15, diameter etc. are required for accurate calculating and controlled, and are used to
Form flow velocity, the Jet Stream of flow needed for obtaining.Those skilled in the art can be on the basis of design proposed by the present invention
Further calculated and controlled according to actual conditions, this calculating and control can use existing conventional technical means,
Nor the emphasis that the present invention is paid close attention to, is also no longer repeated one by one.
In order to avoid the arrangement of pipeline 51,52 causes excessive interference to Flow Field in Wind Tunnel, in a preferred embodiment, the
One pipeline 51 and second pipe 52 promote the two ends of two wings 20 of model aircraft 10 to enter vector from vector and promote aircraft mould
The fuselage interior of type 10 simultaneously connects the first vector propelling nozzle 11 and the second vector propelling nozzle 15 respectively.Can from Fig. 2
Go out, by this arrangement of the present embodiment, there is no any extra part of increase in the vertical direction of wind-tunnel, only in vector
Promote the horizontal distalmost end of model aircraft 10 to be connected with pipeline 51,52 (Fig. 3), therefore the gas of model aircraft 10 is promoted for vector
The interference that dynamic profile is produced is minimum, is conducive to obtaining more accurate test data.
In another specific embodiment, as shown in figure 3, the first vector propelling nozzle 11 and the second vector propelling nozzle 15
Between be connected with adjustment pipeline 30, it is described adjustment pipeline 30 in be provided with adjustment flow magnetic valve 40.The purpose of this set
It is to enter the air of the first vector propelling nozzle 11 and the second vector propelling nozzle 15 by the first pipeline 51 and second pipe 52
Flow, pressure there may be certain difference due to factors such as line size, being completely embedded property, and if necessary to simulation, two are started
The state of the equal thrust of machine, then need the air mass flow and flow velocity of the first pipeline 51 of point-device control and second pipe 52,
This is very troublesome something, and the requirement to equipment and personnel is very high.And use the setting of the present embodiment, it is thus only necessary to it is logical
Cross magnetic valve 40 open adjustment pipeline 30 can be to cause in the first vector propelling nozzle 11 and the second vector propelling nozzle 15
Air pressure reaches unanimously, it is easy to reaches that identical thrust is controlled by this small design, reduces control and require, greatly
Regulation and control time and cost are saved greatly.
In another specific embodiment, set around the first vector propelling nozzle 11 and the outside of the second vector propelling nozzle 15
It is equipped with electrical heating wire 50.Can be certainly, prior with the condition of high temperature of simple analog jet engine by electrical heating wire 50,
First vector propelling nozzle 11 and the second vector propelling nozzle 15 can be heated by electrical heating wire 50 so that therein
High pressure draught expanded by heating improves jet velocity.That is, providing lasting supersonic speed spray only by compressed air source 4
Gas velocity degree is extremely difficult, and very high for the equipment requirement of generation compressed air, the present embodiment is set by electrical heating wire 50
The equipment requirement of compressed air source 4 can partly be reduced by putting, and save cost.
Likewise, in order to further improve the speed of the jet in the first vector propelling nozzle 11 and the second vector propelling nozzle 15
Degree, in another specific embodiment, the present invention is also set in the first vector propelling nozzle 11 and the second vector propelling nozzle 15
Current velocity controller 60 is put, concrete structure is as shown in Figure 4,5.
That is, the flow control in the wind tunnel test system according to another specific embodiment of the present invention is shown in Fig. 4
The enlarged diagram of device；The A-A sectional views of current velocity controller shown in Fig. 4 are shown in Fig. 5, can understand from Figure 4 and 5
The current velocity controller 60 for going out the present invention simulates the structure type of Laval nozzle, forms adding for middle shrinkage two ends expansion
The structure type of fast air-flow, Laval nozzle accelerates the principle of air velocity well known in the art, no longer describes.
Specifically, the current velocity controller 60 of the present invention includes：Around the first vector propelling nozzle 11 and the second arrow
The symmetrically arranged multiple bores of madial wall 61 for measuring propelling nozzle 15 reduce control panel 62；Around the He of the first vector propelling nozzle 11
The symmetrically arranged multiple bores of madial wall 61 of second vector propelling nozzle 15 expand control panel 63；And covering bore reduces control
Making sheet 62 and bore expand the elastic covering 64 of control panel 63.Sectional view in Fig. 5 is schematically showed around madial wall 61
Symmetrically arranged four pieces of bores expand control panel 63, and those skilled in the art are accordingly it may be speculated that can also around madial wall 61
It is symmetrical arranged four pieces of bores and reduces control panel 62, in order to represent clear, without display elastic covering in the sectional view in Fig. 5.Bullet
Property covering 64 can be using the larger metal lead-covering of elasticity, it would however also be possible to employ the more preferable rubber covering of resilience, it is each to cover
Space between individual control panel 62,63, forms more smooth nozzle wall, for avoiding flow velocity from losing, and improves air velocity
Advantageously.
Further, although accompanying drawing it can easily be seen that the present invention current velocity controller 60 structure, but in order to
The need for word description and rights protection, the present invention is described in further detail referring to the drawings having been carried out for its concrete structure,
That is, bore diminution control panel 62 relative aperture expansion control panel 63 is arranged on the first vector propelling nozzle 11 and the second vector is promoted
The front of the airflow direction of jet pipe 15, wherein airflow direction are indicated in Fig. 2-4 with arrow F.
Further, bore reduces control panel 62 towards the first vector propelling nozzle 11 and the second vector propelling nozzle 15
The front end of airflow direction be hinged on madial wall 61, bore reduces control panel 62 and deviates from the first vector propelling nozzle 11 and second
The rear end of the airflow direction of vector propelling nozzle 15 is hinged on the first hydraulic stem 65.
Further, bore expands control panel 63 away from the first vector propelling nozzle 11 and the second vector propelling nozzle 15
The rear end of airflow direction be hinged on madial wall 61, bore expands control panel 63 towards the first vector propelling nozzle 11 and second
The front end of the airflow direction of vector propelling nozzle 15 is hinged on the second hydraulic stem 66.
During wind tunnel test, in order to control the gas velocity of the first vector propelling nozzle 11 and the second vector propelling nozzle 15
Degree, can manipulate the first hydraulic stem 65 and the second hydraulic stem 66 adjustment bore reduces control panel 62 and bore expands control panel 63
Angle, so that the shape of the Laval configuration of jet pipe is controlled, to reach the purpose that air velocity is flexibly controlled.
In a word, wind tunnel test system of the invention is promoted to vector by pipeline using the pressure-air of compressed air source and sprayed
Pipe discharges to form jet effect to obtain jet power, has simulated the jet state of vector propelling motor, has overcome existing
Technology can not promote the defect of the aerodynamics situation of model aircraft in tunnel simulation vector, can be carried and pushed away by simulation
Under the dynamical state for entering power, the quantity of wind tunnel test is greatly reduced, wind tunnel test is closer to real conditions, and result precision is more
It is high.Also, the present invention additionally uses that pipeline is entered by wing, to adjust pipeline, electrical heating wire, current velocity controller etc. various
Measure reduce further experimentation cost, improve test accuracy.
It will be appreciated by those skilled in the art that although the present invention is described in the way of multiple embodiments,
It is that not each embodiment only includes an independent technical scheme.So narration is used for the purpose of for the sake of understanding in specification,
The skilled in the art should refer to the specification as a whole is understood, and by technical scheme involved in each embodiment
The mode of not be the same as Example can be mutually combined into understand protection scope of the present invention by regarding as.
Schematical embodiment of the invention is the foregoing is only, the scope of the present invention is not limited to.It is any
Those skilled in the art, the equivalent variations made on the premise of the design of the present invention and principle is not departed from, modification and combination,
The scope of protection of the invention all should be belonged to.
Claims (1)
1. a kind of wind tunnel test system, for promoting model aircraft (10) that experiment is blowed vector in wind-tunnel, its feature
It is, the vector promotes the fuselage interior of model aircraft (10) to be provided with a first vector propelling nozzle (11) and one the
The end of two vector propelling nozzles (15), the first vector propelling nozzle (11) and the second vector propelling nozzle (15) is provided with
Stretch out first jet pipe (12) and the second tail in the adjustable jet direction of the afterbody of the vector propulsion model aircraft (10)
Current velocity controller is provided with jet pipe (16), the first vector propelling nozzle (11) and the second vector propelling nozzle (15)
(60)；The current velocity controller (60) includes：Around the first vector propelling nozzle (11) and the second vector propelling nozzle
(15) the symmetrically arranged multiple bores of madial wall (61) reduce control panel (62)；Around the first vector propelling nozzle (11)
Expand control panel (63) with the symmetrically arranged multiple bores of madial wall (61) of the second vector propelling nozzle (15)；And covering institute
State the elastic covering (64) that bore reduces control panel (62) and bore expansion control panel (63)；The wind tunnel test system bag
One is included to be fixedly connected with the floor (200) of the wind-tunnel and top plate (300) and vertically disposed support column (400) and one
For supporting the vector to promote the pole (500) of model aircraft (10)；One end of the pole (500) and the support column
(400) connect, the other end is fixed on the first vector propelling nozzle (11) and that the vector promotes model aircraft (10)
On fuselage between two vector propelling nozzles (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710508256.7A CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710508256.7A CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
| CN201510712904.1A CN105203291B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system for vector propulsion model aircraft |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510712904.1A Division CN105203291B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system for vector propulsion model aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107271136A true CN107271136A (en) | 2017-10-20 |
| CN107271136B CN107271136B (en) | 2019-10-11 |
Family
ID=54951089
Family Applications (9)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710506953.9A Expired - Fee Related CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| CN201710507559.7A Expired - Fee Related CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| CN201710506983.XA Expired - Fee Related CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
| CN201710506958.1A Expired - Fee Related CN107389296B (en) | 2015-10-28 | 2015-10-28 | A kind of model aircraft for wind-tunnel |
| CN201710507560.XA Expired - Fee Related CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
| CN201510712904.1A Expired - Fee Related CN105203291B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system for vector propulsion model aircraft |
| CN201710508256.7A Expired - Fee Related CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
| CN201710508245.9A Expired - Fee Related CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft |
| CN201710507558.2A Expired - Fee Related CN107271135B (en) | 2015-10-28 | 2015-10-28 | The wind tunnel system of model aircraft test is promoted for vector |
Family Applications Before (6)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710506953.9A Expired - Fee Related CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| CN201710507559.7A Expired - Fee Related CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| CN201710506983.XA Expired - Fee Related CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
| CN201710506958.1A Expired - Fee Related CN107389296B (en) | 2015-10-28 | 2015-10-28 | A kind of model aircraft for wind-tunnel |
| CN201710507560.XA Expired - Fee Related CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
| CN201510712904.1A Expired - Fee Related CN105203291B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system for vector propulsion model aircraft |
Family Applications After (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710508245.9A Expired - Fee Related CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft |
| CN201710507558.2A Expired - Fee Related CN107271135B (en) | 2015-10-28 | 2015-10-28 | The wind tunnel system of model aircraft test is promoted for vector |
Country Status (1)
| Country | Link |
|---|---|
| CN (9) | CN107271137B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110009979A (en) * | 2019-05-07 | 2019-07-12 | 中国人民解放军国防科技大学 | Laval nozzle demonstration device and system |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106441780B (en) * | 2016-09-06 | 2020-11-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Pulse excitation method for flutter flight test of scaling model |
| CN106644361B (en) * | 2016-09-30 | 2018-12-28 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of simple and easy method measuring transonic wind tunnel test section space flow field symmetry |
| CN106599401B (en) * | 2016-11-28 | 2020-03-06 | 北京动力机械研究所 | Adjustable tail nozzle flexibility simulation method based on friction equivalence and orthogonal experiment |
| CN107115678A (en) * | 2017-06-16 | 2017-09-01 | 中电科芜湖通用航空产业技术研究院有限公司 | Model aircraft support meanss |
| CN108750143B (en) * | 2018-06-23 | 2020-05-05 | 中电科芜湖钻石飞机制造有限公司 | Empennage supporting device applied to airplane wind tunnel test |
| CN109186934B (en) * | 2018-11-15 | 2023-09-26 | 中国航空工业集团公司沈阳空气动力研究所 | Space near-field acoustic explosion characteristic high-precision measuring device |
| CN110261057A (en) * | 2019-07-03 | 2019-09-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
| CN113959726B (en) * | 2021-09-21 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Power system of jet engine ground test platform |
| CN113899516B (en) * | 2021-09-30 | 2022-03-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ground simulation device and method for rocket engine jet flow interference effect |
| CN114152402B (en) * | 2022-02-07 | 2022-05-31 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test water content measuring device |
| CN115436010B (en) * | 2022-11-08 | 2023-02-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet pipe thrust measurement test method based on afterbody and jet pipe integrated design |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1130375A1 (en) * | 2000-01-18 | 2001-09-05 | EADS Deutschland Gmbh | System and method for measuring aircraft flight data |
| JP2008008686A (en) * | 2006-06-27 | 2008-01-17 | Matsushita Electric Works Ltd | Flow field measuring method using particle tracking method |
| RU2477460C1 (en) * | 2011-07-14 | 2013-03-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Method of defining factors of aerodynamic forces and moments at steady-state rotation of aircraft model and device to this end |
| CN103048110A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Experimental facility for realizing thrust deflexion and experimental technique thereof |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2192942B (en) * | 1986-06-05 | 1991-01-16 | British Aerospace | Powerplant simulators for aircraft |
| RU1779969C (en) * | 1990-10-14 | 1992-12-07 | Центральный аэрогидродинамический институт им.проф.Н.Е.Жуковского | Method and apparatus for determining aerodynamic forces and moments during aperiodic motion of mock-up model |
| US5395073A (en) * | 1992-03-13 | 1995-03-07 | Freewing Aerial Robotics Corporation | STOL/VTOL free wing aircraft with articulated tail boom |
| RU2232281C1 (en) * | 2002-12-26 | 2004-07-10 | Открытое акционерное общество Авиамоторный научно-технический комплекс "Союз" | Air-jet engine two-dimensional exit nozzle |
| RU2287796C1 (en) * | 2005-04-27 | 2006-11-20 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт им. проф. Н.Е. Жуковского" (ФГУП "ЦАГИ") | Device for measurement of aerodynamic force vector's components and of moment |
| CN101934152B (en) * | 2010-01-25 | 2012-01-25 | 朱一帆 | Vectoring nozzle model jet aircraft |
| CN102305699A (en) * | 2011-05-19 | 2012-01-04 | 北京航空航天大学 | Wind tunnel experiment system for free flight model |
| CN102519643A (en) * | 2011-12-13 | 2012-06-27 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Six-component force measuring system of engine vector spray pipe |
| CN202501972U (en) * | 2012-04-05 | 2012-10-24 | 黄帅文 | Airplane model force-measuring wind tunnel |
| CN104033279B (en) * | 2014-06-06 | 2016-03-30 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of dual vector jet pipe |
| CN104132795B (en) * | 2014-08-11 | 2016-06-15 | 厦门大学 | A kind of model cable support system realizing wind-tunnel virtual flight |
| CN204433072U (en) * | 2015-01-22 | 2015-07-01 | 曹启武 | A kind of canard with vector spout and a kind of aircraft |
-
2015
- 2015-10-28 CN CN201710506953.9A patent/CN107271137B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710507559.7A patent/CN107152996B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710506983.XA patent/CN107340117B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710506958.1A patent/CN107389296B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710507560.XA patent/CN107389292B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201510712904.1A patent/CN105203291B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710508256.7A patent/CN107271136B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710508245.9A patent/CN107356403B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710507558.2A patent/CN107271135B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1130375A1 (en) * | 2000-01-18 | 2001-09-05 | EADS Deutschland Gmbh | System and method for measuring aircraft flight data |
| JP2008008686A (en) * | 2006-06-27 | 2008-01-17 | Matsushita Electric Works Ltd | Flow field measuring method using particle tracking method |
| RU2477460C1 (en) * | 2011-07-14 | 2013-03-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Method of defining factors of aerodynamic forces and moments at steady-state rotation of aircraft model and device to this end |
| CN103048110A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Experimental facility for realizing thrust deflexion and experimental technique thereof |
Non-Patent Citations (1)
| Title |
|---|
| 贾毅 等: "低速风洞推力矢量试验技术研究", 《实验流体力学》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110009979A (en) * | 2019-05-07 | 2019-07-12 | 中国人民解放军国防科技大学 | Laval nozzle demonstration device and system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107356403B (en) | 2019-10-11 |
| CN105203291A (en) | 2015-12-30 |
| CN107340117B (en) | 2019-10-11 |
| CN107389296A (en) | 2017-11-24 |
| CN107271137B (en) | 2019-09-13 |
| CN105203291B (en) | 2017-07-28 |
| CN107152996A (en) | 2017-09-12 |
| CN107152996B (en) | 2019-09-13 |
| CN107271135A (en) | 2017-10-20 |
| CN107389292B (en) | 2019-09-13 |
| CN107389292A (en) | 2017-11-24 |
| CN107271135B (en) | 2019-09-13 |
| CN107356403A (en) | 2017-11-17 |
| CN107271137A (en) | 2017-10-20 |
| CN107389296B (en) | 2019-09-13 |
| CN107271136B (en) | 2019-10-11 |
| CN107340117A (en) | 2017-11-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105203291B (en) | A kind of wind tunnel test system for vector propulsion model aircraft | |
| CN102607799B (en) | Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method | |
| CN105173128B (en) | The test method of thermal environment in simulated flight device flight course | |
| CN114878133B (en) | Variable Mach number test method in supersonic free jet | |
| Bradley et al. | A conceptual study of leading-edge-vortex enhancement by blowing | |
| CN105258915A (en) | Sideslip angle-varying blade belly supporting device in high-speed wind tunnel test | |
| CN107525647B (en) | A kind of dynamical bifurcation generating device of aerodynamic stalling | |
| Chanetz et al. | Experimental Aerodynamics | |
| Cheung et al. | Development of mission adaptive digital composite aerostructure technologies (MADCAT) | |
| Deters et al. | Slipstream measurements of small-scale propellers at low reynolds numbers | |
| Milholen et al. | Enhancements to the FAST-MAC circulation control model and recent high-Reynolds number testing in the National Transonic Facility | |
| CN114942116B (en) | Method for simulating supersonic flow field of front fuselage of aircraft with layout of air inlet channel under abdomen | |
| CN215495659U (en) | Device for demonstrating slip flow side effect of propeller | |
| CN213658218U (en) | Jet flow test device for wind tunnel model | |
| CN104483090B (en) | Dynamitic control and measurement method | |
| CN109726432B (en) | Aircraft bottom structure temperature calculation method | |
| Chan et al. | Thrust removal methodology for the FAST-MAC circulation control model tested in the national transonic facility | |
| Van Empelen et al. | Effect of Engine Integration on a 4.6%-Scale Flying-V Subsonic Transport | |
| Zhang et al. | Trajectory optimization of a deflectable nose missile | |
| Ren et al. | Research on the influence of fluidic thrust vector parameters on the single expansion ramp nozzle of the air-breathing hypersonic vehicle | |
| Rao et al. | Analysis on Aerodynamic Performance of Single-skinned Parawing in the Hypersonic Rarefied flow | |
| Wu et al. | Numerical modeling of Coanda jet controlled nacelle configurations | |
| Yu et al. | Numerical simulation method with engine power and analysis of jet interaction | |
| Chan et al. | Thrust Removal Scheme for the FAST-MAC Circulation Control Model Tested in the National Transonic Facility | |
| Liu et al. | Wind and Water Tunnel Equipment |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191011 Termination date: 20201028 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |