CN107340117B - A kind of wind tunnel test model aircraft - Google Patents
A kind of wind tunnel test model aircraft Download PDFInfo
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- CN107340117B CN107340117B CN201710506983.XA CN201710506983A CN107340117B CN 107340117 B CN107340117 B CN 107340117B CN 201710506983 A CN201710506983 A CN 201710506983A CN 107340117 B CN107340117 B CN 107340117B
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- propelling nozzle
- vector propelling
- vector
- wind tunnel
- model aircraft
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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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- 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
-
- 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
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- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of wind tunnel test model aircrafts, for test to be blowed in wind-tunnel, the fuselage interior of the wind tunnel test model aircraft is provided with a first vector propelling nozzle and a second vector propelling nozzle, the end of the first vector propelling nozzle and the second vector propelling nozzle is provided with the first jet pipe and the second jet pipe for stretching out the adjustable jet direction of afterbody of the wind tunnel test model aircraft, is provided with current velocity controller in the first vector propelling nozzle and the second vector propelling nozzle.Wind tunnel test model aircraft of the invention discharges to form jet effect to obtain jet power to vector propelling nozzle using the pressure-air of compressed air source by pipeline, the jet state for having simulated vector propelling motor, overcoming the prior art can not be in the defect of the aerodynamics situation of tunnel simulation vector propulsion model aircraft.
Description
Technical field
The present invention relates to a kind of aviation aerodynamics testing equipment, especially a kind of wind tunnel test model aircraft.
Background technique
Wind tunnel test is to be fixed on model aircraft or its component, such as fuselage, wing etc. according to aerodynamic principle
In wind-tunnel, model aircraft or its component are flowed through by applying artificial airflow, the state of flight of aerial various complexity is simulated with this, is 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 require largely to be tested in wind-tunnel.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 for evaluating each aircraft in addition to such as speed, height, aircraft weight and is started
Outside the elements such as machine thrust, most important standard first is that the aerodynamic quality of aircraft.The full machine wind tunnel test of aircraft needs will be whole
A model aircraft is supported in wind-tunnel, measures each component of entire model aircraft by pressure test equipment under artificial airflow environment
Pressure distribution data under the conditions of particular flight obtains the dynamic characteristic of aircraft with this.
Vector Push Technology refer to aircraft engine thrust by thrust component that the deflection of jet pipe or tail jet generates come
It substitutes the control surface of former aircraft or enhances the operating function of aircraft, the technology of real-time control is carried out to the flight of aircraft.Vector pushes away
A part of motor power can be allowed to become steering force into technology, instead of or part replace control surface, to greatly reduce thunder
Up to reflective surface area；Regardless of the angle of attack is much and how low flying speed is, aircraft can all be manipulated using this part steering force, this just increases
The navigability of aircraft is added.Due to directly generating steering force, and magnitude 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
It is advantageous, the resistance of aircraft can also reduced, structure mitigates again.It therefore, the use of vector Push Technology is that solution design is contradictory
Optimal selection.
However during carrying out the full machine wind tunnel test of model aircraft, due to tunnel size and model aircraft size
Limitation, it is impossible to real engine is installed inside model aircraft, thus for using vector Push Technology
For model aircraft, it is not possible 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 itself is without power, when wind tunnel test
It is the speed using air flow with respect to model aircraft come simulated flight state.But for using 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 a large amount of static test
Then discrete status data obtains the approximate dynamic number for continuously adjusting propulsive force size and Orientation by way of interpolation
According to tested number is very huge, and time-consuming and laborious expensive and test result is still approximately that accuracy is poor.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of wind tunnel test model aircrafts, are mentioned so that front is reduced or avoided
To the problem of.
Specifically, the present invention provides a kind of wind tunnel test model aircrafts, for test, institute to be blowed in wind-tunnel
The fuselage interior for stating wind tunnel test model aircraft is provided with a first vector propelling nozzle and a second vector propelling nozzle,
The end of the first vector propelling nozzle and the second vector propelling nozzle, which is provided with, stretches out the wind tunnel test model aircraft
The first jet pipe and the second jet pipe of the adjustable jet direction of afterbody, the first vector propelling nozzle and the second vector
Current velocity controller is provided in propelling nozzle；The current velocity controller include: around the first vector propelling nozzle and
The symmetrically arranged multiple bores of the inner sidewall of second vector propelling nozzle reduce control panel；Around the first vector propelling nozzle
Expand control panel with the symmetrically arranged multiple bores of the inner sidewall of the second vector propelling nozzle；And the covering bore reduces control
Making sheet and the bore expand the elastic covering of control panel；The bore reduces the relatively described bore expansion control panel of control panel and sets
Set the front of the airflow direction in the first vector propelling nozzle and the second vector propelling nozzle；The bore reduces control panel
It is hinged on the inner sidewall towards the front end of the first vector propelling nozzle and the airflow direction of the second vector propelling nozzle,
The bore reduces control panel away from the rear end of the first vector propelling nozzle and the airflow direction of the second vector propelling nozzle
It is hinged on the first hydraulic stem.
Wind tunnel test model aircraft of the invention is promoted by pipeline to vector using the pressure-air of compressed air source to be 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 be had by simulation and be pushed away in the defect of the aerodynamics situation of tunnel simulation vector propulsion model aircraft
Into under the dynamical state of 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, it is various by wing entrance, adjustment pipeline, electric heating wire, current velocity controller etc. that the present invention additionally uses pipeline
Measure further reduced experimentation cost, improve test accuracy.
Detailed description of the invention
The following drawings are only intended to schematically illustrate and explain the present invention, not delimit the scope of the invention.Wherein,
The structural schematic diagram of the wind tunnel test model aircraft of a specific embodiment according to the present invention is shown in Fig. 1；
The side view of the wind tunnel test model aircraft of a specific embodiment according to the present invention is shown in Fig. 2；
The top view of the wind tunnel test model aircraft of another specific embodiment according to the present invention is shown in Fig. 3；
The flow control in the wind tunnel test model aircraft of another specific embodiment according to the present invention is shown in Fig. 4
The enlarged diagram of device；
The A-A cross-sectional view of current velocity controller shown in Fig. 4 is shown in Fig. 5.
Specific embodiment
For a clearer understanding of the technical characteristics, objects and effects of the present invention, this hair of Detailed description of the invention is now compareed
Bright specific embodiment.Wherein, identical component uses identical label.
The structural schematic diagram of the wind tunnel test model aircraft of a specific embodiment according to the present invention is shown in Fig. 1,
The fuselage interior of the wind tunnel test model aircraft 10 is provided with a first vector propelling nozzle 11 and second vector promotes
The end of jet pipe 15, the first vector propelling nozzle 11 and the second vector propelling nozzle 15, which is provided with, stretches out the wind tunnel test
The first jet pipe 12 and the second jet pipe 16 of the adjustable jet direction of the afterbody of model aircraft 10.That is, in order to
Overcome the prior art that can not provide in the defect of the aerodynamics situation of tunnel simulation vector propulsion model aircraft, the present invention
A kind of model aircraft of special construction, which has the jet state of analog vector propelling motor, in wind-tunnel
Jet power is generated during test.That is, in above-mentioned wind tunnel test model aircraft 10, setting there are two vector propelling nozzle 11,
15, the two vector propelling nozzles 11,15 can generate 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 vector propelling nozzle 11,15 of the invention
It can be only similar to the such jet-stream wind of jet engine, itself, without rotary part, is not real jet hair
Motivation, thus two jet pipes 12,16 nor the adjustable jet direction of real structure jet pipe, the two jet pipes 12,
16 be only the conical pipeline of fixed shape, which is mounted on the tail end of vector propelling nozzle 11,15, can be by normal
The hydraulic or electromagnetically-operated component (not shown) of rule controls its deflection angle, to control the direction of jet.It is sprayed about tail
The control of 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
It states.
The side view of the wind tunnel test model aircraft of a specific embodiment according to the present invention is shown in Fig. 2；Such as figure
Shown, wind tunnel test model aircraft of the invention can be used in the wind-tunnel of wind tunnel test system to shown in FIG. 1 of the invention
Test is blowed in wind tunnel test model aircraft 10, and the wind tunnel test system includes one and the floor 200 of wind-tunnel and top plate
300 are fixedly connected and vertically disposed support column 400 and one are used to support the strut of the wind tunnel test model aircraft 10
500；One end of strut 500 is connect with support column 400, and the first vector that the other end is fixed on wind tunnel test model aircraft 10 promotes
On fuselage between jet pipe 11 and the second vector propelling nozzle 15 (Fig. 3).
Further, as shown in figure 3, its wind tunnel test that another specific embodiment according to the present invention is shown flies
The top view of machine model；Wherein, the wind tunnel test system further comprise be set to the compressed air source 4 of the outside of wind-tunnel with
And for the compressed air source 4 to be connect with the first vector propelling nozzle 11 and the second vector propelling nozzle 15 respectively
First pipe 51 and second pipe 52.That is, generating injection to simulate jet engine by two vector propelling nozzles 11,15
Air-flow, the present invention are provided with compressed air source 4, are promoted by pipeline 51,52 to vector using the pressure-air of compressed air source 4
The release of jet pipe 11,15 forms high-speed flow, forms jet effect to obtain jet power.In order to clearly show that in Fig. 3, depict
Two compressed air sources 4, in practical work process, the two compressed air sources 4 can be shared, that is, only need a compression empty
Gas source 4.Certainly, it will be appreciated by those skilled in the art that when practical wind tunnel test, about compressed air source 4
Pressure size, the length of pipeline 51,52 and vector propelling nozzle 11,15, diameter etc. are required to accurately calculate and be controlled, and are used
To form the Jet Stream for obtaining required flow velocity, flow.Those skilled in the art can be on the basis of design proposed by the present invention
On further calculated and controlled according to the actual situation, it is this calculating and control can use existing routine techniques hand
Section, nor the emphasis that the present invention is paid close attention to, also no longer repeats 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 enter wind tunnel test aircraft mould from the both ends of two wings 20 of wind tunnel test model aircraft 10
The fuselage interior of type 10 is simultaneously separately connected the first vector propelling nozzle 11 and the second vector propelling nozzle 15.It can from Fig. 2
Out, this arrangement through this embodiment does not increase any additional component, only in wind-tunnel in the vertical direction of wind-tunnel
The horizontal distalmost end of flight test vehicle model 10 is connected with pipeline 51,52 (Fig. 3), therefore for the gas of wind tunnel test model aircraft 10
The interference that dynamic shape generates is minimum, help to obtain 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 solenoid 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 first pipe 51 and second pipe 52
Flow, pressure are since there may be certain differences for the factors such as line size, being completely embedded property, and if necessary to simulation, two are started
The state of the same thrust of machine then needs the air mass flow and flow velocity of point-device control first pipe 51 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 logical
Crossing the opening adjustment pipeline 30 of solenoid valve 40 can be so that in the first vector propelling nozzle 11 and the second vector propelling nozzle 15
Air pressure reaches consistent, it is easy to reach identical thrust by this small design and control, reduce control and require, greatly
Regulation time and cost have been saved greatly.
In another specific embodiment, set on the outside of the first vector propelling nozzle 11 and the second vector propelling nozzle 15
It is equipped with electric heating wire 50.Can be certainly, prior with the condition of high temperature of simple analog jet engine by electric heating wire 50,
First vector propelling nozzle 11 and the second vector propelling nozzle 15 can be heated by electric 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 be it is very difficult, very high for the equipment requirement for generating compressed air, the present embodiment is set by electric heating wire 50
The equipment requirement that can partially reduce compressed air source 4 is set, cost has been saved.
Likewise, in order to further increase 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 set, specific structure is as shown in Figure 4,5.
That is, the flow velocity in the wind tunnel test model aircraft of another specific embodiment according to the present invention is shown in Fig. 4
The enlarged diagram of control device；The A-A cross-sectional view of current velocity controller shown in Fig. 4 is shown in Fig. 5, can be clear from Figure 4 and 5
Chu finds out that current velocity controller 60 of the invention simulates the structure type of Laval nozzle, forms the expansion of middle shrinkage both ends
Acceleration air-flow structure type, Laval nozzle accelerate air velocity principle it is well known in the art, no longer describe.
Specifically, the current velocity controller 60 of the invention includes: around the first vector propelling nozzle 11 and the second arrow
The symmetrically arranged multiple bores of inner sidewall 61 for measuring propelling nozzle 15 reduce control panel 62；Around 11 He of the first vector propelling nozzle
The symmetrically arranged multiple bores of the inner sidewall 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.Cross-sectional view in Fig. 5 is schematically showed around inner sidewall 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 be with around inner sidewall 61
It is symmetrical arranged four pieces of bores and reduces control panel 62, in order to indicate clear, without display elastic covering in the cross-sectional view in Fig. 5.Bullet
Property covering 64 can be using the biggish metal lead-covering of elasticity, can also be each to cover using springing back better rubber covering
Gap between a control panel 62,63 forms more smooth nozzle wall, for avoiding flow velocity from losing, improves air velocity
Advantageously.
Further, although attached drawing it can easily be seen that current velocity controller 60 of the invention structure, in order to
The needs of verbal description and rights protection, the present invention its specific structure has been carried out referring to attached drawing it is described in further detail,
That is, bore, which reduces 62 relative aperture of control panel, expands the setting of control panel 63 in the first vector propelling nozzle 11 and the propulsion of the second vector
The front of the airflow direction of jet pipe 15, wherein airflow direction is 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 inner sidewall 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 inner sidewall 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 flexibly controls.
In short, wind tunnel test model aircraft of the invention is pushed away by pipeline to vector using the pressure-air of compressed air source
It discharges to form jet effect to obtain jet power into jet pipe, has simulated the jet state of vector propelling motor, overcome
The prior art can not can pass through in the defect of the aerodynamics situation of tunnel simulation vector propulsion model aircraft and simulate band
Under propulsive dynamical state, the quantity of wind tunnel test is greatly reduced, wind tunnel test is closer to real conditions, as a result accurately
Du Genggao.Also, the present invention additionally uses pipeline by wing entrance, adjustment pipeline, electric heating wire, current velocity controller etc.
Various measures further reduced 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 contains an independent technical solution.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 solution involved in each embodiment
Regard as and can be combined with each other into the modes of different embodiments to understand protection scope of the present invention.
The foregoing is merely the schematical specific embodiment of the present invention, the range being not intended to limit the invention.It is any
Those skilled in the art, made equivalent variations, modification and combination under the premise of not departing from design and the principle of the present invention,
It should belong to the scope of protection of the invention.
Claims (1)
1. a kind of wind tunnel test model aircraft, for test, the wind tunnel test model aircraft (10) to be blowed in wind-tunnel
Fuselage interior be provided with a first vector propelling nozzle (11) and a second vector propelling nozzle (15), first arrow
The end of amount propelling nozzle (11) and the second vector propelling nozzle (15), which is provided with, stretches out the wind tunnel test model aircraft (10)
Afterbody adjustable jet direction the first jet pipe (12) and the second jet pipe (16), which is characterized in that described first
Current velocity controller (60) are provided in vector propelling nozzle (11) and the second vector propelling nozzle (15)；The flow control dress
It includes: symmetrical around the inner sidewall (61) of the first vector propelling nozzle (11) and the second vector propelling nozzle (15) for setting (60)
The multiple bores being arranged reduce control panel (62)；Around the first vector propelling nozzle (11) and the second vector propelling nozzle
(15) the symmetrically arranged multiple bores of inner sidewall (61) expand control panel (63)；And the covering bore reduces control panel
(62) and the bore expand control panel (63) elastic covering (64)；The bore reduces control panel (62) relatively described bore
Expand control panel (63) setting in the airflow direction of the first vector propelling nozzle (11) and the second vector propelling nozzle (15)
Front；The bore reduces control panel (62) towards the first vector propelling nozzle (11) and the second vector propelling nozzle
(15) front end of airflow direction is hinged on the inner sidewall (61), and the bore reduces control panel (62) and deviates from described first
The rear end of the airflow direction of vector propelling nozzle (11) and the second vector propelling nozzle (15) is hinged on the first hydraulic stem (65).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710506983.XA CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710506983.XA CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
| 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 |
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| CN201510712904.1A Division CN105203291B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system for vector propulsion model aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN107340117A CN107340117A (en) | 2017-11-10 |
| CN107340117B true CN107340117B (en) | 2019-10-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710507559.7A Expired - Fee Related CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| CN201710508256.7A Expired - Fee Related CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
| 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 |
| CN201710506953.9A Expired - Fee Related CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| CN201710506958.1A Expired - Fee Related CN107389296B (en) | 2015-10-28 | 2015-10-28 | A kind of model aircraft for wind-tunnel |
| 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 |
| CN201710506983.XA Expired - Fee Related CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
| CN201710508245.9A Expired - Fee Related CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft |
| CN201710507560.XA Expired - Fee Related CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710507559.7A Expired - Fee Related CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| CN201710508256.7A Expired - Fee Related CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
| 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 |
| CN201710506953.9A Expired - Fee Related CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| CN201710506958.1A Expired - Fee Related CN107389296B (en) | 2015-10-28 | 2015-10-28 | A kind of model aircraft for wind-tunnel |
| 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 |
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| CN201710508245.9A Expired - Fee Related CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft |
| CN201710507560.XA Expired - Fee Related CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
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| 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 |
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| 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 |
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| 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 |
| 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 |
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| 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 CN201710507559.7A patent/CN107152996B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710508256.7A patent/CN107271136B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710507558.2A patent/CN107271135B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710506953.9A patent/CN107271137B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710506958.1A patent/CN107389296B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201510712904.1A patent/CN105203291B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710506983.XA patent/CN107340117B/en not_active Expired - Fee Related
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Also Published As
| Publication number | Publication date |
|---|---|
| CN107356403B (en) | 2019-10-11 |
| CN105203291B (en) | 2017-07-28 |
| CN107340117A (en) | 2017-11-10 |
| CN107152996A (en) | 2017-09-12 |
| CN107389292A (en) | 2017-11-24 |
| CN107152996B (en) | 2019-09-13 |
| CN107356403A (en) | 2017-11-17 |
| CN107271137A (en) | 2017-10-20 |
| CN107389296A (en) | 2017-11-24 |
| CN107389296B (en) | 2019-09-13 |
| CN107271136B (en) | 2019-10-11 |
| CN107271135A (en) | 2017-10-20 |
| CN105203291A (en) | 2015-12-30 |
| CN107271135B (en) | 2019-09-13 |
| CN107389292B (en) | 2019-09-13 |
| CN107271136A (en) | 2017-10-20 |
| CN107271137B (en) | 2019-09-13 |
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