CN107389296A - A kind of model aircraft for wind-tunnel - Google Patents
A kind of model aircraft for wind-tunnel Download PDFInfo
- Publication number
- CN107389296A CN107389296A CN201710506958.1A CN201710506958A CN107389296A CN 107389296 A CN107389296 A CN 107389296A CN 201710506958 A CN201710506958 A CN 201710506958A CN 107389296 A CN107389296 A CN 107389296A
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- Prior art keywords
- propelling nozzle
- vector propelling
- vector
- model aircraft
- tunnel
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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
-
- 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
Abstract
The invention discloses a kind of model aircraft for wind-tunnel, for experiment to be blowed in wind-tunnel, the fuselage interior of the 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 first jet pipe and the second jet pipe in the adjustable jet direction for the afterbody for stretching out the model aircraft, and current velocity controller is provided with the first vector propelling nozzle and the second vector propelling nozzle.The model aircraft for wind-tunnel of the present invention discharges to form jet effect to obtain jet power by pipeline using the pressure-air of compressed air source to vector propelling nozzle, simulated the jet state of vector propelling motor, overcome prior art can not tunnel simulation vector promote model aircraft aerodynamics situation the defects of.
Description
Technical field
The present invention relates to a kind of aviation aerodynamics testing equipment, especially a kind of model aircraft for wind-tunnel.
Background technology
Wind tunnel test is according to aerodynamic principle, and model aircraft or its part, such as fuselage, wing etc. are fixed on
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 for largely being 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 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 aircraft engine thrust by thrust component caused 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 pushes 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 does not have power in itself, when wind tunnel test
It is come simulated flight state using speed of the air flow with respect to model aircraft.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 utilize substantial amounts of static test to obtain
Discrete status data, the approximate dynamic number of continuous adjustment propulsive force size and Orientation is then obtained 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
The technical problem to be solved in the present invention is to provide a kind of model aircraft for wind-tunnel, so that above institute is reduced or avoided
The problem of mentioning.
Specifically, the invention provides a kind of model aircraft for wind-tunnel, for experiment to be blowed in wind-tunnel,
The fuselage interior of the model aircraft is provided with a first vector propelling nozzle and a second vector propelling nozzle, and described
The end of one vector propelling nozzle and the second vector propelling nozzle is provided with the adjustable of the afterbody that stretches out the model aircraft
Set in first jet pipe and the second jet pipe in jet direction, the first vector propelling nozzle and the second vector propelling nozzle
There is current velocity controller；The current velocity controller includes：Spray is promoted around the first vector propelling nozzle and the second vector
The symmetrically arranged multiple bores of madial wall of pipe reduce control panel；Promoted around the first vector propelling nozzle and the second vector
The symmetrically arranged multiple bores of madial wall of jet pipe expand control panel；And the covering bore reduces control panel and the bore
Expand the elastic covering of control panel；The bore reduces the relatively described bore expansion control panel of control panel and is arranged on first arrow
Measure the front of the airflow direction of propelling nozzle and the second vector propelling nozzle；The bore reduces control panel away from the described first arrow
The rear end of the airflow direction of amount propelling nozzle and the second vector propelling nozzle is hinged on the first hydraulic stem；The bore expands control
Making sheet is hinged on the second hydraulic pressure towards the front end of the first vector propelling nozzle and the airflow direction of the second vector propelling nozzle
On bar.
The model aircraft for wind-tunnel of the present invention is promoted using the pressure-air of compressed air source by pipeline to vector
Jet pipe discharges to form jet effect to obtain jet power, has simulated the jet state of vector propelling motor, overcomes existing
Have technology can not tunnel simulation vector promote model aircraft aerodynamics situation the defects of, can by simulation carry
Under the dynamical state of propulsive force, the quantity of wind tunnel test is greatly reduced, wind tunnel test is closer to real conditions, result precision
It is higher.Also, the present invention additionally uses pipeline and is entered by wing, adjusts pipeline, electrical heating wire, current velocity controller etc. respectively
Kind measure 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 of the model aircraft for wind-tunnel of a specific embodiment according to the present invention is shown in Fig. 1
Figure；
The side view of the model aircraft for wind-tunnel of a specific embodiment according to the present invention is shown in Fig. 2；
The top view of the model aircraft for wind-tunnel of another specific embodiment according to the present invention is shown in Fig. 3；
The flow velocity control in the model aircraft for wind-tunnel according to another specific embodiment of the present invention is shown in Fig. 4
The enlarged diagram of device processed；
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 the effect of the present invention is more clearly understood, now control illustrates this hair
Bright embodiment.Wherein, identical part uses identical label.
The structural representation of the model aircraft for wind-tunnel of a specific embodiment according to the present invention is shown in Fig. 1
Figure, the fuselage interior of the model aircraft 10 are provided with a first vector propelling nozzle 11 and a second vector propelling nozzle
15, the end of the first vector propelling nozzle 11 and the second vector propelling nozzle 15, which is provided with, stretches out the model aircraft 10
First jet pipe 12 and the second jet pipe 16 in the adjustable jet direction of afterbody.That is, in order to overcome prior art
Can not tunnel simulation vector promote model aircraft aerodynamics situation the defects of, the invention provides a kind of special knot
The model aircraft of structure, the model carries the jet state that can simulate vector propelling motor, to be produced during wind tunnel test
Raw jet power.That is, in above-mentioned model aircraft 10, two vector propelling nozzles 11,15, the two vector propelling nozzles are provided with
11st, 15 jet-stream wind can be produced as jet engine, and the jet direction of its jet pipe 12,16 is to adjust
's.Certainly, it will be understood by those skilled in the art that the vector propelling nozzle 11,15 of the present invention can simply be similar to jet hair
The such jet-stream wind of motivation, itself is not real jet engine without rotary part, therefore two jet pipes
12nd, 16 nor the jet pipe in the adjustable jet direction of real structure, the two jet pipes 12,16 are only the cone of solid shape
Shape pipeline, the conical pipeline are arranged on the tail end of vector propelling nozzle 11,15, hydraulic pressure that can be by routine or electromagnetically-operated portion
Part (not shown) controls its deflection angle, so as to control the direction of jet.Control on the jet direction of jet pipe 12,16
System can use routine techniques, not be the emphasis that the present invention is paid close attention to, this is no longer going to repeat them.
The side view of the model aircraft for wind-tunnel of a specific embodiment according to the present invention is shown in Fig. 2；Such as
Shown in figure, the model aircraft for wind-tunnel of the invention can be used in the wind-tunnel of wind tunnel test system to this hair shown in Fig. 1
Experiment is blowed in bright model aircraft 10, and the wind tunnel test system includes one and consolidated with the floor 200 of wind-tunnel and top plate 300
Fixed connection and vertically disposed support column 400 and a pole 500 for being used to support the model aircraft 10；Pole 500
One end is connected with support column 400, and the other end is fixed on the first vector propelling nozzle 11 of model aircraft 10 and the second vector promotes
On fuselage between jet pipe 15 (Fig. 3).
Further, as shown in figure 3, it is shown is used for wind-tunnel according to another specific embodiment of the present invention
The top view of model aircraft；Wherein, the wind tunnel test system further comprises the compressed air source 4 for the outside for being arranged at wind-tunnel
And for the compressed air source 4 to be connected with the first vector propelling nozzle 11 and the second vector propelling nozzle 15 respectively
The first pipeline 51 and second pipe 52.That is, spray is produced in order to simulate jet engine by two vector propelling nozzles 11,15
Emanate stream, the present invention is provided with compressed air source 4, is pushed away using the pressure-air of compressed air source 4 by pipeline 51,52 to vector
Enter the release of jet pipe 11,15 and form high velocity air, form jet effect to obtain jet power.In order to clearly show that in Fig. 3, draw
Two compressed air sources 4, in practical work process, the two compressed air sources 4 can share, that is, only need a compression
Air-source 4.Certainly, it will be appreciated by those skilled in the art that when actual wind tunnel test, on compressed air source 4
Pressure size, the length of pipeline 51,52 and vector propelling nozzle 11,15, diameter etc. be required for it is accurate calculate and control,
To form the Jet Stream of flow velocity, flow needed for acquisition.Those skilled in the art can be in the base of design proposed by the present invention
Further calculated and controlled according to actual conditions on plinth, this calculating and control can use existing routine techniques hand
Section, 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 enter the fuselage interior of model aircraft 10 simultaneously from the both ends of two wings 20 of model aircraft 10
The first vector propelling nozzle 11 and the second vector propelling nozzle 15 are connected respectively.From figure 2 it can be seen that pass through the present embodiment
This arrangement, do not increase any extra part in the vertical direction of wind-tunnel, it is only farthest in the level of model aircraft 10
End is connected with pipeline 51,52 (Fig. 3), therefore minimum for being disturbed caused by the aerodynamic configuration of model aircraft 10, is advantageous 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 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 the air mass flow and flow velocity of the first pipeline 51 of point-device control and second pipe 52 are needed,
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
The opening adjustment of magnetic valve 40 can of pipeline 30 is crossed to cause in the first vector propelling nozzle 11 and the second vector propelling nozzle 15
Air pressure reaches consistent, it is easy to reaches identical thrust by this small design and controls, 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, lasting supersonic speed spray is provided 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 stream in the model aircraft for wind-tunnel according to another specific embodiment of the present invention is shown in Fig. 4
The enlarged diagram of velocity control device；The A-A sectional views of current velocity controller shown in Fig. 4 are shown in Fig. 5, can be with from Figure 4 and 5
The current velocity controller 60 for being apparent from the present invention simulates the structure type of Laval nozzle, forms the expansion of middle shrinkage both ends
The structure type for the acceleration air-flow opened, Laval nozzle accelerate the principle of air velocity well known in the art, no longer described.
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 use the larger metal lead-covering of elasticity, can also use the more preferable rubber covering of resilience, to cover respectively
Space between individual control panel 62,63, more smooth nozzle wall is formed, for avoiding flow velocity from losing, improve air velocity
Advantageously.
Further, although accompanying drawing it can easily be seen that the present invention current velocity controller 60 structure, in order to
The needs of 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 promotes
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 expansion control panel 63 deviates 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, the first hydraulic stem 65 can be manipulated and the second hydraulic stem 66 adjustment bore reduces control panel 62 and bore expands control panel 63
Angle, so as to control the shape of the Laval configuration of jet pipe, to reach the purpose that air velocity flexibly controls.
In a word, the model aircraft for wind-tunnel of the invention using the pressure-air of compressed air source by pipeline to vector
Propelling nozzle discharges to form jet effect to obtain jet power, has simulated the jet state of vector propelling motor, has overcome
Prior art can not can pass through simulation tunnel simulation vector promotes the aerodynamics situation of model aircraft the defects of
With the quantity of wind tunnel test under propulsive dynamical state, is greatly reduced, wind tunnel test is as a result accurate closer to real conditions
Exactness is higher.Also, the present invention additionally uses such as pipeline and is entered by wing, adjusts pipeline, electrical heating wire, current velocity controller
Experimentation cost is reduce further etc. various measures, improves 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 modes of different embodiments can be mutually combined into understand protection scope of the present invention by regarding as.
The schematical embodiment of the present invention is the foregoing is only, is not limited to the scope of the present invention.It is any
Those skilled in the art, equivalent variations, modification and the combination made on the premise of the design of the present invention and principle is not departed from,
The scope of protection of the invention all should be belonged to.
Claims (1)
- A kind of 1. model aircraft for wind-tunnel, for experiment to be blowed in wind-tunnel, it is characterised in that the model aircraft (10) fuselage interior is provided with a first vector propelling nozzle (11) and a second vector propelling nozzle (15), and described The end of one vector propelling nozzle (11) and the second vector propelling nozzle (15) is provided with the machine for stretching out the model aircraft (10) First jet pipe (12) and the second jet pipe (16) in the adjustable jet direction of body afterbody, the first vector propelling nozzle (11) With the second vector propelling nozzle (15) in be provided with current velocity controller (60)；The current velocity controller (60) includes：Surround The first vector propelling nozzle (11) and the symmetrically arranged multiple bores of madial wall (61) of the second vector propelling nozzle (15) Reduce control panel (62)；Around the first vector propelling nozzle (11) and the madial wall (61) of the second vector propelling nozzle (15) Symmetrically arranged multiple bores expand control panel (63)；And the covering bore reduces control panel (62) and the bore expands The elastic covering (64) of control panel (63)；The bore reduces the relatively described bore of control panel (62) and expands control panel (63) setting In the first vector propelling nozzle (11) and the front of the airflow direction of the second vector propelling nozzle (15)；The bore reduces Control panel (62) is away from the first vector propelling nozzle (11) and the rear end of the airflow direction of the second vector propelling nozzle (15) It is hinged on the first hydraulic stem (65)；The bore expands control panel (63) towards the first vector propelling nozzle (11) and the The front end of the airflow direction of two vector propelling nozzles (15) is hinged on the second hydraulic stem (66).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710506958.1A CN107389296B (en) | 2015-10-28 | 2015-10-28 | A kind of model aircraft for wind-tunnel |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510712904.1A CN105203291B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system for vector propulsion model aircraft |
| CN201710506958.1A CN107389296B (en) | 2015-10-28 | 2015-10-28 | A kind of model aircraft for wind-tunnel |
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 |
|---|---|
| CN107389296A true CN107389296A (en) | 2017-11-24 |
| CN107389296B CN107389296B (en) | 2019-09-13 |
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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 |
| 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 |
| CN201710506958.1A Expired - Fee Related CN107389296B (en) | 2015-10-28 | 2015-10-28 | A kind of model aircraft for wind-tunnel |
| CN201710506953.9A Expired - Fee Related CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| 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 |
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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 |
| 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 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710506953.9A Expired - Fee Related CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| 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 |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN107356403B (en) | 2019-10-11 |
| CN107152996A (en) | 2017-09-12 |
| CN107271135A (en) | 2017-10-20 |
| CN107271137A (en) | 2017-10-20 |
| CN107152996B (en) | 2019-09-13 |
| CN105203291A (en) | 2015-12-30 |
| CN107389292A (en) | 2017-11-24 |
| CN107271135B (en) | 2019-09-13 |
| CN107340117A (en) | 2017-11-10 |
| CN107356403A (en) | 2017-11-17 |
| CN107271137B (en) | 2019-09-13 |
| CN107389292B (en) | 2019-09-13 |
| CN107271136A (en) | 2017-10-20 |
| CN107340117B (en) | 2019-10-11 |
| CN107271136B (en) | 2019-10-11 |
| CN105203291B (en) | 2017-07-28 |
| CN107389296B (en) | 2019-09-13 |
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