CN107340117A - A kind of wind tunnel test model aircraft - Google Patents
A kind of wind tunnel test model aircraft Download PDFInfo
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- CN107340117A CN107340117A CN201710506983.XA CN201710506983A CN107340117A CN 107340117 A CN107340117 A CN 107340117A CN 201710506983 A CN201710506983 A CN 201710506983A CN 107340117 A CN107340117 A CN 107340117A
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- propelling nozzle
- vector
- vector propelling
- wind tunnel
- tunnel test
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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
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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
- G01M9/02—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 aircraft, for experiment 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 first jet pipe and the second jet pipe in the adjustable jet direction for the afterbody for stretching out the wind tunnel test model aircraft, and current velocity controller is provided with the first vector propelling nozzle and the second vector propelling nozzle.The wind tunnel test model aircraft 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 wind tunnel test model aircraft.
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 wind tunnel test model aircraft, to be carried before being reduced or avoided
To the problem of.
Specifically, the invention provides a kind of wind tunnel test model aircraft, for experiment, 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
First jet pipe and the second jet pipe in the adjustable jet direction of afterbody, the first vector propelling nozzle and the second vector
Current velocity controller is provided with propelling nozzle；The current velocity controller includes：Around the first vector propelling nozzle and
The symmetrically arranged multiple bores of madial wall 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 madial wall 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 set
Put 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 towards the front end of the first vector propelling nozzle and the airflow direction of the second vector propelling nozzle on the madial wall,
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.
The wind tunnel test model aircraft of the present invention is promoted using the pressure-air of compressed air source by pipeline to vector 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 tunnel simulation vector promotes the aerodynamics situation of model aircraft the defects of, can be by simulation with pushing away
Enter under the dynamical state of power, greatly reduce the quantity of wind tunnel test, 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.
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 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 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.
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 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
Jet pipe 15, the end of the first vector propelling nozzle 11 and the second vector propelling nozzle 15, which is provided with, stretches out the wind tunnel test
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 tunnel simulation vector promote model aircraft aerodynamics situation the defects of, the present invention provide
A kind of model aircraft of special construction, the model carries the jet state that can simulate vector propelling motor, in wind-tunnel
Jet power is produced during experiment.That is, in above-mentioned wind tunnel test 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, without rotary part, is not real jet hair
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.Sprayed on tail
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 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 of the invention shown in Fig. 1
Experiment 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 for the pole that supports the wind tunnel test model aircraft 10
500；One end of pole 500 is connected 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 the vector propelling nozzle 15 of jet pipe 11 and second (Fig. 3).
Further, as shown in figure 3, it is shown is flown according to the wind tunnel test of another specific embodiment of the present invention
The top view of machine model；Wherein, the wind tunnel test system further comprise the compressed air source 4 of the outside for being arranged at wind-tunnel with
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
First pipeline 51 and second pipe 52.That is, injection is produced in order 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 using the pressure-air of compressed air source 4 by pipeline 51,52 to vector
The release of jet pipe 11,15 forms high velocity air, 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 share, that is, only need a compression empty
Source of the gas 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. are required for accurate calculating and control, use
To form the Jet Stream of flow velocity, flow needed for acquisition.Those skilled in the art can be on the basis of design proposed by the present invention
On further calculated and controlled according to actual conditions, 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, 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 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 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, do not increase any extra part in the vertical direction of wind-tunnel, only in 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
Interference caused by dynamic profile is minimum, 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 flow velocity in the wind tunnel test model aircraft according to another specific embodiment of the present invention is shown in Fig. 4
The enlarged diagram of control device；The A-A sectional views of current velocity controller shown in Fig. 4 are shown in Fig. 5, can be clear from Figure 4 and 5
Chu finds out that the current velocity controller 60 of the present 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 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, wind tunnel test model aircraft of the invention is pushed away using the pressure-air of compressed air source by pipeline to vector
Enter jet pipe to discharge to form jet effect to obtain jet power, simulated the jet state of vector propelling motor, overcome
Prior art can not tunnel simulation vector promote model aircraft aerodynamics situation the defects of, can be by simulating 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 and is entered by wing, adjusts pipeline, electrical heating wire, current velocity controller etc.
Various measures 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 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)
1. a kind of wind tunnel test model aircraft, for experiment to be blowed in wind-tunnel, it is characterised in that the wind tunnel test flies
The fuselage interior of machine model (10) is 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) is provided with the stretching wind tunnel test and flown
First jet pipe (12) and the second jet pipe (16) in the adjustable jet direction of the afterbody of machine model (10), first arrow
Current velocity controller (60) is provided with amount propelling nozzle (11) and the second vector propelling nozzle (15)；The current velocity controller
(60) include：Madial wall (61) around the first vector propelling nozzle (11) and the second vector propelling nozzle (15) is symmetrically set
The multiple bores put reduce control panel (62)；Around the first vector propelling nozzle (11) and the second vector propelling nozzle (15)
The symmetrically arranged multiple bores of madial wall (61) expand control panels (63)；And the covering bore reduce 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
Making sheet (63) is arranged on the front of the airflow direction of the first vector propelling nozzle (11) and the second vector propelling nozzle (15)；
The bore reduces control panel (62) towards the first vector propelling nozzle (11) and the gas of the second vector propelling nozzle (15)
The front end in stream direction is hinged on the madial wall (61), and the bore reduces control panel (62) and promoted away from first vector
The rear end of the airflow direction of jet pipe (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 |
|---|---|---|---|
| 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 |
|---|---|
| CN107340117A true CN107340117A (en) | 2017-11-10 |
| CN107340117B CN107340117B (en) | 2019-10-11 |
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Family Applications (9)
| 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 |
Family Applications Before (6)
| 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 |
Family Applications After (2)
| Application Number | Title | Priority Date | Filing Date |
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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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| CN (9) | CN107152996B (en) |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN107356403B (en) | 2019-10-11 |
| CN105203291B (en) | 2017-07-28 |
| CN107152996A (en) | 2017-09-12 |
| CN107340117B (en) | 2019-10-11 |
| 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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