CN107389296B - A kind of model aircraft for wind-tunnel - Google Patents
A kind of model aircraft for wind-tunnel Download PDFInfo
- Publication number
- CN107389296B CN107389296B CN201710506958.1A CN201710506958A CN107389296B CN 107389296 B CN107389296 B CN 107389296B CN 201710506958 A CN201710506958 A CN 201710506958A CN 107389296 B CN107389296 B CN 107389296B
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- propelling nozzle
- vector propelling
- vector
- tunnel
- wind
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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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- 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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- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of model aircrafts for wind-tunnel, for test 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 the first jet pipe and the second jet pipe for stretching out the adjustable jet direction of afterbody of the model aircraft, is provided with current velocity controller in the first vector propelling nozzle and the second vector propelling nozzle.Model aircraft for wind-tunnel 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 model aircraft for wind-tunnel.
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 model aircrafts for wind-tunnel, front institute is reduced or avoided
The problem of mentioning.
Specifically, the present invention provides a kind of model aircrafts for wind-tunnel, for test 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 for stretching out the model aircraft
Setting in the first jet pipe and the second jet pipe of jet direction, the first vector propelling nozzle and the second vector propelling nozzle
There is current velocity controller；The current velocity controller includes: to promote spray around the first vector propelling nozzle and the second vector
The symmetrically arranged multiple bores of the inner sidewall of pipe reduce control panel；It is promoted around the first vector propelling nozzle and the second vector
The symmetrically arranged multiple bores of the inner sidewall 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 of control panel and expands control panel setting in 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 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
It is hydraulic that the front end of making sheet towards the first vector propelling nozzle and the airflow direction of the second vector propelling nozzle is hinged on second
On bar.
Model aircraft for wind-tunnel of the invention is promoted by pipeline to vector using the pressure-air of compressed air source
Jet pipe discharges to form jet effect to obtain jet power, has simulated the jet state of vector propelling motor, overcomes existing
There is technology that can not have by simulation in the defect of the aerodynamics situation of tunnel simulation vector propulsion model aircraft
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, it is each by wing entrance, adjustment pipeline, electric heating wire, current velocity controller etc. that the present invention additionally uses pipeline
Kind 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 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 of another specific embodiment according to the present invention is shown in Fig. 4
The enlarged diagram of device processed；
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 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
The first jet pipe 12 and the second jet pipe 16 of the adjustable jet direction of afterbody.That is, in order to overcome the prior art
Can not be in the defect of the aerodynamics situation of tunnel simulation vector propulsion model aircraft, the present invention provides a kind of special knots
The model aircraft of structure, which has the jet state of analog vector propelling motor, to produce during wind tunnel test
Raw jet power.That is, there are two vector propelling nozzle 11,15, the two vector propelling nozzles for setting in above-mentioned model aircraft 10
11,15 jet-stream wind can be generated as jet engine, and the jet direction of its jet pipe 12,16 is adjustable
's.Certainly, it will be understood by those skilled in the art that vector propelling nozzle 11,15 of the invention can only 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
12,16 nor the adjustable jet direction of real structure jet pipe, the two jet pipes 12,16 are only the cone of fixed shape
Shape pipeline, the conical pipeline are mounted on the tail end of vector propelling nozzle 11,15, can pass through conventional hydraulic or electromagnetically-operated portion
Part (not shown) controls its deflection angle, to control the direction of jet.The control of jet direction about 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 for sending out shown in FIG. 1 in the wind-tunnel of wind tunnel test system
Test is blowed in bright model aircraft 10, and the wind tunnel test system includes one solid with the floor 200 of wind-tunnel and top plate 300
Fixed connection and vertically disposed support column 400 and one are used to support the strut 500 of the model aircraft 10；Strut 500
One end is connect 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, its be shown another specific embodiment according to the present invention for wind-tunnel
The top view of model aircraft；Wherein, the wind tunnel test system further comprises the compressed air source 4 for being set to the outside of wind-tunnel
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 spray to simulate jet engine by two vector propelling nozzles 11,15
It emanates stream, the present invention is provided with compressed air source 4, is pushed away by pipeline 51,52 to vector using the pressure-air of compressed air source 4
High-speed flow is formed into the release of jet pipe 11,15, forms 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 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. require to accurately calculate and control,
To form the Jet Stream for obtaining required flow velocity, flow.Those skilled in the art can be in the base of design proposed by the present invention
It is further calculated and is controlled according to the actual situation 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, 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 the fuselage interior of model aircraft 10 simultaneously from the both ends of two wings 20 of model aircraft 10
It is separately connected the first vector propelling nozzle 11 and the second vector propelling nozzle 15.From figure 2 it can be seen that through this embodiment
This arrangement does not increase any additional component in the vertical direction of wind-tunnel, only farthest in the level of model aircraft 10
End is connected with pipeline 51,52 (Fig. 3), therefore the interference generated for the aerodynamic configuration of model aircraft 10 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 stream in the model aircraft for wind-tunnel of another specific embodiment according to the present invention is shown in Fig. 4
The enlarged diagram of velocity control device；The A-A cross-sectional view of current velocity controller shown in Fig. 4 is shown in Fig. 5, can be with from Figure 4 and 5
It is apparent from current velocity controller 60 of the invention and simulates the structure type of Laval nozzle, form 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 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, the model aircraft for wind-tunnel of the invention passes through pipeline to vector using the pressure-air of compressed air source
Propelling nozzle discharges to form jet effect to obtain jet power, has simulated the jet state of vector propelling motor, has overcome
The prior art can not tunnel simulation vector promote model aircraft aerodynamics situation defect, can pass through simulation
With the quantity of wind tunnel test under propulsive dynamical state, is greatly reduced, wind tunnel test is as a result quasi- closer to real conditions
Exactness is higher.Also, the present invention additionally uses such as pipeline and is entered by wing, adjusts pipeline, electric heating wire, current velocity controller
It further reduced experimentation cost etc. various measures, 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 model aircraft for wind-tunnel, for test to be blowed in wind-tunnel, which is characterized 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), which is respectively arranged with, stretches out the model aircraft (10)
Afterbody adjustable jet direction the first jet pipe (12) and the second jet pipe (16), the first vector propelling nozzle
(11) and in the second vector propelling nozzle (15) current velocity controller (60) are provided with；The current velocity controller (60) includes:
Inner sidewall (61) around the first vector propelling nozzle (11) and the second vector propelling nozzle (15) is symmetrically arranged multiple
Bore reduces control panel (62), surrounds the inner sidewall of the first vector propelling nozzle (11) and the second vector propelling nozzle (15)
(61) symmetrically arranged multiple bores expand control panel (63), and the covering bore reduces control panel (62) and the bore
Expand the elastic covering (64) of control panel (63)；The bore reduces control panel (62) relatively described bore and expands control panel (63)
The front of airflow direction in the first vector propelling nozzle (11) and the second vector propelling nozzle (15) is set；The bore
Control panel (62) are reduced away from the airflow direction of the first vector propelling nozzle (11) and the second vector propelling nozzle (15)
Rear end is hinged on the first hydraulic stem (65)；The bore expands control panel (63) towards the first vector propelling nozzle (11)
It is hinged on the second hydraulic stem (66) with the front end of the airflow direction of the second vector propelling nozzle (15).
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 |
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| Publication Number | Publication Date |
|---|---|
| CN107389296A CN107389296A (en) | 2017-11-24 |
| CN107389296B true CN107389296B (en) | 2019-09-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
| 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 |
| CN201710508256.7A Expired - Fee Related CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
| CN201710507559.7A Expired - Fee Related CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| 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 |
| CN201710508245.9A Expired - Fee Related CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of 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 |
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| Application Number | Title | Priority Date | Filing Date |
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| 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 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710506953.9A Expired - Fee Related CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| CN201710507560.XA Expired - Fee Related CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
| CN201710508256.7A Expired - Fee Related CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
| CN201710507559.7A Expired - Fee Related CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| 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 |
| CN201710508245.9A Expired - Fee Related CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of 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 |
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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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| 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 CN201710507558.2A patent/CN107271135B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710506958.1A patent/CN107389296B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710506953.9A patent/CN107271137B/en not_active Expired - Fee Related
- 2015-10-28 CN CN201710507560.XA patent/CN107389292B/en not_active Expired - Fee Related
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Also Published As
| Publication number | Publication date |
|---|---|
| CN107389292B (en) | 2019-09-13 |
| CN107271137A (en) | 2017-10-20 |
| CN107271136B (en) | 2019-10-11 |
| CN107389292A (en) | 2017-11-24 |
| CN107271135B (en) | 2019-09-13 |
| CN107152996A (en) | 2017-09-12 |
| CN107152996B (en) | 2019-09-13 |
| CN107356403A (en) | 2017-11-17 |
| CN107271137B (en) | 2019-09-13 |
| CN107271136A (en) | 2017-10-20 |
| CN107340117B (en) | 2019-10-11 |
| CN107389296A (en) | 2017-11-24 |
| CN107271135A (en) | 2017-10-20 |
| CN105203291B (en) | 2017-07-28 |
| CN107340117A (en) | 2017-11-10 |
| CN105203291A (en) | 2015-12-30 |
| CN107356403B (en) | 2019-10-11 |
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