CN105203291A - Wind tunnel experiment system used for vector-boosting airplane model - Google Patents
Wind tunnel experiment system used for vector-boosting airplane model Download PDFInfo
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- CN105203291A CN105203291A CN201510712904.1A CN201510712904A CN105203291A CN 105203291 A CN105203291 A CN 105203291A CN 201510712904 A CN201510712904 A CN 201510712904A CN 105203291 A CN105203291 A CN 105203291A
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- vector
- propelling nozzle
- vector propelling
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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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- 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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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a wind tunnel experiment system used for a vector-boosting airplane model. A first vector propulsion spray pipe and a second vector propulsion spray pipe are arranged in the machine body of the vector-boosting airplane model; the wind tunnel experiment system comprises a support pillar, a supporting rod used for supporting the vector-boosting airplane model, a compressed air source arranged outside the wind tunnel, as well as a first pipeline and a second pipeline; the first pipeline and the second pipeline are used for connecting the compressed air source with the first vector propulsion spray pipe and the second vector propulsion spray pipe. The wind tunnel experiment system has the advantages that high-pressure air in the compressed air source is released to the vector propulsion spray pipes through pipelines, so as to obtain air blast power, simulate the air blast state of a vector propulsion engine, and overcome the defect that in the prior art, the aerodynamics state of the vector propulsion airplane model cannot be simulated in a wind tunnel.
Description
Technical field
The present invention relates to a kind of aviation aerodynamics testing equipment, especially a kind of wind tunnel test system that can be used for vector propelling model aircraft.
Background technology
Wind tunnel test is that by model aircraft or its parts, such as fuselage, wing etc. are fixed in wind-tunnel according to aerodynamic principle, flowing through model aircraft or its parts, simulating the state of flight of aerial various complexity, obtain test figure with this by applying artificial airflow.Wind-tunnel carries out aerodynamic studies and the most basic testing equipment of aircraft development, and the development of each type aircraft all needs to carry out a large amount of tests in wind-tunnel.The fundamental purpose of wind tunnel test is the Changing Pattern of the various aerodynamic parameter that will obtain model aircraft.Evaluate the flying quality of each aircraft, except such as speed, highly, except the key element such as aircraft weight and motor power, one of most important standard is the aerodynamic quality of aircraft.The wind tunnel test of aircraft full machine needs whole model aircraft to be supported in wind-tunnel, measures the pressure distribution data of each parts of whole model aircraft under particular flight condition, obtain the dynamic characteristic of aircraft with this under artificial airflow environment by pressure test equipment.
Vector Push Technology refers to that aircraft engine thrust is carried out the control surface of alternative former aircraft by the thrust component that the deflection of jet pipe or tail jet produces or strengthens the operating function of aircraft, the flight of aircraft is carried out to the technology controlled in real time.Vector Push Technology can allow a part for motor power become steering force, replaces or partly replaces control surface, thus greatly reducing radar area; No matter how low the angle of attack is much with flying speed, and aircraft all can utilize this part steering force to handle, and this adds increased the navigability of aircraft.Owing to directly producing steering force, and value and direction mutability, also just add the agility of aircraft, thus can suitably reduce or remove vertical fin, also can substitute some other control surface.This is favourable to the detectivity of reduction aircraft, and the resistance of aircraft also can be made to reduce, and structure heavily alleviates.Therefore, vector Push Technology is used to be the optimal selection solving design contradiction.
But in the process of full machine wind tunnel test of carrying out model aircraft, due to the restriction of tunnel size and model aircraft size, in model aircraft inside, a real engine can not be installed, thus for the model aircraft that have employed vector Push Technology, the method that there is no simulates the aerodynamics situation that vector advances model aircraft in wind tunnel test.That is, in existing wind-tunnel technique, model aircraft is that static support (sometimes also can adjust the attitude of aircraft in wind-tunnel flyoff process, but cannot the dynamic situation of analog band), model aircraft itself does not have power, is to utilize the speed of the relative model aircraft of air flow to carry out simulated flight state when wind tunnel test.But for have employed the model aircraft of vector Push Technology, when the propelling power size and Orientation of aircraft engine changes, the wind tunnel test under quiescent conditions can only simulate the aerodynamics situation under a kind of state.Existing wind tunnel test system can only utilize a large amount of envelope tests to obtain discrete status data, then the approximate dynamic data of continuous setup propelling power size and Orientation is obtained by the mode of interpolation, tested number is very huge, waste time and energy expensive and test findings remains approximate, accuracy is poor.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of wind tunnel test system advancing model aircraft for vector, to reduce or to avoid problem noted earlier.
Specifically, the invention provides a kind of wind tunnel test system advancing model aircraft for vector, for advancing model aircraft to blow test to vector in wind-tunnel, wherein, described vector advances the fuselage interior of model aircraft to be provided with a first vector propelling nozzle and a second vector propelling nozzle, the end of described first vector propelling nozzle and the second vector propelling nozzle is provided with and stretches out the first jet pipe and the second jet pipe that described vector advances the adjustable jet direction of the afterbody of model aircraft, described wind tunnel test system comprises one and to be fixedly connected with top board with the floor of described wind-tunnel and vertically disposed support column and one advance the pole of model aircraft for supporting described vector, one end of described pole is connected with described support column, and the other end is fixed on the fuselage between the described first vector propelling nozzle of described vector propelling model aircraft and the second vector propelling nozzle.
Preferably, described wind tunnel test system comprise further the outside being arranged at described wind-tunnel compressed air source and for the first pipeline of connecting described compressed air source and described first vector propelling nozzle and the second vector propelling nozzle and second pipe.
Preferably, described first pipeline and second pipe advance the two ends of two wings of model aircraft enter the fuselage interior of described vector propelling model aircraft and be connected described first vector propelling nozzle and the second vector propelling nozzle respectively from described vector.
Preferably, between described first vector propelling nozzle and the second vector propelling nozzle, be connected with adjustment pipeline, in described adjustment pipeline, be provided with the solenoid valve of adjustment flow.
Preferably, electrical heating wire is had around described first vector propelling nozzle and the second vector propelling nozzle arranged outside.
Preferably, current velocity controller is provided with in described first vector propelling nozzle and the second vector propelling nozzle.
Preferably, described current velocity controller comprises: the symmetrically arranged multiple bore of madial wall around described first vector propelling nozzle and the second vector propelling nozzle reduces control panel; The symmetrically arranged multiple bore of madial wall around described first vector propelling nozzle and the second vector propelling nozzle expands control panel; And cover the elasticity covering that described bore reduces control panel and described bore expansion control panel.
Preferably, described bore reduces the front that control panel relatively described bore expansion control panel is arranged on the airflow direction of described first vector propelling nozzle and the second vector propelling nozzle.
Preferably, described bore reduces control panel and is hinged on described madial wall towards the front end of the airflow direction of described first vector propelling nozzle and the second vector propelling nozzle, and described bore reduces the rear end that control panel deviates from the airflow direction of described first vector propelling nozzle and the second vector propelling nozzle and is hinged on the first hydraulic stem.
Preferably, described bore expands the rear end that control panel deviates from the airflow direction of described first vector propelling nozzle and the second vector propelling nozzle and is hinged on described madial wall, and described bore expands control panel and is hinged on the second hydraulic stem towards the front end of the airflow direction of described first vector propelling nozzle and the second vector propelling nozzle.
Wind tunnel test system for vector propelling model aircraft of the present invention utilizes the pressure-air of compressed air source to form jet effect to obtain jet power by pipeline to the release of vector propelling nozzle, simulate the jet state of vector propelling motor, overcome prior art cannot advance the aerodynamics situation of model aircraft defect at tunnel simulation vector, can by under the propulsive dynamical state of analog band, greatly reduce the quantity of wind tunnel test, wind tunnel test is closer to real conditions, and result precision is higher.Further, the present invention additionally uses that such as pipeline is entered by wing, the various measures such as pipeline, electrical heating wire, current velocity controller that adjust reduce further experimentation cost, improves test accuracy.
Accompanying drawing explanation
The following drawings is only intended to schematically illustrate the present invention and explain, not delimit the scope of the invention.Wherein,
What Fig. 1 showed is the structural representation advancing model aircraft according to the vector of a specific embodiment of the present invention;
Fig. 2 display be the side view of wind tunnel test system advancing model aircraft for vector according to a specific embodiment of the present invention;
Fig. 3 display be the vertical view of wind tunnel test system advancing model aircraft for vector according to another specific embodiment of the present invention;
Fig. 4 display be the enlarged diagram of current velocity controller advanced for vector in the wind tunnel test system of model aircraft according to another specific embodiment of the present invention;
Fig. 5 display be the A-A cut-open view of current velocity controller shown in Fig. 4.
Embodiment
In order to there be understanding clearly to technical characteristic of the present invention, object and effect, now contrast accompanying drawing and the specific embodiment of the present invention is described.Wherein, identical parts adopt identical label.
What Fig. 1 showed is the structural representation advancing model aircraft according to the vector of a specific embodiment of the present invention, this vector advances the fuselage interior of model aircraft 10 to be provided with a first vector propelling nozzle 11 and a second vector propelling nozzle 15, and the end of described first vector propelling nozzle 11 and the second vector propelling nozzle 15 is provided with and stretches out the first jet pipe 12 and the second jet pipe 16 that described vector advances the adjustable jet direction of the afterbody of model aircraft 10.That is, the defect of the aerodynamics situation of model aircraft cannot be advanced at tunnel simulation vector in order to overcome prior art, the invention provides a kind of model aircraft of special construction, this model with the jet state can simulating vector propelling motor, in order to produce jet power in wind tunnel test process.That is, above-mentioned vector advances in model aircraft 10, and be provided with two vector propelling nozzles 11,15, these two vector propelling nozzles 11,15 can produce jet-stream wind as jet engine, and the jet direction of its jet pipe 12,16 is adjustable.Certainly, those skilled in the art should understand, vector propelling nozzle 11 of the present invention, 15 just can be similar to the such jet-stream wind of jet engine, itself is without rotary part, it is not real jet engine, therefore two jet pipes 12, 16 neither the jet pipe in adjustable jet direction of real structure, these two jet pipes 12, 16 is only the conical pipeline of solid shape, this conical pipeline is arranged on vector propelling nozzle 11, the tail end of 15, its deflection angle can be controlled by conventional hydraulic pressure or electromagnetically-operated parts (not shown), thus control jet direction.Control about the jet direction of jet pipe 12,16 can adopt routine techniques, and be not the emphasis that the present invention pays close attention to, this is no longer going to repeat them.
Fig. 2 display be the side view of wind tunnel test system advancing model aircraft for vector according to a specific embodiment of the present invention; As shown in the figure, of the present inventionly advance the wind tunnel test system of model aircraft to be used in wind-tunnel for vector to advance model aircraft 10 to blow test to the vector of the present invention shown in Fig. 1, described wind tunnel test system comprises one and to be fixedly connected with top board 300 with the floor 200 of wind-tunnel and vertically disposed support column 400 and one advance the pole 500 of model aircraft 10 for supporting described vector; One end of pole 500 is connected with support column 400, and the other end is fixed on the fuselage between the first vector propelling nozzle 11 of vector propelling model aircraft 10 and the second vector propelling nozzle 15 (Fig. 3).
Further, as shown in Figure 3, its display is the vertical view of wind tunnel test system advancing model aircraft for vector according to another specific embodiment of the present invention; Wherein, described wind tunnel test system comprise further the outside being arranged at wind-tunnel compressed air source 4 and for the first pipeline 51 of connecting described compressed air source 4 and described first vector propelling nozzle 11 and the second vector propelling nozzle 15 and second pipe 52.Namely, jet-stream wind is produced in order to simulate jet engine by two vector propelling nozzles 11,15, the present invention is provided with compressed air source 4, utilize the pressure-air of compressed air source 4 to discharge formation high velocity air by pipeline 51,52 to vector propelling nozzle 11,15, form jet effect to obtain jet power.In order to clear display in Fig. 3, depict two compressed air sources 4, in practical work process, these two compressed air sources 4 can share, that is only need a compressed air source 4.Certainly, those skilled in the art are to be understood that, when actual wind tunnel test, length, diameter etc. about the pressure size of compressed air source 4, pipeline 51,52 and vector propelling nozzle 11,15 all need accurate Calculation and control, in order to form the Jet Stream obtaining required flow rate, flow.The basis of the design that those skilled in the art can propose in the present invention further calculate according to actual conditions and control, this calculating and control to adopt existing routine techniques means, neither the emphasis paid close attention to of the present invention, also repeat no longer one by one.
In order to avoid the layout of pipeline 51,52 causes excessive interference to Flow Field in Wind Tunnel, in a preferred embodiment, the first pipeline 51 and second pipe 52 advance the two ends of two wings 20 of model aircraft 10 enter the fuselage interior of vector propelling model aircraft 10 and be connected the first vector propelling nozzle 11 and the second vector propelling nozzle 15 respectively from vector.As can be seen from Figure 2, by this layout of the present embodiment, the vertical direction of wind-tunnel does not increase any extra parts, only the horizontal distalmost end of model aircraft 10 is advanced to be connected with pipeline 51,52 (Fig. 3) at vector, therefore advance the interference of the aerodynamic configuration of model aircraft 10 generation minimum for vector, be conducive to obtaining more accurate test figure.
In another specific embodiment, as shown in Figure 3, be connected with adjustment pipeline 30 between the first vector propelling nozzle 11 and the second vector propelling nozzle 15, in described adjustment pipeline 30, be provided with the solenoid valve 40 of adjustment flow.The object of this set is, by the first pipeline 51 and second pipe 52 enter the air mass flow of the first vector propelling nozzle 11 and the second vector propelling nozzle 15, pressure due to line size, be connected the factors such as compactedness and may there is certain difference, if need the state of simulation two equal thrusts of engine, then need air mass flow and the flow velocity of point-device control first pipeline 51 and second pipe 52, this is very troublesome something, very high to the requirement of equipment and personnel.And adopt the setting of the present embodiment, only needing to open adjustment pipeline 30 by solenoid valve 40 just can make the first vector propelling nozzle 11 reach consistent with the air pressure in the second vector propelling nozzle 15, reach identical thrust easily via this little design to control, reduce control overflow, greatly save regulation and control time and cost.
In another specific embodiment, there is electrical heating wire 50 around the first vector propelling nozzle 11 and the second vector propelling nozzle 15 arranged outside.Can the condition of high temperature of simple analog jet engine by electrical heating wire 50, certainly, prior, can be heated the first vector propelling nozzle 11 and the second vector propelling nozzle 15 by electrical heating wire 50, make high pressure draught expanded by heating wherein improve jet velocity.That is, lasting supersonic jet speed is provided to be very difficult only by compressed air source 4, very high for the compressed-air actuated equipment requirement of generation, the present embodiment arranges the equipment requirement that partly can reduce compressed air source 4 by electrical heating wire 50, has saved cost.
Same, in order to improve the jet velocity in the first vector propelling nozzle 11 and the second vector propelling nozzle 15 further, in another specific embodiment, the present invention is also provided with current velocity controller 60 in the first vector propelling nozzle 11 and the second vector propelling nozzle 15, and concrete structure as shown in Figure 4,5.
That is, Fig. 4 display is the enlarged diagram of current velocity controller advanced for vector in the wind tunnel test system of model aircraft according to another specific embodiment of the present invention; Fig. 5 display be the A-A cut-open view of current velocity controller shown in Fig. 4, can know from Figure 4 and 5 and find out that current velocity controller 60 of the present invention simulates the version of Laval nozzle, define the version of the acceleration air-flow of middle shrinkage two ends expansion, the principle that Laval nozzle accelerates gas velocity is well known in the art, no longer describes.
Concrete, described current velocity controller 60 of the present invention comprises: the symmetrically arranged multiple bore of madial wall 61 around the first vector propelling nozzle 11 and the second vector propelling nozzle 15 reduces control panel 62; The symmetrically arranged multiple bore of madial wall 61 around the first vector propelling nozzle 11 and the second vector propelling nozzle 15 expands control panel 63; And cover the elasticity covering 64 that bore reduces control panel 62 and bore expansion control panel 63.Cut-open view in Fig. 5 show schematically show and expands control panel 63 around the symmetrically arranged four pieces of bores of madial wall 61, those skilled in the art can infer accordingly, also can be symmetrical arranged four pieces of bores around madial wall 61 and reduce control panel 62, in order to represent clear, in the cut-open view in Fig. 5, do not show elasticity covering.The metallic aluminium covering that elasticity covering 64 can adopt elasticity larger, also can adopt the better rubber covering of resilience, in order to cover the space between each control panel 62,63, form more smooth nozzle wall, for avoiding flow velocity to lose, improve gas velocity advantageously.
Further; although accompanying drawing can be easy to the structure finding out current velocity controller 60 of the present invention; but in order to the needs of text description and rights protection; the present invention has carried out further detailed description with reference to accompanying drawing for its concrete structure; namely; bore reduces control panel 62 relative aperture and expands the front that control panel 63 is arranged on the airflow direction of the first vector propelling nozzle 11 and the second vector propelling nozzle 15, and wherein airflow direction represents with arrow F in Fig. 2-4.
Again further, bore reduces control panel 62 and is hinged on madial wall 61 towards the front end of the airflow direction of the first vector propelling nozzle 11 and the second vector propelling nozzle 15, and bore reduces the rear end that control panel 62 deviates from the airflow direction of the first vector propelling nozzle 11 and the second vector propelling nozzle 15 and is hinged on the first hydraulic stem 65.
Further, bore expands the rear end that control panel 63 deviates from the airflow direction of the first vector propelling nozzle 11 and the second vector propelling nozzle 15 and is hinged on madial wall 61, and bore expands control panel 63 and is hinged on the second hydraulic stem 66 towards the front end of the airflow direction of the first vector propelling nozzle 11 and the second vector propelling nozzle 15.
In wind tunnel test process, in order to control the gas velocity of the first vector propelling nozzle 11 and the second vector propelling nozzle 15, the first hydraulic stem 65 and the second hydraulic stem 66 can be manipulated adjust bore and reduce the angle that control panel 62 and bore expand control panel 63, thus control the shape of the Laval configuration of jet pipe, to arrive the object that gas velocity controls flexibly.
In a word, wind tunnel test system for vector propelling model aircraft of the present invention utilizes the pressure-air of compressed air source to form jet effect to obtain jet power by pipeline to the release of vector propelling nozzle, simulate the jet state of vector propelling motor, overcome prior art cannot advance the aerodynamics situation of model aircraft defect at tunnel simulation vector, can by under the propulsive dynamical state of analog band, greatly reduce the quantity of wind tunnel test, wind tunnel test is closer to real conditions, and result precision is higher.Further, the present invention additionally uses that such as pipeline is entered by wing, the various measures such as pipeline, electrical heating wire, current velocity controller that adjust reduce further experimentation cost, improves test accuracy.
Although it will be appreciated by those skilled in the art that the present invention is described according to the mode of multiple embodiment, not each embodiment only comprises an independently technical scheme.So describe in instructions be only used to clear for the purpose of; instructions should integrally be understood by those skilled in the art, and regards technical scheme involved in each embodiment as the mode that mutually can be combined into different embodiment to understand protection scope of the present invention.
The foregoing is only the schematic embodiment of the present invention, and be not used to limit scope of the present invention.Any those skilled in the art, the equivalent variations done under the prerequisite not departing from design of the present invention and principle, amendment and combination, all should belong to the scope of protection of the invention.
Claims (10)
1. one kind advances the wind tunnel test system of model aircraft for vector, for advancing model aircraft (10) to blow test to vector in wind-tunnel, it is characterized in that, described vector advances the fuselage interior of model aircraft (10) to be provided with a first vector propelling nozzle (11) and a second vector propelling nozzle (15), the end of described first vector propelling nozzle (11) and the second vector propelling nozzle (15) is provided with and stretches out the first jet pipe (12) and the second jet pipe (16) that described vector advances the adjustable jet direction of the afterbody of model aircraft (10), described wind tunnel test system comprises one and to be fixedly connected with top board (300) with the floor (200) of described wind-tunnel and vertically disposed support column (400) and one advance the pole (500) of model aircraft (10) for supporting described vector, one end of described pole (500) is connected with described support column (400), and the other end is fixed on the fuselage between the described first vector propelling nozzle (11) of described vector propelling model aircraft (10) and the second vector propelling nozzle (15).
2. wind tunnel test system as claimed in claim 1, it is characterized in that, described wind tunnel test system comprise further the outside being arranged at described wind-tunnel compressed air source (4) and for the first pipeline (51) of connecting described compressed air source (4) and described first vector propelling nozzle (11) and the second vector propelling nozzle (15) and second pipe (52).
3. wind tunnel test system as claimed in claim 2, it is characterized in that, described first pipeline (51) and second pipe (52) advance from described vector the two ends of two wings (20) of model aircraft (10) to enter described vector and advance the fuselage interior of model aircraft (10) and be connected described first vector propelling nozzle (11) and the second vector propelling nozzle (15) respectively.
4. wind tunnel test system as claimed in claim 2, it is characterized in that, be connected with adjustment pipeline (30) between described first vector propelling nozzle (11) and the second vector propelling nozzle (15), in described adjustment pipeline (30), be provided with the solenoid valve (40) of adjustment flow.
5. wind tunnel test system as claimed in claim 2, is characterized in that there is electrical heating wire (50) around described first vector propelling nozzle (11) and the second vector propelling nozzle (15) arranged outside.
6. wind tunnel test system as claimed in claim 2, is characterized in that, be provided with current velocity controller (60) in described first vector propelling nozzle (11) and the second vector propelling nozzle (15).
7. wind tunnel test system as claimed in claim 6, it is characterized in that, described current velocity controller (60) comprising: the symmetrically arranged multiple bore of madial wall (61) around described first vector propelling nozzle (11) and the second vector propelling nozzle (15) reduces control panel (62); The symmetrically arranged multiple bore of madial wall (61) around described first vector propelling nozzle (11) and the second vector propelling nozzle (15) expands control panel (63); And cover the elasticity covering (64) that described bore reduces control panel (62) and described bore expansion control panel (63).
8. wind tunnel test system as claimed in claim 7, it is characterized in that, described bore reduces the relatively described bore of control panel (62) and expands the front that control panel (63) is arranged on the airflow direction of described first vector propelling nozzle (11) and the second vector propelling nozzle (15).
9. wind tunnel test system as claimed in claim 8, it is characterized in that, described bore reduces control panel (62) and is hinged on described madial wall (61) towards the front end of the airflow direction of described first vector propelling nozzle (11) and the second vector propelling nozzle (15), and described bore reduces the rear end that control panel (62) deviates from the airflow direction of described first vector propelling nozzle (11) and the second vector propelling nozzle (15) and is hinged on the first hydraulic stem (65).
10. wind tunnel test system as claimed in claim 8, it is characterized in that, described bore expands the rear end that control panel (63) deviates from the airflow direction of described first vector propelling nozzle (11) and the second vector propelling nozzle (15) and is hinged on described madial wall (61), and described bore expansion control panel (63) is hinged on the second hydraulic stem (66) towards the front end of the airflow direction of described first vector propelling nozzle (11) and the second vector propelling nozzle (15).
Priority Applications (9)
| 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 |
| CN201710506983.XA CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
| CN201710507558.2A CN107271135B (en) | 2015-10-28 | 2015-10-28 | The wind tunnel system of model aircraft test is promoted for vector |
| CN201710507560.XA CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
| CN201710506953.9A CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| CN201510712904.1A CN105203291B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system for vector propulsion model aircraft |
| CN201710508256.7A CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
| CN201710507559.7A CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| CN201710508245.9A CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft |
Applications Claiming Priority (1)
| 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 |
Related Child Applications (8)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710506953.9A Division CN107271137B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion wind tunnel pilot system |
| CN201710506958.1A Division CN107389296B (en) | 2015-10-28 | 2015-10-28 | A kind of model aircraft for wind-tunnel |
| CN201710507558.2A Division CN107271135B (en) | 2015-10-28 | 2015-10-28 | The wind tunnel system of model aircraft test is promoted for vector |
| CN201710507560.XA Division CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
| CN201710506983.XA Division CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
| CN201710507559.7A Division CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| CN201710508256.7A Division CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
| CN201710508245.9A Division CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105203291A true CN105203291A (en) | 2015-12-30 |
| CN105203291B CN105203291B (en) | 2017-07-28 |
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Family Applications (9)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710508245.9A Expired - Fee Related CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft |
| CN201710507558.2A Expired - Fee Related CN107271135B (en) | 2015-10-28 | 2015-10-28 | The wind tunnel system of model aircraft test is promoted for vector |
| CN201710506983.XA Expired - Fee Related CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
| 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 |
| CN201710507559.7A Expired - Fee Related CN107152996B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft for wind tunnel test |
| CN201710507560.XA Expired - Fee Related CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
| 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 |
| CN201710508256.7A Expired - Fee Related CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
Family Applications Before (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710508245.9A Expired - Fee Related CN107356403B (en) | 2015-10-28 | 2015-10-28 | A kind of vector propulsion model aircraft |
| CN201710507558.2A Expired - Fee Related CN107271135B (en) | 2015-10-28 | 2015-10-28 | The wind tunnel system of model aircraft test is promoted for vector |
| CN201710506983.XA Expired - Fee Related CN107340117B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test model aircraft |
Family Applications After (5)
| 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 |
| CN201710507560.XA Expired - Fee Related CN107389292B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel system for vector propulsion trial |
| 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 |
| CN201710508256.7A Expired - Fee Related CN107271136B (en) | 2015-10-28 | 2015-10-28 | A kind of wind tunnel test system |
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| CN106441780A (en) * | 2016-09-06 | 2017-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Scaling model flight flutter test pulse excitation method |
| CN106599401A (en) * | 2016-11-28 | 2017-04-26 | 北京动力机械研究所 | Method for simulating flexibility of adjustable tailpipe nozzle based on friction equivalence and orthogonal experiment |
| CN106644361A (en) * | 2016-09-30 | 2017-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Simple method for measuring transonic wind tunnel test section space flow field symmetry |
| CN107115678A (en) * | 2017-06-16 | 2017-09-01 | 中电科芜湖通用航空产业技术研究院有限公司 | Model aircraft support meanss |
| CN110261057A (en) * | 2019-07-03 | 2019-09-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
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| CN106644361B (en) * | 2016-09-30 | 2018-12-28 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of simple and easy method measuring transonic wind tunnel test section space flow field symmetry |
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| CN107115678A (en) * | 2017-06-16 | 2017-09-01 | 中电科芜湖通用航空产业技术研究院有限公司 | Model aircraft support meanss |
| CN110261057A (en) * | 2019-07-03 | 2019-09-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
| CN113899516A (en) * | 2021-09-30 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ground simulation device and method for rocket engine jet flow interference effect |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107271136A (en) | 2017-10-20 |
| CN107356403A (en) | 2017-11-17 |
| CN107271137B (en) | 2019-09-13 |
| CN107389292B (en) | 2019-09-13 |
| CN107356403B (en) | 2019-10-11 |
| CN107389292A (en) | 2017-11-24 |
| CN107389296B (en) | 2019-09-13 |
| CN107389296A (en) | 2017-11-24 |
| CN107271137A (en) | 2017-10-20 |
| CN107340117B (en) | 2019-10-11 |
| CN107271135B (en) | 2019-09-13 |
| CN107152996B (en) | 2019-09-13 |
| CN105203291B (en) | 2017-07-28 |
| CN107271135A (en) | 2017-10-20 |
| CN107271136B (en) | 2019-10-11 |
| CN107340117A (en) | 2017-11-10 |
| CN107152996A (en) | 2017-09-12 |
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