CN205981615U - Realize set out supporting mechanism of match test of small -size advancing device in intermittent wind tunnel - Google Patents
Realize set out supporting mechanism of match test of small -size advancing device in intermittent wind tunnel Download PDFInfo
- Publication number
- CN205981615U CN205981615U CN201621041194.0U CN201621041194U CN205981615U CN 205981615 U CN205981615 U CN 205981615U CN 201621041194 U CN201621041194 U CN 201621041194U CN 205981615 U CN205981615 U CN 205981615U
- Authority
- CN
- China
- Prior art keywords
- sideslip
- joint
- tunnel
- line
- wind
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model provides a realize set out supporting mechanism of match test of small -size advancing device in intermittent wind tunnel, but includes preceding stores pylon, back stores pylon, branch, turns to and becomes the hypoplastron that sideslips, becomes to sideslip and connect expansion joint, side line and the back line that rises that rises, preceding, the rear end of branch be connected with respectively before stores pylon and back stores pylon, the testpieces is connected with preceding stores pylon and back stores pylon, the rear end of branch becomes the hypoplastron that sideslips and is connected with turning to, turns to to become the hypoplastron that sideslips and connect, turns to to become sideslip hypoplastron and the change articulate that sideslips, the joint passes through expansion joint and is connected with the wind -tunnel tulwar but the change is sideslipped, line and the change articulate that sideslips that rises that inclines, rise by the line and be connected with the wind -tunnel tulwar in the back. Utilize the intermittent wind tunnel, adopt the utility model discloses a structure can realize the set out matching performance test of small -size advancing device, the problem of the wake flame that forms of engine ignition and the influence of tail gas is solved, it is stable to support connection structure, an experimental enviroment of true engine ignition is provided.
Description
Technical field
This utility model is related to small-sized propulsion wind tunnel experimental technique field and in particular to realizing little in a kind of intermittent wind tunnel
The supporting mechanism of type propulsion plant inlet engine compatibility test.
Background technology
Air intake duct is mated with jet flow field, is primarily referred to as air intake port flow distortion and its to engine air dynamic stability
Property impact evaluation.The research that aircraft air inlet/engine is entered/sent out with compatibility matching problem mainly includes two aspects：
One is the impact to the pneumatic aspect of performance of electromotor, i.e. the aerodynamic response problem to inlet distortion for the electromotor；Two is to electromotor
The impact of structural intergrity aspect, i.e. the structural response problem to inlet distortion for the electromotor.In order to solve aircraft, air intake duct and send out
The consistency problem of motivation, abroad generally adopts two kinds of propulsion system simulated test facilitys, one is altitude simulation test platform, and two are
Propulsion wind tunnel.There is no propulsion wind tunnel due to domestic, using intermittent wind tunnel, need to design a kind of special propping up for this wind-tunnel
Support mechanism.
Utility model content
Based on above weak point, this utility model provides to be realized small-sized propulsion plant and sets out in a kind of intermittent wind tunnel
The supporting mechanism of match test, for carrying out small-sized propulsion plant inlet engine compatibility compatibility test in intermittent wind tunnel.
The technology that this utility model adopts is as follows：A kind of special support attachment structure of inlet engine compatibility test, including front hanging
Frame, rear hanger, pole, turn to become sideslip lower plate, become sideslip joint, collapsible joint, side rise by line and rises line in back, described
The front and back ends of bar are connected to front hanger and rear hanger, and testpieces is connected with front hanger and rear hanger, the rear end of pole with turn
To becoming the connection of sideslip lower plate, turn to and become the connection of sideslip lower plate, turn to change sideslip lower plate and be connected with becoming sideslip joint, become sideslip joint
It is connected with wind-tunnel tulwar by collapsible joint, rise line and become sideslip joint and connect for side, and the back line that rises is connected with wind-tunnel tulwar.
This utility model also has following technical characteristic：This structure also includes communication cable line, and communication cable line depends on
Pole is fixed, and in its outer wrap thermally protective materials.
Advantage of the present utility model and having the beneficial effects that：Intermittent wind tunnel can be utilized using structure of the present utility model
Realize propulsion wind tunnel function, complete small-sized propulsion plant inlet engine compatibility performance test；Solve the wake flame of engine ignition formation
And the impact problem of tail gas；Support attachment structure stable；Provide the experimental enviroment of actual engine igniting, can be used for inspection and send out
Motivation and Inlet Port Matching starting ignition and acceleration, under the different angles of attack of inspection and yaw angle combination, electromotor and air intake duct
Coupling cooperation performance, inspection fuel system and electromotor start, accelerate and active section matching performance, and obtain and start
Windmill rotary speed property under the conditions of the air intake duct of coupling for the machine, windmilling startup under the conditions of the air intake duct of coupling for the research electromotor
Feasibility.
Brief description
Fig. 1 is that inlet engine compatibility supports attachment structure sketch,
Fig. 2 is inlet engine compatibility test observing and controlling flow chart.
Wherein, 1- testpieces, 2- propulsion plant, 3- turn to and become sideslip lower plate, 4- collapsible joint, 5- pole, 6- front hanging
Hanger after frame, 7-, 8- become sideslip joint, rise in 9- back line, 10- side rise line, 11- wind tunnel body, 12- wind-tunnel tulwar, 13- wind-tunnel
Control system, 14- dynamic data collection system, 15- Propulsion Control System.
Specific embodiment
In conjunction with accompanying drawing 1,2, provide following examples, the technical solution of the utility model is described further.
Embodiment 1
As shown in figure 1, realizing the supporting mechanism of small-sized propulsion plant inlet engine compatibility test in a kind of intermittent wind tunnel, including
Front hanger 6, rear hanger 7, pole 5, turn to become sideslip lower plate 3, become sideslip joint 8, rise line 10 and back in collapsible joint 4, side
Rise line 9, and the front and back ends of described pole 5 are connected to front hanger 6 and rear hanger 7, testpieces 1 and front hanger 6 and rear hanger
7 connections, realize the support of the testpieces 1 with propulsion plant, and the rear end of pole 5 is connected with turning to change sideslip lower plate 3, and realizing will
Testpieces 1 is positioned between wind-tunnel supporting plate and hole wall it is ensured that propulsion plant wake flame is to wind-tunnel facilities fanout free region, turns to and becomes under sideslip
Plate 3 connects, and turns to change sideslip lower plate 3 and is connected with becoming sideslip joint 8, becomes sideslip joint 8 and passes through collapsible joint 4 and wind-tunnel tulwar
12 connections, rise line 10 and become sideslip joint 8 and connect for side, this supporting construction is reinforced, line 9 is risen by with wind-tunnel tulwar 12 even in back
Connect.Communication cable line depends on pole 5 and is fixed, and in its outer wrap thermally protective materials it is ensured that it being capable of normal work.
This support attachment structure ensure that stability and the safety of testpieces, eliminates support to flow field around inlet lip simultaneously
Interference it is ensured that the safety of wind-tunnel facilities and communication cable normal work under hot environment.Support is to abdominal part embedded type air inlet
Around road, flow field is noiseless.Ensure that the normal work of cable under hot conditionss using thermally protective materials.
Embodiment 2
As shown in Fig. 2 inlet engine compatibility test observing and controlling flow process can ensure that wind tunnel control system 13, dynamic data collection system
14 and Propulsion Control System 15 three time shafts unification, wind tunnel control system 13 is after testpieces 1 reaches suitable attitude
To Propulsion Control System 15 and dynamic collect system 14 sending signal, the two enters corresponding working state, propulsion plant control
System 15 processed carries out State Transferring and carries out data record, to wind tunnel control system 13 and Dynamic Data Acquiring system after the completion of action
System 14 carries out signal response, and wind tunnel control system carries out pose adjustment again to testpieces, repeats said process, until performance is surveyed
Examination finishes.
Claims (2)
1. in a kind of intermittent wind tunnel, realize the supporting mechanism of small-sized propulsion plant inlet engine compatibility test, including before hanger (6), after
Hanger (7), pole (5), turn to become sideslip lower plate (3), become sideslip joint (8), rise line (10) and the back of the body in collapsible joint (4), side
Portion rise line (9) it is characterised in that：The front and back ends of described pole (5) are connected to front hanger (6) and rear hanger (7), examination
Test part (1) to be connected with front hanger (6) and rear hanger (7), the rear end of pole (5) is connected with turning to change sideslip lower plate (3), turn to and become
Sideslip lower plate (3) connects, and turns to change sideslip lower plate (3) and is connected with becoming sideslip joint (8), and change sideslip joint (8) is passed through scalable
Joint (4) is connected with wind-tunnel tulwar (12), and rise line (10) and become sideslip joint (8) and connect for side, and rise line (9) and wind-tunnel tulwar at back
(12) connect.
2. in a kind of intermittent wind tunnel according to claim 1, realize the support machine of small-sized propulsion plant inlet engine compatibility test
Structure it is characterised in that：Also include communication cable line, communication cable line depends on pole (5) and is fixed, and in its outer wrap
Thermally protective materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621041194.0U CN205981615U (en) | 2016-09-07 | 2016-09-07 | Realize set out supporting mechanism of match test of small -size advancing device in intermittent wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621041194.0U CN205981615U (en) | 2016-09-07 | 2016-09-07 | Realize set out supporting mechanism of match test of small -size advancing device in intermittent wind tunnel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205981615U true CN205981615U (en) | 2017-02-22 |
Family
ID=58039883
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621041194.0U Active CN205981615U (en) | 2016-09-07 | 2016-09-07 | Realize set out supporting mechanism of match test of small -size advancing device in intermittent wind tunnel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205981615U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106441785A (en) * | 2016-09-07 | 2017-02-22 | 中国航空工业集团公司沈阳空气动力研究所 | Support mechanism for small propulsion device inlet engine compatibility test in intermittent wind tunnel |
| CN107976315A (en) * | 2017-11-17 | 2018-05-01 | 西安航天动力测控技术研究所 | A kind of angle of attack yaw angle servo control mechanism for Ducted rocket free jet test |
-
2016
- 2016-09-07 CN CN201621041194.0U patent/CN205981615U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106441785A (en) * | 2016-09-07 | 2017-02-22 | 中国航空工业集团公司沈阳空气动力研究所 | Support mechanism for small propulsion device inlet engine compatibility test in intermittent wind tunnel |
| CN107976315A (en) * | 2017-11-17 | 2018-05-01 | 西安航天动力测控技术研究所 | A kind of angle of attack yaw angle servo control mechanism for Ducted rocket free jet test |
| CN107976315B (en) * | 2017-11-17 | 2019-05-31 | 西安航天动力测控技术研究所 | A kind of angle of attack yaw angle servo mechanism for Ducted rocket free jet test |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106441785A (en) | Support mechanism for small propulsion device inlet engine compatibility test in intermittent wind tunnel | |
| CN103630363B (en) | Test method and test device for simulating high altitude ignition ability of turbine engine | |
| CN106568568B (en) | A kind of high-temperature fuel gas stream supersonic wind tunnel pilot system | |
| CN103149010B (en) | NPLS measurement system and method for air inlet channel flow field based on high-supersonic-velocity pulse wind tunnel | |
| CN205981615U (en) | Realize set out supporting mechanism of match test of small -size advancing device in intermittent wind tunnel | |
| CN103970957B (en) | Simulation method for elastic waverider hypersonic flight vehicle | |
| CN105784318A (en) | Low-speed wind tunnel model flying experimental system and method | |
| CN103954389B (en) | Jet vane dynamometer check device | |
| CN201983918U (en) | Retractable diffuser for supersonic wind tunnel | |
| CN107436219B (en) | Inlet and exhaust pipeline device in unconventional layout form | |
| CN102478451A (en) | Active flow control testing unit for air inlet duct of high-speed wind tunnel | |
| CN207045661U (en) | Eight rotor plant protection unmanned planes and its flying wing arm knob are disassembled | |
| CN109470401A (en) | It is a kind of with meet side angle degree resolving straight rod type pitot | |
| CN108502188A (en) | A kind of plant protection drone spraying operation wind field test system and method | |
| CN103499447B (en) | For zero Mach number test unit of turbine engine | |
| CN102818692B (en) | Yaw-angle free vibration test device with short and blunt appearance like spacecraft | |
| CN109026524B (en) | A kind of variable Rate feathering halt control method of wind power generating set | |
| CN112284675A (en) | Wind tunnel for multi-body separation dynamics research | |
| CN207163318U (en) | A kind of unmanned plane with trap setting | |
| CN204286804U (en) | A kind of turbo oar engine ground run bench frame apparatus | |
| CN112415220B (en) | Method and system for estimating toppling wind speed of winged aircraft in vertical state | |
| CN206688230U (en) | A kind of four rotor kites | |
| CN105387990A (en) | Direct-current wind tunnel device and working method thereof | |
| CN208860571U (en) | Propulsive thrust test pressure-air, which disappears, disturbs device | |
| CN208688345U (en) | The hollow non-priming system guided missile of air intake duct |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |