CN205785823U - A kind of space propulsion plume measures heat flow transducer fixing device - Google Patents
A kind of space propulsion plume measures heat flow transducer fixing device Download PDFInfo
- Publication number
- CN205785823U CN205785823U CN201620452649.1U CN201620452649U CN205785823U CN 205785823 U CN205785823 U CN 205785823U CN 201620452649 U CN201620452649 U CN 201620452649U CN 205785823 U CN205785823 U CN 205785823U
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- Prior art keywords
- flow transducer
- heat flow
- fixing device
- plume
- diameter
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model discloses a kind of space propulsion plume and measure heat flow transducer fixing device, heat flow transducer can be fixed on deflection cone, neither affect the plume of free diffusing at engine nozzle, ensure black matrix and deflection cone flush simultaneously, accurately measure the changes of heat flux situation of this position, the installation of heat flow transducer freely adjusts with deflection cone change in location, short form test set-up procedure, reaches the effect accurately measured.
Description
Technical field
This utility model relates to space propulsion technical field, particularly relates to a kind of space propulsion plume and measures hot-fluid
Sensor fastening device.
Background technology
Space propulsion is widely used on the spacecraft such as rocket, satellite.When electromotor is lighted a fire under vacuum conditions, in spray
The plume of external environment free wxpansion will be formed at Kou.The spacecraft surface being pointed in plume is produced and hits by plume
Hit, and cause power, heat and surface contamination effect.In plume, the local in short-term of heat raises the surface genus that will destroy spacecraft
Property or damage scientific instrument, shorten the spacecraft life-span, even result in spacecraft lost efficacy.
At present, the thermal change research method of plume includes plume numerical simulation, space carrying flight test and plume
Ground experiment.Plume numerical simulation relies primarily on the method for CFD and DSMC coupling and is modeled Vacuum Plume pressure and analyzes,
The calculating of single thruster/many thruster plumes field, some complicated air-flows and the numerical simulation of effect thereof can be carried out.But, number
Value simulation study needs test data to verify, some of complex operating mode, as the change of plume boundary member pressure cannot be passed through
Emulation carrys out Accurate Analysis；Space carrying flight test is directly to measure to obtain key position during the practical flight of spacecraft
Pressure information, be characterized in that measurement result is authentic and valid, but test number (TN) be few, single test cost height, cycle length, obtain number
Limited according to amount；The system Construction one-time investment of plume ground experiment is big, but single test low cost, and examination can be repeated
Test.Can also carry out multi-state, multi-mode principle and proving test, the data of acquisition are more suitable for being analyzed and studying.
For the Financial cost that plume ground experiment is high, the Heat Flow Analysis of domestic existing plume is still in theoretical point
Analysis and modeling and simulating stage, the indivedual plume testings carried out also cause measurement result to there is certain deviation because of condition shortcoming.
The Vacuum Plume testing stand that work office of national defence section in 2015 reply, Beijing Institute of Aerospace Testing Technology invest to build is the full chi of the domestic seat of honour
Very little space propulsion plume experimental study system, is also domestic unique one and tries for full-scale space propulsion plume
Test the heat-flow measurement system built.
The most conventional heat-flow measurement element is circular foil heat flux transducer.Circular foil heat flux transducer can be used in vacuum
The measurement of the hot-fluid under environment.Its simple in construction, response rapidly, non-cpntact measurement can be carried out, thus obtain extensive concern.
Due to the unique texture of circular foil heat flux transducer, there is no the mounting means for circular foil heat flux transducer at present
And corresponding mechanical erection frock, when mounted, heat flow transducer is entered by metal rack and iron wire that usual employing is built temporarily
Row is fixing, will tie up and be fixed on brandreth by heat flow transducer, and the method is difficult to install, and adjusts and be highly inconvenient for.
Utility model content
In view of this, this utility model provides a kind of space propulsion plume and measures heat flow transducer fixing device,
Ensure that sensor is installed quickly and easily in the range of measuring, it is intended to accurately measure vacuum plumage in engine working process
The changes of heat flux in flow field.
A kind of space propulsion plume measures heat flow transducer fixing device, and described heat flow transducer includes black matrix, heat
Heavy body, screwed hole and base, described fixing device is annular cylindrical structure, and interior circular diameter is more than described heat sink body diameter, outward
Circular diameter is equal to described base diameter, and height is less than the height of described heat sink body, and annular surface is distributed 6 identical leading to of size
Hole, through-hole diameter is identical with the big footpath of described screwed hole, and the reference circle of 6 through holes is identical with the reference diameter of screwed hole.
It is also preferred that the left the material of described fixing device is duralumin.
This utility model has the advantages that
The space propulsion plume of the present invention measures heat flow transducer fixing device, it is possible to be fixed on by heat flow transducer
On deflection cone.Neither affect the plume of free diffusing at engine nozzle, ensure black matrix and deflection cone flush, accurately simultaneously
Measure the changes of heat flux situation of this position.The installation of heat flow transducer freely adjusts with deflection cone change in location, and short form test is accurate
Standby process, reaches the effect accurately measured.
Accompanying drawing explanation
Fig. 1 is circular foil heat flux transducer structural representation；
Fig. 2 is electromotor and deflection cone position relationship schematic diagram；
Fig. 3 is heat flow transducer mounting tool structural representation；
Fig. 4 (a) is deflection cone structure chart, and Fig. 4 (b) is the sectional view of heat flow transducer mounting structure, and heat flow transducer is pacified
Assembling structure, Fig. 4 (c) be heat flow transducer mounting structure upward view.
Wherein, 1-heat flow transducer, 1.1-black matrix, 1.2-is heat sink body, 1.3-screwed hole, 1.4-base, 1.5-holding wire,
2-electromotor, 3-deflection cone, 4-screw, 5-nut.
Detailed description of the invention
Develop simultaneously embodiment below in conjunction with the accompanying drawings, is described in detail this utility model.
As it is shown in figure 1, circular foil heat flux transducer 1 includes black matrix 1.1, heat sink body 1.2, screwed hole 1.3, base 1.4 He
Holding wire 1.5.Screwed hole 1.3 a size of M3x1.During heat-flow measurement, black matrix 1.1 will be just to the tested hot-fluid side of stream
To, i.e. by black matrix 1.1 perception thermal change situation, thus black matrix 1.1 can not be blocked or destroy.
When the position relationship schematic diagram of electromotor 2 and deflection cone 3 is as in figure 2 it is shown, test, deflection cone 3 is placed on electromotor 2
Spout direction, after the gas that nozzle sprays downwards runs into deflection cone 3, spread in the horizontal direction by the shape of deflection cone 3, with
Prevent high heat gas from quicking rebound destruction engine jet pipe.
Deflection cone 3 is the taper seat aluminium sheet that 6mm is thick, and surface has the through hole of Ф 3, and basal diameter is 1m, high 180mm, cone
20 ° of angle, is arranged in electromotor flame and carrys out flow path direction, and surface is surrounded by heat-barrier material.
At the trial, heat flow transducer 1 should be arranged according to the shape of deflection cone 3 and position.
For achieving the above object, the technical solution of the utility model is:
A kind of space propulsion plume measures heat flow transducer fixing device, as it is shown on figure 3, material is duralumin, for ring
Shape column structure, interior circular diameter is slightly larger than heat flow transducer heat sink body 1.2 diameter, and outside diameter is equal to base 1.4 diameter, highly
Being slightly less than the height of heat sink body 1.2, annular surface is distributed 6 identical through holes of size, and through-hole diameter is big with screwed hole 1.3
Footpath is identical, and the reference circle of 6 through holes is identical with the reference diameter of screwed hole 1.3.
Described space propulsion plume measures heat flow transducer fixing device, in test set-up procedure, such as Fig. 4
Shown in (a), Fig. 4 (b) and Fig. 4 (c), by low temperature glue, fixing device 2 is bonded in deflection cone 3 back side, then by thermal-flow sensor
The heat sink body 1.2 of device 1 stretches in fixing device, it is ensured that black matrix 1.1 and the flush of deflection cone 2.The ailhead of flat head screw 4 with
Deflection cone 3 flush, the screw rod of flat head screw 4 is each passed through deflection cone 3 surface through hole, the through hole of fixing device 2 and circle paper tinsel
The screwed hole 1.3 of formula heat flow transducer 1, and fasten at the end face nut 5 of heat flow transducer base 1.4.
Heat flow transducer fixing device is measured, it is possible to by solid for heat flow transducer 1 by described space propulsion plume
It is scheduled on deflection cone 3.Neither affect the plume of electromotor 2 nozzle free diffusing, ensure black matrix 1.1 and deflection cone 3 table simultaneously
Face is concordant, accurately measures the changes of heat flux situation of this position.The installation of heat flow transducer 1 is freely adjusted with deflection cone 3 change in location
Whole, short form test set-up procedure, reach the effect accurately measured.
In sum, these are only preferred embodiment of the present utility model, be not intended to limit of the present utility model
Protection domain.All within spirit of the present utility model and principle, any modification, equivalent substitution and improvement etc. made, all should wrap
Within being contained in protection domain of the present utility model.
Claims (2)
1. space propulsion plume measures a heat flow transducer fixing device, and described heat flow transducer (1) includes black matrix
(1.1), heat sink body (1.2), screwed hole (1.3) and base (1.4), it is characterised in that described fixing device is annular cylindrical
Structure, interior circular diameter is more than described heat sink body (1.2) diameter, and outside diameter is equal to described base (1.4) diameter, and height is less than institute
Stating the height of heat sink body (1.2), annular surface is distributed 6 identical through holes of size, through-hole diameter and described screwed hole (1.3)
Big footpath identical, the reference circle of 6 through holes is identical with the reference diameter of screwed hole (1.3).
2. a kind of space propulsion plume as claimed in claim 1 measures heat flow transducer fixing device, it is characterised in that
The material of described fixing device is duralumin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620452649.1U CN205785823U (en) | 2016-05-18 | 2016-05-18 | A kind of space propulsion plume measures heat flow transducer fixing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620452649.1U CN205785823U (en) | 2016-05-18 | 2016-05-18 | A kind of space propulsion plume measures heat flow transducer fixing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205785823U true CN205785823U (en) | 2016-12-07 |
Family
ID=58119032
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620452649.1U Expired - Fee Related CN205785823U (en) | 2016-05-18 | 2016-05-18 | A kind of space propulsion plume measures heat flow transducer fixing device |
Country Status (1)
| Country | Link |
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| CN (1) | CN205785823U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107860544A (en) * | 2017-10-24 | 2018-03-30 | 北京特种机械研究所 | A kind of Vacuum Plume water conservancy diversion ground experiment protector |
| CN107894320A (en) * | 2017-11-07 | 2018-04-10 | 北京特种机械研究所 | The plume water conservancy diversion ground experiment protector of detector is disposed vertically in vacuum chamber |
| CN114264446A (en) * | 2021-12-23 | 2022-04-01 | 中国电子科技集团公司第十八研究所 | Multi-degree-of-freedom pose adjustable electric propulsion plume test tool |
| CN115680943A (en) * | 2022-10-31 | 2023-02-03 | 北京航天试验技术研究所 | Rocket engine heat radiation measuring device |
-
2016
- 2016-05-18 CN CN201620452649.1U patent/CN205785823U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107860544A (en) * | 2017-10-24 | 2018-03-30 | 北京特种机械研究所 | A kind of Vacuum Plume water conservancy diversion ground experiment protector |
| CN107860544B (en) * | 2017-10-24 | 2019-09-10 | 北京特种机械研究所 | A kind of Vacuum Plume water conservancy diversion ground experiment protective device |
| CN107894320A (en) * | 2017-11-07 | 2018-04-10 | 北京特种机械研究所 | The plume water conservancy diversion ground experiment protector of detector is disposed vertically in vacuum chamber |
| CN114264446A (en) * | 2021-12-23 | 2022-04-01 | 中国电子科技集团公司第十八研究所 | Multi-degree-of-freedom pose adjustable electric propulsion plume test tool |
| CN114264446B (en) * | 2021-12-23 | 2023-08-29 | 中电科蓝天科技股份有限公司 | Multi-degree-of-freedom pose-adjustable electric propulsion plume test tool |
| CN115680943A (en) * | 2022-10-31 | 2023-02-03 | 北京航天试验技术研究所 | Rocket engine heat radiation measuring device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161207 Termination date: 20170518 |