CN109186377A - A kind of supersonic inlet inside alternating temperature heating means - Google Patents
A kind of supersonic inlet inside alternating temperature heating means Download PDFInfo
- Publication number
- CN109186377A CN109186377A CN201811016745.1A CN201811016745A CN109186377A CN 109186377 A CN109186377 A CN 109186377A CN 201811016745 A CN201811016745 A CN 201811016745A CN 109186377 A CN109186377 A CN 109186377A
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- CN
- China
- Prior art keywords
- valve
- flow
- intake duct
- air
- air intake
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Steam Or Hot-Water Central Heating Systems (AREA)
Abstract
The present invention relates to alternating temperature heating means inside a kind of supersonic inlet.The present invention includes the following steps: step 1, flows to connection room temperature gas source, air heater, gate valve, proportioning valve, two-way valve, bypass outlet, air intake duct according to inlet flow；The gate valve band flowmeter；The proportioning valve band flowmeter；Step 2, air intake duct installs thermocouple；Step 3, unheated air enters air heater by the road and is heated；Step 4, regulation gate valve, the flow of proportioning valve and temperature.The present invention passes through while controlling flow and temperature, can in the case of truer simulation overall trajectory supersonic inlet environment.
Description
Technical field
The invention belongs to quiet heat integration experimental techniques, are related to a kind of supersonic inlet inside alternating temperature heating means.
Background technique
Guided missile in supersonic flight, air intake duct there are serious Aerodynamic Heating phenomenon, air intake duct Inside Air Temperature and
Flow changes with the increase of flight time.For bearing capacity of examination air intake duct under the conditions of thermal force, heat examination need to be carried out
Test the air-flow heating course of simulation air intake duct air intake duct in overall trajectory.It is heated according to traditional quartz lamp internal radiation
Method, be limited to air intake duct size and structure, it is difficult to realize.
Summary of the invention
The technical problem to be solved by the present invention is providing in the case of a kind of overall trajectory, alternating temperature adds inside supersonic inlet
Hot method.
In order to solve the above technical problems, the present invention adopts the following technical solutions: a kind of supersonic inlet inside alternating temperature adds
Hot method, includes the following steps:
Step 1, connection room temperature gas source, air heater, gate valve, proportioning valve, two-way valve, side are flowed to according to inlet flow
Way outlet, air intake duct；The gate valve band flowmeter；The proportioning valve band flowmeter；
Step 2, air intake duct installs thermocouple；
Step 3, unheated air enters air heater by the road and is heated；
Step 4, regulation gate valve, the flow of proportioning valve and temperature.
The beneficial effects of the present invention are: the present invention passes through while controlling flow and temperature, can truer simulation it is complete
The environment of supersonic inlet in the case of trajectory.
Detailed description of the invention
Fig. 1 is air intake duct temperature rise curve of the invention；
Fig. 2 is air intake duct flow curve of the invention；
Fig. 3 is air intake duct temperature adjustment schematic diagram in the present invention；
Wherein, 1- room temperature gas source, 2- air heater, 3- gate valve, 4- proportioning valve, 5- two-way valve, 6- bypass outlet, 7- wave
Line pipe, 8- air intake duct, 9- pipeline.
Specific embodiment
Illustrate a specific embodiment of the invention with reference to the accompanying drawing.
Specific step is as follows for alternating temperature heating means inside supersonic inlet of the present invention:
Step 1, room temperature gas source, air heater, gate valve (band flowmeter), proportioning valve (band stream are connected with pipeline, bellows
Meter), two-way valve 5, bypass outlet 6, air intake duct 8.
According to Fig. 3, pipeline 9, bellows 7 are connected into room temperature gas source 1, air heater 2, gate valve 3 (band flowmeter), ratio
Valve 4 (band flowmeter), two-way valve 5, bypass outlet 6, air intake duct 8 are installed.
Step 2, air intake duct installs thermocouple；
Thermocouple is installed inside air intake duct 8, measures the temperature of 8 inner air of air intake duct.
Step 3, unheated air enters air heater through pipeline and is heated.
Room temperature gas source 1 enters air heater 2 by pipeline 9, is preheated, obtains high temperature gas flow.High temperature gas flow is through pipe
Road 9 flows to gate valve 3 (band flowmeter), then 9 flows to two-way valve 5 by the road, while room temperature gas source 19 flows to proportioning valve 4 by the road
(band flowmeter), then 9 two-way valve 5 is flowed to by the road, two-way valve 5 opens bypass outlet 6 and overheating air flow is discharged.Converge through two-way valve 5
Air-flow afterwards flows to air intake duct 8 by bellows 7.
Step 4, regulation gate valve, the flow of proportioning valve and temperature.
Thermocouple measured temperature is fed back into gate valve 3 (band flowmeter) and proportioning valve 4 (band flowmeter).According to air intake duct temperature
Rise curve graph 1 and air intake duct flow curve graph 2, the temperature of control gate valve 3 (with flowmeter), 4 air-flow of proportioning valve, regulation gate valve 3
The flow of (with flowmeter), proportioning valve 4 (with flowmeter), and real-time variation is synchronized, control 8 air themperature of air intake duct.
Claims (4)
1. alternating temperature heating means inside a kind of supersonic inlet, it is characterized in that the heating means include the following steps:
Step 1 flows to connection room temperature gas source, air heater, gate valve, proportioning valve, two-way valve, bypass according to inlet flow
Outlet, air intake duct；The gate valve band flowmeter；The proportioning valve band flowmeter；
Step 2, air intake duct install thermocouple；
Step 3, unheated air enter air heater by the road and are heated；
Step 4, regulation gate valve, the flow of proportioning valve and temperature.
2. heating means according to claim 1, it is characterized in that: in the step 3, room temperature gas source (1) passes through pipeline
(9) enter air heater (2), preheated, obtain high temperature gas flow；High temperature gas flow flows to gate valve (3) by the road (9), then passes through
Pipeline (9) flows to two-way valve (5), while room temperature gas source (1) flows to proportioning valve (4) by the road (9), then (9) flow direction is double by the road
To valve (5), two-way valve (5) opens bypass outlet (6) discharge overheating air flow；Air-flow after two-way valve (5) converges, passes through bellows
(7) air intake duct (8) are flowed to.
3. heating means according to claim 1, it is characterized in that: in the step 4, thermocouple measured temperature is fed back
Return gate valve (3) and proportioning valve (4)；The temperature of control gate valve (3), proportioning valve (4) air-flow, regulation gate valve (3), proportioning valve (4)
Flow, and real-time variation is synchronized, control air intake duct (8) air themperature.
4. heating means according to claim 3, it is characterized in that: in the step 4, according to air intake duct temperature rise curve figure
With air intake duct flow curve graph, the flow of regulation gate valve (3), proportioning valve (4), and real-time variation is synchronized, control air intake duct (8) is empty
Temperature degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811016745.1A CN109186377A (en) | 2018-08-31 | 2018-08-31 | A kind of supersonic inlet inside alternating temperature heating means |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811016745.1A CN109186377A (en) | 2018-08-31 | 2018-08-31 | A kind of supersonic inlet inside alternating temperature heating means |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109186377A true CN109186377A (en) | 2019-01-11 |
Family
ID=64917771
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811016745.1A Pending CN109186377A (en) | 2018-08-31 | 2018-08-31 | A kind of supersonic inlet inside alternating temperature heating means |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109186377A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6648235B2 (en) * | 2002-04-08 | 2003-11-18 | Guard Sound Industry Co., Ltd. | Control method of thermostatic system |
| CN104360702A (en) * | 2014-10-30 | 2015-02-18 | 北京航空航天大学 | System for dynamically testing aviation thermal power and method for dynamically controlling temperature and pressure environments |
| CN104460790A (en) * | 2014-12-30 | 2015-03-25 | 北京航空航天大学 | Dynamic aviation thermal power testing system and rapid temperature and pressure control method |
| CN108458852A (en) * | 2018-05-24 | 2018-08-28 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high-temperature tunnel quick changeable temperature potential device and alternating temperature voltage-transforming method |
-
2018
- 2018-08-31 CN CN201811016745.1A patent/CN109186377A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6648235B2 (en) * | 2002-04-08 | 2003-11-18 | Guard Sound Industry Co., Ltd. | Control method of thermostatic system |
| CN104360702A (en) * | 2014-10-30 | 2015-02-18 | 北京航空航天大学 | System for dynamically testing aviation thermal power and method for dynamically controlling temperature and pressure environments |
| CN104460790A (en) * | 2014-12-30 | 2015-03-25 | 北京航空航天大学 | Dynamic aviation thermal power testing system and rapid temperature and pressure control method |
| CN108458852A (en) * | 2018-05-24 | 2018-08-28 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high-temperature tunnel quick changeable temperature potential device and alternating temperature voltage-transforming method |
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Legal Events
| Date | Code | Title | Description |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190111 |
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| RJ01 | Rejection of invention patent application after publication |