CN203811348U - Airplane liquid discharge simulation device used for wind tunnel tests - Google Patents
Airplane liquid discharge simulation device used for wind tunnel tests Download PDFInfo
- Publication number
- CN203811348U CN203811348U CN201420149288.4U CN201420149288U CN203811348U CN 203811348 U CN203811348 U CN 203811348U CN 201420149288 U CN201420149288 U CN 201420149288U CN 203811348 U CN203811348 U CN 203811348U
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- China
- Prior art keywords
- liquid
- wind tunnel
- wind
- test
- analogue means
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- 238000012360 testing method Methods 0.000 title claims abstract description 69
- 239000007788 liquid Substances 0.000 title claims abstract description 46
- 238000004088 simulation Methods 0.000 title claims abstract description 15
- 239000012530 fluid Substances 0.000 claims abstract description 39
- 238000002347 injection Methods 0.000 claims description 11
- 239000007924 injection Substances 0.000 claims description 11
- 239000007789 gas Substances 0.000 claims description 10
- 238000009434 installation Methods 0.000 claims description 7
- 238000007599 discharging Methods 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 6
- 238000012546 transfer Methods 0.000 claims description 4
- 230000006698 induction Effects 0.000 claims description 3
- 238000012856 packing Methods 0.000 claims description 3
- 230000001052 transient effect Effects 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 4
- 230000003139 buffering effect Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000000889 atomisation Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000012857 repacking Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Abstract
The utility model discloses an airplane liquid discharge simulation device used for wind tunnel tests. The airplane liquid discharge simulation device comprises a liquid storage part (10), a buffer room (20) and a liquid discharge part (30); the liquid storage part contains test liquid, the test liquid in the liquid storage part (10) is supplied to the buffer room (20) through a conveying part and is stored and buffered in the surge chamber (20) temporarily; the liquid discharge part (30) is in fluid communication with the surge chamber (20) and extends to pass through an opening in a wind-tunnel wall and enters a wind tunnel test area; wherein the test liquid entering the wind tunnel test area is in a liquid flow state under actual flight conditions. The airplane liquid discharge simulation device used for the wind tunnel tests needs to be obtained only by slightly refitting present wind tunnel equipment, technicists can intuitively and reliably carry out simulation tests of the fluid state of liquid discharged out of the airplane during the airplane flight period, and furthermore the design of a airplane liquid discharge scheme can be effectively guided.
Description
Technical field
The utility model relates to wind-tunnel technique field, relates in particular to a kind of aircraft fluid discharge analogue means for wind tunnel test.
Background technology
In wind tunnel test field, current test unit and means less than flow state after the discharge of liquid under tunnel simulation airplane operating conditions body.Therefore, technician cannot be studied in advance and contrast various aircraft discharge opeing schemes intuitively by wind tunnel test, can only instruct by theoretical analysis and experience the design of aircraft discharge opeing scheme, and then check the effect of discharge opeing scheme by the flight test of true aircraft.Consequently, experimentation cost is high, the cycle is long, and aircraft cleans wastes time and energy, and the liquid giving off may, to other system generation considerable influence of aircraft, have certain Risk of flight-test.
Utility model content
The purpose of this utility model is that the shortcoming that overcomes above-mentioned existing testing program is with not enough, provide a kind of aircraft fluid discharge analogue means for wind tunnel test, simulation and the research of flow state after liquid discharge body can realize aircraft flight by this analogue means time in wind-tunnel.
According to the utility model, comprise fluid storage parts for the aircraft fluid discharge analogue means of wind tunnel test, in it, hold test(ing) liquid; Surge chamber, the test(ing) liquid in described fluid storage parts is supplied to described surge chamber temporary transient storage therein and is cushioned by transfer unit; Discharge opeing parts, it is communicated with described surge chamber fluid and the opening that extends through on wind-tunnel wall enters wind tunnel test region; Wherein, the described test(ing) liquid that enters wind tunnel test region has the liquid flowing state under practical flight condition.
According to a kind of embodiment, described test(ing) liquid enters described surge chamber under self gravitation effect.This can realize by multiple means, for example, described fluid storage parts is placed on to certain altitude position, makes test(ing) liquid just can flow into smoothly surge chamber by gravity under trystate.
According to another kind of embodiment, described analogue means also comprises ejection system, and described ejection system comprises high-pressure air source, pressure regulator valve and adjustable induction apparatus, is used for that gases at high pressure are introduced to described surge chamber and carries out injection discharge opeing simulation.In this way, aircraft fluid discharge analogue means of the present utility model can provide the analog capability of gas injection discharge opeing simultaneously, and real flight test environment is provided.
According to a kind of embodiment, described surge chamber and described discharge opeing parts are constructed to one.
According to a kind of embodiment, described discharge opeing parts are sealingly connected to the opening on described wind-tunnel wall by stationary installation.
Alternatively, described stationary installation comprise be socketed on the joint flange of described discharge opeing parts and be arranged in described joint flange and described wind-tunnel wall between packing ring.Those skilled in the art will be understood that any parts that other realization is tightly connected all can adopt.
According to a kind of embodiment, described discharge opeing parts are dismountable, and the discharge opeing bar of difformity and size or discharging tube can be served as discharge opeing parts and be connected with whole aircraft fluid discharge analogue means, thereby can meet different discharge opeing needs.As selection, also can remove discharge opeing bar or discharging tube and carry out the simulation of zero elevation outage discharge opeing.
Only need existing wind-tunnel facilities (being generally direct current wind-tunnel) to carry out repacking slightly according to the aircraft fluid discharge analogue means for wind tunnel test of the present utility model, can contribute to technician by wind tunnel test intuitive and reliable carry out fluid discharge during aircraft flight and go out the simulation test of fluid state after body, and then effectively instruct the design of aircraft discharge opeing scheme.In addition, except discharge opeing parts, other parts of analogue means of the present utility model are all positioned at wind-tunnel outside, are convenient to technician and implement.
Brief description of the drawings
More features of the present utility model and advantage are by by understanding better the further description of preferred implementation below in conjunction with accompanying drawing.Wherein:
Fig. 1 is according to the structural representation of the aircraft fluid discharge analogue means for wind tunnel test of a kind of preferred implementation of the utility model.
Embodiment
Discuss enforcement and the use of embodiment below in detail.But, should be appreciated that discussed specific embodiment only exemplarily illustrates and implements and use ad hoc fashion of the present utility model, and unrestricted scope of the present utility model.
Referring to Fig. 1, mainly comprise fluid storage parts 10, surge chamber 20 and discharge opeing parts 30 according to the aircraft fluid discharge analogue means for wind tunnel test of the present utility model.Test(ing) liquid is contained in fluid storage parts 10, and by transfer unit, such as fluid regulating valve (not shown), liquid feeding pipeline 11, feed flow port one 2 etc. are supplied in surge chamber 20 and realize continuous, adjustable, gageable test(ing) liquid supply.Surge chamber 20 provides test(ing) liquid to enter temporary transient storage and the buffering before wind-tunnel, can simulated aircraft cabin the liquid of body bottom accumulate, and also can be used as the mixing chamber of gas injection for injection discharge opeing simulation.Discharge opeing parts 30 are communicated with surge chamber 20 fluids and the opening that extends through on wind-tunnel wall 40 enters wind tunnel test region, thereby have the liquid flowing state under practical flight condition after the test(ing) liquid mixing through buffering or injection in surge chamber 20 enters wind tunnel test region.
In the illustrative embodiments shown in Fig. 1, discharge opeing parts 30 are sealingly connected to the opening on wind-tunnel wall 40 by stationary installation 50.Stationary installation 50 for example comprise be socketed on the joint flange 51 of discharge opeing parts 30 and be arranged in joint flange 51 and wind-tunnel wall 40 between packing ring 52.Like this, stationary installation 50 can be used as test(ing) liquid and enters the passage in wind tunnel test region and aircraft fluid discharge analogue means is fixed on to the device on wind-tunnel wall 40.Discharge opeing parts 30 can be constructed to become one with surge chamber 20, or dismountable, have various types of discharge opeing bars of difformity and size or discharging tube and can be used as discharge opeing parts and be fixedly attached to easily on whole aircraft fluid discharge analogue means.In the optional embodiment of one, also can remove as required discharge opeing bar or discharging tube and carry out the simulation of zero elevation outage discharge opeing.In this case, the length that discharge opeing parts extend beyond wind-tunnel wall 40 should be controlled as zero.
According to the utility model, described aircraft fluid discharge analogue means can carry out injection discharge opeing simulation.As shown in Figure 1, ejection system comprises high-pressure air source 60, pressure regulator valve (not shown) and adjustable induction apparatus (not shown), by injection parameters such as adjustments of gas pressure, injection nozzle exit areas, and via transfer units such as supply air line 61, injector depth adjustment bar 62, injector nozzles 63, gases at high pressure are introduced to surge chamber 20 or mixing chamber.
When test, test(ing) liquid enters wind tunnel test region via the discharge opeing parts 30 through wind-tunnel wall 40 under Action of Gravity Field or gases at high pressure ejector action, can carry out the observation of liquid flowing state.Specifically, appropriate test(ing) liquid be stored in the fluid storage parts 10 with metering scale and be placed on certain altitude position, making it under trystate, just can flow into smoothly surge chamber 20 by gravity.By switching and the flow of fluid regulating valve control liquid, make flow through liquid feeding pipeline 11, feed flow port one 2 of test(ing) liquid enter surge chamber 20.The liquid that enters surge chamber 20 enters discharge opeing parts 30 and enters wind tunnel test region by the opening on wind-tunnel wall 40 after buffering.Thus, can carry out discharge opeing test with the pumping equipment such as discharge opeing bar or discharging tube of various shapes and size.In the time that introducing gases at high pressure carry out injection discharge opeing test, gases at high pressure are adjusted to the required pressure of test and introduce surge chamber 20 through pressure regulator valve.The degree of depth that the height and position of the injector nozzle 63 in surge chamber 20 can insert surge chamber 20 by adjustment injector depth adjustment bar 62 regulates easily and accurately.Injector nozzle 63 is also removable, for testing the effect of different-diameter nozzle.Test(ing) liquid enters after surge chamber 20, through the injection of gases at high pressure, under the effect of same direction jet, accelerate, break, atomization, and then enter wind tunnel test region by discharge opeing parts 30, under the effect of wind tunnel test region high speed air-flow vertical fluid, test(ing) liquid carries out secondary breaking and atomization.Data analysis and research that technician obtains according to wind tunnel test, can be in addition simulation test of the design of various aircraft discharge opeing schemes.
To description of the present utility model, be not difficult to find out that the aircraft fluid discharge analogue means for wind tunnel test of the present utility model is simple in structure, low cost of manufacture and easy to implement by above.Should be understood that, what shown in accompanying drawing, also described is only principle of the present utility model, and above-mentioned embodiment exists many alter modes, and these modes are clearly to various equivalent modifications.Any simple modification, equivalent variations and modification that every foundation technical spirit of the present utility model is done above embodiment, all fall in the protection domain of technical solutions of the utility model.
Claims (7)
1. for the aircraft fluid discharge analogue means of wind tunnel test, it is characterized in that, described analogue means comprises:
Fluid storage parts (10), hold test(ing) liquid in it;
Surge chamber (20), the test(ing) liquid in described fluid storage parts (10) is supplied to described surge chamber (20) temporary transient storage therein and is cushioned by transfer unit;
Discharge opeing parts (30), it is communicated with described surge chamber (20) fluid and the opening that extends through on wind-tunnel wall (40) enters wind tunnel test region;
Wherein, the described test(ing) liquid that enters wind tunnel test region has the liquid flowing state under practical flight condition.
2. the aircraft fluid discharge analogue means for wind tunnel test according to claim 1, is characterized in that, described test(ing) liquid enters described surge chamber (20) under self gravitation effect.
3. the aircraft fluid discharge analogue means for wind tunnel test according to claim 1, it is characterized in that, described analogue means also comprises ejection system, described ejection system comprises high-pressure air source (60), pressure regulator valve and adjustable induction apparatus, is used for that gases at high pressure are introduced to described surge chamber (20) and carries out injection discharge opeing simulation.
4. the aircraft fluid discharge analogue means for wind tunnel test according to claim 1, is characterized in that, described surge chamber (20) is constructed to one with described discharge opeing parts (30).
5. the aircraft fluid discharge analogue means for wind tunnel test according to claim 1, it is characterized in that, described discharge opeing parts (30) are sealingly connected to the opening on described wind-tunnel wall (40) by stationary installation (50).
6. the aircraft fluid discharge analogue means for wind tunnel test according to claim 5, it is characterized in that, described stationary installation (50) comprise be socketed on the joint flange (51) of described discharge opeing parts (30) and be arranged in described joint flange (51) and described wind-tunnel wall (40) between packing ring (52).
7. the aircraft fluid discharge analogue means for wind tunnel test according to claim 1, it is characterized in that, described discharge opeing parts (30) are dismountable, and the discharge opeing bar of difformity and size or discharging tube can be served as discharge opeing parts (30) and be connected with whole aircraft fluid discharge analogue means.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420149288.4U CN203811348U (en) | 2014-03-28 | 2014-03-28 | Airplane liquid discharge simulation device used for wind tunnel tests |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420149288.4U CN203811348U (en) | 2014-03-28 | 2014-03-28 | Airplane liquid discharge simulation device used for wind tunnel tests |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203811348U true CN203811348U (en) | 2014-09-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420149288.4U Expired - Lifetime CN203811348U (en) | 2014-03-28 | 2014-03-28 | Airplane liquid discharge simulation device used for wind tunnel tests |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203811348U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106800096A (en) * | 2015-11-26 | 2017-06-06 | 中国飞行试验研究院 | Aircraft flammable liquid emission testing method |
| CN111980803A (en) * | 2019-05-24 | 2020-11-24 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
-
2014
- 2014-03-28 CN CN201420149288.4U patent/CN203811348U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106800096A (en) * | 2015-11-26 | 2017-06-06 | 中国飞行试验研究院 | Aircraft flammable liquid emission testing method |
| CN111980803A (en) * | 2019-05-24 | 2020-11-24 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
| CN111980803B (en) * | 2019-05-24 | 2022-03-15 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140903 |