CN203037599U - Variable angle high temperature hot test devicefor high-speed aircraft oblique section taper type casing - Google Patents
Variable angle high temperature hot test devicefor high-speed aircraft oblique section taper type casing Download PDFInfo
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- CN203037599U CN203037599U CN 201220720277 CN201220720277U CN203037599U CN 203037599 U CN203037599 U CN 203037599U CN 201220720277 CN201220720277 CN 201220720277 CN 201220720277 U CN201220720277 U CN 201220720277U CN 203037599 U CN203037599 U CN 203037599U
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Abstract
A variable angle high temperature hot test device for a high-speed aircraft oblique section taper type casing comprises a U-shaped copper support, a taper type fastening screw, an annular flat copper support, an adjustable electrode support, a connecting locking shaft, the high-speed aircraft oblique section taper type casing, a quartz lamp heating pipe and a water cooled copper pipe. An angle of the infrared radiation quartz lamp heating pipe installed on a water cooler can be changed conveniently through the device in pneumatic hot simulation tests, so that the infrared radiation quartz lamp heating pipe can be matched with the high-speed aircraft oblique section taper type casing rapidly and conveniently. Simultaneously, an electrode of the quartz lamp heating pipe can be cooled through cooling water in the pneumatic hot simulation tests, and burning of the quartz lamp heating pipe electrode caused by leakage of inert gas caused by large deformation of the quartz lamp heating pipe electrode caused by a too high temperature is avoided. Through the variable angle high temperature hot test device, convenient and safe high temperature hot environment test means are provided for the pneumatic hot simulation tests of the high-speed aircraft oblique section taper type casing.
Description
Technical field
The utility model relates to high-speed aircraft oblique section tapered housing angle changing degree elevated temperature heat test unit.Particularly when the pneumatic heating environment of high speed aircraft such as simulated missile test, has flexible, the easy to use advantage of profile angle followability to the tapered housing in aircraft front end oblique section.Provide the thermal environment simulation research technique of quick and safe for developing high-speed missile and high-speed aircraft aerospace vehicle.
Background technology
Along with high-speed aircraft design flying speed increases substantially, the elevated temperature heat environment that is produced by pneumatic heating becomes very harsh.If when high speed aircraft such as guided missile, spacecraft flew with 6 Mach numbers, the transient heat flow density before its high-speed aircraft on the end housing can surpass 1.2Mw/m
2, temperatures at localized regions can be up to 1200 ℃.So exceedingly odious elevated temperature heat environmental baseline makes the thermal protection of high-speed aircraft material and structure and hot strength problem become concerning the key issue of developing success or failure.The high temperature that serious pneumatic heating produces during high-speed flight, can significantly reduce the strength degree of hypersonic aircraft material and the load-bearing capacity of Flight Vehicle Structure, make structure produce thermal deformation, destroy the aerodynamic configuration of parts and influence the security performance of Flight Vehicle Structure.For guaranteeing the safety of high-speed aircraft, thermal shock and elevated temperature heat stress rupture that the material of affirmation aircraft and structure produce in the time of whether standing high-speed flight must carry out pneumatic thermal modeling test and thermal strength test to hypersonic aircraft material and structure.This work has very important practical significance for the thermal protection of missile flight device with the safety design.
The high-speed aircraft front end facings the wind and partly mostly is the tapered shell structure of oblique section, that is to say that the diameter of both ends of the surface is different.When carrying out the pneumatic heat test of high temperature simulation, aircraft outside surface heating arrangement must be designed to the shape with the tapered shell structure conformal in oblique section, mate with inclination angle and distance between the tapered housing of the quartz burner that guarantees well heater and oblique section.
Prior art is with the end face design of fixed electorde bearing and is processed into band angle oblique section shape, is fixed on heater and loads onto the angulation coupling.Come the pneumatic thermal environment of high temperature of the tapered housings in high speed aircraft oblique section such as simulated missile.But owing to load onto with the heating of annular distribution quartz lamp One's name is legion at heater, the bearing quantity of fixed electorde is very big, and it is very big to make bevel wear the processing capacity of fixed electorde bearing of angle, in case process the angle that the back just is difficult for the modification oblique section.
In addition, missile flight device for some serial model No.s, though its physical dimension has certain variation, but overall variable quantity is not very big, if adopt the fixed electorde bearing technology of existing band angle then all must re-design the oblique section parts of a large amount of band angles at every turn, process-cycle is long, and assembling is adjusted complicated.
Because copper quartz lamp heating tube electrode thermal expansion coefficient is big, at high temperature copper quartz lamp heating tube electrode is subjected to thermogenetic axial large deformation to cause that easily inert gas in the quartz lamp heating tube leaks and burns, and must be quartz lamp heating tube electrode drop temperature by flow media therefore.Moreover, very fragile owing to quartz lamp heating tube electrode is wrapped by the thin-walled quartz glass, be subjected to very easily damaging after the external force.Because the product dispersiveness during the quartz lamp heating tube is produced, the axis of a part of quartz lamp heating tube electrode can not overlap fully with the axis of quartz lamp heating tube, has a little angle.If adopt existing fixed electrode support technology, very easily cause under the crimping by force of unified angle, the damage of quartz lamp heating tube electrode has influence on the security of test and the reliability of test findings.
Designed a kind of high-speed aircraft oblique section tapered housing angle changing degree elevated temperature heat test unit for this reason.When the pneumatic heating environment of high speed aircraft such as simulated missile test, has flexible, the easy to use advantage of profile angle followability to the tapered housing in aircraft front end oblique section; This device has good heat conductivility simultaneously, can be quartz lamp heating tube electrode drop temperature by the chilled water that flows.Provide the elevated temperature heat environmental simulation test means of quick and safe for developing high-speed missile and high-speed aircraft aerospace vehicle.
The utility model content
Technology of the present utility model is dealt with problems and is: overcome the deficiencies in the prior art, a kind of high-speed aircraft oblique section tapered housing angle changing degree elevated temperature heat test unit is provided.This device can change the heating angle of the infrared radiation quartz lamp heating tube that is installed on the water cooler easily when pneumatic heat test simulation test, make it and the tapered housing in high-speed aircraft oblique section between can be fast, coupling easily.Can also in hot test, lower the temperature to quartz lamp heating tube electrode by chilled water simultaneously, avoid quartz lamp heating tube electrode large deformation to occur owing to temperature is too high and cause that inert gas leaks and burn.For the pneumatic thermal modeling test of the tapered housings in high speed aircraft oblique section such as guided missile provides effective hot test means.
Technical solution of the present utility model is: high-speed aircraft oblique section tapered housing angle changing degree elevated temperature heat test unit comprises: U-shaped copper bearing, taper holding screw, ring-type flat copper support, adjustable electrode bearing, connection lock shaft, the tapered housing in high-speed aircraft oblique section, quartz lamp heating tube, quartz lamp heating tube electrode, electrode jackscrew and water-cooled copper; Described U-shaped copper bearing is fixed on the ring-type flat copper support by the taper holding screw, the adjustable electrode bearing is connected with U-shaped copper bearing by connecting lock shaft, two ring-type flat copper supports, each ring-type flat copper support of having diameter not wait in the both ends of the surface outside of the tapered housing in high-speed aircraft oblique section are equipped with quantity and equate U-shaped copper bearing, in the circular hole on the electrode insertion adjustable electrode bearing at quartz lamp radiation heating tube two ends, fixing and the location by the electrode jackscrew, the inboard of ring-type flat copper support is welded with the water-cooled copper of hollow.
Described adjustable electrode bearing can rotate at U-shaped copper bearing, change the angle of inclination, reach the purpose of adjusting the relative angle between the tapered housing of quartz lamp heating tube and high-speed aircraft oblique section easily, realize the fastening locking of angle by connecting lock shaft in the back well in angular setting.
The water-cooled copper of described hollow flows through chilled water when the pneumatic thermal modeling test of guided missile high temperature, reduce the temperature of quartz lamp heating tube electrode in the elevated temperature heat process of the test.
Described U-shaped copper bearing, taper holding screw, ring-type flat copper support, adjustable electrode bearing and connect lock shaft and all make with the good red copper of heat conductivility and plastic property, make by the conjunction plane contact of each parts after the afterburning locking good, guarantee in the water-cooled copper mobile chilled water can and quartz lamp heating tube electrode between have good heat exchange performance.
Principle of the present utility model: part mostly is the tapered shell structure of oblique section because high speed aircraft front ends such as guided missile facing the wind, when carrying out the pneumatic heat test of high temperature simulation, need aircraft outside surface heating arrangement is designed to and the tapered housing of quartz burner that the shape of the tapered shell structure conformal in oblique section guarantees well heater and oblique section between inclination angle and distance mate.Coupling method with the fixed electorde bearing of traditional use band angle oblique section, change into the subassembly coupling method of the variable-angleization of partly being formed by U-shaped copper bearing and adjustable electrode bearing etc., when the pneumatic heating environment of high speed aircraft such as simulated missile test, the followability that this device has aircraft front end oblique section tapered housing profile angle reaches safe advantage easy to use flexibly.And the parts of this oblique section tapered housing angle changing degree elevated temperature heat test unit adopt thermal conductivity and the good red copper material of plastic property to make, when having guaranteed the elevated temperature heat test, the heat eliminating medium in the cooling duct can carry out good heat interchange with quartz lamp heating tube electrode.Provide the elevated temperature heat environmental simulation test means of quick and safe for developing high-speed missile and high-speed aircraft aerospace vehicle.
The utility model beneficial effect compared with prior art is:
(1) prior art is that a end face with the fixed electorde bearing is processed into the fixed in shape of band angle oblique section on the flat copper support, come the pneumatic thermal environment of high temperature of the tapered housings in high speed aircraft oblique section such as simulated missile, because the heating quartz lamp One's name is legion of annular distribution, the quantity of fixed electorde bearing is very big, it is very big to make bevel wear the processing capacity of fixed electorde bearing of angle, in case process the angle that the back just is difficult for revising the oblique section.The utility model adopts the adjustable electrode bearing by connecting the mode that lock shaft is connected with U-shaped copper bearing, can adjust the relative angle between the tapered housing of quartz lamp heating tube and high-speed aircraft oblique section easily, angular setting back is well carried out fastening location by connecting lock shaft.
(2) wrapped by the thin-walled quartz glass owing to quartz lamp heating tube electrode, very fragile, be subjected to very easily damaging after the external force.And because the dispersiveness in the production of quartz lamp heating tube, the axis of a part of quartz lamp heating tube electrode fails to overlap fully with the axis of quartz lamp heating tube, has a little angle.The utility model adopts the adjustable electrode bearing can carry out the virtual condition that angle finely tunes to adapt to each quartz lamp heating tube electrode, the damage of quartz lamp heating tube electrode when avoiding adopting traditional unification to decide the fixed angle electrode support, the safe reliability when having improved test.
(3) for the missile flight device of some serial model No.s, though its physical dimension has certain variation, but overall variation is not very big, if adopt the fixed electorde bearing technology of existing band angle then all must re-design a large amount of band angle oblique section parts at every turn, process-cycle is long, and assembling is adjusted complicated.The utility model adopts the adjustable electrode bearing, can adapt to the designing requirement of multiple model easily, saves between the man-hour of a large amount of new frocks of making, has shortened the lead time of newer versions of these missiles.
(4) because copper quartz lamp heating tube electrode thermal expansion coefficient is big, the thermal expansivity of the quartz glass of copper quartz lamp heating tube electrode and quartz lamp heating tube differs about 30 times, the axial large deformation of copper quartz lamp heating tube electrode at high temperature causes that easily the inert gas in the quartz lamp heating tube leaks and burns, be welded with water-cooled copper in the inboard of ring-type flat copper support for this reason, chilled water is flow through to reduce the temperature of quartz lamp heating tube electrode in water-cooled copper inside, avoids quartz lamp heating tube electrode large deformation to occur owing to temperature is too high and causes that inert gas leaks and burn.
(5) the U-shaped copper bearing in the utility model, taper holding screw, ring-type flat copper support, adjustable electrode bearing and connect lock shaft and all make with the good red copper of heat conductivility and plastic property, make that the joint face contact of each parts is good after the parts adjustment is fixing, guaranteed that the chilled water in the water-cooled copper can carry out good heat interchange with quartz lamp heating tube electrode.
(6) the utility model apparatus structure is succinct, and is easy to use, for the high temperature hot strength of the tapered housings in high speed aircraft oblique section such as guided missile is provided by the ground experiment that has more dirigibility and the security means that provide.
Description of drawings
Fig. 1 is structural representation of the present utility model.
Embodiment
As shown in Figure 1, the utility model is made up of with water-cooled copper 10 U-shaped copper bearing 1, taper holding screw 2, ring-type flat copper support 3, adjustable electrode bearing 4, connection lock shaft 5, the tapered housing 6 in high-speed aircraft oblique section, quartz lamp heating tube 7, quartz lamp heating tube electrode 8, electrode jackscrew 9.U-shaped copper bearing 1 is fixed on the ring-type flat copper support 3 by taper holding screw 2, adjustable electrode bearing 4 is connected with U-shaped copper bearing 1 by connecting lock shaft 5, two ring-type flat copper supports 3 that have diameter not wait in the both ends of the surface outside of the tapered housing 6 in high-speed aircraft oblique section, the U-shaped copper bearing 1 that quantity equates is installed on each ring-type flat copper support 3, in the circular hole that the heating tube electrode 8 at quartz lamp radiation heating tube 7 two ends inserts on the adjustable electrode bearing 4, by electrode jackscrew 9 fixing and location, the inboard of ring-type flat copper support 3 is welded with the water-cooled copper 10 of hollow, flows through chilled water when the pneumatic thermal modeling test of guided missile high temperature.
The utility model is by adjusting the relative angle of adjustable electrode bearing 4 and U-shaped copper bearing 1, can adjust the relative angle between the tapered housing 6 in quartz lamp heating tube 7 and high-speed aircraft oblique section easily, angular setting back is well undertaken fastening by connecting lock shaft 5.The utility model also can be finely tuned at above-mentioned angle easily, even revise because the axis of the quartz lamp heating tube electrode 8 that the dispersiveness of production causes and quartz lamp heating tube 7 also can carry out the angle fine setting when certain skew is arranged, avoid the damage of fragile quartz lamp heating tube electrode 8.
Adjustable electrode bearing 4 in the utility model, connection lock shaft 5, U-shaped copper bearing 1, taper holding screw 2 are made by the good red copper material of high temperature heat conductivility.With water-cooled copper 10 by oxygen welding with after ring-type flat copper support 3 links to each other, in hot test, give quartz lamp heating tube electrode 8 coolings by the quick conductive characteristic of mobile chilled water and each copper assembly, avoid quartz lamp heating tube electrode 8 to be damaged by the vacuum seal that high temperature causes, improved reliability and the security of high-speed aircraft hot test.
Varied angle frock matching efficiency and accuracy when the utility model makes the tapered housing heat test in high-speed aircraft oblique section are greatly improved, have characteristics quickly and easily, and make the tapered Shell test in high-speed aircraft oblique section be improved with the security of quartzy radiation heating tube.
The utility model does not elaborate part and belongs to techniques well known.
Claims (2)
1. the tapered housing angle changing degree in high-speed aircraft oblique section elevated temperature heat test unit is characterized in that comprising: U-shaped copper bearing (1), taper holding screw (2), ring-type flat copper support (3), adjustable electrode bearing (4), connection lock shaft (5), the tapered housing in high-speed aircraft oblique section (6), quartz lamp heating tube (7), quartz lamp heating tube electrode (8), electrode jackscrew (9) and water-cooled copper (10); Adjustable electrode bearing (4) is connected with U-shaped copper bearing (1) by connecting lock shaft (5), two ring-type flat copper supports (3), each ring-type flat copper support (3) of having diameter not wait in the both ends of the surface outside of the tapered housing in high-speed aircraft oblique section (6) are equipped with the U-shaped copper bearing (1) that quantity equates, U-shaped copper bearing (1) is fixed on the ring-type flat copper support (3) by taper holding screw (2); In the circular hole on heating tube electrode (8) the insertion adjustable electrode bearing (4) at quartz lamp radiation heating tube (7) two ends, the fixing and location by electrode jackscrew (9); The inboard of described ring-type flat copper support (3) is welded with the water-cooled copper (10) of hollow.
2. high-speed aircraft oblique section according to claim 1 tapered housing angle changing degree elevated temperature heat test unit is characterized in that: described U-shaped copper bearing (1), taper holding screw (2), ring-type flat copper support (3), adjustable electrode bearing (4) and connect lock shaft (5) and make by red copper.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220720277 CN203037599U (en) | 2012-12-24 | 2012-12-24 | Variable angle high temperature hot test devicefor high-speed aircraft oblique section taper type casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220720277 CN203037599U (en) | 2012-12-24 | 2012-12-24 | Variable angle high temperature hot test devicefor high-speed aircraft oblique section taper type casing |
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| Publication Number | Publication Date |
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| CN203037599U true CN203037599U (en) | 2013-07-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220720277 Withdrawn - After Issue CN203037599U (en) | 2012-12-24 | 2012-12-24 | Variable angle high temperature hot test devicefor high-speed aircraft oblique section taper type casing |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103033527A (en) * | 2012-12-24 | 2013-04-10 | 北京航空航天大学 | Variable-angle high-temperature heat testing device for conical housing with oblique section of high-speed aircraft |
| CN103439133A (en) * | 2013-08-27 | 2013-12-11 | 北京航空航天大学 | Hypersonic flight vehicle 250 DEG C per-second high-speed heat shock testing device and method |
| CN104925269A (en) * | 2015-05-08 | 2015-09-23 | 湖北航天技术研究院总体设计所 | Ultrahigh-speed aircraft cabin thermal environment testing device and method |
| CN109297895A (en) * | 2018-10-30 | 2019-02-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of cone shaped radiation heating device |
| CN109297894A (en) * | 2018-10-30 | 2019-02-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of radiant heating device of the big temperature gradient of multi-temperature zone |
| CN109856177A (en) * | 2017-11-30 | 2019-06-07 | 中国飞机强度研究所 | A kind of aircraft protective cover thermal release experimental rig |
-
2012
- 2012-12-24 CN CN 201220720277 patent/CN203037599U/en not_active Withdrawn - After Issue
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103033527A (en) * | 2012-12-24 | 2013-04-10 | 北京航空航天大学 | Variable-angle high-temperature heat testing device for conical housing with oblique section of high-speed aircraft |
| CN103033527B (en) * | 2012-12-24 | 2014-12-10 | 北京航空航天大学 | Variable-angle high-temperature heat testing device for conical housing with oblique section of high-speed aircraft |
| CN103439133A (en) * | 2013-08-27 | 2013-12-11 | 北京航空航天大学 | Hypersonic flight vehicle 250 DEG C per-second high-speed heat shock testing device and method |
| CN103439133B (en) * | 2013-08-27 | 2016-02-17 | 北京航空航天大学 | Hypersonic aircraft 250 DEG C/sec of high speed thermal shock rigs and method |
| CN104925269A (en) * | 2015-05-08 | 2015-09-23 | 湖北航天技术研究院总体设计所 | Ultrahigh-speed aircraft cabin thermal environment testing device and method |
| CN104925269B (en) * | 2015-05-08 | 2016-09-21 | 湖北航天技术研究院总体设计所 | The assay device of a kind of high hypervelocity aircraft cabin section thermal environment and method |
| CN109856177A (en) * | 2017-11-30 | 2019-06-07 | 中国飞机强度研究所 | A kind of aircraft protective cover thermal release experimental rig |
| CN109856177B (en) * | 2017-11-30 | 2021-04-20 | 中国飞机强度研究所 | Aircraft safety cover thermal separation test device |
| CN109297895A (en) * | 2018-10-30 | 2019-02-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of cone shaped radiation heating device |
| CN109297894A (en) * | 2018-10-30 | 2019-02-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of radiant heating device of the big temperature gradient of multi-temperature zone |
| CN109297895B (en) * | 2018-10-30 | 2021-08-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Conical radiation heating device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130703 Effective date of abandoning: 20141210 |
|
| RGAV | Abandon patent right to avoid regrant |