CN205175698U - Projectile shell separator and aeroengine testing equipment - Google Patents
Projectile shell separator and aeroengine testing equipment Download PDFInfo
- Publication number
- CN205175698U CN205175698U CN201520970968.7U CN201520970968U CN205175698U CN 205175698 U CN205175698 U CN 205175698U CN 201520970968 U CN201520970968 U CN 201520970968U CN 205175698 U CN205175698 U CN 205175698U
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- missile
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- tripping device
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Abstract
The utility model discloses a projectile shell separator and aeroengine testing equipment relates to aeroengine technical field. The problem of the prior art existence can destroy the gesture of projectile and lead to the bullet to hold in the palm broken technique is solved. This projectile shell separator, including shell interception passageway, shell interception passageway exists projectile inlet port and projectile exit wound of bullet, the interior wall energy of shell interception passageway utilize frictional force to reduce the forward velocity of the projectile that gets into by the projectile inlet port gradually and only permit the shell with the shell interception of projectile in shell interception passageway in the projectile jet out from the projectile exit wound of bullet. This aeroengine testing equipment includes the utility model provides a projectile shell separator. The utility model is used for ensure that the gesture of shell is invariable, the structural integrity at the in -process of separation projectile shell.
Description
Technical field
The utility model relates to aero engine technology field, particularly relates to a kind of missile shell tripping device and arranges the Aero Engine Testing equipment of this missile shell tripping device.
Background technology
The security of aeromotor is most important, in order to ensure the security of aeromotor, needs to carry out casing containment test and foreign object inhalation test to aeromotor in the design process.Generally, these tests can by being that missile is implemented with certain speed and attitude homed on its target by the air bubble of power with pressurized air.
In order to the profile and gun tube that make emitting substance closely cooperate, need to install outward at emitting substance to coordinate the bullet holder of gun tube internal diameter as shell, therefore need the shelling problem considering emitting substance.The power source of gas big gun is pressurized air, can produce huge noise when launching bullet, therefore shelling and noise elimination technique are links very important in air bubble emission test technology.
Existing air bubble system generally directly arranges blocking type separation of the projectile seat device in gun tube exit, blocking type separation of the projectile seat device can when body 4 passes through the small-bore hole 510 on baffle plate 51 as shown in Figure 1, utilize baffle plate 51 to stop bullet holder 42, bullet holder 42 is separated from missile 41.
The applicant finds: prior art at least exists following technical matters:
Existing blocking type separation of the projectile seat device is stopping, is being separated in the process of bullet holder 42 as shown in Figure 1, and bullet holder 42 moderating process is too violent, first can form disturbance to missile 41, destroys the attitude of missile 41; Secondly bullet holder 42 can be caused broken, and the fragment of bullet holder 42 is unfavorable for experimenter's viewing test process after flying away the space around missile 41.
Utility model content
At least one object of the present utility model proposes a kind of missile shell tripping device and arranges the Aero Engine Testing equipment of this missile shell tripping device, solves prior art existence and can destroy the attitude of missile and cause the technical matters of bullet holder fragmentation.Many technique effects that optimal technical scheme in many technical schemes that the utility model provides can produce refer to hereafter sets forth.
For achieving the above object, the utility model provides following technical scheme:
The missile shell tripping device that the utility model embodiment provides, comprises shell interception passage, wherein: described shell interception passage exists missile inlet port and missile exit wound of bullet;
The interior wall energy of described shell interception passage utilizes friction force reduce the pace of the missile entered by described missile inlet port gradually and in described shell interception passage, only allow described missile to penetrate from described missile exit wound of bullet the interception of the shell of described missile.
The optimization of technical scheme after the arbitrary technical scheme provided above or hereinafter as the utility model or arbitrary optimization, the conducting area of described shell interception passage is along reducing gradually from described missile inlet port to the direction of described missile exit wound of bullet.
The optimization of technical scheme after the arbitrary technical scheme provided above or hereinafter as the utility model or arbitrary optimization, described shell interception passage is that the track of at least two bar shapeds forms around the circumferential direction arrangement of the center line of described missile.
The optimization of technical scheme after the arbitrary technical scheme provided above or hereinafter as the utility model or arbitrary optimization, described shell interception passage is linear pattern, and the angle between the bearing of trend of the length direction of described track and the center line of described missile is 1 ° ~ 5 °.
The optimization of technical scheme after the arbitrary technical scheme provided above or hereinafter as the utility model or arbitrary optimization, the Reinforced Hoop by least one annular between described track is fixed together.
The optimization of technical scheme after the arbitrary technical scheme provided above or hereinafter as the utility model or arbitrary optimization, the inwall of described Reinforced Hoop is provided with mounting groove, and described track to be plugged in described mounting groove and to be fixedly connected with the inwall of described mounting groove (being preferably welded and fixed).
The optimization of technical scheme after the arbitrary technical scheme provided above or hereinafter as the utility model or arbitrary optimization, wherein one end of described track is fixedly connected with mounting flange, and the center pit of described mounting flange forms described missile inlet port.
After the arbitrary technical scheme provided above or hereinafter as the utility model or arbitrary optimization, the optimization of technical scheme, described mounting flange is provided with at least two connecting through holes.
The optimization of technical scheme after the arbitrary technical scheme provided above or hereinafter as the utility model or arbitrary optimization, the xsect of described track is polygon (being preferably provided with the polygon of chamfering or fillet) or circle.
The Aero Engine Testing equipment that the utility model embodiment provides, comprises the missile shell tripping device that air bubble and the arbitrary technical scheme of the utility model provide, wherein:
The described missile inlet port of described shell interception passage is connected with the body emission port of described air bubble.
Based on technique scheme, the utility model embodiment at least can produce following technique effect:
Because wall energy in the shell interception passage that the utility model provides utilizes friction force reduce the pace of the missile entered by missile inlet port gradually and only allow the missile in shell to penetrate from missile exit wound of bullet in shell interception passage the interception of the shell (such as bullet holder) of missile, thus, in separate housings and shell body process in, shell moderating process is steady, disturbance can not be formed to missile, the attitude of missile can not be destroyed, also bullet holder can not be caused broken, so the fragment that it also avoid shell flies away the space around missile and causes harmful effect to experimenter's viewing test process, solve prior art existence can destroy the attitude of missile and cause the technical matters of bullet holder fragmentation.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, and form a application's part, schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is a kind of schematic diagram that can realize the device that missile shell is separated in prior art;
The schematic diagram of the spatial structure of the missile shell tripping device that Fig. 2 provides for the utility model embodiment;
Fig. 3 is a schematic diagram of partial structurtes in Fig. 2;
Fig. 4 is another schematic diagram of partial structurtes in Fig. 2;
The schematic diagram of the spatial structure of the track of the missile shell tripping device that Fig. 5 provides for the utility model embodiment;
The schematic diagram of the Reinforced Hoop of the missile shell tripping device that Fig. 6 provides for the utility model embodiment;
The track of missile shell tripping device that Fig. 7 provides for the utility model embodiment and the schematic diagram of Reinforced Hoop matching relationship;
The schematic diagram of relative position between the inner outline of the shell interception passage of the missile shell tripping device that Fig. 8 provides for the utility model embodiment and the center line of missile;
The schematic diagram of the relative position of the bearing of trend of the track of missile shell tripping device that Fig. 9 provides for the utility model embodiment and the center line of missile;
A kind of embodiment that Figure 10 is track shown in Fig. 9 is along the cross-sectional schematic of A-A line;
Another embodiment that Figure 11 is track shown in Fig. 9 is along the cross-sectional schematic of A-A line;
Another embodiment that Figure 12 is track shown in Fig. 9 is along the cross-sectional schematic of A-A line;
The cross-sectional schematic of the missile that the missile shell tripping device that Figure 13 provides for the utility model embodiment is separated;
The schematic diagram of the process of the missile shell tripping device separation missile that Figure 14 provides for the utility model embodiment;
The schematic diagram of annexation between the missile shell tripping device that Figure 15 provides for the utility model embodiment and the gun tube of air bubble;
Reference numeral: 1, shell interception passage; 11, missile inlet port; 12, missile exit wound of bullet; 101, track; 102, Reinforced Hoop; 103, mounting groove; 104, mounting flange; 105, connecting through hole; 2, gun tube; 3, body; 31, shell; 32, missile; 4, body; 41, missile; 42, bullet holder; 51, baffle plate; 510, hole.
Embodiment
Content of the present utility model and the distinctive points between the utility model and prior art can be understood below with reference to accompanying drawing Fig. 1 ~ Figure 15 and word content.Hereafter by accompanying drawing and the mode enumerating embodiment more of the present utility model, the technical solution of the utility model (comprising optimal technical scheme) is described in further detail.It should be noted that: any technical characteristic in the present embodiment, any technical scheme is all one or more in the technical characteristic of plurality of optional or optional technical scheme, cannot exhaustive all alternative technical characteristics of the present utility model and alternative technical scheme in order to describe succinct to need in presents, also the embodiment being not easy to each technical characteristic all emphasizes that it is one of optional numerous embodiments, so those skilled in the art should know: arbitrary technological means that the utility model can be provided carries out two or more technological means any of replacing or being provided by the utility model or technical characteristic carries out mutually combining and obtaining new technical scheme.Any technical characteristic in the present embodiment and any technical scheme all do not limit protection domain of the present utility model, protection domain of the present utility model should comprise those skilled in the art do not pay creative work thinkable any alternate embodiments and those skilled in the art two or more technological means any that the utility model is provided or the technical characteristic new technical scheme carrying out mutually combining and obtain.
The utility model embodiment provide a kind of can not destroy missile attitude, can not cause that bullet holder is broken, structure is simple and there is the missile shell tripping device of noise elimination function and the Aero Engine Testing equipment of this missile shell tripping device is set.
Below in conjunction with the elaboration that Fig. 1 ~ Figure 15 carries out specifically to the technical scheme that the utility model provides.
As shown in Fig. 2 ~ Figure 15, the missile shell tripping device that the utility model embodiment provides, comprises shell interception passage 1, wherein:
There is missile inlet port 11 and missile exit wound of bullet 12 in shell interception passage 1; Shell interception passage 1 interior wall energy utilize friction force reduce gradually the missile entered by missile inlet port 11 pace and the shell 31 of missile 32 is tackled shell interception passage 1 in only allow the missile 32 in shell 31 to penetrate from missile exit wound of bullet 12.
In the shell interception passage 1 provided due to the utility model the missile 32 that wall energy utilizes friction force to reduce gradually to be entered by missile inlet port 11 pace and in shell interception passage 1, only allow the missile 32 in shell 31 to penetrate from missile exit wound of bullet 12 interception of the shell 31 (such as bullet holder) of missile, thus, separate housings 31 is with the process of missile 32 in shell 31, shell 31 moderating process is steady, disturbance can not be formed to missile 32, the attitude of missile 32 can not be destroyed, also bullet holder can not be caused broken, so the fragment that it also avoid shell 31 flies away the space around missile and causes harmful effect to experimenter's viewing test process.
As embodiment embodiment alternatively, the conducting area of shell interception passage 1 is along reducing gradually from the direction of missile inlet port 11 to missile exit wound of bullet 12.Its inwall of shell interception passage 1 that this structure is formed can increase gradually to the friction force that the shell 31 of missile applies, and then can reliably realize slowing down gradually, steadily of shell 31.
As embodiment embodiment alternatively, shell interception passage 1 is that the track 101 of at least two bar shapeds forms around the circumferential direction arrangement of the center line of missile.The shell interception passage 1 that this structure is formed not only saves material, and the gap between the track 101 of adjacent bar shaped also has the effect of noise elimination.Thus, the utility model achieves shelling and noise elimination function by same structure simultaneously, decreases number of parts.The quantity of track 101 can be 6 ~ 8.As shown in Figure 2, the length L of track 101 can be 0.5m ~ 2m.
As embodiment embodiment alternatively, shell interception passage 1 is linear pattern, and the angle β between the bearing of trend of the length direction of track 101 and the center line of missile 32 is 1 ° ~ 5 °.The shell interception passage 1 that this structure is formed not only can realize steady deceleration, and has the advantage that structure is simple, save material, be convenient to maintenance.In addition, the inwall of shell interception passage 1 can be changed to the size of the friction force that the shell 31 of missile 32 applies by the mode of the angle value changing angle β, and then shell can be regulated to tackle the slowing effect of passage 1, select suitable retarded velocity according to different body 3.Linear pattern shell interception passage 1 can also play good guide effect to missile 32, and then can stablize missile 32 attitude.
As embodiment embodiment alternatively, the Reinforced Hoop 102 by least one annular between track 101 is fixed together.The Reinforced Hoop 102 of annular has structure simply, convenient processing, the advantage manufactured.Reinforced Hoop 102 is specifically as follows annular, elliptical annular structure, also can be polygonal ring shape structure.As shown in Figure 2, the distance D between Reinforced Hoop 102 (containing flange) is 0.3 ~ 0.5m.Number, the setting position of Reinforced Hoop 102 can design as required.Preferably, the end of track 101 has end Reinforced Hoop 102, and the interior bore of end Reinforced Hoop 102 is less than bore in mounting flange 104.
As shown in Figure 6 and Figure 7, as embodiment embodiment alternatively, the inwall of Reinforced Hoop 102 is provided with mounting groove 103, and track 101 to be plugged in mounting groove 103 and to be fixedly connected with the inwall of mounting groove 103 (being preferably welded and fixed).Track 101 is plugged in mounting groove 103, and make Reinforced Hoop 102 and track 101 define the syndeton of joggle, this structure has compact conformation, is connected firmly, advantage reliably.
As embodiment embodiment alternatively, wherein one end of track 101 is fixedly connected with mounting flange 104, and the center pit of mounting flange 104 forms missile inlet port 11.The setting party of mounting flange 104 the attended operation of the utility model missile shell tripping device and missile emitter (such as: air bubble).Mounting flange 104 also can be called flange mounting edge, and the interior bore of mounting flange 104 is identical with the bore that the missile of missile emitter sends mouth, makes body 3 expeditely can enter tripping device.
As embodiment embodiment alternatively, mounting flange 104 is provided with at least two connecting through holes 105.The securing member such as bolt or screw can be adopted to be fixed on missile emitter (such as: air bubble) by missile shell tripping device by the connecting through hole 105 of mounting flange 104.
As embodiment embodiment alternatively, the xsect of track 101 can be polygon (such as rectangle is preferably provided with the polygon of chamfering or fillet) or circle, also can be the polygon with chamfering or fillet.Track 101 tactical rule of this structure, convenient processing, manufacture and assembling.
The Aero Engine Testing equipment that the utility model embodiment provides, comprises the missile shell tripping device that air bubble and the arbitrary technical scheme of the utility model provide, wherein:
The shell interception missile inlet port 11 of passage 1 is connected with the body emission port of air bubble.
Aero Engine Testing equipment is suitable for adopting the utility model to realize not destroying the shell (also can be called bullet holder) 31 of air bubble, realizes being separated of shell 31 and missile 32 under keeping the complete prerequisite of shell 31.
When using the utility model to carry out impulse test to aeromotor, body 3 is with after certain speed injection air bubble gun tube 2, enter the missile shell tripping device be connected with gun tube 2, gas can be released by the gap between track 101, and noise can decrease thus.Under the maintenance effect of track 101, the attitude of missile 32 keeps stable, and bullet holder moves forward along track 101 and slows down gradually in the tapered channels that track 101 is formed, and finally stays in missile shell tripping device.Be arranged on missile 32 in bullet holder due to inertia effect, depart from bullet holder 31, fly out forward, clash into target.
Above-mentioned arbitrary technical scheme disclosed in the utility model unless otherwise stated, if the numerical range of it discloses, so disclosed numerical range is preferred numerical range, anyly it should be appreciated by those skilled in the art: preferred numerical range is only the numerical value that in many enforceable numerical value, technique effect is obvious or representative.Because numerical value is more, cannot be exhaustive, so the utility model just discloses component values to illustrate the technical solution of the utility model, and the above-mentioned numerical value enumerated should not form restriction the utility model being created to protection domain.
If employ the word such as " first ", " second " herein to limit parts, those skilled in the art should know: the use of " first ", " second " is only used to be convenient to describe carry out difference as not having outside Stated otherwise to parts, the implication that above-mentioned word is not special.Simultaneously, if above-mentioned the utility model discloses or relate to parts or the structural member of connection fastened to each other, so, unless otherwise stated, be fixedly connected with and can be understood as: can releasably be fixedly connected with (such as using bolt or screw to connect), also can be understood as: to be non-removablely fixedly connected with (such as rivet, weld), certainly, connection fastened to each other also can be replaced by integral type structure (such as use casting technique is integrally formed create) (obviously cannot adopt except integrally formed technique).
In addition, apply in arbitrary technical scheme disclosed in above-mentioned the utility model for represent position relationship or shape term unless otherwise stated its implication comprise approximate with it, similar or close state or shape.Arbitrary parts that the utility model provides both can be assembled by multiple independent ingredient, and also can be one of the forming manufacture technics separate part out.
If employ term " " center " in description of the present utility model, " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", " outward " etc., orientation or the position relationship of so above-mentioned term instruction are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the missile shell tripping device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
Finally should be noted that: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although be described in detail the utility model with reference to preferred embodiment, those of ordinary skill in the field have been to be understood that: still can modify to embodiment of the present utility model or carry out equivalent replacement to portion of techniques feature; And not departing from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technical scheme scope of the utility model request protection.
Claims (10)
1. a missile shell tripping device, is characterized in that, comprises shell interception passage (1), wherein: described shell interception passage (1) exists missile inlet port (11) and missile exit wound of bullet (12);
The interior wall energy of described shell interception passage (1) utilizes friction force reduce the pace of the missile (32) entered by described missile inlet port (11) gradually and in described shell interception passage (1), only allow described missile (32) to penetrate from described missile exit wound of bullet (12) interception of the shell (31) of described missile.
2. missile shell tripping device according to claim 1, it is characterized in that, the conducting area of described shell interception passage (1) reduces gradually along from described missile inlet port (11) to the direction of described missile exit wound of bullet (12).
3. missile shell tripping device according to claim 1, it is characterized in that, described shell interception passage (1) is that the track (101) of at least two bar shapeds forms around the circumferential direction arrangement of the center line of described missile (32).
4. missile shell tripping device according to claim 3, it is characterized in that, described shell interception passage (1) is linear pattern, and the angle between the bearing of trend of the length direction of described track (101) and the center line of described missile is 1 ° ~ 5 °.
5. missile shell tripping device according to claim 3, is characterized in that, the Reinforced Hoop (102) by least one annular between described track (101) is fixed together.
6. missile shell tripping device according to claim 5, it is characterized in that, the inwall of described Reinforced Hoop (102) is provided with mounting groove (103), and described track (101) to be plugged in described mounting groove (103) and to be fixedly connected with the inwall of described mounting groove (103).
7. missile shell tripping device according to claim 3, it is characterized in that, wherein one end of described track (101) is fixedly connected with mounting flange (104), and the center pit of described mounting flange (104) forms described missile inlet port (11).
8. missile shell tripping device according to claim 7, is characterized in that, described mounting flange (104) is provided with at least two connecting through holes (105).
9. missile shell tripping device according to claim 3, is characterized in that, the xsect of described track (101) is polygon or circle.
10. an Aero Engine Testing equipment, is characterized in that, comprises air bubble and the arbitrary described missile shell tripping device of claim 1-9, wherein:
The described missile inlet port (11) of described shell interception passage (1) is connected with the body emission port of described air bubble.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520970968.7U CN205175698U (en) | 2015-11-30 | 2015-11-30 | Projectile shell separator and aeroengine testing equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520970968.7U CN205175698U (en) | 2015-11-30 | 2015-11-30 | Projectile shell separator and aeroengine testing equipment |
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| Publication Number | Publication Date |
|---|---|
| CN205175698U true CN205175698U (en) | 2016-04-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520970968.7U Active CN205175698U (en) | 2015-11-30 | 2015-11-30 | Projectile shell separator and aeroengine testing equipment |
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| CN (1) | CN205175698U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115200870A (en) * | 2022-09-14 | 2022-10-18 | 中国航发四川燃气涡轮研究院 | Target adjusting method for bird swallowing test of aircraft engine |
-
2015
- 2015-11-30 CN CN201520970968.7U patent/CN205175698U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115200870A (en) * | 2022-09-14 | 2022-10-18 | 中国航发四川燃气涡轮研究院 | Target adjusting method for bird swallowing test of aircraft engine |
| CN115200870B (en) * | 2022-09-14 | 2023-02-17 | 中国航发四川燃气涡轮研究院 | Target adjusting method for bird swallowing test of aircraft engine |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |