CN113532865A - Low-scattering carrier suitable for various engines - Google Patents
Low-scattering carrier suitable for various engines Download PDFInfo
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- CN113532865A CN113532865A CN202110706493.0A CN202110706493A CN113532865A CN 113532865 A CN113532865 A CN 113532865A CN 202110706493 A CN202110706493 A CN 202110706493A CN 113532865 A CN113532865 A CN 113532865A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- General Physics & Mathematics (AREA)
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- Computer Networks & Wireless Communication (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The application belongs to the technical field of engine tests, and particularly relates to a low-scattering carrier applicable to various engines. The carrier comprises an upper carrier section and a lower carrier section, wherein the upper carrier section and the lower carrier section are both of groove body structures with semicircular sections and can be mutually buckled together to form a cavity for accommodating an aircraft engine, the front end of the cavity is provided with a front carrier section which is of a conical structure, the rear end of the cavity is provided with a rear carrier section, the rear carrier section comprises an upper rear carrier section and a lower rear carrier section, and the other ends of the upper rear carrier section and the lower rear carrier section are connected with a carrier tail end; the cavity is internally provided with a carrier front section supporting frame and a carrier middle supporting frame, and the lower carrier rear section is internally provided with a carrier rear section supporting frame for supporting an aircraft engine. The method and the device have great help for the subsequent combined electromagnetic scattering characteristic test of various engines and test pieces, effectively improve the test efficiency and reduce the test error.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to a low-scattering carrier applicable to various engines.
Background
When the electromagnetic characteristics in the cavity structure similar to an aircraft engine are tested, the difference between the radar test and the engine installation state (the engine is arranged in an airplane, and only a spray pipe part is exposed) of the engine model is large, the radar characteristics are greatly influenced by the external structure, and the radar characteristics of the engine cannot be represented by test data. Therefore, the low-scattering carrier is required to shield the external structure (simulate the engine installation state) to avoid influencing electromagnetic data.
The carrier needs to meet the requirements of low scattering property of a specific angular region, structural installation of a test engine or a test piece, placement or rotation of a test bench and the like.
At present, most of the domestic carrier interfaces for the radar test of the engine are of an axisymmetric structure, a small number of the interfaces are of a rectangular structure, and the engine has a set of carriers for a single-structure engine. The multiple sets of carriers increase the time and difficulty of design and simulation evaluation, occupy a large amount of storehouse space, increase the transportation and installation cost and be high. Especially, when the engines of different structures are compared and tested, the multiple sets of carriers bring inconvenience to the aspects of placement, engine replacement, test period and the like, and when the engines of different types are tested, the multiple carriers are respectively installed and tested in the prior art, and individual differences of the carriers appear in carrier electromagnetic scattering data, so that target characteristics are influenced.
Disclosure of Invention
In order to solve the technical problem, the application provides a low-scattering carrier suitable for various engines, such as engines provided with axisymmetric nozzles, binary nozzles and profiled nozzles.
The low-scattering carrier comprises an upper carrier section and a lower carrier section, wherein the upper carrier section and the lower carrier section are both of groove body structures with semicircular sections and can be mutually buckled together to form a cavity for accommodating an aeroengine, the front end of the cavity is provided with a front carrier section, the front carrier section is of a conical structure, the bottom of the conical structure is butted on the front end surfaces of the upper carrier section and the lower carrier section, the rear end of the cavity is provided with a rear carrier section, the rear carrier section comprises an upper carrier rear section and a lower carrier rear section, the upper carrier rear section is butted with the rear end surface of the upper carrier section, the lower carrier rear section is butted with the rear end surface of the lower carrier section, and the other ends of the upper carrier rear section and the lower carrier rear section are connected with a carrier tail end;
the cavity is internally provided with a carrier front section supporting frame and a carrier middle supporting frame, the lower carrier rear section is internally provided with a carrier rear section supporting frame, and the aircraft engine is fixed in the cavity through the carrier front section supporting frame, the carrier middle supporting frame and the carrier rear section supporting frame.
Preferably, the upper carrier section is connected to the lower carrier section by screws.
Preferably, the lower carrier section is provided with studs extending upwards from two ends of the semicircular cross section, the upper carrier section is provided with side wall grooves on side surfaces of two ends close to the semicircular cross section, positioning holes extend from the bottoms of the side wall grooves, and the studs are adapted to penetrate through the positioning holes to fix the upper carrier section and the lower carrier section.
Preferably, the side wall groove is plugged through a side wall cover plate and is adhered with a wave-absorbing adhesive tape.
Preferably, the carrier front section is of a conical structure, the rear portion of the carrier front section is provided with a plurality of buckles, the upper carrier section and the lower carrier section are provided with a plurality of clamping grooves in the circumferential direction at one end connected with the carrier front section, and the buckles are connected with the clamping grooves in a matched mode.
Preferably, the top outside of carrier upper segment is provided with the top groove, be provided with rings in the top groove, the top groove is through apron and the shutoff of inhaling the wave sticky tape.
Preferably, the inner sides of the upper carrier section and the lower carrier section are provided with a plurality of reinforcing ribs, the hanging ring penetrates through the top wall of the upper carrier section and then is fixed on one of the reinforcing ribs, a threaded base is fixed on the reinforcing rib, and the hanging ring is provided with a screw rod part which is matched and connected with the threaded base.
Preferably, the tail end of the carrier is provided with an opening matched with an engine spray pipe structure, the opening is sealed by a tail end baffle plate, and the tail end baffle plate is connected with the tail end of the carrier through a stealth adhesive tape.
Preferably, the carrier rear section is an axisymmetric carrier rear section, the carrier tail end is an axisymmetric tail end, a groove and a boss are arranged on the axisymmetric carrier rear section, the groove is annularly arranged along the inner wall of the axisymmetric carrier rear section, and the boss extends towards the central axis direction on the inner wall of the axisymmetric carrier rear section and is used for limiting the axisymmetric tail end.
Preferably, the outer side of the bottom of the lower carrier section is arranged to be a plane so as to be fixedly connected with a radar test platform, and the inner side of the bottom of the lower carrier section is arranged to be a flat bottom, so that the radar test installation is facilitated.
The application provides a carrier can carry out radar scattering measurement to multiple engine structure, is applicable to the engine structure of multiple special-shaped spout. The carrier of the application is integrated and multipurpose, the condition that one carrier is in the existing structure is broken through, and the resource cost and the time cost are obviously reduced. The method and the device have great help for the subsequent combined electromagnetic scattering characteristic test of various engines and test pieces, effectively improve the test efficiency and reduce the test error.
Drawings
FIG. 1 is a schematic structural view of a preferred embodiment of the low scatter carrier of the present application suitable for use in a variety of engines.
FIG. 2 is a schematic diagram of a front section of the carrier according to the embodiment of FIG. 1.
Fig. 3 is a schematic view of the embodiment of fig. 1 of the present application showing the engagement between the carrier front-end snap and the slot.
Fig. 4 is a schematic diagram of the connection between the upper carrier section and the lower carrier section according to the embodiment shown in fig. 1.
Fig. 5 is a schematic view of the structure of the sidewall groove of the upper carrier segment according to the embodiment of fig. 1.
FIG. 6 is a schematic view of the top end slot structure of the embodiment of FIG. 1 of the present application.
Fig. 7 is a schematic view of the inner side structure of the upper carrier section according to the embodiment shown in fig. 1 of the present application.
Fig. 8 is a schematic view of the carrier rear section support bracket of the embodiment of fig. 1 of the present application.
Fig. 9 is a schematic position diagram of the support stand according to the embodiment of fig. 1 of the present application.
FIG. 10 is a schematic diagram of the rear section and the symmetrical end structure of the axisymmetric carrier according to the embodiment of the present application shown in FIG. 1.
Fig. 11 is a schematic view of the connection of the rear section of the axisymmetric carrier and the axisymmetric tail end of the embodiment shown in fig. 10 of the present application.
The method comprises the following steps of 1-a carrier front section, 11-a buckle, 2-a carrier upper section, 21-a carrier front section support frame, 22-a carrier middle support frame, 23-a side wall groove, 24-a top end groove, 25-a hanging ring, 26-a reinforcing rib, 27-a threaded base, 28-a positioning hole, 3-a top end cover plate, 4-an upper carrier rear section, 5-a tail end baffle plate, 6-a carrier tail end, 7-a lower carrier rear section, 71-a carrier rear section support frame, 72-a groove, 73-a boss, 8-a carrier lower section, 81-a stud and 9-a side wall cover plate.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a low scattering carrier suitable for various structures aeroengine. Can be applicable to multiple complex structure, integrative multi-purpose, convenient and fast. The carrier main body structure is consistent, when measuring many times, the unified gap of being convenient for is handled and the rack installation, has alleviateed the design of multiple carrier, has processed, has deposited, cost such as transportation, storage.
The application provides a low-scattering carrier suitable for various engines, as shown in fig. 1-11, the low-scattering carrier comprises a carrier upper section 2 and a carrier lower section 8, the carrier upper section 2 and the carrier lower section 8 are both of groove body structures with semicircular cross sections and can be mutually buckled together to form a cavity for accommodating an aircraft engine, the front end of the cavity is provided with the carrier front section 1, the carrier front section 1 is of a conical structure, the bottom of the conical structure is butted on the front end surfaces of the carrier upper section 2 and the carrier lower section 8, the rear end of the cavity is provided with a carrier rear section, the carrier rear section comprises an upper carrier rear section 4 and a lower carrier rear section 7, the upper carrier rear section 4 is butted with the rear end surface of the carrier upper section 2, the lower carrier rear section 7 is butted with the rear end surface of the carrier lower section 8, and the other ends of the upper carrier rear section 4 and the lower carrier rear section 7 are connected with a carrier tail end 6;
as shown in fig. 8 and 9, a carrier front section support frame 21 and a carrier middle support frame 22 are arranged in the cavity, a carrier rear section support frame 71 is arranged in the lower carrier rear section 7, and the aircraft engine is fixed in the cavity through the carrier front section support frame 21, the carrier middle support frame 22 and the carrier rear section support frame 71.
The utility model provides a support frame 22 and carrier back end support frame 71 are all can dismantle the connection in the middle of carrier anterior segment support frame 21, the carrier, and solitary support frame structure conveniently changes the outfit, is applicable to the engine or the testpieces of multiple complex construction.
Most structures in the carrier are kept unchanged, and the measured background data are only influenced by different structural parts, so that the difference is small and the precision is higher compared with different whole carriers; the gap of the carrier is an important scattering source of the carrier, the gap processing needs to be carried out on the carrier during electromagnetic testing, the gap processing of the carrier main body can be used for different engine tests once, and the states of the main body are kept consistent.
In the aspect of cost, the engine model electromagnetic test with different structures can be met only by replacing part of the structure, and compared with the use of a plurality of carriers, the design, processing, installation, transportation and storage costs of the carriers are greatly reduced. In the aspect of efficiency, the efficiency of the method is higher in the aspects of rack trial assembly, gap treatment and the like, and the time for the same operation of various carriers is greatly shortened.
In some alternative embodiments, the upper carrier section 2 is connected to the lower carrier section 8 by screws.
In some alternative embodiments, as shown in fig. 4 and 5, the lower carrier section 8 has studs 81 extending upward from two ends of the semicircular cross section, the upper carrier section 2 has side wall grooves 23 formed on two side surfaces near the semicircular cross section, positioning holes 28 extend from bottoms of the side wall grooves 23, and the studs 81 are adapted to pass through the positioning holes to fix the upper carrier section 2 and the lower carrier section 8.
In some alternative embodiments, as shown in fig. 1, the side wall groove 23 is sealed by the side wall cover plate 9, and the wave-absorbing adhesive tape is adhered.
In some alternative embodiments, as shown in fig. 2, the carrier front section 1 is a tapered structure, the rear portion of the carrier front section 1 is provided with a plurality of buckles 11, the carrier upper section 2 and the carrier lower section 8 are provided with a plurality of slots along the circumferential direction at one end connected to the carrier front section 1, as shown in fig. 3, the buckles 11 are connected with the slots in a matching manner.
It can be understood that the buckling structure of the front section 1 of the carrier and the design of the detachable pointed cone can ensure the installation of an engine or a test piece and reduce the forward electromagnetic property. The special carrier buckle structure enables the test piece to be installed in the carrier, and finally the carrier is sealed. Meanwhile, the forward electromagnetic characteristic of the carrier is effectively reduced due to the pointed cone design at the front end, and the influence of the outer structures of the carrier such as an engine spray pipe on the forward radar electromagnetic characteristic can be realized.
In some alternative embodiments, as shown in fig. 6, a top groove 24 is provided on the top outer side of the carrier upper section 2, and a hanging ring 25 is provided in the top groove 24, as shown in fig. 1, the top groove 24 is blocked by the top cover plate 3 and the wave-absorbing adhesive tape.
It should be noted that the top cover plate and the side cover plate are curved structures, and the curved structures can be attached to the carrier appearance structure, so that lower electromagnetic characteristics are ensured. The circular design of the top cover plate is adaptive to the structural curve of the carrier, the electromagnetic characteristic of the gap of the cover plate is reduced, and the precision is improved. The shape of the side wall cover plate, the included angle between the outline and the horizontal line and the design of the guide circle are suitable for the structural curve of the carrier, the electromagnetic characteristic of the gap of the cover plate is reduced, and the precision is improved. The cover plate and the groove structure corresponding to the cover plate ensure that an engine or a test piece is installed and a carrier is sealed.
In some alternative embodiments, as shown in fig. 7, the inner sides of the upper carrier section 2 and the lower carrier section 8 are provided with a plurality of reinforcing ribs 26, the hanging ring 25 passes through the top wall of the upper carrier section 2 and is fixed on one of the reinforcing ribs, a threaded base 27 is fixed on the reinforcing rib, and the hanging ring 25 has a screw portion adapted to be connected with the threaded base 27.
In some alternative embodiments, as shown in fig. 1, the carrier tail end 6 has an opening adapted to the engine nozzle structure, the opening is closed by a tail end shielding plate 5, and the tail end shielding plate 5 and the carrier tail end 6 are connected by a stealth adhesive tape.
This application is applicable to the carrier main part and the tail end structure of multiple complex construction, and the tail end structure can be dismantled and the form is various to guarantee to match with multiple pattern spout, except that the structure shown in figure 1, this application can also be through changing the carrier tail end with adaptation axisymmetric engine. The rear section of the carrier and the two groups of structures at the tail end are used for realizing the assembly of nozzles in different structures of engines or test pieces, and when the engines and the test pieces with different structures are tested, the two groups of structures are integrally replaced. The method can not only deal with the installation problem of a complex structure, but also ensure the low scattering property of the external surface of the carrier, and avoid the problems of overlarge installation and electromagnetic property caused by a group of direct structures.
In some optional embodiments, as shown in fig. 10 and 11, the rear carrier section is an axisymmetric rear carrier section, the rear carrier section 5 is an axisymmetric rear carrier section, the axisymmetric rear carrier section is provided with a groove 72 and a boss 73, the groove is annularly arranged along an inner wall of the axisymmetric rear carrier section, and the boss extends towards a central axis direction on the inner wall of the axisymmetric rear carrier section and is used for limiting the axisymmetric rear carrier section.
It should be noted that the tail end of the axisymmetric carrier and the axisymmetric rear section form a screw-free closed installation structure, and the boss of the axisymmetric rear section is matched with the axisymmetric tail end to position the spatial position of the tail end. When the upper and lower structures of the rear section of the axisymmetric carrier are butted, the axisymmetric tail end can be clamped together to ensure that the axisymmetric tail end cannot slip off after being fixed, thereby realizing the screw-free closed installation.
In some optional embodiments, the outer side of the bottom of the lower carrier section 8 is a plane to be fixedly connected with a radar test platform, as shown in fig. 9, the inner side of the bottom of the lower carrier section 8 is a flat bottom, which facilitates radar test installation.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A low-scattering carrier suitable for various engines is characterized by comprising an upper carrier section (2) and a lower carrier section (8), the upper carrier section (2) and the lower carrier section (8) are both of groove body structures with semicircular sections, and can be mutually buckled together to form a cavity for accommodating an aircraft engine, the front end of the cavity is provided with a carrier front section (1), the carrier front section (1) is of a conical structure, the bottom of the conical structure is butted on the front end surfaces of the carrier upper section (2) and the carrier lower section (8), a carrier rear section is arranged at the rear end of the cavity and comprises an upper carrier rear section (4) and a lower carrier rear section (7), the upper carrier rear section (4) is in butt joint with the rear end face of the carrier upper section (2), the lower carrier rear section (7) is in butt joint with the rear end face of the carrier lower section (8), and the other ends of the upper carrier rear section (4) and the lower carrier rear section (7) are connected with a carrier tail end (6);
the cavity is internally provided with a carrier front section supporting frame (21) and a carrier middle supporting frame (22), the lower carrier rear section (7) is internally provided with a carrier rear section supporting frame (71), and the aircraft engine is fixed in the cavity through the carrier front section supporting frame (21), the carrier middle supporting frame (22) and the carrier rear section supporting frame (71).
2. The low scatter carrier suitable for many engines according to claim 1, wherein the carrier upper section (2) and the carrier lower section (8) are connected by screws.
3. The low scattering carrier for various engines as claimed in claim 2, wherein the lower carrier section (8) has studs (81) extending upward from both ends of its semicircular cross section, the upper carrier section (2) has side wall grooves (23) formed on its side surfaces near both ends of its semicircular cross section, positioning holes (28) extend from the bottoms of the side wall grooves (23), and the studs (81) are adapted to pass through the positioning holes to fix the upper carrier section (2) and the lower carrier section (8).
4. The low-scattering carrier for various engines as claimed in claim 3, wherein the side wall grooves (23) are closed by side wall cover plates (9) and are adhered with wave-absorbing adhesive tapes.
5. The low-scattering carrier applicable to various engines as claimed in claim 1, wherein the carrier front section (1) is of a conical structure, the rear part of the carrier front section is provided with a plurality of fasteners (11), the carrier upper section (2) and the carrier lower section (8) are provided with a plurality of slots along the circumferential direction at one end connected with the carrier front section (1), and the fasteners (11) are connected with the slots in a matching manner.
6. The low-scattering carrier applicable to various engines as claimed in claim 1, wherein a top groove (24) is arranged on the outer side of the top of the carrier upper section (2), a hanging ring (25) is arranged in the top groove (24), and the top groove (24) is blocked by a top cover plate (3) and a wave-absorbing adhesive tape.
7. The low-scattering carrier for various engines as claimed in claim 6, wherein a plurality of reinforcing ribs (26) are arranged on the inner side of the upper carrier section (2) and the lower carrier section (8), the suspension ring (25) penetrates through the top wall of the upper carrier section (2) and is fixed on one of the reinforcing ribs, a threaded base (27) is fixed on the reinforcing rib, and the suspension ring (25) is provided with a screw portion which is matched and connected with the threaded base (27).
8. The low-scattering carrier suitable for various engines as claimed in claim 1, characterized in that the carrier tail end (6) has an opening adapted to the engine nozzle structure, the opening is blocked by a tail end baffle (5), and the tail end baffle (5) is connected with the carrier tail end (6) by a stealth adhesive tape.
9. The low scattering carrier for various engines as claimed in claim 1, wherein the carrier rear section is an axisymmetric carrier rear section, the carrier rear end (5) is an axisymmetric rear end, the axisymmetric carrier rear section is provided with a groove (72) and a boss (73), the groove is annularly arranged along the inner wall of the axisymmetric carrier rear section, and the boss extends towards the central axis direction on the inner wall of the axisymmetric carrier rear section for limiting the axisymmetric rear end.
10. The low-scattering carrier applicable to various engines as claimed in claim 1, wherein the outer side of the bottom of the lower carrier section (8) is arranged to be a plane for fixedly connecting with a radar test platform, and the inner side of the bottom of the lower carrier section (8) is arranged to be a flat bottom, so that radar test installation is facilitated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110706493.0A CN113532865B (en) | 2021-06-24 | 2021-06-24 | Low-scattering carrier suitable for various engines |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110706493.0A CN113532865B (en) | 2021-06-24 | 2021-06-24 | Low-scattering carrier suitable for various engines |
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| CN113532865A true CN113532865A (en) | 2021-10-22 |
| CN113532865B CN113532865B (en) | 2022-06-07 |
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| CN115267687A (en) * | 2022-09-29 | 2022-11-01 | 中国航发四川燃气涡轮研究院 | Low-cost modularized multi-posture engine low-scattering carrier |
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| CN114044164A (en) * | 2021-11-10 | 2022-02-15 | 北京环境特性研究所 | Low-scattering carrier for RCS (Radar Cross section) test of wing parts |
| CN114355311A (en) * | 2022-03-10 | 2022-04-15 | 成都飞机工业（集团）有限责任公司 | Low-scattering carrier for RCS (Radar Cross section) test of airfoil leading edge wave-absorbing structure and test method |
| CN114355311B (en) * | 2022-03-10 | 2022-08-12 | 成都飞机工业（集团）有限责任公司 | Low-scattering carrier for RCS (Radar Cross section) test of airfoil leading edge wave-absorbing structure and test method |
| CN115267687A (en) * | 2022-09-29 | 2022-11-01 | 中国航发四川燃气涡轮研究院 | Low-cost modularized multi-posture engine low-scattering carrier |
| CN115267687B (en) * | 2022-09-29 | 2023-02-21 | 中国航发四川燃气涡轮研究院 | Low-cost modularized multi-posture engine low-scattering carrier |
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| CN113532865B (en) | 2022-06-07 |
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