CN112591139B - Low-scattering support system of mounting aircraft - Google Patents
Low-scattering support system of mounting aircraft Download PDFInfo
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- CN112591139B CN112591139B CN202011566274.9A CN202011566274A CN112591139B CN 112591139 B CN112591139 B CN 112591139B CN 202011566274 A CN202011566274 A CN 202011566274A CN 112591139 B CN112591139 B CN 112591139B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The application belongs to the technical field of aircraft ground static tests, and particularly relates to a low-scattering support system of a packaged aircraft. The system comprises a front bracket (1) which is arranged in front of a support field and used for supporting the head of an airplane; the two rear supports (2) are arranged behind the supporting field side by side and are used for supporting the left side and the right side of the tail of the airplane; the two protective supports (3) are respectively arranged on the left side and the right side of the supporting field and are used for supporting wings of the airplane; the tops of the front support (1), the rear support (2) and the protective support (3) are all configured to be in adaptive contact with the arc-shaped surface of the fuselage or the wing. The application provides a brand-new support system from the aspects of multi-point support, low scattering of appearance, multi-system combination and the like, and can meet the test requirements of large bearing, low scattering, convenient posture adjustment, high safety and the like of radar stealth test of the real aircraft simultaneously.
Description
Technical Field
The application belongs to the technical field of aircraft ground static tests, and particularly relates to a low-scattering supporting system of a solid-mounted aircraft.
Background
The ground static test is a main means for the radar stealth test of a real-mounted airplane, and in order to ensure that the radar stealth performance of the whole airplane can be accurately obtained, the airplane needs to be supported to a certain height (about 2 m) through a low-scattering support system (mainly a low-scattering foam column) so as to reduce the influences of ground scattering, airplane coupling scattering and the like. The design requirements of the supporting system are large bearing, low scattering, convenient posture adjustment and high safety.
The traditional foam supporting mode has certain limitations:
(1) The supporting point is single, and the stability is poor: the traditional foam supporting system is mostly designed to be supported at 1 or 2 points, and the contact form of the airplane and the supporting system is mostly based on a plane, so that the airplane cannot be completely attached to the airplane, the stability is poor, and certain potential safety hazards exist;
(2) The system has single appearance design and high scattering: the traditional foam support system is mostly designed into a straight cylinder form, the cylindrical surface scattering is high, the test requirement of a conventional three-generation airplane can be met, but the accurate test cannot be realized aiming at stealth airplanes such as a third-generation stealth improved airplane, a fourth-generation airplane and the like of a fighter-16 airplane;
(3) The system has a single combination form, and the test posture is difficult to ensure: the traditional foam supporting system is mostly designed into a single combination, and a foam cushion block is adopted at the contact position of the airplane and the foam to realize the adjustment of the pitching angle of the airplane. But for the requirement of large pitch angle test, it has the following disadvantages:
the aircraft pitch angle cannot be accurately adjusted: the foam cushion block has small size and high compressibility;
the aircraft pitch angle can be limited: the safety of the airplane is affected by the oversize cushion block;
the field operation is complex: and (3) once adjusting, namely erecting a jack, padding a foam block, collecting the jack, measuring the angle, and repeatedly adjusting if the angle is inaccurate.
In order to realize the precise radar stealth test of the whole airplane, a low-scattering support system of a packaged airplane, which can meet the requirements of large bearing, low scattering, convenient posture adjustment and high safety, is urgently needed.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, provides a three-band wave-absorbing and two-band wave-transmitting low-scattering support system of a practical airplane, and aims to solve the technical problem that the conventional passband embedded type practical airplane low-scattering support system is complex in structure. The technical problem that the existing double-wave-transparent and wave-transparent integrated FSS is insufficient in high-frequency wave absorption rate is solved.
The application realizes low scattering braced system of aircraft mainly includes:
the front bracket is arranged in front of the support field and is used for supporting the head of the airplane;
the two rear supports are arranged behind the supporting field side by side and used for supporting the left side and the right side of the tail of the airplane;
the protection supports are respectively arranged on the left side and the right side of the support field and used for supporting the wings of the airplane;
the top of the front support, the top of the rear support and the top of the protective support are all configured to be in adaptive contact with the arc-shaped surface of the fuselage or the wing.
Preferably, the front support and the rear support both comprise a plurality of components, and the change of the aircraft pitch angle is realized through the collocation of different components.
Preferably, a first pitch attitude of the aircraft is constituted by a front bracket, a rear bracket and a protective bracket, the front bracket includes a first upper layer portion, a first middle layer portion and a first lower layer portion in the first pitch attitude, each of the rear brackets includes a first upper layer portion and a first lower layer portion, and an attitude angle of the first pitch attitude is 0 °.
Preferably, a second pitch attitude of the aircraft is constituted by a front bracket, a rear bracket and a protective bracket, the front bracket including a second upper section, and each rear bracket including a second upper section and a second lower section in the second pitch attitude, and an attitude angle of the second pitch attitude is +5 °.
Preferably, a third pitch attitude of the aircraft is constituted by a front bracket, a rear bracket and a protective bracket, the front bracket includes a third upper layer portion and a third lower layer portion in the third pitch attitude, each rear bracket includes a third lower layer portion, and an attitude angle of the third pitch attitude is-5 °.
Preferably, the front support, the rear support and the protection support are all arranged to be of a column structure, and the included angle between the side edge of the column and the vertical direction is 15 degrees.
The application provides a brand-new support system from the aspects of multi-point support, low scattering of appearance, multi-system combination and the like, and can meet the test requirements of large bearing, low scattering, convenient posture adjustment, high safety and the like of radar stealth test of the packaged aircraft simultaneously.
Drawings
FIG. 1 is a schematic view of a multi-point support design of "3+2" in a preferred embodiment of the low scattering support system of the present invention.
Fig. 2 is a schematic diagram of the top shaping design of the low scattering support system according to an embodiment of the present invention.
FIG. 3 is a schematic view of a low scattering support system tilt design according to an embodiment of the present invention.
FIG. 4 is a block diagram of a low scatter support system according to an embodiment of the present invention.
Wherein, 1-a front bracket, 2-a rear bracket and 3-a protective bracket.
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 accompanying 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 present application provides a low-scattering support system for a packaged aircraft, as shown in fig. 1-4, comprising:
the front support 1 is arranged in front of a support field and used for supporting the head of an airplane;
the two rear supports 2 are arranged behind the supporting field side by side and are used for supporting the left side and the right side of the tail of the airplane;
the two protective supports 3 are respectively arranged on the left side and the right side of the supporting field and are used for supporting wings of the airplane;
the top of the front bracket 1, the top of the rear bracket 2 and the top of the protective bracket 3 are all configured to be in adaptive contact with the arc-shaped surface of the fuselage or the wing.
The design concept of multi-point support is provided for a heavy aircraft, the position of a main supporting point is preferably selected by combining the distribution characteristics of a bearing frame of the aircraft, the selection principle mainly comprises that the main supporting point does not interfere with the supporting position of a jack, the positions of front and rear supporting points are far as possible and do not exceed a rotary table and the like, on the basis, 2 auxiliary support foam columns are additionally arranged at the positions, close to the wing tips, of the left side and the right side of the aircraft to prevent the aircraft from rolling under the action of side wind, and the design schematic diagram of the multi-point support is shown in figure 1. Meanwhile, the top end shape of the support foam column and the surface shape of the airplane are designed in a shaping mode, as shown in fig. 2, perfect fitting of the support system and the surface of the airplane is achieved, friction is increased, and safety is greatly improved.
In some optional embodiments, the front support 1, the rear support 2 and the protection support 2 are all configured as a pillar structure, and an included angle between a side edge of the pillar and the vertical direction is 15 °.
After the support points are determined, the tip contact area is taken into account to ensure large load-bearing characteristics, and the requirement of low scattering, preferably a 15 ° tilt angle design, as shown in fig. 3. Tests prove that the scattering magnitude of the form can reach-25 dBm < 2 > -30dBm < 2 >, can be reduced by more than 10dB compared with the traditional vertical column form, and completely meets the requirement of high-precision testing.
In some optional embodiments, each of the front support 1 and the rear support 2 includes a plurality of components, and the change of the aircraft pitch angle is realized by matching different components.
Aiming at the test requirements of different pitching angles of the airplane, a 'building block type' combined design is provided, namely based on 18 foam columns, aiming at different pitching angles, the attitude can be accurately adjusted through specific foam column combination, and the combination form is shown in figure 4. The design has the advantages of accurate pitching posture, high posture adjustment efficiency, full fit of the top end and the like. The specific combination is as follows.
A first pitching attitude of the airplane is formed by the front support 1, the rear support 2 and the protective support 2, the front support comprises a first upper layer part, a first middle layer part and a first lower layer part under the first pitching attitude, each rear support comprises a first upper layer part and a first lower layer part, and the attitude angle of the first pitching attitude is 0 degree.
Constitute the second every single move gesture of aircraft through fore-stock 1, after-poppet 2 and protective cradle 2, under the second every single move gesture, the fore-stock includes second upper strata part, every the after-poppet includes second upper strata part and second lower floor part, the gesture angle of second every single move gesture is + 5.
The front support 1, the rear support 2 and the protection support 2 form a third pitching attitude of the airplane, the front support comprises a third upper layer part and a third lower layer part under the third pitching attitude, each rear support comprises a third lower layer part, and the attitude angle of the third pitching attitude is-5 degrees.
The invention has the beneficial effects that: the invention provides a design method of a low-scattering support system of a solid-mounted aircraft, aiming at the radar stealth performance test requirements of the solid-mounted stealth aircraft such as large bearing, low scattering, convenient attitude adjustment, high safety and the like. The invention can meet the support requirement of the heavy test target large pitching angle test on the basis of the traditional single-point support mode, greatly improves the test safety, and provides technical support for the stealth tests of airplanes such as the future three-generation airplane stealth improved type airplane, the fourth-generation airplane and the like.
In the specific implementation process, firstly, the structural characteristics and the test requirements of the airplane are combined, the positions of the front supporting frame and the rear supporting frame are preferably selected, the auxiliary supporting positions are selected at the wingtips of the left wing and the right wing, the protection effect is realized, and then the shaping design of the top surface of the supporting system is developed by combining the contact surface of the airplane and the low-scattering supporting system; then, low-scattering design is carried out respectively for the front and rear supports by combining the characteristics of airplane layout; and then according to the requirement of the pitch angle of the plane, different pitch attitudes of the plane are realized through 'building block type' combination based on 18 foam columns.
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 (2)
1. A low scatter support system for a surface mount aircraft, comprising:
the front bracket (1) is arranged in front of a support field and is used for supporting the head of an airplane;
the two rear supports (2) are arranged behind the supporting field side by side and are used for supporting the left side and the right side of the tail of the airplane;
the two protective supports (3) are respectively arranged on the left side and the right side of the supporting field and are used for supporting the wings of the airplane;
the tops of the front support (1), the rear support (2) and the protective support (3) are matched to be in contact with the arc-shaped surface of the fuselage or the wing;
the front support (1) and the rear support (2) both comprise a plurality of components, the change of the pitch angle of the airplane is realized through the collocation of different components, a first pitch attitude of the airplane is formed through the front support (1), the rear support (2) and the protective support (3), the front support comprises a first upper layer part, a first middle layer part and a first lower layer part under the first pitch attitude, each rear support comprises a first upper layer part and a first lower layer part, and the attitude angle of the first pitch attitude is 0 degree; a second pitching attitude of the aircraft is formed by the front support (1), the rear support (2) and the protective support (3), the front support comprises a second upper layer part, each rear support comprises a second upper layer part and a second lower layer part, and the attitude angle of the second pitching attitude is +5 degrees; constitute the third every single move gesture of aircraft through fore-stock (1), after-poppet (2) and protective cradle (3), under the third every single move gesture, the fore-stock includes third upper strata part, third lower floor's part, every the after-poppet includes third lower floor's part, the gesture angle of third every single move gesture is-5.
2. A packaged aircraft low-scatter support system according to claim 1, characterised in that the front support (1), the rear support (2) and the protective support (3) are arranged in a column configuration, the side of the column forming an angle of 15 ° with the vertical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011566274.9A CN112591139B (en) | 2020-12-25 | 2020-12-25 | Low-scattering support system of mounting aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011566274.9A CN112591139B (en) | 2020-12-25 | 2020-12-25 | Low-scattering support system of mounting aircraft |
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| Publication Number | Publication Date |
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| CN112591139A CN112591139A (en) | 2021-04-02 |
| CN112591139B true CN112591139B (en) | 2023-02-28 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114104331B (en) * | 2021-11-12 | 2023-06-30 | 北京环境特性研究所 | Wave absorber for reducing low-frequency dispersion |
| 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 |
Citations (5)
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| US5612687A (en) * | 1993-04-02 | 1997-03-18 | Aerospatiale Societe Nationale Industrielle | Process for regulating the orientation of a support structure such as that carrying a head-up control system on an aircraft |
| CN205201460U (en) * | 2015-12-08 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Supporting apparatus |
| CN107957575A (en) * | 2017-12-29 | 2018-04-24 | 北京航空航天大学 | A kind of two one are hung the method that support system realizes conical scanning |
| CN109581314A (en) * | 2018-12-14 | 2019-04-05 | 中国航空工业集团公司北京航空精密机械研究所 | The device of aircraft RCS test |
| CN111562792A (en) * | 2019-12-24 | 2020-08-21 | 中国航空工业集团公司北京航空精密机械研究所 | Airplane pitch angle adjusting control device and working method thereof |
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2020
- 2020-12-25 CN CN202011566274.9A patent/CN112591139B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5612687A (en) * | 1993-04-02 | 1997-03-18 | Aerospatiale Societe Nationale Industrielle | Process for regulating the orientation of a support structure such as that carrying a head-up control system on an aircraft |
| CN205201460U (en) * | 2015-12-08 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Supporting apparatus |
| CN107957575A (en) * | 2017-12-29 | 2018-04-24 | 北京航空航天大学 | A kind of two one are hung the method that support system realizes conical scanning |
| CN109581314A (en) * | 2018-12-14 | 2019-04-05 | 中国航空工业集团公司北京航空精密机械研究所 | The device of aircraft RCS test |
| CN111562792A (en) * | 2019-12-24 | 2020-08-21 | 中国航空工业集团公司北京航空精密机械研究所 | Airplane pitch angle adjusting control device and working method thereof |
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