阅读说明：本技术 一种飞机背负倾斜式两面阵穹顶结构 (Plane bearing inclined two-area array dome structure ) 是由 陈磊 陈永利 梁永贵 张俊亮 王康 赵占军 张建波 谭小辉 张秋雁 张超 于 2021-10-28 设计创作，主要内容包括：本发明属于航空技术领域,公开了一种飞机背负倾斜式两面阵穹顶结构。穹顶结构通过两个支腿1安装在机身正上方；所述穹顶结构包括：雷达罩4和金属骨架5；雷达罩4包含对称的左右罩体,所述左右罩体分别固定安装在金属骨架5的左右两侧；金属骨架5沿飞机航向的剖面为梯形,用于天线带角度安装；雷达罩4用于雷达阵面透波和整流,金属骨架5用于安装雷达罩、雷达阵面,并承受穹顶结构受到的气动力和惯性载荷。在满足强度、刚度要求的情况下,实现雷达阵面的安装角度要求。(The invention belongs to the technical field of aviation, and discloses a piggyback inclined two-area array dome structure of an airplane. The dome structure is arranged right above the fuselage through two supporting legs 1; the dome structure includes: a radome 4 and a metal skeleton 5; the radome 4 comprises symmetrical left and right covers which are respectively fixedly arranged at the left and right sides of the metal framework 5; the section of the metal framework 5 along the course of the airplane is trapezoidal and is used for installing the antenna at an angle; radome 4 is used for the radar front wave-transmitting and rectifying, and metal framework 5 is used for installing radome, radar front to bear the aerodynamic force and the inertial load that the dome structure received. Under the condition of meeting the requirements on strength and rigidity, the requirement on the installation angle of the radar array surface is met.)

1. A plane bearing inclined two-area array dome structure is characterized in that the dome structure is arranged right above a plane body through two support legs 1; the dome structure includes: a radome 4 and a metal skeleton 5; the radome 4 comprises symmetrical left and right covers which are respectively fixedly arranged at the left and right sides of the metal framework 5;

the section of the metal framework 5 along the course of the airplane is trapezoidal and is used for installing the antenna at an angle;

radome 4 is used for the radar front wave-transmitting and rectifying, and metal framework 5 is used for installing radome, radar front to bear the aerodynamic force and the inertial load that the dome structure received.

2. The airplane piggyback tilting two-area array dome structure as claimed in claim 1, wherein the metal framework 5 is composed of a left end frame 6, a right end frame 6, an upper wall plate 7, a lower wall plate 7, a cross beam 8, a mouth frame 9 and an end rib 10 structure;

the left end frame 6, the right end frame 6, the upper wall plate 7 and the lower wall plate 7 are connected together through a plurality of cross beams 8 in the metal framework 5; between two cross beams 8 in the middle, the bottom of the cross beam is provided with an opening frame 9, and the front end and the rear end of the metal framework 5 are provided with end ribs 10 which are used for connecting the ends of the left end frame 6, the right end frame 6, the upper wall plate 7 and the lower wall plate 7.

3. The airplane backpack tilting two-sided array dome structure as claimed in claim 2, wherein said left and right end frames 6 are used as array face mounting structures, said left and right cover bodies and antenna are respectively fixedly mounted on the left and right end frames 6, and the left and right end frames 6 are tilting.

4. The piggyback tilting two-area array dome structure of claim 2, wherein aerodynamic and inertial loads on the dome structure during flight are borne by the left and right end frames, the cross beam and the mouth frame, and are finally transmitted to the legs through the mouth frame and then transmitted to the fuselage structure by the legs to achieve force and moment balance.

5. A piggyback tilting two-area array dome structure according to claim 2, characterised in that the end rib 10 is formed by a detachable leading edge 14 and an end rib beam 15;

the removable leading edge 14 is mounted on an end rib 15.

6. The airplane piggyback tilting two-area array dome structure of claim 6, wherein the left and right end frames 6 are formed by upright posts 16, cross beams 17, end frame flanges 12;

the cross beam 17 is fixedly connected to the upright post 16, and both ends of the upright post 16 are respectively fixed to the end frame flanges 12.

7. A piggyback tilting two-area array dome structure according to claim 3, wherein undercuts 13 are provided at the front and rear ends of the end rim strip 12 to compensate for radome assembly tolerances.

8. An airplane backpack tilting two-area array dome structure according to claim 5, wherein said end rib 15 comprises a web and upper and lower flanges mounted on the upper and lower sides of the web, said end rib 15 connecting the ends of the left and right end frames 6 and the upper and lower wall plates 7 via the upper and lower flanges.

Technical Field

The invention belongs to the technical field of aviation, and particularly relates to a piggyback inclined two-area array dome structure of an airplane.

Background

For special airplanes, in order to meet the installation requirements of large radar array surfaces, airplanes are usually used for bearing an outer hanging object as an installation structure, such as a bearing dome structure, a shield structure and the like. The dome-type outer hanger has large overall dimension, can realize 360-degree all-directional radiation of a radar array surface without shielding, and is a preferred outer hanger structure of a large airborne radar.

According to the loading requirement of the radar array surface, the internal structure framework of the dome-type external hanging object can be set into various layouts, the common layout has two types of planar arrays and three planar arrays, the radar array surface and the plane horizontal surface are installed in the normal direction in the two types of layout schemes which are disclosed at present, and when the radar array surface needs to be installed at a certain inclined included angle with the plane horizontal surface, the existing layout can not meet the installation requirement of the radar array surface.

Disclosure of Invention

The invention overcomes the defects in the prior art, provides a piggyback inclined two-surface-array dome structure of an airplane, adopts inclined two-surface-array layout aiming at the interior of a dome-type outer hanging object of a certain airplane, and realizes the installation angle requirement of a radar array surface under the condition of meeting the requirements of strength and rigidity through layout optimization and force transmission path design of structural members.

In order to achieve the purpose, the invention is realized by adopting the following technical scheme.

A plane bears two inclined planar array dome structures, the dome structures are arranged right above a plane body through two supporting legs 1; the dome structure includes: a radome 4 and a metal skeleton 5; the radome 4 comprises symmetrical left and right covers which are respectively fixedly arranged at the left and right sides of the metal framework 5;

the section of the metal framework 5 along the course of the airplane is trapezoidal and is used for installing the antenna at an angle;

radome 4 is used for the radar front wave-transmitting and rectifying, and metal framework 5 is used for installing radome, radar front to bear the aerodynamic force and the inertial load that the dome structure received.

The technical scheme of the invention has the characteristics and further improvements that:

(1) the metal framework 5 is composed of a left end frame 6, a right end frame 6, an upper wall plate 7, a lower wall plate 7, a cross beam 8, a mouth frame 9 and an end rib 10;

the left end frame 6, the right end frame 6, the upper wall plate 7 and the lower wall plate 7 are connected together through a plurality of cross beams 8 in the metal framework 5; between two cross beams 8 in the middle, the bottom of the cross beam is provided with an opening frame 9, and the front end and the rear end of the metal framework 5 are provided with end ribs 10 which are used for connecting the ends of the left end frame 6, the right end frame 6, the upper wall plate 7 and the lower wall plate 7.

(2) The left end frame 6 and the right end frame 6 are used as array surface mounting structures, the left cover body, the right cover body and the antenna are fixedly mounted on the left end frame 6 and the right end frame 6 respectively, and the left end frame and the right end frame 6 are inclined.

(3) Aerodynamic force and inertial load borne by the dome structure in the flying process are borne by the left end frame, the right end frame, the cross beam and the mouth frame, are finally transmitted to the supporting legs through the mouth frame and then are transmitted to the fuselage structure through the supporting legs, and force and moment balance is achieved.

(4) The end rib 10 is made up of a detachable leading edge 14 and an end rib beam 15;

the removable leading edge 14 is mounted on an end rib 15.

(5) The left end frame 6 and the right end frame 6 are composed of upright posts 16, cross beams 17 and end frame edge strips 12;

the cross beam 17 is fixedly connected to the upright post 16, and both ends of the upright post 16 are respectively fixed to the end frame flanges 12.

(6) Undercuts 13 are provided at the front and rear ends of the end rim strip 12 to compensate for radome assembly tolerances.

(7) The end rib beam 15 is composed of a web plate, upper and lower edge strips, the upper and lower edge strips are installed on the upper and lower sides of the web plate, and the end rib beam 15 is connected with the ends of the left and right end frames 6 and the upper and lower wall plates 7 through the upper and lower edge strips.

The invention provides a plane bearing inclined two-face array dome structure, which is arranged in an inclined manner by mounting an end frame on a radar array face in order to adapt to the inclination requirement of the radar array face and reduce extra additional bending moment caused by the fact that the radar array face is not parallel to an end frame mounting face on the premise of meeting the design requirements of strength, rigidity and bird impact resistance through reasonable layout and load distribution design of the structure. Effectively solved the not enough of the outer thing structural configuration of hanging of current aircraft dome formula can't satisfy the radar array face slope installation requirement.

Drawings

FIG. 1 is a schematic view of a connection between a piggyback tilting two-area array dome structure of an airplane and the airplane according to an embodiment of the present invention;

FIG. 2 is a front view of a metal skeleton construction;

FIG. 3 is a view of the metal skeleton structure taken along direction A of FIG. 1;

FIG. 4 is a view of the left end frame structure of FIG. 3 in the direction B;

FIG. 5 is a schematic view of an end frame strip configuration;

FIG. 6 is a schematic view of an end rib configuration;

wherein: 1. the structure comprises supporting legs, 2, a two-sided array dome structure, 3, a machine body, 4, a radar cover, 5, a metal framework, 6, left and right end frames, 7, upper and lower wall plates, 8, a metal framework cross beam, 9, a mouth frame, 10, end ribs, 11, a radar array face, 12, end frame edge strips, 13, edge strips sinking, 14 detachable front edges, 15 end rib beams, 16 upright columns, 17 and left and right end frame cross beams.

Detailed Description

The embodiment of the invention provides a piggyback inclined two-area array dome structure of an airplane, and as shown in figure 1, the dome structure is arranged right above an airplane body through two support legs 1; the dome structure includes: a radome 4 and a metal skeleton 5; the radome 4 comprises symmetrical left and right covers which are respectively fixedly arranged at the left and right sides of the metal framework 5;

as shown in fig. 2, the section of the metal framework 5 along the aircraft course is trapezoidal, and is used for the antenna installation with an angle;

radome 4 is used for the radar front wave-transmitting and rectifying, and metal framework 5 is used for installing radome, radar front to bear the aerodynamic force and the inertial load that the dome structure received.

Specifically, as shown in fig. 3, the metal framework 5 is composed of a left end frame 6, a right end frame 6, an upper wall plate 7, a lower wall plate 7, a cross beam 8, a mouth frame 9 and end ribs 10;

the left end frame 6, the right end frame 6, the upper wall plate 7 and the lower wall plate 7 are connected together through a plurality of cross beams 8 in the metal framework 5; between two cross beams 8 in the middle, the bottom of the cross beam is provided with an opening frame 9, and the front end and the rear end of the metal framework 5 are provided with end ribs 10 which are used for connecting the ends of the left end frame 6, the right end frame 6, the upper wall plate 7 and the lower wall plate 7.

The left and right end frames 6 are used as array surface mounting structures, the left and right cover bodies and the antenna are respectively fixedly mounted on the left and right end frames 6, and the left and right end frames 6 are inclined (as shown in fig. 2).

Aerodynamic force and inertial load borne by the dome structure in the flying process are borne by the left end frame, the right end frame, the cross beam and the mouth frame, are finally transmitted to the supporting legs through the mouth frame and then are transmitted to the fuselage structure through the supporting legs, and force and moment balance is achieved.

As shown in fig. 6, the end rib 10 is comprised of a removable leading edge 14 and an end rib spar 15;

the removable leading edge 14 is mounted on an end rib 15.

As shown in fig. 4, the left and right end frames 6 are composed of a pillar 16, a cross member 17, and an end frame edge strip 12;

the cross beam 17 is fixedly connected to the upright post 16, and both ends of the upright post 16 are respectively fixed to the end frame flanges 12.

As shown in fig. 5, undercuts 13 are provided at the front and rear ends of the end frame strip 12 to compensate for radome assembly tolerances.

The end rib beam 15 is composed of a web plate, upper and lower edge strips, the upper and lower edge strips are installed on the upper and lower sides of the web plate, and the end rib beam 15 is connected with the ends of the left and right end frames 6 and the upper and lower wall plates 7 through the upper and lower edge strips.

According to the technical scheme, an inclined two-area array dome structure 2 is arranged on a machine body 3 through supporting legs 1, and the dome structure is composed of a radome 4 and a metal framework 5. The radome is used for radar array face wave-transmitting and rectification, and the metal framework is used for installing equipment such as radome, radar array face, bears aerodynamic force and inertial load that the dome structure received to satisfy the windward side and resist the bird and hit the requirement. The metal framework is composed of a left end frame 6, a right end frame 6, an upper wall plate 7, a lower wall plate 7, a cross beam 8, a mouth frame 9 and end ribs 10, in order to meet the inclined installation requirement of a radar array surface 11 and reduce extra additional bending moment of the metal framework caused by inclined installation, the left end frame and the right end frame installed on the array surface are designed into inclined installation structures, and the whole metal framework is assembled in a trapezoidal layout. Aerodynamic force and inertial load applied to the dome structure in the flying process are mainly borne by the left end frame, the right end frame, the cross beam and the mouth frame, and are finally transmitted to the supporting legs through the mouth frame and then transmitted to the fuselage structure through the supporting legs to achieve force and moment balance. The dome structure is characterized in that the front edge and the rear edge of the dome structure are provided with the end rib structures 10 which are composed of the detachable front edge 14 and the end rib beams 15, so that the bird impact resistance of the windward side of the dome structure is improved, and the replacement and maintenance convenience of a damaged structure after bird impact is taken into consideration. When the left end frame and the right end frame are designed, sinking parts 13 are arranged at the front end and the rear end of the end frame edge strip 12, and the compensation allowance of the radome assembly process is increased so as to solve the radome assembly difficulty caused by the inclined layout. Through the reasonable layout and the load distribution design of the structure, on the premise of meeting the design requirements of strength, rigidity and bird impact resistance, the additional bending moment caused by the fact that the radar array surface is not parallel to the end frame mounting surface is reduced for meeting the requirement of radar array surface inclination, and the radar array surface mounting end frame is arranged in an inclined mode. Effectively solved the not enough of the outer thing structural configuration of hanging of current aircraft dome formula can't satisfy the radar array face slope installation requirement.