Four-point mounting structure of narrow-space aircraft engine

Abstract

The invention discloses a four-point mounting structure of a narrow-space aircraft engine. Comprising an outer main installation section (1) and an inner main installation section (2) which are installed on a front fuselage frame, a transverse pulling assembly installed on a rear fuselage frame (39), and an inclined pulling assembly installed on a rear fuselage middle partition plate (40). The rear fuselage frame (39) and the rear fuselage middle partition plate (40) are located on the same cross section. The outer and inner main mounting sections (1) are respectively connected with outer and inner main mounting section joints on the engine; and the transverse and inclined pulling assemblies are respectively connected with an upper hanging joint (28) and an inclined hanging joint on the engine. The stress level of engine mounting parts can be reduced, and the comfort of a driver can be effectively improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine mounting structures, in particular to a four-point mounting structure for an aircraft engine in a narrow space. Background Art

[0002] As one of the power sources of an aircraft, the installation and fixing form of the engine is a very important part of the aircraft structure design. Due to the different installation positions, reserved spaces and engine types of the engine on the aircraft, the installation forms are also different. The engine is usually installed at three points. However, this installation method has the following disadvantages: the vibration transmitted from the engine to the fuselage structure is large, and the stress of the engine installation parts is large, which affects the comfort of the pilot. Summary of the invention

[0003] The purpose of the present invention is to provide a four-point mounting structure for a narrow-space aircraft engine, which can reduce the stress level of engine mounting parts and effectively improve the comfort of the pilot.

[0004] Technical solution. A four-point mounting structure for a narrow-space aircraft engine, comprising an outer main mounting section and an inner main mounting section mounted on a front fuselage frame, a horizontal pull assembly mounted on a rear fuselage frame, and an oblique pull assembly mounted on a rear fuselage center partition; the rear fuselage frame and the rear fuselage center partition are in the same cross section; the outer and inner main mounting sections are respectively connected to the outer and inner main mounting section joints provided on the engine, and the horizontal and oblique pull assemblies are respectively connected to the upper suspension joint and oblique suspension joint provided on the engine.

[0005] In the aforementioned four-point mounting structure of the narrow space aircraft engine, the outer main mounting section includes a left thrust pin, a movable clamp A, and an outer main mounting section support; one end of the left thrust pin with a fork ear structure A is connected to the outer main mounting section joint provided on the engine through a left bolt, and the other end is fixed to the outer main mounting section support through an annular boss A; one end of the movable clamp A with an ear piece is connected to the outer main mounting section support through a pin A and can rotate around the pin A, and the other end is locked to the outer main mounting section support groove through a movable bolt; the movable bolt is rotatably connected to the groove position of the outer main mounting section support through a pin B, and the outer main mounting section support is fixed to the front fuselage frame.

[0006] In the aforementioned four-point mounting structure of the narrow space aircraft engine, a bushing is installed at the matching position between the fork ear structure of the left thrust pin and the left bolt.

[0007] In the aforementioned four-point mounting structure of the narrow space aircraft engine, the left thrust pin is an integrated design, and a lightening recess is provided at the bottom of the cylinder connected to the outer main mounting node support. This not only reduces processing errors and facilitates disassembly and assembly, but also meets the requirements of lightweight design.

[0008] In the aforementioned four-point mounting structure of the narrow space aircraft engine, the inner main mounting section includes a right thrust pin, an eccentric bushing and an inner main mounting section support; one end of the right thrust pin with a fork ear structure is connected to the inner main mounting section joint provided on the engine via a right bolt, and the other end is sleeved with an eccentric bushing, which is connected to the inner main mounting section support via an annular boss B and is locked via a live clamp B; the right thrust pin can move axially and rotate around the axis in the eccentric bushing; the inner main mounting section support is fixed to the front fuselage frame.

[0009] In the aforementioned four-point mounting structure of the narrow space aircraft engine, the tie assembly includes a tie rod, one end of the tie rod equipped with a lifting eye is connected to the upper suspension joint on the engine, and the other end equipped with a fork ear structure B is connected to the tie rod support through a tie rod bolt; the tie rod support is fixed to the rear fuselage frame, and the lifting eye and fork ear structure B of the tie rod can both move axially along the sleeve of the tie rod; the ear hole connections at both ends of the tie rod are equipped with ball shafts A.

[0010] In the aforementioned four-point mounting structure of the narrow space aircraft engine, the reinforcing ribs at the edges of the tie rod support holes are all chamfered.

[0011] In the aforementioned four-point mounting structure of the narrow space aircraft engine, the diagonal stay assembly includes a diagonal stay rod, one end of which is connected to the diagonal suspension joint on the engine, and the other end is fixed to the flat plate support by the diagonal stay rod bolts; the ear holes of the two ear pieces are equipped with ball shafts B; the side wall of the flat plate support is fixed to the aircraft frame by the side connecting bolts, and the bottom plate is connected to the rear fuselage center partition by the bottom connecting bolts.

[0012] Beneficial effects: Compared with the three-point installation form, the present invention adopts a four-point installation, the load on the installation joint is smaller, and the vibration transmitted from the engine to the fuselage structure is smaller, which can not only reduce the stress level of the engine installation parts, but also effectively improve the comfort of the driver. The thrust pin of the outer main installation section adopts an integrated design, and is directly fixed to the support by designing an annular boss at the cylindrical end of the thrust pin, thereby reducing the number of parts and improving assembly efficiency. Unlike the thrust pin of the outer main installation section, the thrust pin of the inner main installation section does not directly contact the support of the outer main installation section, but is fixed to the main installation section support through an external bushing. The thrust pin of the inner main installation section can move and rotate around the axis along the axial direction of the eccentric bushing, thereby eliminating the thermal stress generated in the wingspan direction. Since the main installation section of the engine is designed in the form of a live bolt and a clamp, the rear suspension and the oblique suspension adopt the form of a pull rod and a support, so the assembly is simple and can be quickly disassembled and assembled. In addition, a lightening socket is designed on the main mounting section support, and the diagonal tie rod is directly connected to the flat-plate support on the middle partition by bolts, so the required assembly space is smaller and the weight is lighter.

[0013] In summary, the four-point mounting structure of an aircraft engine provided by the present invention is easy to disassemble and assemble, and the load and vibration transmitted from the engine to the fuselage mechanism are smaller, and the overall stress level of the mounting structure is lower, which can effectively improve the comfort of the pilot while taking into account the safety of the aircraft. At the same time, a lightening recess is designed on the main mounting section support, and the diagonal tie rod support adopts a flat plate support, which not only requires a smaller assembly space, but also makes the overall weight of the engine mounting structure lighter; the outer main mounting section thrust pin adopts an integrated design, which can not only reduce processing errors, but also improve assembly efficiency. In addition, both the main mounting section support and the auxiliary mounting section support are chamfered, which can effectively avoid stress concentration, thereby extending the service life of the components. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is the assembly drawing when the aircraft engine adopts the four-point installation form;

[0015] Figure 2 This is a schematic diagram of the external main installation section;

[0016] Figure 3 Sectional view of the outer main installation section

[0017] Figure 4 This is a schematic diagram of the main installation section;

[0018] Figure 5 Schematic diagram of the tie rod structure;

[0019] Figure 6 Schematic diagram of the inclined rod structure. DETAILED DESCRIPTION

[0020] Example 1. A four-point mounting structure for a narrow space aircraft engine, see Figure 1-Figure 6 , including an outer main mounting section 1 and an inner main mounting section 2 installed on the front fuselage frame, a transverse pull assembly installed on the rear fuselage frame 39, and an oblique pull assembly installed on the rear fuselage middle partition 40; the rear fuselage frame 39 and the rear fuselage middle partition 40 are in the same cross section; the outer and inner main mounting sections 1 are respectively connected to the outer and inner main mounting section joints provided on the engine, and the transverse and oblique pull assemblies are respectively connected to the upper suspension joint 28 and the oblique suspension joint provided on the engine.

[0021] The aforementioned outer main mounting section 1 comprises a left thrust pin 7, a hinged clamp A8, and an outer main mounting section support 10; one end of the left thrust pin 7 having a fork ear structure A is connected to the outer main mounting section joint provided on the engine via a left bolt 15, and the other end is fixed to the outer main mounting section support 10 via an annular boss A41, and the annular boss A41 is used to limit the axial movement of the left thrust pin 7; one end of the hinged clamp A8 having an ear piece is connected to the outer main mounting section support 10 via a pin A9, and can rotate around the pin A9, and the other end is locked at the groove of the outer main mounting section support 10 via a hinged bolt 12; the hinged bolt 12 is rotatably connected to the groove position of the outer main mounting section support 10 via a pin B11, and the outer main mounting section support 10 is fixed to the front fuselage frame.

[0022] A bushing 17 is installed at the matching position between the fork ear structure of the left thrust pin 7 and the left bolt 15 .

[0023] The aforementioned left thrust pin 7 is of integrated design, and a lightening recess 42 is provided at the bottom of the cylinder connected to the outer main mounting section support 10, which not only reduces processing errors and facilitates assembly and disassembly, but also meets the requirements of lightweight design.

[0024] The aforementioned inner main mounting section 2 comprises a right thrust pin 18, an eccentric bushing 19 and an inner main mounting section support 20; one end of the right thrust pin 18 with a fork ear structure is connected to the inner main mounting section joint provided on the engine via a right bolt, and the other end is sleeved with the eccentric bushing 19, the eccentric bushing 19 is connected to the inner main mounting section support 20 via an annular boss B43, and is locked via a live clamp B44; the right thrust pin 18 can move axially and rotate around the axis in the eccentric bushing 19; the inner main mounting section support 20 is fixed on the front fuselage frame.

[0025] The aforementioned tie rod assembly includes a tie rod, one end of which is equipped with a lifting eye 21 and is connected to the upper suspension joint 28 on the engine, and the other end of which is equipped with a fork ear structure B27 is connected to the tie rod support 25 through a tie rod bolt 23; the tie rod support 25 is fixed on the rear fuselage frame 39, and the lifting eye 21 and the fork ear structure B27 of the tie rod can both move axially along the sleeve 22 of the tie rod; ball shafts A26 are installed at the ear hole connections at both ends of the tie rod.

[0026] The reinforcing ribs at the hole edges of the aforementioned tie rod support 25 are all chamfered.

[0027] The aforementioned inclined-stayed assembly includes an inclined-stayed rod 29, one end of which is connected to the inclined suspension joint on the engine, and the other end is fixed to a flat-plate support 34 through an inclined-stayed rod bolt 33; ball shafts B32 are installed in the ear holes of the two ear holes; the side wall of the flat-plate support 34 is fixed to the aircraft frame through side connecting bolts 30, and the bottom plate is connected to the rear fuselage middle partition 40 through bottom connecting bolts 35.

[0028] The structure of the outer main installation section is as follows Figure 2 and 3 As shown, the structure of the inner main installation section is as follows Figure 4 As shown, the tie rod structure is as follows Figure 5 As shown, the inclined rod structure is as follows Figure 6 As shown. Since the installation forms of the left and right engines are exactly the same, only the installation positions are different, only the installation and removal process of the left engine is introduced. After confirming that the engine is firmly fixed on the engine installation vehicle, slowly push the engine installation vehicle under the rear fuselage of the aircraft, and lift the engine to an appropriate position. First, connect the end of the left thrust pin 7 of the left engine with a fork ear structure to the main installation joint joint on the engine, and the other end is fixed to the main installation joint support 10 through an annular boss. The left thrust pin adopts an integrated design, and a lightening groove is designed at the bottom of the cylinder connected to the support. On the basis of reducing processing errors and facilitating disassembly and assembly, it also meets the requirements of lightweight design. The side of the lug with the movable clamp 8 is connected to the main installation joint support 10 through the pin A9, and can rotate around the pin A9, and the other side is locked to the bottom of the groove of the support 10 through the movable bolt 12, the gasket 13 and the nut 14. The movable bolt 12 is connected to the support 10 through the pin 11, and the support 10 is fixed to the fuselage frame by 4 bolts. In order to reduce the friction between the left bolt 15 and the lug of the thrust pin 7, bushings 17 are installed in both lug holes of the thrust pin 7, and the nut is connected to the thrust pin 7 through a gasket 16. The installation forms of the inner main mounting section and the outer main mounting section of the left engine are basically the same. The main difference is that the thrust pin 18 of the inner main mounting section does not directly contact the inner main mounting section support 20, but is connected to the support 20 through an eccentric bushing 19 with an annular boss connected to the outer side of the thrust pin 18. The thrust pin 18 can move and rotate in the eccentric bushing 19 in the axial direction, thereby eliminating the thermal expansion phenomenon of the engine in the lateral direction.

[0029] One end of the tie rod equipped with a lifting ring 21 is connected to the upper suspension joint 28 on the engine, and the other end equipped with a fork ear structure 27 is connected to the tie rod support 25 through a tie rod bolt 23. The tie rod support 25 is fixed to the rear fuselage frame 39 by three 8mm bolts 24. In order to reduce its stress level and thus extend its service life, the reinforcing ribs on the edge of the hole of the tie rod support 25 are chamfered. The lifting ring 21 and the fork ear structure 27 can move along the axial direction of the sleeve 22, thereby achieving the purpose of changing the length of the tie rod and increasing the applicable scope of the structure. The ear hole connection at both ends of the tie rod is equipped with a ball shaft 26 to compensate for the installation error of the engine. One ear piece of the inclined tie rod 29 is connected to the inclined suspension joint on the engine, and the other ear piece is fixed to the flat support 34 by bolts 33, nuts 36, bushings 31, perforated pins 37 and gaskets 38. Ball shafts 32 are installed in the ear holes on both sides. While compensating for installation errors, the angle θ between the axis of the diagonal tie rod and the horizontal reference line of the aircraft can also be adjusted. In order to increase the wear resistance, low-temperature stability and service life of the ball shaft during rotation, the rotating parts of the ball shaft are coated with an appropriate amount of low-temperature grease. The side wall of the flat-plate support 34 is fixed to the aircraft frame by four bolts 30, and the bottom plate is connected to the rear fuselage partition by bolts 35. Compared with other types of supports, the distance d between the two engines required by the flat-plate support is smaller, the weight is lighter, and the installation is more convenient. When the engine needs to be removed, just pull out the pins of the inner and outer main mounting nodes, take out the perforated pins in the cross-tie rod and the diagonal tie rod structure, and loosen the corresponding fasteners.

Claims

1. A four-point mounting structure for a narrow space aircraft engine, characterized in that: The invention comprises an outer main installation section (1) and an inner main installation section (2) installed on a front fuselage frame, a transverse pull assembly installed on a rear fuselage frame (39), and an oblique pull assembly installed on a rear fuselage middle partition (40); the rear fuselage frame (39) and the rear fuselage middle partition (40) are in the same cross section; the outer and inner main installation sections (1) are respectively connected to the outer and inner main installation section joints provided on the engine, and the transverse and oblique pull assemblies are respectively connected to the upper suspension joint (28) and the oblique suspension joint provided on the engine.

2. The four-point mounting structure for a narrow space aircraft engine according to claim 1, characterized in that: The outer main mounting section (1) comprises a left thrust pin (7), a hinged clamp A (8), and an outer main mounting section support (10); one end of the left thrust pin (7) with a fork ear structure A is connected to the outer main mounting section joint provided on the engine via a left bolt (15), and the other end is fixed to the outer main mounting section support (10) via an annular boss A (41); one end of the hinged clamp A (8) with an ear piece is connected to the outer main mounting section support (10) via a pin A (9) and can rotate around the pin A (9), and the other end is locked to the groove of the outer main mounting section support (10) via a hinged bolt (12); the hinged bolt (12) is rotatably connected to the groove position of the outer main mounting section support (10) via a pin B (11), and the outer main mounting section support (10) is fixed to the front fuselage frame.

3. The four-point mounting structure for a narrow space aircraft engine according to claim 2, characterized in that: A bushing (17) is installed at the matching position between the fork ear structure of the left thrust pin (7) and the left bolt (15).

4. The four-point mounting structure for a narrow space aircraft engine according to claim 2, characterized in that: The left thrust pin (7) is of integrated design, and a lightening recess (42) is provided at the bottom of the cylinder connected to the outer main mounting section support (10), which not only reduces processing errors and facilitates assembly and disassembly, but also meets the requirements of lightweight design.

5. The four-point mounting structure for a narrow space aircraft engine according to claim 1, characterized in that: The inner main installation section (2) comprises a right thrust pin (18), an eccentric bushing (19) and an inner main installation section support (20); one end of the right thrust pin (18) with a fork ear structure is connected to the inner main installation section joint provided on the engine via a right bolt, and the other end is sleeved with the eccentric bushing (19); the eccentric bushing (19) is connected to the inner main installation section support (20) via an annular boss B (43) and is locked via a live clamp B (44); the right thrust pin (18) can move axially and rotate around the axis in the eccentric bushing (19); the inner main installation section support (20) is fixed on the front fuselage frame.

6. The four-point mounting structure for a narrow space aircraft engine according to claim 1, characterized in that: The tie rod assembly comprises a tie rod, one end of which is provided with a lifting ring (21) and connected to an upper suspension joint (28) provided on the engine, and the other end of which is provided with a fork ear structure B (27) and connected to a tie rod support (25) via a tie rod bolt (23); the tie rod support (25) is fixed to a rear fuselage frame (39), the lifting ring (21) and the fork ear structure B (27) of the tie rod can both move axially along a sleeve (22) of the tie rod; and ball shafts A (26) are provided at the ear hole connection points at both ends of the tie rod.

7. The four-point mounting structure for a narrow space aircraft engine according to claim 6, characterized in that: The reinforcing ribs at the hole edges of the tie rod support (25) are all chamfered.

8. The four-point mounting structure for a narrow space aircraft engine according to claim 1, characterized in that: The inclined-stayed assembly comprises an inclined-stayed rod (29), one end ear piece of the inclined-stayed rod (29) is connected to an inclined suspension joint provided on the engine, and the other end ear piece is fixed to a flat-plate support (34) through an inclined-stayed rod bolt (33); a ball shaft B (32) is installed in the ear holes of the two ear pieces; the side wall of the flat-plate support (34) is fixed to the aircraft frame through side connecting bolts (30), and the bottom plate is connected to a rear fuselage middle partition (40) through bottom connecting bolts (35).

Images