Airplane power supply pod and assembly method

Abstract

The invention discloses an aircraft power supply pod and an assembly method, a pod main body frame is composed of a plurality of detachable upper and lower half frame units and a connecting bracket, a generator is connected with the upper half frame through a mounting rack with a waist-shaped hole, and the position can be flexibly adjusted; the turboshaft engine is fixed to the lower half frame through a supporting assembly composed of the main supporting piece and the auxiliary supporting piece, the main supporting piece comprises a hinge structure and an adjusting gasket, the auxiliary supporting piece is fixed in an inserted connection mode, and accurate installation is ensured. The airplane connecting frame is matched with the pod clamping groove through the inverted-T-shaped connecting plate, so that the airplane connecting frame is detachably connected with the airplane body. During assembly, the connecting support and the engine are sequentially installed, the upper half frame and the lower half frame are combined, and then the skin, the aircraft connecting frame, the lateral support and the generator are sequentially installed. The problem that the generator and the engine cannot be coaxially arranged is solved, normal operation of equipment is guaranteed through the simple and stable structural design and the scientific assembly process, the influence of the pod weight on the flight performance of an aircraft is reduced, and the application prospect is wide.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft equipment, and particularly relates to an aircraft power supply pod and an assembly method thereof. Background Art

[0002] With the rapid development of aviation technology, the functional requirements of aircraft have become increasingly diversified and complex. As an important device that can provide additional external power for aircraft, the aircraft power supply pod plays a crucial role in ensuring the normal operation of the aircraft avionics system and airborne equipment, as well as meeting the power consumption requirements of special missions. It is usually suspended at the wing or belly position of the aircraft and has become an important component for improving aircraft performance and expanding aircraft functions due to its flexible mounting and strong versatility.

[0003] Currently, the main structure of the aircraft power supply pod on the market consists of a generator and an engine used to drive the generator. Among them, the turboshaft engine has become one of the common engine forms for driving the generator due to its advantages such as high power density and strong reliability. In the traditional design concept, in order to achieve efficient power transmission, the generator and the engine often adopt a coaxial arrangement. This arrangement is based on the principle that the rotation of the turboshaft engine rotor drives the engine output shaft, which in turn directly drives the generator to work, and can ensure the stability and efficiency of power transmission under ideal conditions, reducing energy loss.

[0004] However, in actual engineering application scenarios, the coaxial arrangement of the engine and the generator faces many insurmountable challenges. On the one hand, the internal space of the aircraft power supply pod is limited, and many auxiliary devices need to be installed, such as heat dissipation devices, electrical control systems, fuel supply systems, etc. When these auxiliary devices are arranged, they will inevitably occupy the space between the engine and the generator, resulting in the inability to install them according to the requirements of the coaxial arrangement. On the other hand, due to the characteristics of its own structure design, the output shaft and the rotor of some turboshaft engines are not on the same axis. If a coaxial arrangement scheme is forced, not only does it require large-scale structural modification of the engine, increasing the design and manufacturing costs, but it may also reduce the reliability and stability of the engine.

[0005] To solve the above problems, attempts have been made in the prior art to achieve power transmission by adding a transmission mechanism, but this method will introduce additional mechanical losses and vibration problems, and at the same time, it will also make the pod structure more complex, increasing the maintenance difficulty and cost. In addition, some studies have tried to optimize the layout of the pod space, but in actual applications, it is still difficult to fully meet the installation requirements of the engine and the generator under the influence of different external factors, and it often leads to an increase in the weight of the pod, affecting the fuel economy and flight performance of the aircraft.

[0006] Therefore, how to reasonably arrange the engine rotor and the generator in the limited space of the aircraft power supply pod when they are not coaxial, ensure the normal operation of the equipment, and at the same time ensure that the weight of the pod will not have an adverse impact on the overall flight of the aircraft has become a key problem to be solved urgently in the current aircraft power supply pod technology field. Summary of the Invention

[0007] The purpose of the present invention is to provide an aircraft power supply pod and an assembly method, aiming to solve the installation problem under the condition that the generator and the engine cannot be coaxially arranged, ensure the normal connection and operation of the engine and the generator in the pod, and at the same time make the whole pod structure simple, stable and light in weight.

[0008] To achieve the above purpose, the present invention adopts the following technical means:

[0009] An aircraft power supply pod includes a skin, a generator, a coupling, an aircraft connection frame, a main body frame, a skin support, and an engine. The generator, the coupling, and the engine are arranged in the main body frame. The generator is connected to the engine through the coupling. The aircraft connection frame is fixedly connected to the top of the main body frame and is detachably connected to the aircraft body. The skin support is externally connected to the main body frame through a support member, and the skin is externally connected to the skin support;

[0010] The main body frame includes a plurality of mounting frame units and a plurality of connecting brackets. The mounting frame units are arranged in sequence along the axial direction of the generator, and the connecting brackets are arranged between adjacent mounting frame units and are connected;

[0011] The generator is connected to the mounting frame unit through a generator mounting frame, and the engine is connected to the mounting frame unit adjacent to the generator through an engine support assembly;

[0012] The aircraft connection frame includes an aircraft connection plate and a pod connection frame. The pod connection frame is connected to the mounting frame unit. The cross section of the aircraft connection plate is "convex", and a card slot corresponding to the aircraft connection plate is provided on the pod connection frame. The protruding part of the aircraft connection plate is embedded in the card slot and fixedly connected to the pod connection frame.

[0013] A further scheme of the present invention is that the generator mounting frame includes a fixing plate and a generator mounting seat. The generator mounting seat is fixedly connected to the fixing plate. The fixing plate is connected to a group of the mounting frame units. Bolt connection holes for connecting the fixing plate are provided on the mounting frame unit connected to the fixing plate, and waist-shaped holes corresponding to the positions of the bolt connection holes are provided on the fixing plate. The relative position of the fixing plate and the mounting frame unit is adjusted through the waist-shaped holes to make the output shafts of the generator, the coupling, and the engine on the same axis.

[0014] A further solution of the present invention is that each of the mounting frame units is square as a whole. The mounting frame unit includes an upper half-frame and a lower half-frame, which are detachably connected. The aircraft connecting frame is fixedly connected to the top of the upper half-frame, and the connecting brackets are arranged between the adjacent lower half-frames and connected.

[0015] A further solution of the present invention is that the generator is connected to the upper half-frame of the corresponding mounting frame unit through a generator mounting frame, and the engine is connected to the lower half-frame of the corresponding mounting frame unit through an engine support assembly.

[0016] A further solution of the present invention is that the engine support assembly includes a main support member and a sub-support member, and the main support member and the sub-support member are respectively installed on different mounting frame units;

[0017] The main support member includes a main support plate, a support arm, a first adjustment gasket, and a first support column. The main support plate is hinged to the support arm. The first support column is fixedly connected to the lower half-frame of the corresponding mounting frame unit and supports the support arm upward. The first adjustment gasket is arranged between the support arm and the first support column. The main support plate is provided with a mounting through-hole and a positioning convex column. The surface of the engine is provided with a positioning hole corresponding to the positioning convex column and a bolt hole corresponding to the mounting through-hole;

[0018] The sub-support member includes a sub-support plate, a second adjustment gasket, and a second support column. The second support column is fixedly connected to the lower half-frame of the corresponding mounting frame unit and supports the sub-support plate upward. The second adjustment gasket is arranged between the sub-support plate and the second support column. The sub-support plate is provided with a connection plug for connecting with the engine, and the engine is provided with a plug-in part corresponding to the connection plug. The connection plug and the plug-in part are fixedly connected by bolts.

[0019] A further solution of the present invention is that the support arm and the sub-support plate are respectively provided with mounting holes. The first adjustment gasket and the second adjustment gasket are respectively provided with through-holes corresponding to the corresponding mounting holes. The first support column and the second support column are respectively provided with bolt counterbores corresponding to the corresponding through-holes. Bolts pass through the corresponding mounting holes, through-holes and bolt counterbores to connect, so as to fix the support arm and the first support column and the sub-support plate and the second support column.

[0020] A further solution of the present invention is that a skin support frame is provided at the top of the mounting frame unit, and the skin support frame is connected to the skin support bracket.

[0021] A further solution of the present invention is that the mounting frame unit is further connected to the aircraft connecting frame through a lateral support. The lateral support is a frame structure and is in the shape of a right triangle.

[0022] A further solution of the present invention is that the engine is a turboshaft engine.

[0023] An assembly method for an aircraft pod includes the following steps:

[0024] S1. Install a connecting bracket between the lower frames of adjacent mounting frame units;

[0025] S2. The engine is fixedly connected to the lower frame of the corresponding mounting frame unit through an engine support assembly; [[ID=(12]]

[0026] S3. The upper frame and the lower frame of the mounting frame unit are connected to form a main frame;

[0027] S4. Install a skin on the skin support frame;

[0028] S5. Connect the aircraft connecting frame to the mounting frame unit of the main frame;

[0029] S6. The mounting frame unit is further connected to the aircraft connecting frame through a lateral support;

[0030] S7. Install the generator on the upper frame of the corresponding mounting frame unit through a generator mounting bracket, and connect the output shaft of the engine to the input shaft of the generator through a coupling;

[0031] S8. Connect to the aircraft through the aircraft connecting frame; [[ID=3(0]]

[0032] S9. Install skin brackets on the periphery of the main frame through supports, and each mounting frame unit is externally connected to a skin bracket;

[0033] S10. Lay the skin on the skin brackets.

[0034] Advantages of the present invention:

[0035] 1. Solve the problem of coaxial arrangement: The aircraft power supply pod of the present invention solves the installation problem under the condition that the generator and the engine cannot be coaxially arranged through a unique main frame structure design and the ingenious setting of the generator mounting bracket and the engine support assembly. Traditional coaxial arrangement is easily interfered by external factors, while in the present invention, even when the engine and the generator cannot be coaxially arranged due to factors such as too many auxiliary devices and the non-coaxiality between the output shaft of the engine and the rotor, it can ensure the normal connection and operation of the two in the pod, greatly expanding the application scenarios of the pod and meeting the use requirements under complex working conditions.

[0036] 2. Structurally stable and lightweight: The main frame adopts a combination of multiple mounting frame units and connecting brackets. Together with the further connection of the lateral supports and the aircraft connection frame, a solid mechanical structure is constructed, making the entire pod highly stable during operation and capable of withstanding vibrations and impacts in various flight environments. At the same time, weight factors were fully considered during the design process. By reasonably planning the materials, shapes, and connection methods of each component, unnecessary weight increase caused by solving coaxial problems was avoided, ensuring that the pod is lightweight and will not have a significant impact on the overall flight performance and fuel consumption of the aircraft, achieving a good balance between structural strength and lightweight.

[0037] 3. Easy to assemble and adjust: The assembly method steps are clear, and the installation sequence of each component is carefully designed to meet the actual operation requirements of the project. During the assembly process, the slotted holes on the generator mounting frame and the adjusting shims in the engine support assembly play a key role. Through the slotted holes, the relative position of the fixing plate and the mounting frame unit can be flexibly adjusted, and the installation height and attitude of the engine can be finely adjusted using the adjusting shims, thus conveniently and accurately calibrating the positions of the generator and the engine, ensuring their connection accuracy, reducing the assembly difficulty, improving the assembly efficiency and product quality, and reducing the subsequent debugging and maintenance costs caused by installation errors. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 is a structural schematic diagram of the present invention;

[0039] Figure 2 is an internal structural schematic diagram of the present invention after removing the skin;

[0040] Figure 3 is an internal structural schematic diagram of the present invention after removing the skin and the skin brackets;

[0041] Figure 4 is a connection schematic diagram of the skin support frame and the main frame of the present invention;

[0042] Figure 5 is a structural schematic diagram of the generator mounting frame of the present invention;

[0043] Figure 6 is a structural schematic diagram of the aircraft connection frame of the present invention;

[0044] Figure 7 is a structural schematic diagram of the main frame of the present invention;

[0045] Figure 8 is a structural schematic diagram of the mounting frame unit of the present invention;

[0046] Figure 9 is a connection schematic diagram of the skin bracket and the support member of the present invention;

[0047] Figure 10 Structural schematic diagram of the auxiliary support member of the present invention;

[0048] Figure 11 Structural schematic diagram of the main support member of the present invention;

[0049] Reference numerals:

[0050] Skin 1, generator 2, generator mounting bracket 3, coupling 4, aircraft connection bracket 5, skin support frame 6, main body frame 7, skin bracket 8, support member 9, lateral support 10, engine 11, auxiliary support member 12, main support member 13, fixing plate 301, generator mounting seat 302, waist-shaped hole 303, aircraft connection plate 501, nacelle connection bracket 502, card slot 503, mounting bracket unit 701, bolt connection hole 702, connection bracket 703, auxiliary support plate 1201, second adjusting gasket 1202, second support column 1203, main support plate 1301, support arm 1302, first adjusting gasket 1303, first support column 1304, upper half frame 7011, lower half frame 7012. Detailed implementation manners

[0051] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of them. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0052] Embodiment

[0053] As Figures 1 to 11 shown, an aircraft power supply nacelle includes a skin 1, a generator 2, a coupling 4, an aircraft connection bracket 5, a main body frame 7, a skin bracket 8, and an engine 11. The generator 2, the coupling 4, and the engine 11 are arranged inside the main body frame 7. The generator 2 is connected to the engine 11 through the coupling 4. The aircraft connection bracket 5 is fixedly connected to the top of the main body frame 7 and is detachably connected to the aircraft body. The skin bracket 8 is externally connected to the main body frame 7 through a support member 9, and the skin 1 is externally connected to the skin bracket 8;

[0054] The main body frame 7 includes a plurality of mounting bracket units 701 and a plurality of connection brackets 703. The mounting bracket units 701 are arranged in sequence along the axial direction of the generator 2, and the connection brackets 703 are arranged between adjacent mounting bracket units 701 and are connected;

[0055] The generator 2 is connected to the mounting bracket unit 701 through a generator mounting bracket 3, and the engine 11 is connected to the mounting bracket unit 701 adjacent to the generator 2 through an engine support assembly;

[0056] The aircraft connecting frame 5 includes an aircraft connecting plate 501 and a pod connecting frame 502. The pod connecting frame 502 is connected to the mounting frame unit 701. The cross-section of the aircraft connecting plate 501 is in a "convex" shape. A card slot 503 corresponding to the aircraft connecting plate 501 is provided on the pod connecting frame 502. The protruding part of the aircraft connecting plate 501 is embedded in the card slot 503 and fixedly connected to the pod connecting frame 502.

[0057] The generator mounting frame 3 includes a fixing plate 301 and a generator mounting seat 302. The generator mounting seat 302 is fixedly connected to the fixing plate 301. The fixing plate 301 is connected to a group of mounting frame units 701. Bolt connection holes 702 for connecting to the fixing plate 301 are provided on the mounting frame unit 701 connected to the fixing plate 301. A waist-shaped hole 303 corresponding to the position of the bolt connection hole 702 is provided on the fixing plate 301. By adjusting the relative position of the fixing plate 301 and the mounting frame unit 701 through the waist-shaped hole 303, the coaxiality of the generator 2, the coupling 4, and the output shaft of the engine 11 is satisfied to be on the same axis.

[0058] The advantages of the above settings are as follows:

[0059] Achieving precise coaxial adjustment: The design of the waist-shaped hole 303 enables the fixing plate 301 to move flexibly within a certain range and can be finely adjusted along the long axis direction of the waist-shaped hole 303. This characteristic is crucial because in the actual assembly process, even if the manufacturing precision of each component is very high, there will inevitably be small errors. The coaxiality of the engine 11 and the generator 2 has a direct impact on the power transmission efficiency and the service life of the equipment. By adjusting the relative position of the fixing plate 301 and the mounting frame unit 701 through the waist-shaped hole 303, these manufacturing and assembly errors can be precisely compensated, ensuring that the input shafts of the generator 2, the coupling 4, and the engine 11 are on the same axis, improving the power transmission efficiency, and extending the service life of the equipment.

[0060] Simplifying the assembly process: In the traditional fixed-hole connection method, extremely high precision is required to align the hole positions during assembly, which often takes a lot of time for measurement and adjustment. However, the existence of the waist-shaped hole 303 in the present invention greatly reduces the assembly difficulty. The assembly personnel do not need to precisely align the positions of each component at the initial stage. After rough positioning, fine adjustment can be carried out through the waist-shaped hole 303. This method not only shortens the assembly time, but also reduces the requirements for the skill level of the assembly personnel, improves the assembly efficiency, and reduces the labor cost.

[0061] Each mounting frame unit 701 is integrally square. The mounting frame unit 701 includes an upper half frame 7011 and a lower half frame 7012. The upper half frame 7011 and the lower half frame 7012 are detachably connected. The aircraft connecting frame 5 is fixedly connected to the top of the upper half frame 7011. The connecting bracket 703 is arranged between adjacent lower half frames 7012 and connected.

[0062] The advantages of the above settings are as follows:

[0063] The modular design facilitates assembly and maintenance: The mounting frame unit 701 is designed as a detachable upper half frame 7011 and a lower half frame 7012, forming a modular structure. This design enables independent operations on the lower half frame 7012 and the upper half frame 7011 respectively during the assembly process. For example, when installing the engine 11, the engine 11 can be fixedly connected to the lower half frame 7012 through the engine support assembly first, and then the upper half frame 7011 is connected to the lower half frame 7012. This makes it convenient to perform complex installation operations in a relatively open space, improving the assembly efficiency. During maintenance and repair, if it is necessary to inspect or replace the equipment inside the pod, simply disassemble the connection between the upper half frame 7011 and the lower half frame 7012, and the internal equipment can be easily inspected, greatly reducing the maintenance difficulty and time cost.

[0064] Optimize the force distribution of the structure: The aircraft connecting frame 5 is fixedly connected to the top of the upper half frame 7011, and the connecting bracket 703 is arranged between adjacent lower half frames 7012. This layout makes the force path of the entire pod more reasonable. When the pod is suspended on the aircraft, the load is transmitted upward through the lower half frame 7012 to the upper half frame 7011, and then to the top connecting frame 5. This structural design effectively avoids stress concentration, improves the structural strength and stability of the pod, and can better withstand various vibrations and impacts during flight.

[0065] Meet the installation requirements of equipment: The generator 2 is connected to the upper half frame 7011 of the corresponding mounting frame unit 701 through the generator mounting frame 3, and the engine 11 is connected to the lower half frame 7012 of the corresponding mounting frame unit 701 through the engine support assembly. The detachable design of the upper half frame 7011 and the lower half frame 7012 provides convenience for the installation of the generator 2 and the engine 11. When installing the generator 2 and the engine 11, according to their sizes, weights, and connection requirements, the upper half frame 7011 and the lower half frame 7012 can be accurately positioned and adjusted respectively to ensure the accurate relative position of the two, so as to ensure that the generator 2, the coupling 4, and the input shaft of the engine 11 are on the same axis, improving the power transmission efficiency.

[0066] The generator 2 is connected to the upper half frame 7011 of the corresponding mounting frame unit 701 through the generator mounting frame 3, and the engine 11 is connected to the lower half frame 7012 of the corresponding mounting frame unit 701 through the engine support assembly.

[0067] The advantages of the above settings are as follows:

[0068] Hierarchical layout: The generator 2 is installed on the upper half frame 7011, and the engine 11 is installed on the lower half frame 7012, forming a spatial structure with upper and lower layers. This layout makes full use of the space in the height direction of the nacelle, avoiding the increase in volume caused by the horizontal stacking of equipment, and is especially suitable for the compactness requirements of aircraft external nacelles.

[0069] Modular maintenance: The detachable connection between the upper half frame 7011 and the lower half frame 7012 allows the generator 2 or the engine 11 to be disassembled separately without affecting other components. For example, when maintaining the generator, only the connection of the upper half frame 7011 needs to be loosened, without touching the engine support structure below.

[0070] Precise positioning and adjustment: The waist-shaped holes 303 of the generator mounting bracket 3 and the adjustment shims 1303 and 1202 of the engine support assembly can be operated independently. When coaxiality adjustment is required, the upper half frame 7011 and the lower half frame 7012 can be finely adjusted separately to avoid mutual interference and improve the assembly accuracy.

[0071] Enhanced structural stability and vibration isolation

[0072] Rigid support optimization: The upper half frame 7011 is directly connected to the aircraft body through the aircraft connection bracket 5 to provide a stable support for the generator 2; the lower half frame 7012 forms a continuous frame through the connection bracket 703 to disperse the vibration during the operation of the engine 11. This "tight upper and connected lower" structural design effectively reduces the impact of equipment vibration on the overall nacelle.

[0073] Vibration isolation: The articulated structures in the engine support assembly, such as the main support plate 1301, the support arm 1302, and the adjustment shims 1303 and 1202, can absorb part of the vibration energy, preventing it from being directly transmitted to the generator 2, extending the equipment life and reducing noise.

[0074] The engine support assembly includes a main support member 13 and a secondary support member 12, and the main support member 13 and the secondary support member 12 are respectively installed on different mounting frame units 701;

[0075] The main support member 13 includes a main support plate 1301, a support arm 1302, a first adjustment shim 1303, and a first support column 1304. The main support plate 1301 is hinged to the support arm 1302. The first support column 1304 is fixedly connected to the lower half frame 7012 of the corresponding mounting frame unit 701 and supports the support arm 1302 upward. The first adjustment shim 1303 is arranged between the support arm 1302 and the first support column 1304. The main support plate 1301 is provided with mounting through holes and positioning convex columns, and the surface of the engine 11 is provided with positioning holes corresponding to the positioning convex columns and bolt holes corresponding to the mounting through holes;

[0076] The secondary support member 12 includes a secondary support plate 1201, a second adjusting gasket 1202, and a second support column 1203. The second support column 1203 is fixedly connected to the lower half frame 7012 of the corresponding mounting frame unit 701 to support and connect the secondary support plate 1201 upward. The second adjusting gasket 1202 is arranged between the secondary support plate 1201 and the second support column 1203. A connection plug for connecting to the engine 11 is provided on the secondary support plate 1201, and a plug-in portion corresponding to the connection plug is provided on the engine 11. The connection plug and the plug-in portion are fixedly connected by bolts.

[0077] The advantages of the above settings are as follows:

[0078] Three-dimensional precise adjustment ability

[0079] Multi-degree-of-freedom adjustment: The articulated structure of the main support member 13 allows the engine 11 to have a certain degree of rotational freedom on the horizontal plane. Combined with the selection of the thickness of the first adjusting gasket 1303, fine adjustment in the height direction of the engine can be achieved; the second adjusting gasket 1202 of the secondary support member 12 further compensates for the installation height difference. This combined design can accurately calibrate the position of the engine to ensure the coaxiality of its output shaft and the input shaft of the generator 2.

[0080] The cooperation of the positioning convex column and the positioning hole: The positioning convex column on the main support plate 1301 and the positioning hole on the surface of the engine 11 form precise positioning, preventing offset during the installation process and improving the assembly efficiency and accuracy.

[0081] Modular installation and maintenance

[0082] Step-by-step assembly: The main support member 13 and the secondary support member 12 are respectively installed on different mounting frame units 701 and can be pre-assembled independently. For example, first fix the main support member 13 to the corresponding lower half frame 7012, then quickly dock the engine 11 through the connection plug 1201 of the secondary support member 12, and finally tighten with bolts, simplifying the assembly process.

[0083] Quick replacement: When the engine needs to be repaired or replaced, only the bolts connecting the connection plug 1201 and the plug-in portion, and the connection bolts between the main support plate 1301 and the engine need to be removed, then the engine can be lifted out as a whole without disassembling the entire support structure, greatly shortening the maintenance time.

[0084] Load dispersion and structural strengthening

[0085] Double-point support layout: The main support member 13 and the secondary support member 12 act on different positions of the engine 11 respectively to form a stable double-point support structure, effectively dispersing the weight of the engine and the dynamic load generated during operation. This layout avoids stress concentration that may be caused by single-point support and improves the reliability of the nacelle structure.

[0086] The support arm 1302 and the auxiliary support plate 1201 are respectively provided with mounting holes. The first adjustment gasket 1303 and the second adjustment gasket 1202 are respectively provided with through holes corresponding to the corresponding mounting holes. The first support column 1304 and the second support column 1203 are respectively provided with bolt counterbores corresponding to the corresponding through holes. Bolts pass through the corresponding mounting holes, through holes and are connected to the bolt counterbores to realize the fixation of the support arm 1302 and the first support column 1304, and the auxiliary support plate 1201 and the second support column 1203.

[0087] The advantages of the above settings are as follows:

[0088] Ensure reliable fixation and structural stability: Bolts pass through the mounting holes on the support arm 1302 and the auxiliary support plate 1201, as well as the through holes on the first adjustment gasket 1303 and the second adjustment gasket 1202, and finally are connected to the bolt counterbores on the first support column 1304 and the second support column 1203. This connection method can provide strong fastening force. During the flight of the aircraft, under the action of complex loads such as vibration and impact generated by the operation of the engine 11, the rigid structure formed by the bolt connection can effectively prevent relative displacement between the support arm 1302, the auxiliary support plate 1201 and the support column, ensure the overall structural stability of the engine support assembly, ensure the stable installation of the engine 11, and avoid equipment failures and safety hazards caused by loosening.

[0089] Facilitate installation and adjustment: The corresponding design of the mounting holes, through holes and bolt counterbores makes the positioning and connection operations of the components more convenient during the assembly process. Assembly personnel can quickly align the support arm 1302, the auxiliary support plate 1201, the adjustment gasket and the support column, and fix them by passing bolts through the hole positions of each component in turn. At the same time, the setting of the first adjustment gasket 1303 and the second adjustment gasket 1202. If it is found that the position of the engine 11 needs to be finely adjusted during the installation process, the height and position of the support arm 1302 and the auxiliary support plate 1201 can be flexibly adjusted by replacing adjustment gaskets of different thicknesses and using the existing hole connection structure, without re-designing or modifying the components, greatly improving the installation efficiency and assembly accuracy.

[0090] Facilitate maintenance and replacement: When the engine 11 or the support assembly fails and needs to be maintained or replaced, only need to unscrew the bolts to separate the support arm 1302 and the first support column 1304, and the auxiliary support plate 1201 and the second support column 1203. Compared with other complex connection methods, this bolt-based connection and disassembly process is simple and fast, which is convenient for technicians to check, repair or replace individual components, reducing the maintenance difficulty and maintenance time cost. In addition, due to the standardized hole position design of each component, the new components after replacement can also be quickly and accurately installed in place through bolt connection, ensuring the equipment performance after maintenance.

[0091] Improve structural compactness and space utilization: The design of the bolt counterbore allows the bolt head to sink into the support column, avoiding the protrusion of the bolt head and occupying extra space, ensuring the compactness of the overall structure of the support assembly. In the limited space of the aircraft power supply pod, this design can rationally utilize the space, avoid interference with other components, and is also conducive to the installation of external structures such as the skin 1, making the overall structure layout of the pod more regular, and improving the space utilization rate on the premise of ensuring the realization of functions.

[0092] The top of the mounting frame unit 701 is connected to the skin support frame 6, the skin support frame 6 is connected to the skin 1, and the skin support frame 6 corresponds to the skin support bracket 8.

[0093] As the basic support, the mounting frame unit 701 is connected to the skin support frame 6 through the top, and can evenly transfer the external load to the overall structure, avoiding local stress concentration on the skin 1, which may cause deformation or damage.

[0094] The skin support frame 6 and the skin support bracket 8 are correspondingly arranged to form a "frame - bracket" linkage system, enhancing the overall rigidity of the structure, reducing displacement or deformation caused by external forces, and ensuring that the skin maintains a stable shape under complex working conditions.

[0095] Relying on the corresponding structure of the support frame 6 and the support bracket 8 for the installation of the skin 1 facilitates the adoption of a standardized assembly process, improves production efficiency, ensures the matching accuracy between different components, and reduces the debugging difficulty.

[0096] The mounting frame unit 701 is further connected to the aircraft connecting frame 5 through the lateral support 10. The lateral support 10 is a frame structure in the shape of a right triangle.

[0097] The advantages of the above settings are as follows:

[0098] Enhance structural stability and anti - deformation ability: The right - triangle frame structure has natural geometric stability, and its unique mechanical properties can quickly disperse the external forces received. During the flight of the aircraft, the power supply pod will be subjected to lateral forces caused by air - flow disturbances, flight attitude changes, etc. The lateral support 10 transfers these forces along the three sides of the triangle to the mounting frame unit 701 and the aircraft connecting frame 5, effectively avoiding local stress concentration, greatly enhancing the overall stability of the pod structure, preventing the pod from undergoing lateral deformation or shaking, and ensuring the normal operation of internal equipment such as the generator 2 and the engine 11.

[0099] Optimize the force distribution: The lateral support 10 tightly connects the mounting frame unit 701 to the aircraft connecting frame 5, forming a stable force system. When the pod bears an external load, the lateral support 10 can not only share the force of the mounting frame unit 701, but also directly transfer part of the load to the aircraft connecting frame 5, and then be transferred to the aircraft body by the aircraft connecting frame 5. This multi-path force transfer method can disperse the load more evenly compared to a single connection structure, reduce the force intensity on each component, and extend the service life of the pod structure.

[0100] Improve the anti-vibration performance: During the operation of the engine 11 and the flight of the aircraft, vibration is inevitable. The frame structure of the lateral support 10 can jointly form a damping system with the mounting frame unit 701 and the aircraft connecting frame 5 to absorb and consume vibration energy. Its rigid triangular structure restricts the relative displacement between components, reduces the risk of loosening caused by vibration, reduces the impact of vibration on the precision equipment inside the pod, and improves the reliability of equipment operation.

[0101] The engine 11 is a turboshaft engine.

[0102] The advantages of the above settings are as follows:

[0103] High power density and power output stability: The turboshaft engine is a gas turbine engine characterized by turbine shaft power output. Its core advantage lies in high power density - the power output per unit weight is significantly higher than that of piston engines. At the same time, the turboshaft engine adopts a continuous combustion gas turbine drive method, with stable power output and low vibration frequency. Compared with the periodic explosive work of piston engines, it is more conducive to the generator 2 to maintain a stable speed and improve the quality of electric energy output.

[0104] Compact structure adapts to the space limitation of the pod: The core components of the turboshaft engine, such as the rotor, combustion chamber, and turbine, adopt a coaxial integrated design, with a compact overall structure and a short axial length.

[0105] High reliability and long service life cycle: The gas turbine system of the turboshaft engine adopts a mature aviation-grade design, and key components have undergone strict high-temperature, high-pressure, and fatigue tests, and can work stably in complex flight environments.

[0106] Fuel economy and environmental adaptability: The turboshaft engine uses aviation kerosene as fuel, which is compatible with the fuel system of the aircraft body, and there is no need to set up an additional independent fuel supply module, simplifying the pod design. In addition, the turboshaft engine has strong adaptability to changes in environmental temperature and air pressure, meeting the flight requirements under different climate conditions.

[0107] An assembly method for an aircraft pod in this embodiment includes the following steps:

[0108] S1. Install the connecting bracket 703 between the lower frames 7012 of adjacent mounting frame units 701;

[0109] S2. The engine 11 is fixedly connected to the lower frame 7012 of the corresponding mounting frame unit 701 through the engine support assembly;

[0110] S3. The upper frame 7011 and the lower frame 7012 of the mounting frame unit 701 are connected to form the main frame 7;

[0111] S4. Install the skin 1 on the skin support frame 6;

[0112] S5. Connect the aircraft connecting bracket 5 to the mounting frame unit 701 of the main frame 7;

[0113] S6. The mounting frame unit 701 is further connected to the aircraft connecting bracket 5 through the lateral support 10;

[0114] S7. Install the generator 2 on the upper frame 7011 of the corresponding mounting frame unit 701 through the generator mounting bracket 3, and the output shaft of the engine 2 is connected to the input shaft of the generator 11 through the coupling 4;

[0115] S8. Connect to the aircraft through the aircraft connecting bracket 5;

[0116] S9. Install the skin support brackets 8 around the main frame 7 through the support members 9, and each mounting frame unit 701 is externally connected to a skin support bracket 8;

[0117] S10. Lay the skin 1 on the skin support brackets 8.

[0118] Working principle

[0119] When the aircraft power supply pod is operating, the turboshaft engine 11 starts first as the power core. The rotor inside the engine 11 rotates at a high speed, generates power and transmits it outward through its output shaft. The engine 11 is firmly installed in the main body frame 7 through the engine support assembly. The main support member 13 includes a main support plate 1301, a support arm 1302, a first adjusting gasket 1303, and a first support column 1304. The main support plate 1301 is hinged to the support arm 1302. The first support column 1304 is fixedly connected to the lower half frame 7012 of the corresponding mounting frame unit 701 and supports and connects the support arm 1302 upward. The first adjusting gasket 1303 is arranged between the support arm 1302 and the first support column 1304 and can finely adjust the installation attitude of the engine 11. The auxiliary support member 12 includes an auxiliary support plate 1201, a second adjusting gasket 1202, and a second support column 1203. The second support column 1203 is fixedly connected to the lower half frame 7012 of the corresponding mounting frame unit 701 and supports and connects the auxiliary support plate 1201 upward. The second adjusting gasket 1202 is arranged between the auxiliary support plate 1201 and the second support column 1203 to further ensure the stability and accuracy of the installation of the engine 11.

[0120] The power output by the engine 11 is transmitted to the generator 2 via the coupling 4. The generator 2 is connected to the upper half frame 7011 of the mounting frame unit 701 through the generator mounting frame 3. The fixing plate 301 of the generator mounting frame 3 is provided with a waist-shaped hole 303, which cooperates with the bolt connection hole 702 on the mounting frame unit 701, and can flexibly adjust the position of the generator 2 to ensure that the generator 2, the coupling 4, and the input shaft of the engine 11 are in proper coaxiality, and ensure that the power can be transmitted efficiently and stably.

[0121] After the power is transmitted to the generator 2, based on the principle of electromagnetic induction, the generator 2 converts the input mechanical energy into electrical energy. The generated electrical energy is transmitted to the aircraft body through wires. The aircraft connecting frame 5 includes an aircraft connecting plate 501 and a pod connecting frame 502. The cross section of the aircraft connecting plate 501 is in a "convex" shape, and its protruding part is embedded in the card slot 503 of the pod connecting frame 502 and fixedly connected, realizing a reliable connection between the power supply pod and the aircraft body, thereby providing an additional external power supply for the aircraft to meet the power consumption requirements of various electronic devices during flight, such as operation and charging.

[0122] During the whole process, the skin 1 is externally connected to the main body frame 7 through the skin bracket 8 and the support member 9 to form a closed structure, protecting the internal core components such as the engine 11 and the generator 2 from external environmental interference. At the same time, the mounting frame unit 701 is further connected to the aircraft connecting frame 5 through the lateral support 10 to enhance the stability of the overall structure of the pod and ensure that the aircraft power supply pod can work safely and stably.

[0123] In the modification project of a certain model of medium-range airliner, it is necessary to equip it with an additional power supply pod to meet the power consumption requirements of the newly added avionics equipment. The aircraft power supply pod of the present invention is selected for assembly.

[0124] During the assembly process, the operation is carried out strictly in accordance with the assembly method. First, install the connecting bracket 703 between the lower half frames 7012 of the adjacent mounting frame units 701. The connecting bracket 703 is made of high-strength lightweight alloy material to ensure the preliminary stability of the main frame 7. Then, fix the turboshaft engine 11 to the lower half frame 7012 of the corresponding mounting frame unit 701 through the engine support assembly. Among them, the main support plate 1301 of the main support member 13 is connected to the support arm 1302 through a high-precision hinge structure. The first support column 1304 is fixed to the lower half frame 7012 by welding. Place a first adjustment gasket 1303 with a suitable thickness between the support arm 1302 and the first support column 1304. By measurement and calculation, adjust the installation height and attitude of the engine 11 to make it reach the optimal operating position; the second support column 1203 of the auxiliary support member 12 is also welded and fixed to the lower half frame 7012. The second adjustment gasket 1202 is used to finely adjust the position of the auxiliary support plate 1201 to ensure that the connection plug on the auxiliary support plate 1201 is accurately docked with the plug-in part on the engine 11 and fixed by bolts.

[0125] Subsequently, connect the upper half frame 7011 of the mounting frame unit 701 to the lower half frame 7012 to form a complete main frame 7. Install the skin 1 on the skin support frame 6. The skin 1 is made of a composite material with good sound insulation and protection performance. Connect the aircraft connecting frame 5 to the mounting frame unit 701 of the main frame 7. The protruding part of the aircraft connecting plate 501 is accurately embedded in the card slot 503 of the pod connecting frame 502 and fixed with high-strength bolts. The mounting frame unit 701 is further connected to the aircraft connecting frame 5 through the lateral support 10. The right-angled triangular frame structure of the lateral support 10 effectively enhances the lateral stability of the pod.

[0126] Install the generator 2 on the upper half frame 7011 of the corresponding mounting frame unit 701 through the generator mounting frame 3. Utilize the waist-shaped holes 303 on the fixing plate 301 to accurately adjust the position of the generator 2 so that the generator 2, the coupling 4, and the input shaft of the engine 11 are on the same axis to ensure the high efficiency of power transmission. After the output shaft of the engine 11 is connected to the input shaft of the generator 2 through the coupling 4, connect the pod to the aircraft through the aircraft connecting frame 5. Finally, install the skin support 8 on the periphery of the main frame 7 through the support member 9 and lay the skin 1 on the skin support 8 to complete the assembly of the entire pod.

[0127] After assembly, a test run is carried out. During the ground taxiing and take-off phases of the aircraft, the pod operates stably, and the generator 2 can continuously and stably provide sufficient power for the newly added avionics equipment of the aircraft, meeting the power consumption requirements after the aircraft modification, and the increase in the weight of the pod has a minimal impact on the flight performance of the aircraft.

[0128] The examples given in the present invention are illustrative rather than restrictive of the embodiments. For those of ordinary skill in the art, based on the above description, other different forms of changes or modifications can be made. It is not necessary and impossible to enumerate all the embodiments here, and the obvious changes or modifications derived therefrom still fall within the protection scope of the present invention.

Claims

1. An aircraft power supply pod, characterized in that, It includes a skin (1), a generator (2), a coupling (4), an aircraft connecting frame (5), a main body frame (7), a skin bracket (8), and an engine (11). The generator (2), the coupling (4), and the engine (11) are arranged inside the main body frame (7). The generator (2) is connected to the engine (11) through the coupling (4). The aircraft connecting frame (5) is fixedly connected to the top of the main body frame (7) and is detachably connected to the aircraft body. The skin bracket (8) is externally connected to the main body frame (7) through a support member (9). The skin (1) is externally connected to the skin bracket (8). The main body frame (7) includes a plurality of mounting frame units (701) and a plurality of connecting brackets (703). The mounting frame units (701) are arranged in sequence along the axial direction of the generator (2). The connecting brackets (703) are arranged between adjacent mounting frame units (701) and are connected. The generator (2) is connected to the mounting frame unit (701) through a generator mounting frame (3). The engine (11) is connected to the mounting frame unit (701) adjacent to the generator (2) through an engine support assembly. The aircraft connecting frame (5) includes an aircraft connecting plate (501) and a pod connecting frame (502). The pod connecting frame (502) is connected to the mounting frame unit (701). The cross-section of the aircraft connecting plate (501) is "convex". A slot (503) corresponding to the aircraft connecting plate (501) is provided on the pod connecting frame (502). The protruding part of the aircraft connecting plate (501) is embedded in the slot (503) and is fixedly connected to the pod connecting frame (502).

2. The aircraft power supply pod according to claim 1, wherein The generator mounting frame (3) includes a fixing plate (301) and a generator mounting seat (302). The generator mounting seat (302) is fixedly connected to the fixing plate (301). The fixing plate (301) is connected to a group of mounting frame units (701). Bolt connection holes (702) for connecting with the fixing plate (301) are provided on the mounting frame unit (701) connected to the fixing plate (301). A waist-shaped hole (303) corresponding to the position of the bolt connection hole (702) is provided on the fixing plate (301). The relative position of the fixing plate (301) and the mounting frame unit (701) is adjusted through the waist-shaped hole (303) to make the output shafts of the generator (2), the coupling (4), and the engine (11) on the same axis.

3. The aircraft power supply pod according to claim 2, characterized in that, Each mounting frame unit (701) is square as a whole. The mounting frame unit (701) includes an upper half frame (7011) and a lower half frame (7012). The upper half frame (7011) and the lower half frame (7012) are detachably connected. The aircraft connecting frame (5) is fixedly connected to the top of the upper half frame (7011). The connecting brackets (703) are arranged between adjacent lower half frames (7012) and are connected.

4. The aircraft power supply pod according to claim 3, characterized in that, The generator (2) is connected to the upper half-frame (7011) of the corresponding mounting frame unit (701) through a generator mounting bracket (3), and the engine (11) is connected to the lower half-frame (7012) of the corresponding mounting frame unit (701) through an engine support assembly.

5. The aircraft power supply pod according to claim 4, characterized in that, The engine support assembly includes a main support member (13) and a secondary support member (12), and the main support member (13) and the secondary support member (12) are respectively mounted on different mounting frame units (701); The main support member (13) includes a main support plate (1301), a support arm (1302), a first adjusting gasket (1303), and a first support column (1304). The main support plate (1301) is hinged to the support arm (1302). The first support column (1304) is fixedly connected to the lower half-frame (7012) of the corresponding mounting frame unit (701) and supports the support arm (1302) upward. The first adjusting gasket (1303) is arranged between the support arm (1302) and the first support column (1304). The main support plate (1301) is provided with a mounting through-hole and a positioning convex column. The surface of the engine (11) is provided with a positioning hole corresponding to the positioning convex column and a bolt hole corresponding to the mounting through-hole; The secondary support member (12) includes a secondary support plate (1201), a second adjusting gasket (1202), and a second support column (1203). The second support column (1203) is fixedly connected to the lower half-frame (7012) of the corresponding mounting frame unit (701) and supports the secondary support plate (1201) upward. The second adjusting gasket (1202) is arranged between the secondary support plate (1201) and the second support column (1203). The secondary support plate (1201) is provided with a connection plug for connecting to the engine (11). The engine (11) is provided with a plug-in portion corresponding to the connection plug, and the connection plug and the plug-in portion are fixedly connected by bolts.

6. The aircraft power supply pod according to claim 5, characterized in that, Mounting holes are respectively provided on the support arm (1302) and the secondary support plate (1201). Through-holes corresponding to the corresponding mounting holes are respectively provided on the first adjusting gasket (1303) and the second adjusting gasket (1202). Bolt counterbores corresponding to the corresponding through-holes are respectively provided on the first support column (1304) and the second support column (1203). Bolts pass through the corresponding mounting holes, through-holes and bolt counterbores to connect, so as to fix the support arm (1302) to the first support column (1304) and the secondary support plate (1201) to the second support column (1203).

7. The aircraft power supply pod according to claim 1, characterized in that, A skin support frame (6) is connected to the top of the mounting frame unit (701). The skin support frame (6) is connected to a skin (1), and the skin support frame (6) corresponds to a skin bracket (8).

8. The aircraft power supply pod according to claim 1, wherein, The mounting frame unit (701) is further connected to an aircraft connecting frame (5) through a lateral support (10). The lateral support (10) is a frame structure and is in the shape of a right triangle.

9. The aircraft power supply pod according to claim 1, characterized in that, The engine (11) is a turboshaft engine.

10. An assembling method for an aircraft pod according to any one of claims 1-9, characterized in that, It includes the following steps: S1. Install a connecting bracket (703) between the lower half frames (7012) of adjacent mounting frame units (701); S2. Fix the engine (11) to the lower half frame (7012) of the corresponding mounting frame unit (701) through an engine support assembly; S3. Connect the upper half frame (7011) and the lower half frame (7012) of the mounting frame unit (701) to form a main frame (7); S4. Install a skin (1) on the skin support frame (6); S5. Connect the aircraft connecting bracket (5) to the mounting frame unit (701) of the main frame (7); S6. The mounting frame unit (701) is further connected to the aircraft connecting bracket (5) through a lateral support (10); S7. Install the generator (2) on the upper half frame (7011) of the corresponding mounting frame unit (701) through a generator mounting bracket (3), and connect the output shaft of the engine (2) to the input shaft of the generator (11) through a coupling (4); S8. Connect to the aircraft through the aircraft connecting bracket (5); S9. Install skin brackets (8) around the main frame (7) through supports (9), and each mounting frame unit (701) is externally connected to a skin bracket (8); S10. Lay the skin (1) on the skin brackets (8).

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