CN117341977A - Aircraft pod and aircraft equipped with an aircraft pod - Google Patents

Abstract

The present application relates to an aircraft pod and an aircraft equipped with an aircraft pod, the aircraft pod comprising: the main bearing frame comprises a longitudinal beam, a bulkhead and connecting pieces, wherein the bulkhead is connected with the longitudinal beam through the connecting pieces to form one or more outlet cabins; the fire-proof wall comprises fireproof cotton and a fireproof plate, wherein the fireproof cotton covers the surface of the fireproof plate, and the fireproof plate is connected with the longitudinal beam; and the fairing is matched with the structure of the main bearing frame and connected with the longitudinal beam and is used for covering the main bearing frame. The aircraft comprises: a fuselage, on which the aircraft pod is mounted; a wing for generating lift; an engine for providing power; and a horizontal rear wing for maintaining balance. According to the aircraft pod and the aircraft provided with the aircraft pod, the stringers of the aircraft pod are connected with the bulkhead to form one or more cabins, and different size and different functions of aviation equipment can be loaded in different cabins according to requirements.

Description

Aircraft pod and aircraft equipped with an aircraft pod

Technical Field

The present application relates to the field of aviation, and in particular, to an aircraft pod and an aircraft equipped with an aircraft pod.

Background

Currently, most of the civil and military aircraft of existing equipment are used for manned, cargo or military combat applications.

However, some special-purpose aircrafts, such as fire extinguisher, rescue aircraft, anti-submarine aircraft, reconnaissance aircraft, electromagnetic interference aircraft, etc., can only be used for a single task, and cannot meet the requirements of multiple purposes and multiple tasks. Moreover, for aviation onboard electronic equipment developers, a general flight test verification platform capable of mounting multi-purpose, multifunctional and multi-category electronic equipment is required for equipment development and verification.

Disclosure of Invention

In view of the foregoing problems in the prior art, the present application provides an aircraft pod and an aircraft equipped with an aircraft pod.

According to a first aspect of the present application, there is provided an aircraft pod comprising:

the main bearing frame comprises a longitudinal beam, a bulkhead and connecting pieces, wherein the bulkhead is connected with the longitudinal beam through the connecting pieces to form one or more cabins;

the fire-proof wall comprises fireproof cotton and a fireproof plate, wherein the fireproof cotton covers the surface of the fireproof plate, and the fireproof plate is connected with the longitudinal beam; and

and the fairing is matched with the structure of the main bearing frame and connected with the longitudinal beam and is used for covering the main bearing frame.

According to some embodiments, the stringers include left and right beams and the connectors include "L" shaped members and corner joints.

According to some embodiments, the bulkhead comprises a vertical section and a sector section, the vertical section is at the same height as the longitudinal beam, the vertical section is connected with the longitudinal beam through the L-shaped piece, the sector section is integrally formed with the vertical section, and the sector section is connected with the longitudinal beam through the angle joint.

According to some embodiments, the bulkhead is provided with a notch for wiring of the equipment in the cabin.

According to some embodiments, lightning protection strips are arranged on the fairing, and the number of the lightning protection strips is one or more, so as to prevent the lightning from damaging the aircraft nacelle.

According to some embodiments, the device fixing frames are the same in number as the cabins, the device fixing frames are located in the corresponding cabins and used for fixing devices in the corresponding cabins, and the cover plates are installed in the cabins and used for enhancing electromagnetic protection capability of the cabins.

According to some embodiments, the main force bearing frame is made of metal and composite material.

According to some embodiments, the stringers are connected to an aircraft.

According to some embodiments, the fairing is made of a wave-transparent material.

According to a second aspect of the present application, there is provided an aircraft equipped with an aircraft pod, comprising:

the aircraft pod of the first aspect;

a fuselage, on which the aircraft pod is mounted;

wings, including left and right wings, for generating lift;

an engine including a left engine and a right engine for providing power; and

and the horizontal tail wing is positioned at the tail part of the aircraft and is used for keeping pitching balance and pitching operation.

According to the aircraft pod and the aircraft provided with the aircraft pod, on one hand, the stringers of the pod are connected with the bulkhead to form one or more cabins, and different size and different functions of aviation equipment can be loaded in different cabins according to requirements. The nacelle can also be used as a universal nacelle platform for flight test verification of avionics manufacturers, and matched nacelle is not required to be designed for different equipment, so that the research, development and verification cost of avionics is greatly saved. On the other hand, the main bearing frame of the nacelle has strong mounting capacity and large equipment mounting space, can meet the mounting requirements of various equipment, and in addition, the fairing of the nacelle can meet the wave-transmitting and frequency selecting requirements of different equipment under the condition of being made of wave-transmitting materials.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained by those skilled in the art from these drawings without departing from the scope of protection of the present application.

Fig. 1 is an exploded view of an aircraft pod according to one embodiment of the present application.

Fig. 2 is an exploded view of a main load frame of an aircraft pod according to one embodiment of the present application.

FIG. 3 is an assembly view of a main load frame of an aircraft pod according to one embodiment of the present application.

FIG. 4 is a side view of a main load frame of an aircraft pod according to one embodiment of the present application.

FIG. 5 is a heading view of a main load frame of an aircraft pod according to one embodiment of the present application.

FIG. 6 is a schematic illustration of a fairing of an aircraft pod and lightning protection strips disposed on the fairing according to an embodiment of the application.

Fig. 7 is a device installation schematic of an aircraft pod according to one embodiment of the present application.

Fig. 8 is a top view of a main load frame of an aircraft pod according to one embodiment of the present application.

FIG. 9 is a side view of an aircraft equipped with an aircraft pod according to one embodiment of the present application.

FIG. 10 is a top view of an aircraft equipped with an aircraft pod according to one embodiment of the present application.

Reference numerals: the aircraft nacelle comprises an aircraft nacelle body, a 10 main bearing frame, an 11 firewall, a 12 fairing, a 121 front lightning protection strip, a 122 left lightning protection strip, a 123 right lightning protection strip, a 124 rear lightning protection strip, a 13 left beam, a 14 right beam, a 15 bulkhead, a 151 vertical section, a 152 sector section, a 153 notch, a 16 'L' -shaped piece, a 17 angle joint, an 18 equipment fixing frame, a 181 front cabin equipment fixing frame, a 182 middle cabin equipment fixing frame, a 183 rear cabin equipment fixing frame, a 19 cover plate, a 2 airframe and a 21 engine. 22 horizontal tail, 23 wing, 301 front cabin equipment a,302 cabin equipment C,303 rear cabin equipment B.

Detailed Description

The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all, of the embodiments of the present application. All other embodiments, which can be made by those skilled in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.

Fig. 1 is an exploded view of an aircraft pod according to one embodiment of the present application. As shown in fig. 1, the aircraft pod includes: a main bearing frame, a firewall and a fairing. The size of the nacelle can be set according to the size of the aircraft or the size of the actual demand, and the shape of the nacelle can be set into different shapes according to the actual demand.

The pod is connected with the aircraft, the fire in the pod can be caused by various reasons, and in order to prevent the fire in the pod from causing the fire to enter the aircraft body to trigger the aircraft to fire, a firewall is arranged on one side of the pod connected with the aircraft body, and the firewall can prevent the fire in the pod from entering the aircraft body. According to some embodiments, the firewall comprises fireproof cotton and a fireproof plate, wherein the fireproof cotton covers the surface of the fireproof plate, the fireproof plate is made of fireproof materials (such as stainless steel), and the fireproof plate is connected with the main bearing frame.

Fig. 2 is an exploded view of a main load frame of an aircraft pod according to one embodiment of the present application. FIG. 3 is an assembly view of a main load frame of an aircraft pod according to one embodiment of the present application. FIG. 4 is a side view of a main load frame of an aircraft pod according to one embodiment of the present application. FIG. 5 is a heading view of a main load frame of an aircraft pod according to one embodiment of the present application. As shown in fig. 2, 3, 4 and 5, the main load frame includes: longitudinal beams, bulkhead and connecting pieces. The main load-carrying frame is the main load-carrying structure of the nacelle, which is made of strong, resistant material, such as metal and composite material, and the formers are connected to the stringers by means of connectors and form one or more cabins depending on the number of formers.

According to some embodiments, the stringers are provided with a plurality of openings for connection, such as screw openings, rivet openings, and bolt openings, etc., the stringers being connected to the aircraft fuselage. The shape and the structure of the longitudinal beam can be various, such as cuboid, cylinder, polyhedron, etc., and the longitudinal beam can be provided with different sizes according to the size of the airplane or the size of the actual requirement. According to one embodiment, the stringers are of a hollow cuboid structure, and the hollow structure can reduce the weight of the stringers and consequently reduce the load of the aircraft.

The nacelle may be provided with one or more stringers. According to some embodiments, the stringers comprise left and right beams, each of hollow cuboid structure and connected to the fuselage of the aircraft, the left and right beams being equal in length, width and height.

The shape and configuration of the formers may be varied, for example triangular, semicircular, and combinations of shapes, etc., which are required to be able to connect with the stringers and form the cabins.

According to some embodiments, in the present application, the bulkhead comprises a vertical section and a sector section, the vertical section being integrally formed with the sector section. The vertical section is a rectangular plate, and the height of the vertical section is equal to the heights of the left beam and the right beam. The fan-shaped section is a plate with a semicircular structure, the straight edge of the fan-shaped section is connected with one edge of the vertical section, and the sum of the length of the vertical section and the widths of the left beam and the right beam is equal to the diameter of the fan-shaped section. According to some embodiments, the portions of the segment that are connected to the vertical segment may be equal. According to some embodiments, one side of the segment connected to the vertical segment may have a portion on each of the left and right sides of the vertical segment, and the portion may have a width equal to the width of the left and right beams.

According to some embodiments, the bulkhead is provided with a notch for guiding the wire in the compartment and other objects that need to be guided out of the compartment out of the notch. The number, shape and size of the gaps arranged on the bulkhead can be set according to actual requirements, for example, one or more holes can be dug in the middle of the bulkhead, and the holes can be circular, rectangular, triangular and the like. According to one embodiment, a rectangular notch is opened inwardly from the edge of the segment of the former.

The connection of the bulkhead and the longitudinal beam requires the use of connecting pieces, and the shape and the structure of the connecting pieces can be various according to actual requirements, so that the connection of the bulkhead and the longitudinal beam can be adapted.

According to some embodiments, the connector includes an "L" shaped member and an angular joint.

According to some embodiments, the "L" shaped member comprises two rectangular plates connected to create an interior angle at right angles. The height of the L-shaped piece is equal to the height of the vertical section of the bulkhead, the height of the left beam and the height of the right beam. One rectangular plate of the L-shaped piece is connected with the vertical section, and the other rectangular plate is connected with the left beam or the right beam.

According to some embodiments, the corner joint comprises a rectangular plate, a sector plate and a triangular plate, wherein the rectangular plate, the sector plate and the triangular plate are integrally formed, and the whole shape of the corner joint is a triangle-like cone shape, so that the corner joint has good stability and can strengthen the strength of bearing tensile force. The width of the rectangular plate of the angle joint is equal to that of the left beam and the right beam, and the rectangular plate of the angle joint is connected with the left beam or the right beam. The arc edge of the angular joint sector plate is matched with the arc edge of the sector section of the bulkhead, and the angular joint sector plate is connected with the sector section of the bulkhead.

The number of the bulkhead of the nacelle can be set according to actual requirements. According to some embodiments, as shown in fig. 2, the nacelle is provided with four formers, each having an "L" shaped member and an angle joint on each of the left and right sides, respectively, connected to the left and right beams, forming three compartments, a front compartment, a middle compartment and a rear compartment, respectively. According to actual demands, the size of each cabin can be further set by setting the position of each bulkhead. According to one embodiment, the front compartment and the rear compartment are larger in volume for mounting equipment, and the middle compartment is smaller in volume for arranging other smaller equipment or accessories.

According to one embodiment, the left beam and the right beam are respectively provided with corresponding screw holes or rivet holes, and the connecting piece is connected with the bulkhead and the left beam and the right beam through screws or rivets.

According to some embodiments, the formers and stringers may also be connected without connectors, for example by welding or adhesives or the like.

FIG. 6 is a schematic illustration of a fairing of an aircraft pod and lightning protection strips disposed on the fairing according to an embodiment of the application. As shown in fig. 6, the fairing is matched with the main bearing frame, covers the main bearing frame, and lightning protection strips are arranged on the outer surface of the fairing.

According to some embodiments, fairings are connected to the stringers, the shape and configuration of the fairings being set according to the shape and configuration of the main load bearing frame. The fairing covers the whole main bearing frame, protects the main bearing frame and reduces aerodynamic drag when the aircraft flies. According to actual demands, the fairing can be provided with a window which can be opened and closed when flying or not flying, the window can be opened or closed in an aircraft control room, and the window can be manually opened or closed.

According to some embodiments, the fairing is made of a wave-transparent material, so that wave-transparent and frequency-selective requirements of different devices installed in the nacelle can be met.

When the nacelle is connected to an aircraft, electrical currents are generated by friction with the air during flight and may be subjected to lightning, which currents may cause damage to equipment mounted within the nacelle. According to some embodiments, as shown in fig. 6, lightning protection strips are provided on the exterior surface of the nacelle's fairing to prevent equipment installed within the nacelle from being damaged.

The number and location of the lightning protection strips provided on the outer surface of the fairing can be set according to the size or actual requirements of the nacelle. According to some embodiments, a lightning protection strip networking is provided on the fairing, the lightning protection strip networking including a front lightning protection strip, a left lightning protection strip, a right lightning protection strip and a rear lightning protection strip.

Fig. 7 is a device installation schematic of an aircraft pod according to one embodiment of the present application. Fig. 8 is a top view of a main load frame of an aircraft pod according to one embodiment of the present application. As shown in fig. 7 and 8, the pod further includes an equipment fixture and a cover plate.

According to some embodiments, an equipment fixing frame is arranged in each cabin of the nacelle, and the equipment fixing frames in each cabin are respectively matched with equipment arranged in each cabin and used for fixing the equipment in each cabin.

According to one embodiment, the front cabin equipment a and the rear cabin equipment B and the middle cabin equipment C are fixed in the front cabin, the rear cabin and the middle cabin by respective matched mounting fixtures (front cabin equipment fixture, rear cabin fixture and middle cabin fixture), respectively.

According to some embodiments, when the electromagnetic penetration capability of equipment installed in one or more cabins of the nacelle is relatively high, the aircraft is affected, and then a cover plate is separately arranged at the joint of the corresponding cabin and the firewall, the cover plate can enhance the electromagnetic protection capability of the corresponding cabin, and the electromagnetic penetration firewall in the cabin is prevented from affecting the aircraft. According to one embodiment, as shown in fig. 8, a cover plate is provided at a side of the middle compartment where the firewall is connected.

FIG. 9 is a side view of an aircraft equipped with an aircraft pod according to one embodiment of the present application. FIG. 10 is a top view of an aircraft equipped with an aircraft pod according to one embodiment of the present application. As shown in fig. 9 and 10, an aircraft equipped with an aircraft pod includes a fuselage, wings, an engine, and a horizontal tail.

The aircraft pod can be mounted at various locations of the aircraft fuselage, such as the belly, back or nose, etc., as desired. According to some embodiments, the aircraft pod is mounted in a belly position of an aircraft fuselage.

According to some embodiments, the wings of the aircraft comprise a left wing and a right wing, primarily for generating lift.

According to some embodiments, the engines of the aircraft include a left engine and a right engine, primarily for providing power.

According to some embodiments, the horizontal tail of the aircraft is located at the tail of the aircraft, mainly for maintaining pitch balance and pitch operation.

According to the aircraft pod and the aircraft provided with the aircraft pod, on one hand, the stringers of the pod are connected with the bulkhead to form one or more cabins, and different size and different functions of aviation equipment can be loaded in different cabins according to requirements. The nacelle can also be used as a universal nacelle platform for flight test verification of avionics manufacturers, and matched nacelle is not required to be designed for different equipment, so that the research, development and verification cost of avionics is greatly saved. On the other hand, the main bearing frame of the nacelle has strong mounting capacity and large equipment mounting space, can meet the mounting requirements of various equipment, and in addition, the fairing of the nacelle can meet the wave-transmitting and frequency selecting requirements of different equipment under the condition of being made of wave-transmitting materials.

The foregoing has outlined rather broadly the more detailed description of embodiments of the present application, wherein specific examples have been provided herein to illustrate the principles and embodiments of the present application, and wherein the above examples are provided to assist in the understanding of the methods and concepts of the present application. Meanwhile, based on the ideas of the present application, those skilled in the art can make changes or modifications on the specific embodiments and application scope of the present application, which belong to the scope of the protection of the present application. In view of the foregoing, this description should not be construed as limiting the application.

Claims (10)

1. An aircraft pod, comprising:

the main bearing frame comprises a longitudinal beam, a bulkhead and connecting pieces, wherein the bulkhead is connected with the longitudinal beam through the connecting pieces to form one or more cabins;

the fire-proof wall comprises fireproof cotton and a fireproof plate, wherein the fireproof cotton covers the surface of the fireproof plate, and the fireproof plate is connected with the longitudinal beam; and

and the fairing is matched with the structure of the main bearing frame and connected with the longitudinal beam and is used for covering the main bearing frame.

2. The aircraft pod of claim 1, wherein the stringers comprise left and right stringers and the connector comprises an "L" shape and an angle joint.

3. The aircraft pod of claim 2, wherein the bulkhead comprises a vertical section and a sector section, the vertical section being at the same height as the stringer, the vertical section being connected to the stringer by the "L" shaped piece, the sector section being integrally formed with the vertical section, the sector section being connected to the stringer by the corner joint.

4. Aircraft pod according to claim 1, characterized by the fact that the bulkhead is provided with indentations for the wiring of the devices inside the cabin.

5. The aircraft pod of claim 1, wherein the fairing is provided with one or more lightning protection strips for preventing damage to the aircraft pod from lightning.

6. The aircraft pod of claim 1, further comprising a number of equipment holders in a corresponding compartment for securing equipment in the corresponding compartment and a cover plate mounted in the compartment for enhancing electromagnetic shielding of the compartment.

7. An aircraft pod according to any of claims 1 to 6, wherein the main load frame is made of metal and composite material.

8. The aircraft pod of any of claims 1 to 6, wherein the stringers are connected to an aircraft.

9. An aircraft nacelle according to any of claims 1 to 6, wherein the fairing is made of a wave transparent material.

10. An aircraft equipped with an aircraft pod, comprising:

the aircraft pod of any of claims 1 to 9;

a fuselage, on which the aircraft pod is mounted;

wings, including left and right wings, for generating lift;

an engine including a left engine and a right engine for providing power; and

and the horizontal tail wing is positioned at the tail part of the aircraft and is used for keeping pitching balance and pitching operation.