Aerial observation communication system and aircraft equipped with same

Abstract

The present application relates to an aerial observation communication system and an aircraft equipped with the aerial observation communication system, the aerial observation communication system comprising: a first pod comprising a photoelectric observation device, a mounting rack and a first fairing, the photoelectric observation device being used for observing visible light and infrared light; the second pod comprises a radar, a hanging frame, a firewall and a second fairing, and the radar is used for remote detection; and the third pod comprises satellite communication antenna equipment, a satellite communication antenna mounting bracket and a third fairing, and the satellite communication antenna equipment is used for receiving and transmitting signals. According to the air observation communication system and the aircraft equipped with the air observation communication system, photoelectric data observation and radar signal detection can be completed by the same aircraft at the same time, signals can be received and sent, and multiple purposes of rescue and relief work, emergency command communication and the like can be met.

Description

Technical Field

[0001] The present application relates to the aviation field, and in particular to an aerial observation and communication system and an aircraft equipped with the aerial observation and communication system. Background Art

[0002] At present, the existing domestic aircraft used for disaster relief, emergency command and communication are all improved large fixed-wing aircraft or helicopters. In actual use, there are problems such as high price of single aircraft, high maintenance cost, and complex system integration. In addition, there is no aircraft designed for aerial observation and communication to meet the needs of disaster relief, emergency command and communication. Summary of the invention

[0003] Based on this, the present application provides an aerial observation and communication system and an aircraft equipped with the aerial observation and communication system.

[0004] According to a first aspect of the present application, there is provided an aerial observation communication system, characterized in that it comprises:

[0005] A first pod, comprising an optoelectronic observation device, a mounting frame and a first fairing, wherein the optoelectronic observation device is mounted on the mounting frame and is used for observing visible light and infrared light, and the first fairing is used for covering the mounting frame;

[0006] A second pod, comprising a radar, a pylon, a firewall and a second fairing, wherein the radar is installed on one side of the pylon and the other side is connected to the firewall, the radar is used for long-range radar detection, the firewall is used to prevent a fire on one side of the pylon connected to the radar from spreading to the other side of the pylon, and the second fairing is used to cover the pylon, the radar and the firewall; and

[0007] The third pod includes a satellite communication antenna device, a satellite communication antenna mounting bracket and a third fairing. The satellite communication antenna device is installed on the satellite communication antenna mounting bracket for sending and receiving signals. The third fairing is used to cover the satellite communication antenna device and the satellite communication antenna mounting bracket.

[0008] According to some embodiments, the first pod also includes a side panel and a first lightning protection strip, the side panel is provided with multiple rows of drag plate nut interfaces for connecting with the mounting frame, and the first lightning protection strip is located on the side panel to prevent the first pod from being damaged by lightning strikes.

[0009] According to some embodiments, the second pod further includes a second lightning protection strip, which is located on the pylon and is used to prevent the second pod from being damaged by lightning.

[0010] According to some embodiments, the materials of the second fairing and the third fairing are both wave-transmissive materials.

[0011] According to some embodiments, the hanger is an "A"-shaped hanger, and the "A"-shaped hanger includes a left oblique beam, a right oblique beam and a cross beam, the left oblique beam is connected to one end of the right oblique beam, and the cross beam is located between the left oblique beam and the right oblique beam.

[0012] According to some embodiments, the aerial observation and communication system also includes an equipment cabin, which includes an equipment cabin body and an equipment cabin cover. The equipment cabin body is used to place optoelectronic equipment related to the optoelectronic observation equipment, the radar and the satellite communication antenna equipment, and the equipment cabin cover is connected to the equipment cabin body and is used to close the equipment cabin body.

[0013] According to some embodiments, the equipment cabin further includes a maintenance cover and an extension table. The maintenance cover is located on the equipment cabin body and is used to operate the equipment installed in the equipment cabin body after opening the maintenance cover. The extension table is connected to the equipment cabin body and is used to place objects.

[0014] According to some embodiments, the extension platform includes a platform frame, a platform upper cover plate and a platform lower cover plate, and the platform frame, the platform upper cover plate and the platform lower cover plate form a hollow structure.

[0015] According to a second aspect of the present application, there is provided an aircraft equipped with an airborne observation and communication system, characterized in that it comprises:

[0016] The airborne observation communication system as described in the first aspect; and

[0017] A fuselage, comprising a fuselage bulkhead and a skin, wherein the skin covers the fuselage bulkhead;

[0018] Wings, including left and right wings, are used to generate lift;

[0019] The tail fin is located at the tail of the aircraft and is used to maintain pitch balance and pitch operation.

[0020] Engines, including a left engine and a right engine, for providing power;

[0021] The propellers, including the left propeller and the right propeller, are used to propel the aircraft to accelerate.

[0022] According to some embodiments, the first pod is located at the nose of the aircraft, the second pod is located at the belly of the aircraft, and the third pod is located at the back of the aircraft.

[0023] According to the aerial observation and communication system and the aircraft equipped with the aerial observation and communication system provided by the present application, visible light and infrared light can be observed through the optoelectronic observation equipment, the radar can perform remote detection, and the satellite communication antenna equipment can receive and send signals. The same aircraft can simultaneously complete optoelectronic data observation and radar signal detection and can receive and send signals, which can meet various purposes such as disaster relief, emergency command and communication, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without exceeding the scope of protection required by the present application.

[0025] Figure 1 is an exploded view of a first pod of an aerial observation and communication system according to an embodiment of the present application.

[0026] Figure 2 It is an assembly diagram of a first pod of an aerial observation and communication system according to an embodiment of the present application.

[0027] Figure 3 It is a cross-sectional view of a photoelectric ball installed in the first pod of an aerial observation and communication system according to an embodiment of the present application.

[0028] Figure 4 is an exploded view of a second pod of an aerial observation and communication system according to an embodiment of the present application.

[0029] Figure 5 It is an exploded view of the connection between the radar of the second pod and the “A”-shaped bracket of the airborne observation and communication system according to one embodiment of the present application.

[0030] Figure 6 This is an exploded view of the installation of a lightning protection strip on an "A"-shaped rack of a second pod of an aerial observation and communication system according to an embodiment of the present application.

[0031] Figure 7 It is a schematic diagram of the installation of the satellite communication antenna equipment, the satellite communication antenna mounting bracket and the third fairing of the third pod of the aerial observation communication system according to one embodiment of the present application.

[0032] Figure 8 It is a top view of the installation of the satellite communication antenna mounting bracket of the third pod of the aerial observation communication system according to one embodiment of the present application.

[0033] Fig. 9 It is an axonometric view of a satellite communication antenna mounting bracket of a third pod of an aerial observation communication system according to an embodiment of the present application.

[0034] Fig.10 It is a flattened view of a satellite communication antenna mounting bracket of a third pod of an aerial observation communication system according to an embodiment of the present application.

[0035] Fig.11 It is an exploded view of an equipment compartment of an aerial observation and communication system according to an embodiment of the present application.

[0036] Fig.12 This is a schematic diagram of equipment installation in an equipment compartment of an aerial observation communication system according to an embodiment of the present application.

[0037] Fig.13 It is a side view of an aircraft equipped with an airborne observation and communication system according to one embodiment of the present application.

[0038] Fig.14 It is a front view of an aircraft equipped with an airborne observation and communication system according to one embodiment of the present application.

[0039] Reference numerals:

[0040] 21 first pod, 211 optoelectronic ball, 212 mounting frame, 213 first fairing, 215 side panel, 22 second pod, 221 radar, 222 "A" shaped rack, 223 firewall, 224 second fairing, 225 second lightning protection strip, 301 left beam, 302 right beam, 303 cross beam, 23 third pod, 231 satellite communication antenna equipment, 232 satellite communication antenna mounting bracket, 233 third fairing, 24 equipment compartment, 241 Equipment compartment main body, 242 equipment compartment cover, 243 maintenance cover, 244 extension platform, 401 platform frame, 402 platform upper cover, 403 platform lower cover, 25 optoelectronic equipment, 11 fuselage, 111 fuselage bulkhead, 112 skin, 12 wing, 121 left wing, 122 right wing, 13 tail wing, 14 engine, 141 left engine, 142 right engine, 15 propeller, 151 left propeller, 152 right propeller. DETAILED DESCRIPTION

[0041] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0042] The aerial observation communication system includes a first pod, a second pod and a third pod. Each pod is equipped with different equipment and can perform different functions.

[0043] Figure 1is an exploded view of a first pod of an aerial observation and communication system according to an embodiment of the present application. Figure 2 It is an assembly diagram of a first pod of an aerial observation and communication system according to an embodiment of the present application. Figure 3 FIG. 1 is a cross-sectional view of a first pod of an aerial observation communication system according to an embodiment of the present application, in which a photoelectric ball is installed. Figure 1 , 2 The first pod shown in 3 includes an optoelectronic ball, a mounting frame, a first fairing and a side panel.

[0044] According to some embodiments, the photoelectric observation device can observe visible light and infrared light, and the existing photoelectric observation device on the market can be selected according to actual needs, and it is installed on the mounting frame. The structure of the mounting frame matches the structure of the photoelectric observation device, and the number of photoelectric observation devices can be set to one or more according to actual needs. According to one embodiment, the photoelectric observation device selected in this scheme is a photoelectric ball, which is dual-axis and can rotate 360 ​​degrees.

[0045] According to some embodiments, the first fairing is used to cover the mounting frame. After the photoelectric ball is installed on the mounting frame, the first fairing can cover the photoelectric ball and the mounting frame according to actual needs, or only cover the mounting frame without covering the photoelectric ball. According to one embodiment, an opening is opened on the first fairing, and the photoelectric ball extends out of the first fairing from the opening.

[0046] According to some embodiments, multiple rows of drag plate nut interfaces are provided on the side panel, which can be connected to the mounting frame. The multiple rows of drag plate nut interfaces can reserve adjustable interfaces for the mounting frame connection. According to the different connection ports between the mounting frame and the multiple rows of drag plate nuts on the side panel, the connection position of the mounting frame can be adjusted.

[0047] According to some embodiments, a first lightning protection strip may be provided in the first pod to prevent damage to the first pod and the equipment installed therein caused by lightning strikes. The first lightning protection strip may be provided on the first fairing, or may be provided on other parts of the first pod according to actual needs. According to one embodiment, the first lightning protection strip is provided on the side panel.

[0048] Figure 4 FIG. 1 is an exploded view of a second pod of an airborne observation and communication system according to an embodiment of the present application. Figure 4 As shown, the second pod includes a radar, a pylon, a firewall and a second fairing.

[0049] According to some embodiments, the pylon is the main load-bearing structure of the second pod, a radar is installed on one side of the pylon, and the other side is connected to the firewall. The shape and structure of the pylon can be various, such as a triangular structure, a rectangular structure, and a circular structure. According to one embodiment, the pylon is an "A" shaped pylon.

[0050] According to some embodiments, existing radars on the market can be selected according to actual needs. Radars can achieve long-range detection and meet various purposes such as emergency rescue and disaster relief.

[0051] According to some embodiments, after the radar is connected to the bracket, an abnormal situation may occur, causing the radar to generate excessive heat and catch fire. After the fire occurs, the firewall can prevent the fire in the bracket from spreading outside the bracket, causing the fire area to spread and expand. The firewall is made of fire-proof material, such as stainless steel plate, and its structure matches the structure of the bracket.

[0052] According to some embodiments, the second fairing is connected to the "A"-shaped pylon, and its shape and structure match the shape and structure of the pylon and the firewall, and can cover the pylon and the firewall. After the radar is connected to the pylon, the second fairing can also cover the radar at the same time. The second fairing covers the radar, and the radar signal needs to pass through the second fairing. According to some embodiments, the material of the second fairing is a wave-transmitting material, such as glass fiber or quartz fiber and other wave-transmitting materials, which can meet the signal transmission of the radar.

[0053] Figure 5 It is an exploded view of the connection between the radar of the second pod and the “A”-shaped bracket of the airborne observation and communication system according to one embodiment of the present application. Figure 6 FIG. 1 is an exploded view of an A-shaped bracket of the second pod of an aerial observation and communication system according to an embodiment of the present application, wherein a lightning protection strip is installed. Figure 5 and 6 As shown, the hanger is an "A" shaped hanger.

[0054] According to some embodiments, the profile of the "A"-shaped bracket is in the form of the letter A, and is composed of two left and right oblique beams and two middle cross beams to form an integral frame, on which four bolt holes for connecting with the radar are arranged, wherein each of the left and right oblique beams and the two middle cross beams has one bolt hole, and the radar is connected to the four bolt holes of the "A"-shaped bracket using four bolts. The cross-section of the oblique beam and the cross beam is a groove-shaped cross section, which can reduce the weight of the "A"-shaped bracket.

[0055] According to some embodiments, a second lightning protection strip is installed inside the groove structure of the "A"-shaped pylon, and the lightning protection strip is used to prevent the equipment in the second pod from being damaged by lightning. The second lightning protection strip can also be set on the second fairing or on the radar. The number of second lightning protection strips can be set according to actual needs. According to one embodiment, a second lightning protection strip is installed inside the groove structure of the left and right oblique beams and the middle two cross beams of the "A"-shaped pylon respectively.

[0056] Figure 7 It is a schematic diagram of the installation of the satellite communication antenna equipment, the satellite communication antenna mounting bracket and the third fairing of the third pod of the aerial observation communication system according to one embodiment of the present application. Figure 8 It is a top view of the installation of the satellite communication antenna mounting bracket of the third pod of the aerial observation communication system according to one embodiment of the present application. Fig. 9 It is an axonometric view of a satellite communication antenna mounting bracket of a third pod of an aerial observation communication system according to an embodiment of the present application. Fig.10 FIG. 1 is a flattened view of a satellite communication antenna mounting bracket of a third pod of an airborne observation communication system according to an embodiment of the present application. Figure 7 , 8 As shown in Figures 9 and 10, the third pod includes a satellite communication antenna device, a satellite communication antenna mounting bracket and a third fairing.

[0057] According to some embodiments, the satellite communication antenna device is used to receive and send signals and transmit information, and the satellite communication antenna device available on the market can be selected according to actual needs.

[0058] According to some embodiments, the satellite communication antenna equipment mounting frame matches the satellite communication antenna equipment, and the satellite communication antenna equipment is mounted on the satellite communication antenna equipment mounting frame. According to one embodiment, the satellite communication antenna equipment bracket is made of stainless steel or aluminum alloy. According to one embodiment, the structure of the satellite communication antenna equipment mounting frame is as follows: Fig.11 As shown, the holes on the satellite communication antenna equipment mounting frame can be used for wiring while also reducing its own weight.

[0059] According to some embodiments, the third fairing covers the satellite communication antenna equipment and the satellite communication antenna equipment mounting frame to reduce aerodynamic drag during flight. Since the signal transmission of the satellite communication antenna equipment needs to pass through the third fairing, the third fairing is made of a wave-transmitting material. According to one embodiment, the third fairing is made of a wave-transmitting material such as glass fiber or quartz fiber plus foam or honeycomb sandwich.

[0060] Fig.11 It is an exploded view of an equipment compartment of an aerial observation and communication system according to an embodiment of the present application. Fig.12 FIG. 1 is a schematic diagram of equipment installation in an equipment compartment of an airborne observation communication system according to an embodiment of the present application. Fig.11 and 12 As shown, the airborne observation and communication system also includes an equipment cabin.

[0061] According to some embodiments, the equipment cabin includes an equipment cabin body and an equipment cabin cover, and the electrical equipment and cables related to the photoelectric ball of the first pod, the radar of the second pod, and the antenna equipment of the third pod are all placed in the equipment cabin body. The equipment cabin cover is connected to the equipment cabin body and is detachable. When the equipment needs to be placed in the equipment cabin body, the equipment cabin cover is removed. When the equipment does not need to be placed in the equipment cabin body, the equipment cabin cover is installed and connected to the equipment cabin body. After being connected to the equipment cabin body, the equipment cabin body can be closed to prevent the equipment placed in the equipment cabin body from moving out of the equipment cabin body.

[0062] According to some embodiments, a maintenance cover is provided on the equipment compartment body, and the number of the maintenance cover can be set to one or more according to actual needs, and the location of the maintenance cover can be set according to actual needs, for example, the maintenance cover is set at a specific location on the equipment compartment body, and the equipment at this location is prone to failure. After the equipment is placed in the equipment compartment body, if the equipment needs maintenance or the equipment fails and needs to be repaired, and it is inconvenient to take it out of the equipment compartment body, the maintenance cover set on the equipment compartment body can be opened to maintain the specific part.

[0063] When installing and debugging the equipment in the equipment cabin, some objects may be used, such as computers, wrenches, and connecting wires, etc., and the equipment cabin is provided with components for placing these objects. According to some embodiments, an extension table is provided on the equipment cabin, and the extension table is connected to the equipment cabin body for placing objects.

[0064] The structure of the extension platform can be set according to actual needs. According to some embodiments, the extension platform includes a platform frame, a platform upper cover and a platform lower cover. The platform frame, the platform upper cover and the platform lower cover form a hollow structure. Objects can be placed inside the hollow structure, and the platform cover can be opened and closed.

[0065] Fig.13 It is a side view of an aircraft equipped with an airborne observation and communication system according to one embodiment of the present application. Fig.14 FIG. 1 is a front view of an aircraft equipped with an airborne observation and communication system according to an embodiment of the present application. Fig.13 and 14 The aircraft shown includes the airborne observation and communication system, fuselage, wings, tail, engine, and propeller.

[0066] The aircraft equipped with the air observation communication system can be modified from a military aircraft or a large aircraft. According to some embodiments, the aircraft in this case is modified from a small general aircraft or a drone, which can reduce the purchase cost and operation cost of a single aircraft.

[0067] According to some embodiments, the fuselage of the aircraft includes a fuselage bulkhead and a skin, wherein the number of the fuselage bulkheads is multiple and distributed throughout the fuselage of the aircraft, and the skin covers the fuselage bulkhead; the wings include a left wing and a right wing for generating lift; the tail wing is located at the tail of the aircraft and is used to maintain pitch balance and pitch operation; the engine includes a left engine and a right engine for providing power; the propeller includes a left propeller and a right propeller for driving the aircraft to accelerate.

[0068] According to some embodiments, the weight of the first pod is lighter than that of the second pod and the third pod, and is placed at the nose of the aircraft, so as to avoid accidents caused by excessive load on the nose of the aircraft during flight. At the same time, the dual axes of the photoelectric ball of the first pod can rotate 360 ​​degrees, and the first pod is placed at the nose of the aircraft, which can also enable the photoelectric ball to observe the lower part of the aircraft fuselage and the front part of the aircraft nose, so that the photoelectric ball can observe a wider field of view.

[0069] According to some embodiments, the first pod of the air observation communication system is arranged at the nose of the aircraft, the side panel is connected to the fuselage bulkhead at the nose of the aircraft, and the mounting frame is connected to the side panel. The first fairing is connected to the fuselage bulkhead of the aircraft and can serve as the nose of the aircraft. The photoelectric ball can realize observation of the lower part of the aircraft and a certain angle in front of the nose.

[0070] According to some embodiments, the radar of the second pod is mainly used for ground and sea detection. The radar needs to transmit detection signals to the ground and the sea, and the weight of the second pod is heavier than that of the first pod and the third pod. The second pod is arranged on the belly of the aircraft, which can help the aircraft maintain fuselage balance during flight and avoid top-heavy or top-light and foot-heavy situations.

[0071] According to some embodiments, the second pod of the aerial observation and communication system is disposed on the belly of the aircraft, and the front and rear ends of the left and right oblique beams of the "A"-shaped hanger are connected to the fuselage bulkhead on the belly of the aircraft by bolts.

[0072] According to some embodiments, the satellite communication antenna device of the third pod is mainly used to send and receive signals, and it needs to transmit signals to and from satellites in space. The third pod is arranged on the back of the aircraft, which can facilitate the satellite communication antenna device to better transmit and receive signals. At the same time, because the first pod is arranged on the nose of the aircraft, the third pod is arranged on the back of the aircraft near the tail of the fuselage, which can better facilitate the aircraft to maintain balance during flight.

[0073] According to some embodiments, the third pod of the airborne observation communication system is disposed on the back of the aircraft, and the satellite communication antenna equipment mounting frame is fixed to the fuselage bulkhead and skin on the back of the aircraft near the tail of the fuselage.

[0074] According to some embodiments, an aircraft equipped with an aerial observation communication system can meet various application scenarios such as disaster relief and emergency command communication.

[0075] According to the aerial observation and communication system and the aircraft equipped with the aerial observation and communication system provided by the present application, visible light and infrared light can be observed through the optoelectronic observation equipment, the radar can perform remote detection, and the satellite communication antenna equipment can receive and send signals. The same aircraft can simultaneously complete optoelectronic data observation and radar signal detection and can receive and send signals, which can meet various purposes such as disaster relief, emergency command and communication, etc.

[0076] The embodiments of the present application are described in detail above. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method and its core idea of ​​the present application. At the same time, changes or deformations made by those skilled in the art based on the ideas of the present application, the specific implementation methods and the scope of application of the present application, all belong to the scope of protection of the present application. In summary, the content of this specification should not be construed as a limitation on the present application.

Claims

1. An aerial observation communication system, characterized in that: include: A first pod, comprising an optoelectronic observation device, a mounting frame and a first fairing, wherein the optoelectronic observation device is mounted on the mounting frame and is used for observing visible light and infrared light, and the first fairing is used for covering the mounting frame; A second pod, comprising a radar, a pylon, a firewall and a second fairing, wherein the radar is installed on one side of the pylon and the other side is connected to the firewall, the radar is used for long-range radar detection, the firewall is used to prevent a fire on one side of the pylon connected to the radar from spreading to the other side of the pylon, and the second fairing is used to cover the pylon, the radar and the firewall; and The third pod includes a satellite communication antenna device, a satellite communication antenna mounting bracket and a third fairing. The satellite communication antenna device is installed on the satellite communication antenna mounting bracket for sending and receiving signals. The third fairing is used to cover the satellite communication antenna device and the satellite communication antenna mounting bracket.

2. The system according to claim 1, characterized in that The first pod also includes a side panel and a first lightning protection strip. The side panel is provided with multiple rows of drag plate nut interfaces for connecting with the mounting frame. The first lightning protection strip is located on the side panel to prevent the first pod from being damaged by lightning.

3. The system according to claim 1, characterized in that The second pod also includes a second lightning protection strip, which is located on the rack and is used to prevent the second pod from being damaged by lightning.

4. The system according to claim 1, characterized in that The second fairing and the third fairing are both made of wave-transmitting materials.

5. The system according to claim 1, characterized in that The hanger is an "A"-shaped hanger, which includes a left oblique beam, a right oblique beam and a cross beam. The left oblique beam is connected to one end of the right oblique beam, and the cross beam is located between the left oblique beam and the right oblique beam.

6. The system according to any one of claims 1 to 5, characterized in that: It also includes an equipment cabin, which includes an equipment cabin body and an equipment cabin cover. The equipment cabin body is used to place optoelectronic equipment related to the optoelectronic observation equipment, the radar and the satellite communication antenna equipment. The equipment cabin cover is connected to the equipment cabin body and is used to close the equipment cabin body.

7. The system according to claim 6, characterized in that The equipment cabin also includes a maintenance cover and an extension table. The maintenance cover is located on the equipment cabin body and is used to operate the equipment installed in the equipment cabin body after opening the maintenance cover. The extension table is connected to the equipment cabin body and is used to place objects.

8. The system according to claim 7, characterized in that The extension platform comprises a platform frame, a platform upper cover plate and a platform lower cover plate, and the platform frame, the platform upper cover plate and the platform lower cover plate form a hollow structure.

9. An aircraft equipped with an airborne observation and communication system, characterized in that: include: An aerial observation communication system as claimed in any one of claims 1 to 8; A fuselage, comprising a fuselage bulkhead and a skin, wherein the skin covers the fuselage bulkhead; Wings, including left and right wings, are used to generate lift; The tail fin is located at the tail of the aircraft and is used to maintain pitch balance and pitch operation. Engines, including a left engine and a right engine, for providing power; The propellers, including the left propeller and the right propeller, are used to propel the aircraft to accelerate.

10. The aircraft according to claim 9, characterized in that The first pod is located at the nose of the aircraft, the second pod is located at the belly of the aircraft, and the third pod is located at the back of the aircraft.

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