Separable cargo hold unmanned transport plane

Abstract

According to the unmanned transport plane with the separable cargo hold, rapid replacement of different aviation task cabins can be achieved, a plane body longitudinal beam serves as a structure for bearing the overall weight of the plane, a locking structure used for locking the separable cargo hold is arranged at the bottom of the plane body longitudinal beam, and the separable cargo hold is of a universal module structure. The locking structure is opened after the separated cargo hold is supported, the airplane core structure composed of the airplane body longitudinal beams, the front airplane body, the rear airplane body and the airplane wings and the separated cargo hold are respectively replaced with different cargo holds, and the cargo hold structures of the same specification for bearing different tasks are replaced, so that high freight efficiency is achieved; the fuselage longitudinal beams are adopted as main bearing beams, the front fuselage and the rear fuselage only play a role in rectification and do not participate in bearing, the structural weight of the aircraft is reduced to the maximum extent, the loading capacity of the aircraft is greatly improved, meanwhile, standardized, universal and modular accessories are adopted, and all large components have interchangeability, so that the economical efficiency of the aircraft is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft design, and in particular relates to an unmanned transport aircraft with a detachable cargo hold. Background Art

[0002] With the rapid development of drone technology, the market demand for vehicles in the field of unmanned aviation transportation by domestic and foreign users continues to grow rapidly. At present, there is an urgent need to develop a large-scale unmanned aerial cargo system. Currently, fixed cargo holds are commonly used on aircraft, and the cargo hold loading factor is the cargo hold loading weight / aircraft takeoff weight, which is generally around 30%. In order to increase the loading factor to more than 40%, it is necessary to develop all-cargo aircraft transportation and redesign traditional aircraft to minimize the empty weight.

[0003] Traditional civil aviation is limited by factors such as fixed flight frequencies, few airports, complex operating procedures, and poor accessibility, making it difficult to meet the needs of rapid logistics transfer frequency and air / land / sea intermodal transport.

[0004] At present, aircraft platforms need to undergo a lot of modifications to perform different tasks, which is time-consuming and labor-intensive, and it is difficult to quickly meet the requirements of tasks such as cargo transportation, forest / grassland fire fighting, weather modification, rescue material delivery, deep-sea / open sea search and rescue, air emergency communications, and counter-terrorism security. Summary of the invention

[0005] The purpose of the present invention is to provide an unmanned transport aircraft with a detachable cargo compartment, so as to overcome the problem that the existing unmanned transport aircraft adopts an integrated cargo compartment structure, has limited bearing capacity and cannot achieve low separation efficiency.

[0006] A detachable cargo hold unmanned transport aircraft comprises a fuselage longitudinal beam, a detachable cargo hold, a front fuselage, a rear fuselage and aircraft wings, wherein the front fuselage and the rear fuselage are fixed on the fuselage longitudinal beam at intervals, the bottom of the fuselage longitudinal beam forms a cargo hold position between the front fuselage and the rear fuselage, the detachable cargo hold is detachably mounted on the bottom of the fuselage longitudinal beam through a locking structure, the detachable cargo hold is located between the front fuselage and the rear fuselage, the aircraft wings are fixed on the fuselage longitudinal beam, the rear fuselage is rotatably connected to the fuselage longitudinal beam, the rear fuselage can be flipped upward relative to the fuselage longitudinal beam for loading and unloading the detachable cargo hold, and power engines are fixed on both sides of the aircraft wings.

[0007] Preferably, the front fuselage includes a fuselage load-bearing frame and a front cover. The fuselage load-bearing frame is used to arrange an integrated and modular flight control system, a navigation system, a power supply system and an information transmission system. The fuselage load-bearing frame is fixed to the bottom front section of the fuselage longitudinal beam, and the front cover is buckled on the front end of the fuselage load-bearing frame.

[0008] Preferably, the front cover is fixed to the front end of the fuselage load-bearing frame by means of a rotational connection via a rotating shaft.

[0009] Preferably, the power engines fixed on both sides of the aircraft wings use fixed propellers, adjustable propellers or reverse thrust propellers.

[0010] Preferably, a front landing gear is installed at the front end of the fuselage longitudinal beam through a support beam, and a rear landing gear is respectively arranged on the aircraft wings on both sides of the aircraft.

[0011] Preferably, the rear landing gear is installed at the lower end of the aircraft in a three-point installation manner.

[0012] Preferably, the rear landing gear is installed at the lower end of the aircraft in a three-point installation manner, including two main struts and a tail strut, and the main struts and the tail strut are both installed at the lower part of the aircraft wing.

[0013] Preferably, a wing tip is arranged at the end of the aircraft wing, and the aspect ratio of the aircraft wing is 12-15.

[0014] Preferably, both aircraft wings are fixed with tail struts arranged along the length direction of the fuselage longitudinal beam, each tail strut is provided with a vertical tail, the front and rear beams of the vertical tail are directly inserted into the tail strut, and the vertical tail and the tail strut are designed to be integrated; the upper ends of the two vertical tails are connected by a horizontal tail.

[0015] Preferably, the locking structure uses a quick-release lock structure to fix the detachable cargo hold.

[0016] Compared with the prior art, the present invention has the following beneficial technical effects:

[0017] The present invention provides an unmanned transport aircraft with a detachable cargo hold, which can realize the rapid replacement of cabins for different aviation missions. The fuselage longitudinal beam is used as the structure for bearing the overall weight of the aircraft. A locking structure for locking the detachable cargo hold is arranged at the bottom of the fuselage longitudinal beam. The detachable cargo hold adopts a universal module structure. During the disassembly and installation process, it is only necessary to support the detachable cargo hold and then open the locking structure. The aircraft core structure composed of the fuselage longitudinal beam, the front fuselage, the rear fuselage and the aircraft wing is separated from the detached cargo hold and then replaced with a different cargo hold. By replacing the cargo hold structure with the same specifications that carries different missions, the freight efficiency is improved. The fuselage longitudinal beam is used as the main load-bearing beam, and the front fuselage and the rear fuselage only play a rectifying role and do not participate in the load-bearing, thereby reducing the structural weight of the aircraft to the greatest extent and greatly improving the loading capacity of the aircraft. At the same time, standardized, universal and modular accessories are adopted, and each large component is interchangeable to improve the economy of the aircraft.

[0018] Preferably, the front cover at the front end of the fuselage load-bearing frame can rotate relative to it, so that there is a large operating space for repairing the control system in the fuselage load-bearing frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1It is a schematic diagram of the three-dimensional structure of the unmanned transport aircraft with a detachable cargo hold in an embodiment of the present invention.

[0020] Figure 2 It is a front view of the unmanned transport aircraft with a detachable cargo hold in an embodiment of the present invention.

[0021] Figure 3 A side view of an unmanned transport aircraft with a detachable cargo hold according to an embodiment of the present invention.

[0022] Figure 4 A top view of an unmanned transport aircraft with a detachable cargo hold according to an embodiment of the present invention.

[0023] Figure 5 Schematic diagram of the structure of the unmanned transport aircraft with a detachable cargo hold in the open state according to an embodiment of the present invention.

[0024] Figure 6 It is a schematic diagram of the docking between the fuselage longitudinal beam and the mission cargo compartment in an embodiment of the present invention.

[0025] Figure 7 The figure is a schematic diagram of the installation of the front landing gear in an embodiment of the present invention.

[0026] Explanation of numbers in the figure: 1-fuselage longitudinal beam; 2-detached cargo hold; 3-front fuselage; 4-rear fuselage; 5-wing including wingtip; 6-tail support; 7-vertical tail; 8-horizontal tail; 9-power engine; 10-landing gear; 51, left wing; 52, right wing; 53, left wing wingtip; 54, right wing wingtip; 71, left vertical tail; 72, right vertical tail; 101, front landing gear; 102, left rear landing gear; 103, right landing gear. DETAILED DESCRIPTION

[0027] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0028] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0029] Example 1

[0030] To achieve the above object, the present invention provides an unmanned transport aircraft with a detachable cargo hold, which can realize the rapid replacement of different aviation mission cabins, such as Figures 1 to 7 As shown, it specifically includes a fuselage longitudinal beam 1, a separated cargo hold 2, a front fuselage 3, a rear fuselage 4, an aircraft wing 5 and a landing gear 10. The front fuselage 3 and the rear fuselage 4 are fixed on the fuselage longitudinal beam 1 at intervals, and the bottom of the fuselage longitudinal beam 1 forms a cargo hold between the front fuselage 3 and the rear fuselage 4. The separated cargo hold 2 can be detachably installed at the bottom of the fuselage longitudinal beam 1, and the separated cargo hold 2 is located between the front fuselage 3 and the rear fuselage 4. The aircraft wing 5 is fixed on the fuselage longitudinal beam 1, and the rear fuselage 4 is rotatably connected to the fuselage longitudinal beam 1. The rear fuselage 4 can be turned upward relative to the fuselage longitudinal beam 1 for loading and unloading the separated cargo hold 2. Power engines 9 are fixed on both sides of the aircraft wing 5, and the landing gear 10 is arranged at the bottom of the fuselage longitudinal beam 1 and the aircraft wing 5. In the specific implementation manner of the present application, the fuselage longitudinal beam 1 is used as a structure for bearing the weight of the entire aircraft, and the fuselage longitudinal beam 1 is used to support the aircraft. A locking structure for locking the detached cargo hold 2 is provided at the bottom of the beam 1. The detached cargo hold 2 adopts a universal modular structure. During the disassembly and installation process, it is only necessary to support the detached cargo hold 2 and then open the locking structure. The aircraft core structure composed of the fuselage longitudinal beam 1, the front fuselage 3, the rear fuselage 4 and the aircraft wing 5 is separated from the detached cargo hold 2 and then replaced with a different cargo hold. In a specific embodiment of the present invention, by replacing the cargo hold structure of the same specification that carries different tasks, the cargo transportation efficiency is improved. The fuselage longitudinal beam is used as the main load-bearing beam, and the front fuselage and the rear fuselage only play a rectifying role and do not participate in the load-bearing, thereby minimizing the structural weight of the aircraft and greatly improving the loading capacity of the aircraft. At the same time, standardized, universal and modular accessories are adopted, and each major component is interchangeable to improve the economy of the aircraft.

[0031] In a specific embodiment of the present invention, the front fuselage 3 is used as the head structure of the aircraft, and an integrated and modular flight control system, navigation system, power supply system and information transmission system are arranged inside it. The arrangement of cables and pipes is completed through the slot passage on the fuselage longitudinal beam 1, and a single person can use handheld maintenance equipment to perform maintenance and replacement. The UAV has high safety, reliability, testability, usability and maintainability. The fuselage longitudinal beam 1 is provided with a slot passage, and the control circuit and oil circuit of the control system are laid along the slot passage on the fuselage longitudinal beam 1 and connected to the controlled components on the aircraft wing 5.

[0032] The front fuselage 3 includes a fuselage load-bearing frame and a front cover. The fuselage load-bearing frame is mainly used for integrating the control system for aircraft flight control. The fuselage load-bearing frame is fixed to the bottom front section of the fuselage longitudinal beam 1. The front cover is buckled on the front end of the fuselage load-bearing frame to form the head structure of the aircraft and realize the straightening effect of the aircraft. The specific shape and size requirements of the front cover are set according to the use specifications of the aircraft and the corresponding technical requirements and parameters. Specifically, the front cover adopts an elephant trunk structure. The specific structure and size of the aircraft front cover are not specifically elaborated in this application; the fuselage load-bearing frame is used for fixing and installing the aircraft control system. The fuselage load-bearing frame serves as the cockpit for aircraft control, and the front cover serves as the door of the entire cockpit. When maintaining the control system in the fuselage load-bearing frame, the control system in the fuselage load-bearing frame can be maintained or replaced by removing the front cover.

[0033] In a specific embodiment of the present invention, in order to facilitate maintenance and the stability of the overall system, the front cover can be rotatably arranged at the front end of the fuselage load-bearing frame. Specifically, the front cover is connected to the fuselage longitudinal beam 1 through a rotating shaft, and is controlled by an electronic control system. A rotating shaft locking mechanism can be provided, so that the front cover can be in a stable state when it is opened or closed. Specifically, a hydraulic drive rod is arranged on the fuselage load-bearing frame, and the hydraulic drive rod is used to control the opening and closing of the front cover. The hydraulic drive rod is used to support the front cover at the front end of the fuselage load-bearing frame so that it can be rotated upward relative to the fuselage load-bearing frame, thereby having a large operating space to repair the control system in the fuselage load-bearing frame. The front cover and the fuselage longitudinal beam 1 can rotate relative to each other by up to 120°, which is convenient for the maintenance and replacement of the equipment. Similarly, the rear fuselage is opened 120° upward, and the separated cargo hold 2 enters and exits from the rear of the aircraft.

[0034] The control lines of the control system in the fuselage load-bearing frame are arranged along the fuselage longitudinal beam 1. The fuselage longitudinal beam 1 is the main load-bearing structure of the entire aircraft, and its structural strength meets the load-bearing flight requirements of the entire aircraft. In the specific implementation of the present application, the fuselage longitudinal beam 1, the separated cargo hold 2, the front fuselage 3, and the rear fuselage 4 are designed in a serialized and modular manner and can be quickly replaced to meet the needs of scenarios such as artificial weather modification, transportation and delivery of rescue materials, and forest / grassland firefighting.

[0035] The detachable cargo hold 2 is in the form of a mission cargo hold, including a general-purpose container of standard size, an insulated mission cargo hold, a livestock air transport cargo hold, an airdrop mission cargo hold or a special mission cargo hold. The overall cabin structure matches the installation space between the front fuselage 3 and the rear fuselage 4 at the bottom of the fuselage longitudinal beam 1, and can be automatically installed and automatically airdropped.

[0036] Example 2

[0037] In one embodiment provided in the present application, the power engine 9 fixed on both sides of the aircraft wing 5 adopts a fixed propeller, an adjustable propeller or a reverse propeller, which can be selected and used according to the specific usage conditions; the blade angle of the fixed propeller cannot be adjusted; during the flight, this propeller cannot change the thrust direction or thrust magnitude, so it is suitable for slower aircraft, such as airdrops and disaster relief operations; the blade angle of the adjustable propeller can be adjusted by mechanical, hydraulic or electrical mechanisms, and this propeller can adjust the thrust direction and thrust magnitude according to flight requirements, so it is suitable for faster aircraft, such as cargo transportation, deep sea / open sea maritime search and rescue. The blades of the reverse propeller can rotate in the opposite direction to generate backward thrust. This propeller can provide a strong braking force when the aircraft lands, enhancing the maneuverability of the aircraft.

[0038] In the specific implementation of the present application, the fuselage longitudinal beam 1 is the main load-bearing beam that runs through the entire fuselage. The "trunk" area where the longitudinal beam connects to the front and rear fuselages is a pipeline and cable channel; Figure 7 As shown, a front landing gear 101 is installed at the front end of the fuselage longitudinal beam 1 through a support beam. The load received by the front landing gear 101 after landing is transmitted to the fuselage longitudinal beam 1. The support beam used to connect the front landing gear 101 and the fuselage longitudinal beam 1 runs through the front fuselage 3 and can be used as a part of the main beam structure of the front fuselage 3. A rear landing gear is respectively arranged on the aircraft wings 5 ​​on both sides of the aircraft. The rear landing gear is installed at the lower end of the aircraft 5 in a three-point installation manner, specifically including two main struts and a tail strut. The main struts are fixed to the lower part of the aircraft wing 5, and the tail strut is connected to the lower part of the aircraft wing 5. The retracted position is located at the side of the tail strut. Compared with being retracted in the tail strut, the cross-sectional size of the tail strut can be reduced, thereby reducing the weight of the tail strut. Alternatively, a multi-strut installation or a retractable installation method is adopted. It can be customized according to the special needs of the aircraft, such as improving the taxiing stability and reducing the space occupied by the apron.

[0039] In the specific implementation of this application, Figure 1 As shown, in order to improve the flight capability of the aircraft, a wing tip is provided at the end of the aircraft wing 5, which is a wing outer end rectifying part installed on the wing end rib; the aspect ratio on the aircraft wing 5 is 12 to 15.

[0040] In the specific implementation of the present application, a tail strut 6 arranged along the length direction of the fuselage longitudinal beam 1 is fixed on both wings 5 ​​of the aircraft, and a vertical tail 7 is arranged on each tail strut, and the front and rear beams of the vertical tail 7 are directly inserted into the tail strut 6, and the vertical tail 7 and the tail strut are designed in an integrated manner; the upper ends of the two vertical tails 7 are connected by a horizontal tail 8, and the horizontal tail 8 is installed between the two vertical tails 7, which is a key component for the aircraft to maintain stability. The horizontal tail 8 includes a fixed horizontal stabilizer and a deflectable elevator; the horizontal stabilizer is used to make the aircraft have static stability in the pitch direction, that is, the aircraft raises its head or lowers its head. When the aircraft is affected by various updrafts or side winds in the air, the horizontal stabilizer can generate a torque opposite to the disturbance direction to restore the aircraft to its original flight attitude. This stability is crucial for the safe flight of the aircraft. The elevator is the controllable wing surface part of the horizontal tail, and its function is to perform pitch control on the aircraft. When it is necessary to control the aircraft to raise its head or lower its head, the elevator will be deflected upward or downward through the transmission mechanism. After the elevator is deflected, the aerodynamic force it receives will generate an additional torque, thereby changing the pitch angle of the aircraft. For example, when the elevator is deflected upward, a nose-up torque will be generated, causing the aircraft to fly upward; conversely, when the elevator is deflected downward, a nose-down torque will be generated, causing the aircraft to fly downward. This control method allows the pilot to accurately control the flight attitude of the aircraft. The horizontal tail can also generate a downward lift during flight. Compared with the lift generated by the wing, this lift, the lift generated by the wing and the gravity form a set of parallel force systems to jointly maintain the longitudinal stability of the aircraft. When the aircraft is flying horizontally, the horizontal tail will not generate additional torque on the aircraft; but when the aircraft is disturbed, the horizontal tail can quickly generate a reverse torque to help the aircraft return to a horizontal flight state.

[0041] In a specific embodiment of the present application, a fixed paddle structure is provided, such as Figure 2 As shown, the main structure consists of a fuselage longitudinal beam 1, a separated cargo hold 2, a front fuselage 3 and a rear fuselage 4. A left wing 51 and a right wing 52 are arranged on the fuselage longitudinal beam 1; a left wing wing tip 53 is arranged at the end of the left wing 51, and a right wing wing tip 54 is arranged at the end of the right wing 52. The left wing wing tip 53 and the right wing wing tip 54 are the outer end fairing parts of the wings and are installed on the wing end ribs; a left vertical tail 71 is arranged on the left wing 51, and a right vertical tail 72 is arranged on the right wing 52. The right wing 52 and the right vertical tail 72 are connected by a horizontal tail 8 to maintain the flight stability of the aircraft; a left rear landing gear 102 is arranged at the bottom of the left wing 51, and a right landing gear 103 is arranged at the bottom of the right wing 52. A front landing gear 101 is arranged at the front end of the fuselage longitudinal beam 1.

[0042] In another embodiment of the present application, the aircraft adopts an upper monoplane, a tail-supported fuselage, a P-type tail, two wing-mounted piston engines, and a front three-point wing landing gear layout, with a main load-bearing fuselage longitudinal beam, and a separate cargo hold 2 for loading, a wing, a front fuselage, and a front landing gear connected by the fuselage longitudinal beam. The structural parts and system parts of the left and right landing gears used in the present application are designed to be consistent. The types of spare parts are reduced, and it is convenient to use and maintain. The aircraft provided by the present invention can improve operational efficiency, reduce aircraft transit time, and improve the economy of the aircraft by directly replacing the mission cargo hold; different types and specifications of cargo holds can be selected for autonomous docking according to different missions, and can be used for air, ground, and sea transport.

[0043] Example 3

[0044] Specifically, in a detachable cargo hold unmanned transport aircraft provided in the present application, Figure 5 As shown, the locking structure provided on the fuselage longitudinal beam 1 is used to fix the detachable cargo hold 2 to the bottom of the fuselage longitudinal beam 1, and can be unlocked in time when needed, so as to achieve the purpose of quickly disassembling the detachable cargo hold 2. The locking structure specifically adopts a quick-release lock buckle structure to fix the detachable cargo hold 2, which is suitable for cargo holds that need to be frequently disassembled and installed. Specifically, a latch seat is provided at the bottom of the fuselage longitudinal beam 1, and a latch head is provided on the detachable cargo hold 2. The detachable cargo hold 2 can be inserted into the latch seat for locking. The latch head includes a fixed base connected to the detachable cargo hold and an elastic lock pin connected to the plug. The latch seat includes a seat body connected to the fuselage longitudinal beam 1 and an elastic lock hole provided on the seat body. The quick-release lock buckle has the characteristics of simple structure, convenient operation, strong load-bearing capacity, etc. Through the quick locking and releasing mechanism, the fixing and disassembly of the cargo hold can be completed in a short time. This fixing method greatly improves work efficiency and reduces labor costs, and is an important choice in the field of modern logistics.

[0045] In another detachable cargo hold unmanned transport aircraft provided in the present application, a fixing method of a bulkhead plug hole and a wall-mounted base is adopted; a bulkhead plug hole is provided on the fuselage longitudinal beam 1, and a wall-mounted base is installed on the detachable cargo hold 2. By inserting the wall-mounted base into the plug hole of the bulkhead and rotating or locking the mechanism, the detachable cargo hold 2 can be firmly fixed on the fuselage longitudinal beam 1. This fixing method has the characteristics of compact structure, convenient installation, and strong load-bearing capacity, and is suitable for cargo holds of various sizes.

[0046] Example 4

[0047] The present invention provides a control method for the above-mentioned detachable cargo hold unmanned transport aircraft, wherein the detachable cargo hold unmanned transport aircraft comprises a fuselage longitudinal beam 1, a detachable cargo hold 2, a front fuselage 3, a rear fuselage 4 and an aircraft wing 5, wherein the front fuselage 3 and the rear fuselage 4 are fixed at intervals at the lower end of the fuselage longitudinal beam 1, the detachable cargo hold 2 is fixed to the bottom of the fuselage longitudinal beam 1, the detachable cargo hold 2 is located between the front fuselage 3 and the rear fuselage 4, the detachable cargo hold 2 is detachably mounted on the bottom of the fuselage longitudinal beam 1 through a locking structure, and the aircraft wing 5 is fixed to the fuselage longitudinal beam 1, the rear fuselage 4 is rotatably connected with the fuselage longitudinal beam 1, and the rear fuselage 4 can be turned upward relative to the fuselage longitudinal beam 1 for loading and unloading the separated cargo hold 2. Power engines 9 are fixed on both sides of the aircraft wings 5. The front end of the fuselage longitudinal beam 1 is installed with a front landing gear 101 through a bracket beam. The load received by the front landing gear 101 after landing is transmitted to the fuselage longitudinal beam 1. The bracket beam used to connect the front landing gear 101 and the fuselage longitudinal beam 1 is set through the front fuselage 3, and a rear landing gear is respectively set on the aircraft wings 5 ​​on both sides of the aircraft. Specifically, the following steps are included:

[0048] S1, according to the overall specifications and carrying capacity of the aircraft, select the corresponding separated cargo hold 2, install and calibrate the fuselage longitudinal beam 1, the front fuselage 3, the rear fuselage 4 and the aircraft wing 5, open the rear fuselage 4, and hang and fix the separated cargo hold 2 on the fuselage longitudinal beam 1;

[0049] S2, after arriving at the destination according to the flight destination, the detachable cargo hold 2 is separated from the fuselage longitudinal beam 1, and then the empty detachable cargo hold 2 or the loaded detachable cargo hold can be hung to return or go to another destination. The present application adopts a detachable cargo hold and a fuselage structural design, which improves operational efficiency, reduces aircraft stopover time, and improves the economy of the aircraft by directly replacing the mission cargo hold; the aircraft cargo hold can select different types and specifications of cargo holds for autonomous docking according to different missions, and can be used for air, ground, and sea transport.

[0050] Other embodiments of the invention will be apparent to those skilled in the art after considering the specification and disclosure of the invention.

[0051] This application is intended to cover any variation, use or adaptation of the present invention, which follows the general principles of the present invention and includes common knowledge or customary technical means in the art that are not disclosed in the present invention. The description and examples are to be regarded as exemplary only, and the true scope and spirit of the present invention are indicated by the following claims.

[0052] It should be understood that the present invention is not limited to the exact construction that has been described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the present invention is limited only by the appended claims.

[0053] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any way. Any simple modification, change and equivalent structural change made to the above embodiment based on the technical essence of the present invention still falls within the protection scope of the technical solution of the present invention.

Claims

1. An unmanned transport aircraft with a detachable cargo hold, characterized in that: The invention comprises a fuselage longitudinal beam (1), a detachable cargo hold (2), a front fuselage (3), a rear fuselage (4) and an aircraft wing (5). The front fuselage (3) and the rear fuselage (4) are fixed to the fuselage longitudinal beam (1) at intervals. The bottom of the fuselage longitudinal beam (1) forms a cargo hold between the front fuselage (3) and the rear fuselage (4). The detachable cargo hold (2) is detachably mounted on the bottom of the fuselage longitudinal beam (1) through a locking structure. The detachable cargo hold (2) is located between the front fuselage (3) and the rear fuselage (4). The aircraft wing (5) is fixed to the fuselage longitudinal beam (1). The rear fuselage (4) is rotatably connected to the fuselage longitudinal beam (1). The rear fuselage (4) can be turned upward relative to the fuselage longitudinal beam (1) for loading and unloading the detachable cargo hold (2). Power engines (9) are fixed on both sides of the aircraft wing (5).

2. The unmanned transport aircraft with a detachable cargo hold according to claim 1, characterized in that: The front fuselage (3) comprises a fuselage load-bearing frame and a front cover. The fuselage load-bearing frame is used to arrange an integrated and modular flight control system, a navigation system, a power supply system and an information transmission system. The fuselage load-bearing frame is fixed to the bottom front section of the fuselage longitudinal beam (1), and the front cover is buckled on the front end of the fuselage load-bearing frame.

3. The unmanned transport aircraft with a detachable cargo hold according to claim 1, characterized in that: The front cover is fixed to the front end of the fuselage carrying frame by means of a rotating shaft connection.

4. The unmanned transport aircraft with a detachable cargo hold according to claim 1, characterized in that: The power engines (9) fixed on both sides of the aircraft wings (5) adopt fixed propellers, adjustable propellers or reverse thrust propellers.

5. The unmanned transport aircraft with a detachable cargo hold according to claim 1, characterized in that: A front landing gear (101) is installed at the front end of the fuselage longitudinal beam (1) via a support beam, and a rear landing gear is respectively arranged on the aircraft wings (5) located on both sides of the aircraft.

6. The unmanned transport aircraft with a detachable cargo hold according to claim 5, characterized in that: The rear landing gear is installed at the lower end of the aircraft (5) using a three-point installation method.

7. The unmanned transport aircraft with a detachable cargo hold according to claim 6, characterized in that: The rear landing gear is installed at the lower end of the aircraft (5) in a three-point installation manner, and includes two main struts and a tail strut, and the main struts and the tail strut are both installed at the lower part of the aircraft wing (5).

8. The unmanned transport aircraft with a detachable cargo hold according to claim 1, characterized in that: A wing tip is arranged at the end of the aircraft wing (5), and the aspect ratio of the aircraft wing (5) is 12-15.

9. The unmanned transport aircraft with a detachable cargo hold according to claim 1, characterized in that: Tail struts (6) arranged along the length direction of the fuselage longitudinal beam (1) are fixed to both wings (5) of the aircraft, a vertical tail wing (7) is arranged on each tail strut, front and rear beams of the vertical tail wing (7) are directly inserted into the tail struts (6), and the vertical tail wing (7) and the tail struts are designed to be integrated; the upper ends of the two vertical tail wings (7) are connected by a horizontal tail wing (8).

10. The unmanned transport aircraft with a detachable cargo hold according to claim 1, characterized in that: The locking structure uses a quick-release lock structure to fix the detachable cargo hold (2).

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