CN115258190A - Design method and system for modifying unmanned aerial vehicle system by upper single-wing aircraft - Google Patents

Abstract

The invention discloses a design method and a system for modifying an unmanned aerial vehicle system by a single-wing aircraft, which comprises the steps of disassembling part of original aircraft equipment on an original aircraft, and adding equipment for modifying a flight control system and a task load on the original aircraft; according to the weight of the dismounting equipment or the retrofitting equipment, the mounting position of the dismounting equipment or the retrofitting equipment is correspondingly determined or adjusted so as to keep the center of gravity of the original machine; the original machine is modified into a new machine; the whole machine gravity center adjusting method of the novel machine comprises the following steps: the main equipment added with the modified equipment is intensively installed behind the gravity center course of the original machine, an equipment installation box with vibration isolation and electromagnetic and other environmental hazard protection functions is designed, and the installation position of an engine of the original machine is correspondingly adjusted to a position farther away from the front of the gravity center course of the original machine so as to obtain the gravity center balance of the whole machine. The invention controls the maneuvering overload and airspeed limitation through the flight control system and the matched subsystem to realize the adjustment of the loading performance of the unmanned aerial vehicle, and is beneficial to reducing the cost. Various data chains and task loads can be correspondingly modified. The technology of the refitting proposal is mature and feasible.

Description

Design method and system for modifying unmanned aerial vehicle system by upper single-wing aircraft

Technical Field

The invention belongs to the field of aircraft design and control, and relates to application of an overall structure design and control technology in the field of unmanned aerial vehicle system science and technology.

Background

With the continuous progress of technology and the demand of socioeconomic development, large-scale freight unmanned aerial vehicles are entering industrialization from conceptualization. In the technical development of the freight transportation unmanned aerial vehicle, the technical problems to be faced include the problems of load capacity, safety, transportation efficiency, loading and the like. In the prior art, an invention patent (publication number CN108910049 a) applied by shenzhen smart unmanned aerial vehicle limited discloses an unmanned aerial vehicle, which comprises a first fuselage, a second fuselage and wings, wherein the first fuselage and the second fuselage are symmetrically fixed on two sides of a symmetrical center line of the wings in parallel, the first fuselage, the second fuselage and the wings form an accommodating channel for accommodating a freight pod, and the wings are provided with fixing parts capable of fixing the freight pod when the freight pod is translated to the accommodating channel. The unmanned aerial vehicle and the unmanned aerial vehicle system for logistics transportation of this scheme aim at solving the technical problem that the unmanned aerial vehicle conveying efficiency of logistics transportation among the prior art is not high, fail automatic loading goods.

In addition, utility model patent that publication number is CN204802090U discloses a carry cargo hold subassembly and have its unmanned aerial vehicle for unmanned aerial vehicle, unmanned aerial vehicle includes the fuselage, be equipped with power supply battery on the fuselage, carry cargo hold subassembly detachably to establish on the fuselage, carry cargo hold subassembly to include: a cargo carrying bay having an entrance and an exit, the cargo carrying bay defining a chamber for carrying cargo; a cargo door provided on the cargo carrying compartment for opening or closing the outlet; the rechargeable battery is arranged on the cargo carrying cabin and provided with a charging port suitable for being connected with an external power supply, and the rechargeable battery is suitable for being matched with the power supply battery to charge the power supply battery. This cargo hold subassembly can provide sufficient electric power for unmanned aerial vehicle, and has improved the cyclic utilization rate in cargo hold.

However, the selection of the navigation aircraft for modification into the unmanned aerial vehicle system is an effective way for developing civil medium and large unmanned aerial vehicle systems. For example, the upper monowing aircraft is well suited for use in drone systems adapted to carry mission loads or cargo weighing around 200 kilograms and above. However, the technology of adding the single-wing general aviation aircraft into the unmanned aerial vehicle system is not mature at present, and the main reason is that the existing unmanned aerial vehicle mainly adopts plug-in carrying, but does not support air drop for the internal goods; secondly, a design scheme for improving the loading performance at low cost is lacked; thirdly, the loading capacity of the new aircraft is increased on the premise that the maneuvering overload of the aircraft is difficult to accurately control and other flight safety indexes are guaranteed, and the inertia force of the new aircraft is not larger than that of the original aircraft; and fourthly, the airport runway lacking a large number of freight unmanned aerial vehicles for taking off and landing.

Therefore, the method for modifying the single-wing aircraft into the unmanned aerial vehicle system is a significant technical innovation.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides a design method and a system for modifying an unmanned aerial vehicle system by using a single-wing aircraft.

The invention is realized by the following steps:

first, the general concept of the present invention is such that: disassembling part of original machine equipment on an original machine, and adding equipment for modifying a flight control system and a task load on the original machine; correspondingly determining or adjusting the installation position of the dismounting equipment or the retrofitting equipment according to the weight of the dismounting equipment or the retrofitting equipment so as to keep the center of gravity of the original machine; the original machine is modified into a new machine; the whole machine gravity center adjusting method of the novel machine comprises the following steps: the main equipment added with the modified equipment is intensively installed behind the gravity center course of the original machine, an equipment installation box with vibration isolation and electromagnetic and other environmental hazard protection functions is designed, and the installation position of an engine of the original machine is correspondingly adjusted to a position farther away from the front of the gravity center course of the original machine so as to obtain the gravity center balance of the whole machine.

Secondly, according to the design method, the upper single-wing aircraft is converted into an unmanned aerial vehicle system which comprises an aircraft, a flight control system, a data chain, a task load and a ground system. Wherein, the airplane is an upper single-wing navigation airplane, which is called an original airplane for short; all the modified airborne equipment is installed on the original machine, and the connection relation is as follows: the flight control system is connected with the data chain and the task equipment; and the ground system is connected with the flight control system or the task equipment through a data chain.

Specifically, as a necessary improvement of the invention, part of original equipment is disassembled on the airplane, mainly equipment used manually on the original airplane, including but not limited to a handle pedal, an instrument panel or a display screen, a light sound, a seat and a trunk, a modified unmanned system including but not limited to a flight control system, a data chain and equipment contained in a task load is added on the original airplane, and reasonable weight is predicted; the data link comprises a data link case and an antenna, the airborne data link is arranged on the machine, and the ground data link is arranged on the ground; according to the weight of the dismounting equipment or the retrofitting equipment, the mounting positions of the equipment are correspondingly determined or adjusted so as to keep the center of gravity of the original machine; the original machine is modified into a new machine through adding, and the new machine is an unmanned aerial vehicle system. The adjustment method may preferably adopt a standard design scheme: the modified main equipment comprises a flight control system and a matched combined navigation and atmospheric air machine subsystem, a data link case, an equipment installation case, a flight control system and part of matched equipment, and an airborne data link case, wherein the data link case is intensively installed behind the gravity center course of an original aircraft, particularly near the outside of the rear wall structure of an original aircraft cabin; the installation position of the engine of the original machine can be adjusted to a position farther away from the heading front of the gravity center of the original machine so as to obtain the total gravity center balance of the new machine.

In some embodiments, preferably, the installation of the original aircraft engine can be adjusted, firstly, the installation position moves forward to adjust the position of the center of gravity of the aircraft, secondly, the installation position is properly improved relative to the horizontal datum line of the original aircraft, so that the diameter envelope curve of the propeller can be higher than the horizontal plane of the aircraft belly, even the diameter of the propeller can be reduced by adopting four propellers, so that task equipment installed outside the aircraft belly is not shielded or is shielded less, thirdly, the front undercarriage can avoid occupying the space of the aircraft belly by adopting a mode of folding and unfolding along the front wall structure of the cabin or the upper part and the lower part of a firewall, or the front wheels are preferably folded forwards and upwards to reduce the occupied space of the aircraft belly.

In some embodiments, the flight control system may preferably employ a variety of control system architectures, including but not limited to single-redundancy or multi-redundancy flight control systems; the architecture of the flight control system and the arbitrary pipe system can be selected and matched with various subsystems, including but not limited to a combined navigation subsystem, an atmospheric engine and navigation attitude subsystem, a navigation subsystem, a take-off and landing subsystem, a fuel oil and power subsystem and a power subsystem. The power subsystem comprises a monitoring servo mechanism for the fuel oil throttle. The newly modified airplane can adopt a control method to realize the increase of loading performance, namely, a method for controlling the maneuvering overload and the flight airspeed limitation through a flight control system and keeping the maneuvering overload and the flight airspeed limitation within a range not larger than the setting range of the original airplane so as to keep the inertia force and the total load of the original airplane unchanged, thereby realizing the purpose of increasing the maximum takeoff weight of the new airplane under the state of keeping the structural strength of the original airplane, namely realizing the adjustment of the maximum takeoff weight of the airplane and dynamically adjusting the corresponding stall speed and the flight parameter indexes of each flight number. The control method comprises the steps that the overload ratio of the maneuvering overload of the original machine to the maneuvering overload required by the new machine and not larger than the original machine is equal to the weight ratio of the maximum takeoff weight index available for the new machine to the maximum takeoff weight of the original machine, so that the flying control rate of the new machine is determined, and the maneuvering overload of each flying stage is always controlled to be not larger than the overload ratio of the new machine.

In some embodiments, it is preferable that the brake system of the original main landing gear is modified to be a servo actuator which can be controlled and executed by the take-off and landing subsystem of the flight control system (detailed technical description) to replace the original manual operation, and the original nose landing gear is modified to be a servo actuator which is controlled and executed by the take-off and landing subsystem (description) to realize the function of controlling the front wheel steering.

In some embodiments, preferably, a part of the mission load is additionally modified and installed in the original cabin space, called a cabin for short, or installed on the cabin floor structure and is correspondingly modified to add additional section members to reinforce the structural strength and rigidity of the original cabin floor, in order to modify the original cabin floor from a closed structure to an openable and closable cabin door type structure, the middle structure connected with the left and right sides of the fuselage can be disassembled from the original cabin floor structure, the section members are added to the left and right bottom beam structures of the original cabin to reinforce the structural strength and rigidity of the bottom beams, and the section members can be added to the main landing gear installation structure range of the left and right side walls of the fuselage to reinforce the structural strength and rigidity; another portion of the mission load or cargo may be modified to be external to the airframe mounted on the wing or belly structure, or internal or external to the aft fuselage.

The photoelectric pod can be arranged on the extended structure of the front end floor of the belly, can be designed to be retractable or fixed, and can be retracted into an engine cabin or fixedly exposed outside the belly; the task load or goods in the ventral cabin can be loaded and unloaded through the cabin door on the side wall of the original machine body or the cabin floor door can be manufactured through modification, so that the fast loading and unloading including the aerial delivery can be realized, and a mechanism for controlling the opening or closing of the cabin floor door by a flight control system can be designed. In particular, the floor hatches can be designed as fully open hatches, for example hinged or hinged hatches, for which the bottom beam structures on both sides of the original cabin section are reinforced to improve the force transmission performance, for example, between the front wall structure and the back wall structure of the cabin of the original cabin section, profile structures are used to connect the bottom beams on the left and right sides of the floor, so as to form the bottom beams on both sides of the fuselage of the force transmission structure, so that the floor hatches can be connected to the bottom beams on both sides of the fuselage. On the ground, remote control commands can be sent to the airborne flight control system using a ground data link to open the floor hatches.

In some embodiments, preferably, the ground system connects the ground device with the airborne data link through the ground data link so as to connect the airborne flight control system or the mission load, and designs a human-machine operation interface required by the ground system, and a mobile or portable mode, optionally a vehicle-mounted or portable wearable device layout scheme; and data transmission of the information task load and monitoring of the cargo task load are realized through a ground system. The design of the data link is divided into an airborne data link and a ground data link, and the airborne data link and the ground data link are connected in a wireless mode, and the data link can comprise but is not limited to a link module of a 5G private network or a public network, and a combination of a plurality of point-to-point data links is designed, wherein the point-to-point data links comprise over-the-horizon links such as satellite communication or satellite relay links, and line-of-sight links; the 5G communication network is designed to be connected with a plurality of ground communication devices which are interconnected or interoperated; the designed point-to-point data link can support at least two ground communication devices to be connected with the airborne device and share the authority of information or operation, and can be compatible with a point-to-point data link scheme connected with a single ground communication device.

Part or all of the technical schemes of the invention are suitable for being modified into an unmanned aerial vehicle system by a single-wing 2-seat or multi-seat general aviation airplane, such as a Seina 162 airplane and Seina series airplanes, a GA8 caravan and series airplanes thereof, a big brown bear 100 series II airplane and improved series airplanes thereof, and can be modified into the unmanned aerial vehicle system.

Compared with the prior art, the technical scheme of the invention can control the maneuvering overload and the airspeed limitation through the flight control system and the matched subsystem to realize the adjustment of the loading performance of the unmanned aerial vehicle, and the method is favorable for reducing the cost. Various data chains and task loads can be correspondingly modified. The technology of the refitting proposal is mature and feasible.

Drawings

FIG. 1 is a diagram of the connection between the flight control system and the major subsystems of the present invention (dashed lines are optional);

FIG. 2 is a general layout view (side view) of the aircraft of the present invention;

FIG. 3 is an overall layout (overhead view) of the aircraft of the present invention;

FIG. 4 is a nose landing gear plus a modified steering mechanism of the present invention;

fig. 5 is a partial view of the steering engine connecting steering rocker arm of the invention.

The labels in the figures are: the system comprises a flight control computer 1, a flight control computer 2, an AD/DA module, a PWM control 3, a digital quantity interface 4, a control processing module 5, a power supply module 6, a DA/DO module 7, a power subsystem 8, a brake system 9, a fuel subsystem 10, an electric subsystem 11, a servo actuating system 12, an operation subsystem 13, a comprehensive detection subsystem 14, a task load 15, a navigation subsystem 16, a flight parameter recorder 17, an atmospheric data subsystem 18, a radio altimeter 19, a navigation subsystem 20, a satellite navigation subsystem 21, a satellite navigation subsystem 22-5G communication 23-satellite relay 24-sight distance link 25, an engine 26-cabin front wall structure 27-cabin rear wall structure 28-fuselage two-side bottom beams 28-fuselage, an equipment installation box 29, a steering rocker 30, a steering gear 31, a steering engine, a steering wheel 32, a steering wheel 33-steering rocker 33, a steering rope 34 and a support column 35.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to fig. 1 to 5, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Example 1: seslon (Cessna) 162 light-duty sport aircraft converted into unmanned aerial vehicle system

Taking a Sessner 162 airplane as an example, a modified flight control system and task equipment are added, and a navigable 2-seat airplane with commercial capacity of 220.4kg can be changed into an unmanned aerial vehicle with commercial capacity of more than or equal to 320 kg.

According to the performance index and the structure of the airplane, overall layout design is firstly carried out, the structure of the original airplane body is reserved, the configuration of a flight control system and the task load used for modification are selected, overall layout is adjusted to keep the gravity center position of the original airplane unchanged, and the layout result of the new airplane is shown in the attached drawing 1.

The performance index of the unmanned aerial vehicle after the modification is preliminarily measured and calculated, the flight control system is used for meeting the requirements that the flight inertia force of the original aircraft is not changed and the airspeed limit is not changed, the structural total load of the original aircraft can be kept unchanged, the structural strength of the whole aircraft is not required to be enhanced, therefore, the maneuvering overload + 4-2 of the original aircraft is adjusted to the maneuvering overload + 3-2 of the unmanned aerial vehicle, the maximum takeoff weight of the original aircraft can be adjusted to about 800kg through calculating about 600kg of the maximum takeoff weight of the original aircraft, the stall speed of the landing configuration of the original aircraft is correspondingly adjusted to 88km/h about 76km/h, and the performance indexes of other original aircraft are unchanged.

Therefore, the modified commercial load is increased to about 320kg from 220.4kg of the original aircraft, and the maximum flight time and flight distance index and the maximum load weight index are obtained mainly through the distribution of the task load and the fuel weight, so that the visible performance is obviously improved. For example, 66kg of fuel can be used in the state that the original machine is fully loaded by 2 persons and the weight of luggage is increased, or the total available fuel amount is 90.8L, the fuel weight can be increased by about 100kg after the machine is modified, or the fuel weight can be increased by 2.5 times during the flight.

The original nose landing gear is not provided with a steering mechanism, in order to improve steering control and be beneficial to reducing the width of a runway, a front wheel steering mechanism driven by an electric steering engine can be added by modifying the unmanned aerial vehicle, as shown in the attached figure 2; the main wheel brake replaces the original manual brake mode by a steering engine. In order to facilitate the installation of ground and forward observation task equipment at the front end of the belly of the fuselage and reserve the stowable space of the nose landing gear in the engine compartment, the size of an engine mounting bracket can be lengthened forwards along the voyage by combining the gravity center of the whole fuselage, the mounting height of the engine 25 relative to the horizontal datum line of the original fuselage is increased so as to eliminate the shielding of a propeller on the task equipment, namely, the envelope curve of a propeller blade is increased to be close to or higher than the horizontal height of the belly of the fuselage, the mounting structure of the engine 25 on the fuselage and the appearance of a fairing of the engine compartment are correspondingly modified, and the influence of the axial increase of the engine 25 and the modification of the fairing on the longitudinal moment and the resistance of the whole fuselage is not obvious from aerodynamic analysis.

Meanwhile, the additionally-modified main airborne system equipment can be mainly and intensively installed behind the cabin rear wall structure 27 so as to be cooperated with the installation position of the engine 25 to meet the requirement that the center of gravity of the whole aircraft is unchanged, and the installed environment of the additionally-modified main airborne equipment can be controlled by adopting the equipment installation box 29 to embed the airborne system equipment, so that the installed environment tolerance requirement of part of the airborne equipment is allowed to be reduced, and the economical efficiency is improved.

The retrofit solution for other onboard systems is outlined as follows:

1) Flight control system and modification of matched subsystem thereof

(1) According to the application scene analysis provided for the new aircraft, the new aircraft is given consideration to multiple application scenes such as aviation mapping, cargo airdrop, reconnaissance and printing integration and the like, the design scheme of the flight control system is determined to keep the inertia force and the total load of the aircraft unchanged, the maximum flight airspeed limit of the original aircraft is kept, the maximum takeoff weight can be widened from 600 kilograms to about 800 kilograms, and therefore the safety of the original structure of the whole aircraft can be guaranteed, namely the structural strength of the whole aircraft does not need to be supplemented for reinforcement. The connection relationship diagram of the flight control system and the main subsystem is shown in the attached drawing of the embodiment 1.

(2) The main navigation subsystem adopts inertial navigation and satellite combined navigation, such as optical fiber inertial navigation; and a vertical gyroscope and a magnetometer (or optional double GPS antennae) are adopted for the backup attitude and heading subsystem.

(3) The unmanned aerial vehicle is designed to automatically drive in and out of the runway.

(4) The navigation subsystem 16 is composed of a modified (or original) ADS-B host and a transmitting antenna, and realizes real-time automatic broadcasting of information such as ICAO, call sign, longitude and latitude, height, speed and course.

(5) The original engine can be selected or replaced by a ROTAX 914F2 engine, and the original fuel system can be unchanged.

(6) The electric subsystem 11 consists of an onboard main power supply, an auxiliary power supply, an emergency power supply and a ground power supply; the main power supply consists of a DC28V generator and a power supply processing module, and the power supply power is not less than 2Kw; the auxiliary power supply consists of a 12V alternating-current generator and a power supply processing module, and the power supply of the auxiliary power supply is not less than 400w; the emergency power supply consists of a lithium battery, and the emergency power supply time is not less than 15min; the ground power supply consists of commercial power, a diesel generator and a power supply processing module.

2) Modification of data chains

(1) The airborne measurement and control subsystem consists of a line-of-sight link 24, an over-the-horizon link and a 5G network, wherein the action distance of the line-of-sight link 24 can reach 200km, and the over-the-horizon link and the 5G network are optional links; the over-the-horizon link comprises satellite mobile communication or satellite relay 23 communication and short wave link.

(2) The flight control system computer can reserve a satellite equipment interface.

(3) The flight control system computer can reserve a 5G equipment communication interface, such as 5G network CPE equipment, and realize the function of accessing a low-altitude 5G communication link into a 5G network so as to meet the requirements of low-altitude high-speed and low-delay data transmission.

3) Modification of mission loads

The task load subsystem can be composed of multitask loads such as a photoelectric pod (containing CCD, infrared and laser), a Synthetic Aperture Radar (SAR), laser mapping equipment, a small fire extinguishing bomb, 4G/5G mobile relay equipment and the like; the electric interface is reserved by the flight control system; and carrying out adaptive matching installation according to the residual weight and the installation space of the airplane.

Example 2: modified floor cabin door

Still take the example of a seiner (Cessna) 162 airplane with a conversion, taking the mission load 15 mainly as cargo, and can be converted into a freight unmanned aerial vehicle; mission load 15 may include a photovoltaic pod loader. According to analysis and calculation, the original cabin is changed into a cargo hold, and the maximum loading capacity of the blister goods is 300kg. In order to meet the requirements of fast loading and unloading of goods, and meet the requirements of aerial delivery of goods, agriculture and forestry quality protection spraying, emergency rescue delivery and other various aerial delivery application scenes, the floor structure parts on the left and right sides of the symmetrical axis between a cabin section of an original aircraft fuselage structure, namely a cabin front wall structure 26 and a cabin rear wall structure 27 can be additionally modified, floor beams 28 on two sides of the aircraft fuselage can be additionally arranged on the cabin section to serve as force transmission structure parts for replacing the floor structure of the original aircraft cabin, and the floor doors of the cargo cabin which can be additionally modified to be opened and closed are additionally connected with the floor beams 28 on two sides of the aircraft fuselage.

The specific design scheme is that middle structures on the left side and the right side of the cabin section of the connecting seat are disassembled, profile members are additionally arranged near the bottom structures on the left side and the right side of the cabin section of the connecting seat body and are connected to serve as bottom beams 28 on the two sides of the body so as to reinforce the structural strength and rigidity of the body, the profile members are appropriately added above the main undercarriage mounting structures on the left side wall and the right side wall of the body so as to reinforce the structural strength and rigidity of the side walls, the added profile members can be selected from L-shaped, T-shaped, I-shaped, pi-shaped and the like, and the materials can be selected from metal or composite materials. The cargo compartment floor cabin door is designed to be opened and closed through a hinge mechanism or a servo mechanism controlled by a flight control system through a motion mechanism, and a safety design that an opening door lock is added to prevent the cabin door from being opened and closed by mistake to realize secondary unlocking is provided, namely, after the opening door lock which is arranged at the edge of the cabin door and is provided with a controllable switch and a piston mechanism is opened through a command of the flight control system, the cabin door of the cargo compartment floor can be opened again through the command; or the door lock is opened by ground personnel, the floor cabin door can be opened, and the goods can be released to the ground or a goods shelf vehicle on the ground under the controlled release by the fastening mechanism of the floor cabin door after the floor cabin door is opened. The cargo hold is loaded and unloaded in bulk through side wall doors of the body of the original machine or through additionally modifying newly added cargo hold floor doors, so that the cargo in the cargo hold can be loaded and unloaded quickly and can be released in the air.

The above embodiments are merely illustrative of the technical idea of the present invention, and it is apparent to those skilled in the art that the present invention is not limited to the details of the above embodiments, and the present invention can be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Claims (10)

1. A design method for refitting an unmanned aerial vehicle system from an upper single-wing aircraft is characterized by comprising the following steps:

1) Disassembling part of original machine equipment on an original machine, and adding equipment for modifying a flight control system and a task load on the original machine;

2) According to the weight of the dismounting equipment or the retrofitting equipment, the mounting position of the dismounting equipment or the retrofitting equipment is correspondingly determined or adjusted so as to keep the center of gravity of the original machine;

3) The original machine is modified into a new machine; the whole machine gravity center adjusting method of the new machine comprises the following steps: the main equipment added with the modified equipment is intensively installed behind the gravity center course of the original machine, an equipment installation box with vibration isolation and electromagnetic and other environmental hazard protection functions is designed, and the installation position of an engine of the original machine is correspondingly adjusted to a position farther away from the front of the gravity center course of the original machine so as to obtain the gravity center balance of the whole machine.

2. The method of designing a system of retrofitting a drone with a drone, according to claim 1, characterized in that: the rear of the gravity center course of the original aircraft comprises the vicinity outside the rear wall structure of the original aircraft cabin.

3. The method of designing a system of retrofitting a drone with a drone, according to claim 2, characterized in that: the mounting mode of the original engine comprises the following steps:

1) The mounting position is designed to move back and forth so as to adjust the position of the gravity center of the original machine;

2) The installation position is designed to be properly improved relative to the horizontal reference line of the original machine, so that the envelope curve of the diameter of the propeller can be higher than the horizontal plane of the belly, and even the propeller can be replaced to reduce the diameter of the propeller;

3) The retraction mechanism of the nose landing gear is designed to avoid or reduce occupying the space outside the belly by adopting a mode of retracting up and down along the front wall structure of the cabin.

4. The method of designing a system of retrofitting a drone with a drone, according to claim 3, characterized in that: the new plane after being modified can control the maneuvering overload and the flight airspeed limitation through the control method of the flight control system and keep the maneuvering overload and the flight airspeed limitation not larger than the setting range of the original plane, so that the inertia force and the total load of the original plane are kept unchanged, and the purpose of increasing the maximum takeoff weight of the new plane is achieved under the condition that the structural strength of the original plane is kept.

5. A system of retrofitting a drone with a single wing aircraft designed according to the method of any one of claims 1 to 4, characterized in that: the system consists of an airplane, a flight control system, a data chain, a task load and a ground system; wherein, the airplane is an upper single-wing general aviation airplane as an original airplane; the flight control system is connected with the data chain and the task equipment, and the ground system is connected with the flight control system or the task equipment through the data chain.

6. The upper monowing aircraft conversion drone system of claim 5, wherein: the flight control system adopts various control system architectures, including a single-redundancy or multi-redundancy architecture, a flight control system and an arbitrary pipe system architecture; the flight control system is selectively provided with various subsystems, including an integrated navigation subsystem, an atmospheric engine and navigation attitude subsystem, a navigation subsystem, a take-off and landing subsystem, a fuel oil power subsystem and a power supply subsystem.

7. The upper monowing aircraft conversion drone system of claim 5, the method is characterized in that: the brake system of the original main undercarriage is designed into a servo actuating mechanism controlled and executed by a flight control system to replace the original manual operating mechanism, and the original front undercarriage is designed into a servo actuating mechanism controlled and executed by the flight control system to realize the front wheel steering function.

8. The upper monowing aircraft conversion drone system of claim 5, wherein: part of the task load is arranged in the original cabin space of the modified cabin or on a cabin floor structure, and is correspondingly modified to increase the section members so as to locally strengthen the structural strength and rigidity, wherein a photoelectric pod outside the cabin can be arranged on the structure at the front end of the cabin or the cabin floor structure and is designed to be retractable or fixed; the task load in the cabin is loaded and unloaded through a cabin door on the side wall of the original machine body, or the fast loading and unloading is realized through additionally modifying and manufacturing a floor cabin door of the cabin, and a mechanism for controlling the opening or closing of the floor cabin door by a flight control system is designed; on the ground, a ground data chain is used for sending a remote control command to an airborne flight control system to open a floor cabin door; and another part of the task load or goods can be selectively arranged on the wing or the body part of the original machine.

9. The upper monowing aircraft conversion drone system of claim 5, wherein: the ground system is connected with the airborne flight control system or the task load by wirelessly connecting ground equipment with the airborne data chain through the ground data chain, and a human-machine operation interface and a moving or carrying mode required by the ground system are designed; the design of the data chain comprises a link module of a 5G private network or a public network and the combination of a plurality of point-to-point data chains; the 5G network is designed to be connected with a plurality of interconnected or interoperated ground communication devices; the designed point-to-point data link supports the connection of at least two ground communication devices and airborne equipment and is compatible with a scheme of connecting with a single ground communication device.

10. The upper monowing aircraft conversion drone system of claim 5, wherein: the original aircraft comprises a general aviation aircraft with 2 or more seats and a single wing.

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