CN207242004U - A kind of low-latitude flying operation unmanned plane - Google Patents

Abstract

The utility model discloses a kind of low-latitude flying operation unmanned plane, the buffer gear of design and installation main unit of landing gear and nose-gear pillar and the lower end of main unit of landing gear and nose-gear pillar are connected to become slide-type undercarriage (2) structure mainly on the load-carrying construction on the outside of fuselage (1), and improve glide ratio using high lift-drag ratio Aerodynamic Design.The utility model is integrated with low latitude anti-crash technology, low latitude link communication technology and UAV system technology, the fixed-wing unmanned plane of the suitable low latitude operation pneumatically general layout design with power is employed, is the new layout UAV system of a kind of low latitude operations such as suitable agricultural aviation plant protection and safe flight.

Description

A kind of low-latitude flying operation unmanned plane

Technical field

The present invention relates to low-latitude flying operation fixed-wing unmanned plane and its control system and application, belong to General Aviation in agriculture The application in the fields such as industry plant protection, maritime search and rescue and airborne geophysical prospecting.

Background technology

Agricultural plant protection carries out spraying operation using navigation aircraft decades history, is that typical low latitude operation should With.China carries out aircraft pesticide spraying operation from the fifties in last century, only possesses the special navigation aircraft of 200 multi rack agricultural, bag Include domestic fortune -5, agriculture -5, -12 grade aircrafts of fortune -11 and fortune, and aircraft of external import etc..External agricultural plant protection navigation Aircraft is larger.In recent years, agricultural plant protection is explored using agricultural plant protections such as manned versions of helicopter, unmanned multiaxis gyroplanes New technology.By comparing, the application effect of aerial sprays plant protection technology is higher than the operating efficiency of field level machinery sprinkling, does not have Wheel roll off is worried.Fixed-wing navigation aircraft is more much higher than the spraying efficiency of helicopter and multiaxis gyroplane, and flight airflow Be conducive to pesticide fully to contact with the positive and negative of plant leaves, spray uniformly comprehensive, good drug efficacy.Integrated comparative, fixed-wing navigation Aircraft performs agricultural plant protection low latitude operation and has the advantage that：Operating efficiency is high, effect is good, cost is low.It is but manned solid It is larger to determine the technical difficulty of wing general aviation aircraft execution agricultural plant protection low-latitude flying, flies first, carrying out low latitude 3-20 meters of low latitude OK, barrier difficulty height is avoided, flight safety hidden danger is larger.Second, long-time hedgehopping, driver is easily tired, both makes Into flight safety hidden danger, and it is difficult to improve operating efficiency.Third, piloted flight is mainly preferable in illumination and meteorological condition Daytime carries out.For this reason, designing a kind of low latitude operation fixed-wing UAV system and being applied to the field such as agricultural plant protection, maritime search and rescue and be Extremely it is necessary.

The content of the invention

It is an object of the invention to provide a kind of low-latitude flying operation unmanned plane, to overcome problem existing in the prior art.

What the present invention was realized in：

A kind of low latitude operation fixed-wing unmanned plane proposed by the present invention and its control system, by housing construction, mobile system, Ground monitoring station and low latitude operation safeguards system collectively constitute.Housing construction mainly includes fuselage, wing, empennage, undercarriage, work Industry cargo compartment or sprinkling object container.Mobile system mainly includes navigation and flight control system, low latitude link, engine and combustion The spout of oil system, spraying pipe and Integral design.Ground system is mainly ground monitoring station, and low latitude operation safeguards system The satellite navigation difference station that included Active workings are set, 4G/5G signals of communication or base station, the ADS- of ground monitoring station installation B broadcast base stations, ground power supply.Other systems include the airborne alternative and standby system with ground in relation to system.

Specifically, housing construction and the control system detailed description of the present invention is as follows：

1st, fuselage is laid out using Conventional pneumatic, along the established angle in course with certain power transmission on the load-carrying construction of fuselage outer side Angle installs the buffer gear of main unit of landing gear and nose-gear pillar, the established angle to main landing gear about downward vertically to 5-15 degree afterwards, to nose-gear about 5-15 degree forward downward vertically, installation can be adjusted according to flying speed and landing attitude Angle.The upper end of main unit of landing gear and nose-gear pillar connects the buffer gear respectively.Main unit of landing gear and before rise and fall The lower end of post setting is connected to become slide-type landing gear structure, can select installation anti-on the surface on slide-type form touch ground Friction material, its configuration is such as the slide-type undercarriage of helicopter, buffering when skid bottom plate is used for unexpected be grounded or soft Slided on ground, improve the low latitude anti-crash performance of aircraft, for this reason, the front and back end of skid bottom plate can be designed to be bent up it is curved Shape, and the lower semisection of undercarriage leg connection skid is designed to suitably skim to outside fuselage outer side, to guide the side of stress deformation To further increase cushion performance.To meet to apply, the cutting that installation and skid insulation may be selected at the preceding tilting end of skid hinders Hinder thing equipment, installation water float bowl may be selected in the outside of skid.And under main unit of landing gear and nose-gear pillar End is installed on the wheel of ground taxi, wherein preceding wheel is connected in steering mechanism.To special operation application, in main landing gear and Force cell can also be installed on nose-gear pillar, be convenient for measuring aircraft weight center of gravity, the measurement scheme of replacement is ground The platform balance put dynamometer or be commonly called as carries out check weighing so as to draw aircraft weight center of gravity data to four wheels all around.

2nd, wing and the fuselage load-carrying construction of single-blade layout are connected to agent structure, with the agent structure it is coplanar go up and Fuel tank can be installed along the course of wing, double-vane be laid out in the case of to install the wing of engine as host wing, and host wing Agent structure is connected to fuselage load-carrying construction.Airborne Navigation Control and chain-circuit system installation on the body construction, and uses Buffer gear or buffer structure part are coupled for improving survivability energy, can increase electromagnetic shielding and waterproofing design.Fuselage is cut The polygon and joint angle that face is linearly connected with camber line are inscribed arc-shaped transition；The layout details of wing type selecting and fuselage appearance High lift-drag ratio aerodynamic force configuration is designed to, to improve glide ratio and ground effect aerodynamic force and to coordinate slide-type undercarriage to strengthen anti-pendant Ability is ruined, the lift resistance ratio of design seeks higher numerical value in 12-30, should generally reach more than 16.For low-wing configuration, main body Rectangle may be selected in the fuselage cross-section shape of superstructure or up-narrow and down-wide cross sectional shape coordinates the installation of slide-type Landing Gear System, And install air-flow radome fairing drag reduction additional in fuselage outer side, and the inner space of radome fairing allows the rotation of the autonomous appropriateness of undercarriage, should The inner space of fuselage is the cargo compartment for loading purposes, and cargo compartment arranges cargo compartment internal junction along course or for fuselage axis Structure, including bulkhead partition plate, and fuel tank can be changed position and be installed on cargo compartment two side.For shoulder-wing configuration, in main body The installation that up-narrow and down-wide cross sectional shape coordinates slide-type Landing Gear System also may be selected in fuselage side wall below structure, equally can be Fuselage outer side installs air-flow radome fairing drag reduction, the inner space of the fuselage namely the cargo compartment for loading purposes additional, and cargo compartment is along course Or fuselage axis arrangement cargo compartment internal structure, to facilitate the design of weight center of gravity and control, and need to draw according to operation Divide multiple cargo compartment units for loading different objects.Fuel tank is laid out along fuselage both sides, particularly side hanging auxiliary oil tank structure, this Kind structure can conveniently release fuselage inner space, but require Oiltank structure to have higher load performance as general aviation aircraft. Spray appliance is adapted to fit using straight or tapered wing, increases spray width.The hatch door of the cargo disengaging of cargo compartment on fuselage Or lid is arranged in afterbody or head or belly and can facilitate cargo to pass in and out.

3rd, installation sprays the equipment of powdery or liquid object and sprays the outlet of object below wing, and object outlet is set In the course front end of trailing edge purling.For low-wing configuration, the equipment and sprinkling object for spraying object are exported along wing Lower section of the length containing fuselage is continuously arranged.For shoulder-wing configuration, the equipment for spraying object connects along wingspan length and fuselage outer side Continuous arrangement, and spray the outlet of object only can under the wings of an airplane with just arranged under fuselage, form the continuous spout along wingspan length Layout.Spray outlet is arranged under the wings of an airplane and before trailing edge, can be obtained and be sprayed object by stream below purling band trend course line Dynamic effect, and allow ejection object to be connect extensively with plant leaf since the plant leaf movement on ground is brushed in the effect of purling Touch.

The 4th, propeller type or turbogenerator be installed, separate unit or more on wing.To improve the anti-side wind performance of aircraft, adopt With vectored thrust mechanism is configured during a single engine to it, one kind is that universal joint and servo control mechanism are installed in propeller shaft, one Kind is turbogenerator jet bias current pipe/plate, and one kind is fuselage both sides increase by two low thrust assisted engines of installation.Separate unit is sent out The optional head of installation site or the machine back of the body or tail of motivation are simultaneously installed along axes of aircraft.During using two engines, two are started The installation site of machine can be selected on wing, or selection, on fuselage, left and right respectively installs one, and can use thrust type or pulling force Formula propeller configurations, it is poor using the push/pull of engine prop, or the mechanism using vectored thrust is further added by so as to allow hair Motivation and aircraft rudder surface aerodynamic force cooperation, it is common to adjust flight course to improve course keeping ability.Empennage can use more high-order T-shaped configuration, or using more lower position double shoe configurations empennage.For low-wing configuration, two engine designs exist Body upper both sides, such backpack engine are installed on aerofoil profile girder structure as shoulder pole both sides equilibrium load configuration, should The designing scheme of aerofoil profile girder construction includes and is designed to top wing and inside can load fuel oil, and engine prop can select to draw Power formula propeller is preposition and protrudes the leading edge of a wing, or thrust type propeller postposition and prominent trailing edge.Engine is installed on machine Higher position with it can improve its distance with ground, be installed on compared to engine below wing, such backpack Engine installation can reduce interference of the blowing gas stream to trailing edge purling and ejection object after propeller.

5th, housing construction includes the surface peace of fuselage, wing, empennage, undercarriage and engine, its leading edge and protruding parts Fill and coat anti-freeze material.And full machine surface installation and coating antistatic aids and material.To the table using composite material Face, can combine anti-freeze and antistatic material therefor and carry out integrated design.Discharge brush is installed on the trailing edge of wing and empennage And outside.

6th, in mobile system, navigation drives into or out of function automatically with flight control system equipment, and more are started The thrust or pulling force of machine and the special control function of pneumatic rudder face Collaborative Control flight course and anti-side wind.Wherein, navigation system Using the integrated navigation of satellite navigation+inertia+landform tracking, differential signal can be received and be modified, operating area can be matched Terrain data.Flight control system is to pneumatic rudder face servo control mechanism on body, to engine throttle mechanism, to undercarriage brake and Steering mechanism is controlled, and airborne operating load sprinkling/throwing mechanism is controlled.Data-link is set using a variety of links Standby is applied in combination, it is ensured that steady and sustained information and direct orders are obtained, using sighting distance remote measuring and controlling and information transmission link, 4G or 5G mobile communication links, shortwave or ultrashort wave radio set collectively form low latitude trans-horizon link, and abbreviation low latitude link, passes through ground Relevant device and mobile system interconnect data on the monitoring station of face, receive telemetry intelligence (TELINT) and send telecommand.Wherein, 4G or 5G communication links can use the short text of BD satellites or SMS function to substitute.Line of sight link is mainly used for the survey in the landing stage of aircraft Control, the sighting distance remote measuring and controlling in landing stage and the optional about 100km scopes of the sphere of action of information transmission link, select 5-20km It is both economical, and in the operation of low latitude high request such as the unmanned plane of course calibration, can also increase configuration includes airborne defend Star relays or the remote measuring and controlling of aviation relaying and the beyond-the-horizon communication link of information transmission, strengthens low latitude link performance, wherein, it is right Satellite relay remote measuring and controlling is used with the use of the information transmission system and communicated to the intermittent mode of star on and off, but to remote measurement Data can be fitted the continuous monitoring of realization, to save communication cost.Airborne navigation monitoring system is installed, including ADS-B broadcast types are certainly Dynamic dependent surveillance system and aviation management speech repeater system, wherein, the data-link of ADS-B can be as a parallel-chain of low latitude link Road.The video camera of flight job monitoring system is installed, including visible ray or infrared video, its information data is synchronous pass down or Using selection/it is touring by the way of under be transmitted to ground monitoring station, mainly use 4G or 5G mobile communication.To onboard flight control system With the design of low latitude link, using replacing configuration, i.e., same aircraft pneumatic structure can receive a kind of cheap and simple or A kind of airborne navigation of complex and expensive and flight control system and low latitude link, and support easily changes the outfit and normal flight.

7th, ground monitoring station is according to fixed or moveable two kinds of Scheme designs, ground monitoring station and aircraft machine Loading system Aided design, it is corresponding on ground monitoring station that low latitude link is set and navigates by water the supporting transceiver of monitoring system, prison Equipment and corresponding man-machine interface are controlled, it is corresponding that required ground-plane antenna and base station equipment are set, as difference station of navigating, ADS-B are wide Broadcast station.Monitoring flight real time position can be received by these system equipments at ground monitoring station and its machine situation of course line periphery is believed Breath, and Speech Communication can be carried out by airborne aviation management speech forwarding unit and aviation management department during plant protection flying ferry； When satellite relay remote measuring and controlling is used with the use of the information transmission system to communicate to the batch process of star on and off, ground The information of face monitoring station and display accordingly realize continuous Information application and screen display using estimation program.

8th, operation safeguards system in low latitude is to improve the design that flight job position precision and low latitude communication capacity carry out, being At flight job area arrangement certain distance distribution satellite navigation difference station, or navigation base station, and arrangement 4G or 5G communication bases Stand, the difference station and 4G communication base stations that can be set by solar panel for distribution power.Alternative ground satellite difference station is set Standby technical solution is to use airborne RTK navigation system aboard.Low latitude to having been provided with good 4G or 5G signals of communication Operating area, it is possible to reduce arrangement omits arrangement 4G or 5G communication base stations.

9th, to the existing series of fortune five, the series of agriculture five, transport be adapted in 12 series aircrafts the manned aircraft of low latitude operation into The unmanned repacking design of row, that is, install the mobile system of foregoing 6th Partial Feature additional, and increases powder/liquid to fuselage cargo compartment Object puts rolling compartment, and flight control system connects airborne each servo control mechanism and is controlled, and installs low latitude chain-circuit system additional and carries out Communication.Wherein, airborne each servo control mechanism includes each pneumatic rudder face and flap, engine throttle mechanism, undercarriage brake on body Switching mechanism of car and steering mechanism, sprinkling or dispensing material etc..The ground monitoring station of supporting foregoing 7th Partial Feature.

The main application fields of the present invention include：Aerial remote sensing loading device is installed, applied to low latitude agricultural remote sensing plant protection Operation, including pesticide spraying, agricultural land detection and areal analysis, soil constituent analysis, plant planting percent, casualty loss are commented Estimate or terraced fields graphics；Water surface take-off and landing device is reequiped, applied to marine or waterborne rescue and monitoring.

Low latitude operation fixed-wing unmanned plane proposed by the present invention uses fixed-wing configuration, electronic with oil-burning internal combustion engine or power supply Machine (abbreviation engine) is flying power, and performing low-latitude flying using airborne Navigation and Flight Control System controls, and use is low Nil link realizes remote measuring and controlling and the communication of information transmission, implements the operation of low latitude operation by ground monitoring station.Main feature It is with advantage, 1) advantage with execution round-the-clock low-latitude flying operation round the clock, 2) without onboard flight human life safety Risk, 3) aircraft cost is low and homework precision is high, 4) by adaptive improvement design can be applied to maritime search and rescue with The fields such as supervision, agricultural remote sensing, airborne geophysical prospecting.

The present invention is integrated with low latitude anti-crash technology, low latitude link communication technology and UAV system technology, proposes to be adapted to The pneumatic general layout design with power of the fixed-wing unmanned plane of low latitude operation, there is provided be adapted to the new of low latitude operation and safe flight It is laid out UAV system.It covers flight control, ground monitoring, navigation is led to over the horizon in high precision in the low latitude of operating area The technologies such as letter, navigation monitoring system, and corresponding airworthiness standard on aircraft and authorization regulation, flying area laws and regulations on the management, driver The renewal of the full industry value chain such as Training Methodology, Aircraft Design and manufacturing technology, low-latitude flying operation and business model and hair Exhibition.Operation UAV system technology in low latitude can be applied to the low latitude agricultural plant protection of General Aviation, rescue at sea with supervision and extensively Industrial or agricultural aerospace applications, be adapted to carry out the manned general aviation aircraft of existing low latitude operation unmanned repacking to design, Facilitate General Aviation industry new development.

Brief description of the drawings

Fig. 1 is the unmanned plane structure diagram of the thrust type engine of the present invention；

Fig. 2 is the side view of Fig. 1；

Fig. 3 is the unmanned plane structure diagram of the drawing type engine of the present invention；

Fig. 4 is the side view of Fig. 3；

Fig. 5 is low latitude operation safeguards system schematic diagram (ground monitoring station, the signal base station of Active workings arrangement).

Mark in attached drawing for：1- fuselages, 2- skid landing gears, 3- airscrew engines, 4- empennages, 5- wings, 6- Spray appliance, 7- operation aircrafts, 8-4G communication base stations, 9- navigation difference station, 10- ground monitorings station.

Embodiment

Below in conjunction with the attached drawing in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clear, complete Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.It is based on Embodiment in the present invention, those of ordinary skill in the art are obtained every other without making creative work Embodiment, belongs to the scope of protection of the invention.

Fig. 1 and Fig. 3 respectively show the unmanned plane structure of thrust type engine and the nothing of drawing type engine of the present invention Man-machine structure, Fig. 2 and Fig. 4 are the side view of Fig. 1 and Fig. 3 respectively.

As can be seen that this unmanned plane of the present invention mainly includes fuselage 1, wing 5, empennage 4, skid landing gear 2, spiral shell Revolve paddle motor 3 and spray appliance 6.Fig. 5 illustrates the composition of the control system of the unmanned plane, including Fig. 1 using the present invention- The operation aircraft 7 of structure shown in 4, sets navigation difference station 9 and 4G communication base stations in the job area of the operation aircraft 7 8, while fixed or portable ground monitoring station 10 is set.

Described in detail below by two specific embodiments.

Embodiment 1：

A kind of low latitude operation agricultural plant protection unmanned plane of Technical Design according to the invention, and being adapted to property is reequiped Equipment is especially applied to the airborne geophysical prospecting of low-latitude flying to expand purposes.

Technical indicator is flying height 3000m, 5-20 meters of operation flying height, weight of spraying insecticide 400kg, and sprinkling is wide About 50 meters, the normal take-off weight 1850kg of aircraft, operation flight average speed 120km/h, cruising time 12h of degree.The machine designs It is as follows：Using low-wing configuration, two airscrew engines 3 are selected in 18 meters of the span, every 130-160 horsepowers.As shown in Figure 1, Figure 2 Shown, the installation of the lower section of fuselage 5 is used for the spray appliance 6 and liquid spout sprayed insecticide, and 6 structure of spray appliance is pipe-line equipment, The both ends of the length of pipe-line equipment suitably 5 length of prominent wing.Two airscrew engines 3 are installed on the fuselage above lower single-blade 1 back both sides, using one section of aerofoil profile drag reduction girder structure short limb and be connected to 1 back of fuselage, airfoil structure short limb is as flat Both ends respectively one engine of installation is carried on a shoulder pole, and the selection of drawing type engine propeller is preposition and protrudes the leading edge of a wing, it is such to bear The installation of formula engine can reduce interference of the blowing gas stream to sprinkling object under wing after propeller, use rear-mounted propeller engine 3 instead When, inlet channel installation guard prevents foreign matter from entering windward for it.Empennage 4 is laid out using T-shaped horizontal tail is above put, the another kind of empennage 4 Selecting type scheme is to use Bi-Tail-Boom Layout, and Bi-Tail-Boom Layout is suitable for the magnetic spy bar of 1 afterbody of fuselage installation airborne geophysical prospecting.Fuselage The hatch door of 1 cargo compartment is arranged on the rear portion of fuselage 1, and cargo compartment simultaneously sets liquid pesticide to inject lid, and sprinkling medicine passes through pressure The spraying pipe of spray appliance 6 is injected in pumping.Fuel tank is arranged on the both sides in fuselage 1, by fuel pump to engine oil. All design prevents the partition plate that liquid or medicinal powder flow in fuel tank and cargo compartment, is commonly called as anti-sloshing baffles.Meanwhile can be with inside cargo compartment Set up two or more independent cabins separately, load the sprinkling object of different pesticide concentrations respectively.Fuselage 1, wing 5, empennage 4, sprinkling The conducting system of antistatic is all designed on equipment 6, skid landing gear 2 and each airborne equipment, discharge brush is arranged on wing 5 and tail The trailing edge of the wing 4, and can be needed to select on each prominent surface and leading edge design anti-frozen structure material or coating according to user, can In the harm that slight icing meteorology environment in-flight prevents from slightly freezing.1 outer both sides of fuselage installation slide-type undercarriage 2, skid Front and back end bending upwarps, and skid bottom making rub resistance material, the main unit of landing gear and nose-gear pillar on skid Upper end is all connected in Telescopic buffer mechanism on the fuselage 1.Wheel is slided under slide-type structure and undercarriage leg The outside of fuselage 1 at tie point is held, wheel tire protrudes the lower edge of skid.Two nose-gear wheels configure steering mechanism.Machine The airborne equipment for carrying navigation flight control and low latitude chain-circuit system is installed in 1 main structure of fuselage, and is connected on buffering plate, Also it is electromagnetically shielded and waterproofing design.The computer of navigation and flight control, controls engine speed and thrust, and control flies Row height, speed and the line of flight.The antenna of the three-in-one navigation equipments of GPS/BD/GL is installed on 1 back of fuselage, and low latitude link The antenna of system and navigation monitoring system is all separately mounted to 1 back of fuselage or the top of empennage 4 or 1 belly of fuselage.Fuselage 1 is anterior And multiple cameras are installed on periphery, and empennage 4, its image data is transmitted by low latitude link or 4G communication equipments, can be carried For ring fuselage full-view image.The equipment of sighting distance TTC channel selection index system distance 20km in the link of low latitude, is mainly used for aircraft The landing phases that take off monitoring and better economy.Ground monitoring station 10 is installed by transmitting-receiving process equipment and display monitoring navigation The man-machine interface of flight control information, installs the antenna and transmitting-receiving unit equipment of low latitude link, and installs navigation monitoring system ADS-B ground base stations and satellite navigation difference station 9, and voice communication device.

The low-latitude flying of the low latitude operation unmanned plane is highly controlled in 3-20 meters of height, about 50 meters of width of spraying insecticide, energy Enough round-the-clock flight operations.Peak of flight about 5000m.Airborne navigational system select GPS/BD/GL three-in-one antennas and satellite with Inertia combined navigation system, wherein a frame is used for the aircraft of operation course line calibration, change the outfit high performance RTK satellite navigations system System, and airborne earth observation video load system.Onboard flight Control System Design is timely quick to adjust flight pitching Torque parameter, keeps the quick control logic of flying height, according to the testing number of flying speed, height parameter and altitude rate Controlled according to for flying, sensing system of airbome windshear sensor and measurement height and combinations thereof system is used to detect height Change.The logical design selection nose-up pitching moment of flight control system parameter is more sensitive, and nose-down pitching moment keeps suppression course to face upward The upper angle till degree and acute variation at angle.Flight in complicated landform landforms such as massif hillside fields and mountainous region, airborne navigation subsystem The integrated navigation that landform track algorithm carries out depth is added, improves the safety precautions of avoidance and anticollision.The airborne navigation of the machine flies Row control system and low latitude link can change the outfit, a kind of general precision that can select to change the outfit on same aircaft configuration or A kind of high-precision airborne navigation and flight control, or the low latitude link of different bandwidth combination, and conveniently change the outfit and equally just Often flight, meets high level matches with low level of the user to the selectable differentiation of same aircraft, and height is used in high accuracy for a long time with aircraft Flight and complicated landform operation etc. need, low to be used in general job raising economy.

As shown in figure 5, to improve the control accuracy of the height of low latitude plant protection operation area flight and course line, it is certain in operation area Scope and place, set satellite navigation difference station 9.In order to use the low cost and broadband resource in low latitude and over the horizon 4G communications, In operation area, a certain range sets supplement 4G communication base stations 8 to improve the scope that 4G signals of communication cover.For 9 He of navigation difference station The power supply plan of 4G communication base stations 8, mainly using solar panel, conditional location can access the buried power supply in underground Circuit.Low latitude link configuration shortwave/ultra short wave communication radio station, the stronger good economy performance of independence of user, can improve low latitude ultraphotic Receiving ability away from on-board data, the positional information and boat of flight and flight operation are provided for the personnel at ground monitoring station 10 in time The monitoring means of line information.The communication of BD short messages as the link of beyond-the-horizon communication and emergency flight control, it is necessary to apply for user gradation, Byte is less and there are certain propagation delay time, for 4G communications and the alternate backup equipment in ultra short wave communication radio station.Pass through boat Row monitoring system and base station, ground monitoring station 10 can monitor its machine situation of periphery on course line in real time, there is provided safety flies Row information needed, especially aircraft enter operation area before and fulfil assignment the high height maked a return voyage ferry route on can send out Wave the guaranteeing role of monitoring airline operation safety.

Extended use：Aerial remote sensing loading device is installed, such as EO-1 hyperion/multispectral equipment, it is seen that light+laser radar etc., Available for low latitude agricultural remote sensing plant protection operation, including agricultural land detection and areal analysis, soil constituent analysis, plant seedling Rate, Disaster Loss Evaluation, terraced fields graphics etc..

Embodiment 2：

A kind of maritime search and rescue unmanned plane of Technical Design according to the invention, and being adapted to property conversion unit is to expand Big purposes, is especially applied to marine supervision.

The machine carries out 1 structure of fuselage repacking design, and carry out adaptability to mobile system based on embodiment 1 Curve guide impeller, so as to change and expand at lower cost the purposes of low latitude class of jobs UAV system.

As shown in Figure 3, Figure 4, two tension propeller engines 3 are arranged in 1 back of fuselage of the top of wing 5, the height Position layout is to reduce the interference of water wave, and tension propeller protrudes 5 leading edge of wing, and the pulling force of two engines is poor with pneumatic rudder Face forms stronger anti-side wind performance.Low-wing configuration is kept, empennage 4 is using the T-shaped configuration on fuselage.Fuel tank is preferentially installed In the same elevation structural close to the machine back of the body with 1 connection structure of engine short limb and fuselage, and it is laid out along before and after course, passes through oil Oil pump feed.1 cargo compartment section shape of fuselage still maintains up-narrow and down-wide trapezoidal, and the primary structure of embodiment 1 retains substantially to be continued to use. When 1 cargo cabin door of fuselage is arranged on rear body, empennage 4 is still using high-order T-shaped configuration, and 1 cargo cabin door of fuselage selects When being arranged on head, empennage 4 can be changed to use Bi-Tail-Boom Layout.Used in cargo compartment periphery and internal installation easy to rescue at sea Hand grab grip structure or guide mechanism with pedal.

Still main unit of landing gear and nose-gear pillar on 1 outer both sides of fuselage installation slide-type undercarriage 2, skid Upper end all connect in Telescopic buffer mechanism on the fuselage 1.Slide wheel and be installed on slide-type structure and undercarriage leg The outside of fuselage 1 at the tie point of lower end, wheel tire protrude the lower edge of skid.Two nose-gear wheels configure steering mechanism. As search and rescue purposes marine and waterborne, low-resistance line style floating drum is installed in skid structure, and keep wheel can be in ground taxi. The Radio Beacon of seawater trigger switch control is installed.Alternately configuration, undercarriage can also be redesigned using first three point type master Undercarriage and nose-gear configuration, including fixed and two kinds of deployable and collapsible.Equally, marine and water is connected on landing gear structure Upper floating drum.

According to the arrangement of the new position design lid of mobile system equipment on fuselage 1.Airborne navigation flight control system System, low latitude chain-circuit system and navigation monitoring system etc. equipment carry out adaptive improvement design, and may be selected using band with without subtracting The mounting means of Zhen Qi mechanisms.Wherein, required according to user, the aircraft used the neighbouring dense area of urban population in part is airborne System is changed to high-precision equipment, including satellite navigation chooses to install RTK system, and flight control system selects triplex redundance flight control Computer equipment processed.The backup link of low latitude link is passed using the remote measuring and controlling that sighting distance+satellite relay or aviation relay and information Defeated system, including the use country " big S " satellite links, wherein, satellite relay remote measuring and controlling and the information transmission system are made Communicated with using the intermittent mode to star on and off, to save communication cost.Mobile system antenna accordingly adjusts layout.Its The function of his mobile system and the function at ground monitoring station 10 retain.

The machine is as above after Curve guide impeller, suitable for purposes such as marine/waterborne rescue and monitoring.

Certainly, the above is the concrete application example of the present invention, and the present invention also has other embodiments, all using equivalent The technical solution that replacement or equivalent transformation are formed, all falls within protection domain of the presently claimed invention.

Claims (6)

1. A kind of 1. low-latitude flying operation unmanned plane, it is characterised in that：Along the installation in course on the load-carrying construction on the outside of fuselage (1) Angle is with the power transmission angle installation main unit of landing gear designed and the buffer gear of nose-gear pillar, main unit of landing gear and preceding The upper end for falling post setting connects the buffer gear respectively；The lower end of main unit of landing gear and nose-gear pillar is connected to become skid Formula undercarriage (2) structure.
2. 2. low-latitude flying operation unmanned plane according to claim 1, it is characterised in that：In slide-type undercarriage (2) structure Contact the surface installation antifriction material on ground, the cutting equipment of installation and skid insulation at the preceding tilting end of skid；Undercarriage The lower semisection of pillar connection skid is designed to outer slash on the outside of fuselage (1)；Under main unit of landing gear and nose-gear pillar End is installed on the wheel of ground taxi, wherein preceding wheel is connected in steering mechanism；Skid outside install water float bowl and Wheel is kept to roll and turn on the ground.
3. 3. low-latitude flying operation unmanned plane according to claim 2, it is characterised in that：The wing (5) and machine of single-blade layout Body (1) load-carrying construction is connected to agent structure, and fuel oil is installed in coplanar upper with the agent structure and along wing (5) course Case；Double-vane be laid out in the case of to install the wing of engine as host wing, and host wing is connected to fuselage load-carrying construction Agent structure；Airborne Navigation Control and chain-circuit system installation is on the body construction；Fuselage（1）What section was linearly connected with camber line Polygon and joint angle are inscribed arc-shaped transition；Wing type selecting and the layout details of fuselage appearance are designed to high lift-drag ratio aerodynamic force Configuration；

   For low-wing configuration, rectangle or up-narrow and down-wide cross sectional shape may be selected in fuselage (1) cross sectional shape above agent structure Coordinate the installation of slide-type undercarriage (2) system, the inner space of the fuselage (1) is as the cargo compartment for loading purposes, by fuel oil Case changes position and is installed on cargo compartment two side；

   For shoulder-wing configuration, fuselage (1) side wall below agent structure selects up-narrow and down-wide cross sectional shape to coordinate slide-type The installation of undercarriage (2) system, the inner space of the fuselage (1) is as the cargo compartment for loading purposes；Cargo compartment is needed according to operation Divide the cargo compartment unit for loading different objects；The selection of the arrangement of the hatch door of cargo compartment or lid is in fuselage (1) tail on fuselage Portion or head or belly.
4. 4. low-latitude flying operation unmanned plane according to claim 3, it is characterised in that：Installation sprinkling powder below wing (5) The spray appliance of shape or liquid object (6) and spout, the spray appliance are arranged on the course front end of wing (5) trailing edge purling；

   For low-wing configuration, spray appliance (6) and spout are continuously arranged along lower section of wing (5) length containing fuselage (1)；

   For shoulder-wing configuration, spray appliance (6) is continuously arranged along wing (5) length and fuselage outer side, and sprays the spray of object Mouth is only arranged under wing (5) and just under fuselage (1), forms the continuous ejiction opening layout along wing (5) length.
5. 5. low-latitude flying operation unmanned plane according to claim 3, it is characterised in that：Wing installs propeller type on (5) Or turbogenerator, separate unit or more；

   Using vectored thrust mechanism is configured during a single engine to it, one kind is using installation universal joint in propeller shaft and watches Mechanism is taken, a kind of is bias current pipe/plate using turbogenerator jet, and one kind is that fuselage both sides respectively increase by one low thrust of installation Aid in jet engine；The installation site of a single engine is selected in head or the machine back of the body or tail and is installed along axes of aircraft；

   For shoulder-wing configuration, during using two engines, the installation site of two engines is selected in wing (5) or fuselage (1) Or each installation one in left and right on empennage (4), and use thrust type or tension propeller configuration；

   For low-wing configuration, the design and installations of the two engines both sides above fuselage (1), using the beam type knot of aerofoil profile drag reduction Structure is simultaneously connected to fuselage (1) back, fuel oil can be loaded inside the aerofoil profile girder construction, and engine prop selection tensile force type is preposition And prominent wing (5) leading edge or selection thrust type postposition and prominent wing (5) trailing edge.
6. 6. low-latitude flying operation unmanned plane according to claim 1, it is characterised in that：Full machine structure includes fuselage (1), machine Install and coat anti-freeze material in the surface of the wing (5), empennage (4) and engine, its leading edge and protruding parts.