Summary of the invention
In view of this, the utility model be directed to it is a kind of can VTOL Fixed Wing AirVehicle, can VTOL,Energy level run speed is fast again, high reliablity.
In order to achieve the above objectives, the technical solution of the utility model is achieved in that
A kind of Fixed Wing AirVehicle of energy VTOL, including inclining rotary mechanism, the inclining rotary mechanism include steering engine, tiliting axisAnd tilter；The steering engine is set in fuselage by steering engine mounting base；Tiliting axis penetrates wing in parallel, protrudes into inclining in wingRoller end is connected by axle sleeve with the steering engine wheel disc of steering engine, and the tiliting axis end stretched out outside wing is fixedly connected with tilter,Screw mechanism is set on the tilter.
Further, two groups of inclining rotary mechanisms are symmetrical arranged centered on fuselage central axes.
Further, the screw mechanism includes motor, shaft and propeller, and the shaft is rotated by bearing and tilterConnection, the shaft free end above tilter are connected with propeller, are nested with and turn on the shaft outer wall below tilterAxis reducing gear, the motor are fixedly connected with tilter, and the electricity being meshed with shaft reducing gear is arranged on the motor output shaftMachine reducing gear.
Further, fixing set is respectively set in the two sides of tilter, is through in the tiliting axis in fixing set, tiliting axis andFix set is radially correspondingly arranged clamping hole, fixes bolt and is bolted in clamping hole.
Further, aileron is set far from head side on wing.
Further, wing reinforced shaft is respectively set at left and right sides of tiliting axis.
Further, wing girder is respectively set in the two sides up and down of tiliting axis, two wing girder ends are connected by buckleIt connects.
Further, the steering engine mounting base is fixed on fuselage mounting plate by wing attachment base, the wing attachment baseIt is upper that the connecting plate perpendicular with it is set, wing reinforced shaft connecting hole is respectively set on the connecting plate and is connected with wing girderHole.
Further, the empennage is set as twin vertical fin structure, including lateral empennage and is set to hanging down for lateral empennage both endsElevator is arranged in the end of straight tail, the transverse direction empennage, and rudder is respectively set in the end of the vertical tail.
Further, the fuselage includes stringer and bulkhead, and the stringer and bulkhead grafting support, the fuselage surface are overcoatingMask.
Compared with the existing technology, a kind of Fixed Wing AirVehicle of energy VTOL described in the utility model has following excellentGesture:
1, fuselage and wing are the structure of Fixed Wing AirVehicle, and the advantage with Fixed Wing AirVehicle, voyage is remote, level fliesScanning frequency degree is fast；And rotor is set in the wing end pin of Fixed Wing AirVehicle, realize energy VTOL, the ability of vertical flight makesIts aircraft can have both the advantage of the two simultaneously.
2, steering engine and tiliting axis are separately positioned in fuselage and wing, and space utilization rate is high, ingenious in design.
Specific embodiment
It should be noted that in the absence of conflict, the feature in the embodiments of the present invention and embodiment canTo be combined with each other.
In the description of the present invention, it should be understood that term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" isIt is based on the orientation or positional relationship shown in the drawings, is merely for convenience of describing the present invention and simplifying the description, rather than indicateOr imply that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore cannot understandTo limit the utility model.In addition, term " first ", " second " etc. are used for description purposes only, and should not be understood as instruction orIt implies relative importance or implicitly indicates the quantity of indicated technical characteristic." first ", " second " etc. are defined as a result,Feature can explicitly or implicitly include one or more of the features.In the description of the present invention, unless otherwiseIllustrate, the meaning of " plurality " is two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacifiedDress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrallyConnection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,It can be the connection inside two elements.For the ordinary skill in the art, on being understood by concrete conditionState the concrete meaning of term in the present invention.
The utility model will be described in detail below with reference to the accompanying drawings and embodiments.
Picture 1-4, a kind of Fixed Wing AirVehicle of energy VTOL, including inclining rotary mechanism, the inclining rotary mechanism include rudderMachine 1, tiliting axis 2 and tilter 3；The steering engine 1 is set in fuselage 5 by steering engine mounting base 12；Tiliting axis 2 penetrates machine in parallelThe wing 6,2 end of tiliting axis protruded into wing 6 are connected by axle sleeve 13 with the steering engine wheel disc 11 of steering engine 1, and inclining outside wing 6 is stretched out2 end of shaft is fixedly connected with tilter 3, and screw mechanism is arranged on the tilter 3.
Fuselage 5 and wing 6 are the structure of Fixed Wing AirVehicle, and the advantage with Fixed Wing AirVehicle, voyage is remote, level fliesScanning frequency degree is fast；And rotor is set in 6 end pin of the wing of Fixed Wing AirVehicle, realize energy VTOL, the ability of vertical flight makesIts aircraft can have both the advantage of the two simultaneously.
Steering engine 1 and tiliting axis 2 are separately positioned in fuselage 5 and wing 6, and space utilization rate is high, ingenious in design.
Two groups of inclining rotary mechanisms are symmetrical arranged centered on 5 central axes of fuselage.Two groups are symmetrical arranged, aircraft may be implementedYawed flight.
The screw mechanism includes motor 41, shaft 42 and propeller 47, and the shaft 42 passes through bearing and 3 turns of tilterDynamic connection, 42 free end of shaft above tilter 3 are connected with propeller 47, outside the shaft 42 of 3 lower section of tilterShaft reducing gear 44 is nested on wall, the motor 41 is fixedly connected with tilter 3, is arranged on the output shaft of the motor 41 and is turnedThe decelerating through motor tooth 43 that axis reducing gear 44 is meshed.
Shaft reducing gear 44 and decelerating through motor tooth 43 engage, and not only act as the effect of the power output to motor 41, andThe tooth pitch ratio that the shaft reducing gear 44 and decelerating through motor tooth 43 engage is 4:1, also acts as the effect of speed adjusting.
Fixing set 45 is respectively set in the two sides of tilter 3, is through in fixing set 45 in the tiliting axis 2,2 He of tiliting axisFix set 45 is radially correspondingly arranged clamping hole, fixes bolt 46 and is bolted in clamping hole.
It fixes set 45 to be nested with tiliting axis 2, be spirally connected by fixing bolt 46, fixing is stablized, convenient disassembly, and design is reasonable.
Aileron 61 is set far from head side on wing 6.
Aileron 61 is set on wing 6, the rolling of aircraft can be controlled during aircraft flight.
The empennage is set as twin vertical fin structure, including lateral empennage 7 and is set to the vertical tail at lateral 7 both ends of empennage8, elevator 9 is arranged in the end of the transverse direction empennage 7, and rudder 10 is respectively set in the end of the vertical tail 8.
The elevator 9 being arranged on lateral empennage 7 controls the pitching of aircraft, the rudder of the end setting of vertical tail 8The yaw of 10 control aircraft.Whole design is to realize that aircraft controls the flight attitude of aircraft under fixed-wing mode.
Wing girder 63 is respectively set in the two sides up and down of tiliting axis 2, two 63 ends of wing girder are connected by buckle 64It connects.
Wing girder 63 plays the fixed effect of support to wing 6, and 63 end of wing girder is prevented by 64 connection of buckleThe deformation of wing 6 causes wing girder 63 to be absolved, and guarantees the stability of wing 6.
Wing reinforced shaft 62 is respectively set in the left and right sides of tiliting axis 2.
As the ancillary equipment of wing girder 63, plays the role of that wing 6 is reinforced supporting, is combined with wing girder 63,Dual fixed reinforcement, sturdy construction.
The steering engine mounting base 12 is fixed on fuselage mounting plate by wing attachment base 51, on the wing attachment base 51The connecting plate 52 perpendicular with it is set, wing reinforced shaft connecting hole 53 is respectively set on the connecting plate 52 and wing girder connectsConnect hole 54.
The fuselage 5 includes stringer 55 and bulkhead 56, and the stringer 55 and 56 grafting of bulkhead support, 5 surface of fuselageOvercoating mask.
Bulkhead 56 uses linden laminate, and stringer 55 uses carbon fiber pipe, and bulkhead 56 is fuselage ring, 55 grafting bulkhead of stringer56 run through entire fuselage 5, increase by 5 intensity of fuselage.Mask uses Ba Ersha cork wood.The quality of materials that overall structure uses is light, canBy property height, manufacturing cost is low, and processing technology is simple.
The course of work: steering engine 1 carries out angular adjustment to the bracket that verts by tiliting axis 2, to realize to screw mechanismControl, when aircraft vertical landing, screw mechanism drive is moved upwardly or downwardly；When aircraft tilts flight upward or downwardWhen, verted to screw mechanism certain angle using steering engine 1, while realizing aircraft vertical upward or downward, have forward orPulling force backward；When vehicle yaw, two symmetrically arranged inclining rotary mechanisms drive screw mechanism one to previous respectivelyYaw can be realized backward；When two inclining rotary mechanisms turn forward simultaneously to be turn 90 degrees, at this moment screw mechanism is only provided forwardPulling force, the rolling of aircraft can be controlled by carry-on aileron 61, the elevator 9 on empennage controls bowing for aircraftIt faces upward, rudder 10 controls the yaw of aircraft, to realize that aircraft controls the flight attitude of aircraft under fixed-wing mode.
The above is only the preferred embodiment of the utility model only, be not intended to limit the utility model spirit andWithin principle, any modification, equivalent replacement, improvement and so on be should be included within the scope of the utility model.