CN208484828U - A kind of Fixed Wing AirVehicle of energy VTOL - Google Patents
A kind of Fixed Wing AirVehicle of energy VTOL Download PDFInfo
- Publication number
- CN208484828U CN208484828U CN201820696063.9U CN201820696063U CN208484828U CN 208484828 U CN208484828 U CN 208484828U CN 201820696063 U CN201820696063 U CN 201820696063U CN 208484828 U CN208484828 U CN 208484828U
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- wing
- tilter
- steering engine
- shaft
- airvehicle
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Abstract
The utility model provides a kind of Fixed Wing AirVehicle of energy VTOL, including inclining rotary mechanism, the inclining rotary mechanism include steering engine, tiliting axis and tilter；The steering engine is set in fuselage by steering engine mounting base；Tiliting axis penetrates wing in parallel, and the tiliting axis end protruded into wing 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, and screw mechanism is arranged on the tilter.It is described in the utility model it is a kind of can VTOL Fixed Wing AirVehicle, can VTOL and level run speed it is fast, high reliablity.
Description
Technical field
The utility model belongs to unmanned plane field, more particularly, to a kind of Fixed Wing AirVehicle with inclining rotary mechanism.
Background technique
Aircraft is by mankind's manufacture, can fly away from ground, in the instrument flying object of space flight.Model plane and small-sized in recent years
The fast development of aircraft brings convenience for activities such as aerial survey, scoutings in small size air.
Small aircraft is divided into Fixed Wing AirVehicle and rotor craft, the advantage of Fixed Wing AirVehicle be loading capacity it is big,
Horizontal flight speed is fast, voyage is remote and high reliablity, but needs landing runway, cannot complete VTOL movement；And rotor
Although aircraft horizontal direction speed does not have Fixed Wing AirVehicle block, it is irrealizable excellent with Fixed Wing AirVehicle
Gesture, advantage are to adapt to the landform of various complexity, can accomplish quick landing, hovering.
Therefore, designing a aircraft for having both both Fixed Wing AirVehicle and rotor craft advantage has important meaning
Justice.
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 axis
And tilter；The steering engine is set in fuselage by steering engine mounting base；Tiliting axis penetrates wing in parallel, protrudes into inclining in wing
Roller 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 tilter
Connection, the shaft free end above tilter are connected with propeller, are nested with and turn on the shaft outer wall below tilter
Axis reducing gear, the motor are fixedly connected with tilter, and the electricity being meshed with shaft reducing gear is arranged on the motor output shaft
Machine 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 and
Fix 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 buckle
It connects.
Further, the steering engine mounting base is fixed on fuselage mounting plate by wing attachment base, the wing attachment base
It 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 girder
Hole.
Further, the empennage is set as twin vertical fin structure, including lateral empennage and is set to hanging down for lateral empennage both ends
Elevator 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 overcoating
Mask.
Compared with the existing technology, a kind of Fixed Wing AirVehicle of energy VTOL described in the utility model has following excellent
Gesture:
1, fuselage and wing are the structure of Fixed Wing AirVehicle, and the advantage with Fixed Wing AirVehicle, voyage is remote, level flies
Scanning 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 makes
Its 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.
Detailed description of the invention
The attached drawing for constituting a part of the utility model is used to provide a further understanding of the present invention, this is practical new
The illustrative embodiments and their description of type are not constituteed improper limits to the present invention for explaining the utility model.?
In attached drawing:
Fig. 1 is a kind of Fixed Wing AirVehicle broken isometric signal of energy VTOL described in the utility model embodiment
Figure；
Fig. 2 is a kind of Fixed Wing AirVehicle section vertical view signal of energy VTOL described in the utility model embodiment
Figure；
Fig. 3 is part A enlarged diagram in Fig. 2；
Fig. 4 is tilter schematic diagram described in the utility model embodiment.
Description of symbols:
1- steering engine；11- steering engine wheel disc；12- steering engine mounting base；13- axle sleeve；2- tiliting axis；3- tilter；41- motor；
42- shaft；43- decelerating through motor tooth；44- shaft reducing gear；45- fixes set；46- fixes bolt；47- propeller；5- fuselage；
51- wing attachment base；52- connecting plate；53- wing reinforced shaft connecting hole；54- wing girder connecting hole；55- stringer；56- every
Frame；6- wing；61- aileron；62- wing reinforced shaft；63- wing girder；64- buckle；7- transverse direction empennage；8- vertical tail；9-
Elevator；10- rudder.
Specific embodiment
It should be noted that in the absence of conflict, the feature in the embodiments of the present invention and embodiment can
To 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" is
It 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 indicate
Or imply that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore cannot understand
To limit the utility model.In addition, term " first ", " second " etc. are used for description purposes only, and should not be understood as instruction or
It 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 otherwise
Illustrate, 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 pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；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 condition
State 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 rudder
Machine 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 parallel
The 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 out
2 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 flies
Scanning 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 makes
Its 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 implemented
Yawed flight.
The screw mechanism includes motor 41, shaft 42 and propeller 47, and the shaft 42 passes through bearing and 3 turns of tilter
Dynamic connection, 42 free end of shaft above tilter 3 are connected with propeller 47, outside the shaft 42 of 3 lower section of tilter
Shaft 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 turned
The 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, and
The 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 axis
Fix 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 empennage
8, 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 8
The 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 64
It 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 buckle
The 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 51
The 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 connects
Connect hole 54.
The fuselage 5 includes stringer 55 and bulkhead 56, and the stringer 55 and 56 grafting of bulkhead support, 5 surface of fuselage
Overcoating mask.
Bulkhead 56 uses linden laminate, and stringer 55 uses carbon fiber pipe, and bulkhead 56 is fuselage ring, 55 grafting bulkhead of stringer
56 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, can
By 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 mechanism
Control, when aircraft vertical landing, screw mechanism drive is moved upwardly or downwardly；When aircraft tilts flight upward or downward
When, verted to screw mechanism certain angle using steering engine 1, while realizing aircraft vertical upward or downward, have forward or
Pulling force backward；When vehicle yaw, two symmetrically arranged inclining rotary mechanisms drive screw mechanism one to previous respectively
Yaw 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 forward
Pulling force, the rolling of aircraft can be controlled by carry-on aileron 61, the elevator 9 on empennage controls bowing for aircraft
It 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 and
Within principle, any modification, equivalent replacement, improvement and so on be should be included within the scope of the utility model.
Claims (10)
1. a kind of Fixed Wing AirVehicle of energy VTOL, it is characterised in that: including inclining rotary mechanism, the inclining rotary mechanism includes rudder
Machine (1), tiliting axis (2) and tilter (3)；The steering engine (1) is set in fuselage (5) by steering engine mounting base (12)；It verts
Axis (2) penetrates wing (6) in parallel, protrudes into the steering engine that tiliting axis (2) end in wing (6) passes through axle sleeve (13) and steering engine (1)
Wheel disc (11) is connected, and stretches out tiliting axis (2) end of wing (6) outside and is fixedly connected with tilter (3), on the tilter (3)
Screw mechanism is set.
2. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 1, it is characterised in that: in fuselage (5)
Two groups of inclining rotary mechanisms are symmetrical arranged centered on axis.
3. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 2, it is characterised in that: the screw mechanism
Including motor (41), shaft (42) and propeller (47), the shaft (42) is rotatablely connected by bearing and tilter (3), position
Shaft (42) free end above tilter (3) is connected with propeller (47), and the shaft (42) below tilter (3) is outside
It is nested on wall shaft reducing gear (44), the motor (41) is fixedly connected with tilter (3), sets on motor (41) output shaft
Set the decelerating through motor tooth (43) being meshed with shaft reducing gear (44).
4. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 3, it is characterised in that: tilter (3)
Two sides are respectively set fixing and cover (45), are through in fixing set (45) in the tiliting axis (2), tiliting axis (2) and fixing set
(45) be radially correspondingly arranged clamping hole, fix bolt (46) and be bolted in clamping hole.
5. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 1, it is characterised in that: on wing (6)
Far from head side setting aileron (61).
6. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 1, it is characterised in that: in tiliting axis (2)
The left and right sides wing reinforced shaft (62) are respectively set.
7. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 6, it is characterised in that: in tiliting axis (2)
Two sides up and down be respectively set wing girder (63), two wing girder (63) ends pass through buckle (64) connection.
8. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 7, it is characterised in that: the steering engine installation
Seat (12) is fixed on fuselage mounting plate by wing attachment base (51), is arranged on the wing attachment base (51) perpendicular with it
Connecting plate (52), wing reinforced shaft connecting hole (53) and wing girder connecting hole is respectively set on the connecting plate (52)
(54)。
9. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 1, it is characterised in that: empennage is set as double
Vertical fin structure including lateral empennage (7) and is set to the vertical tail (8) at lateral empennage (7) both ends, the transverse direction empennage (7)
End be arranged elevator (9), rudder (10) are respectively set in the end of the vertical tail (8).
10. a kind of Fixed Wing AirVehicle of energy VTOL according to claim 1, it is characterised in that: the fuselage (5)
Including stringer (55) and bulkhead (56), the stringer (55) and bulkhead (56) grafting support, fuselage (5) surface is overcoating to be covered
Plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820696063.9U CN208484828U (en) | 2018-05-10 | 2018-05-10 | A kind of Fixed Wing AirVehicle of energy VTOL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820696063.9U CN208484828U (en) | 2018-05-10 | 2018-05-10 | A kind of Fixed Wing AirVehicle of energy VTOL |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208484828U true CN208484828U (en) | 2019-02-12 |
Family
ID=65253200
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820696063.9U Expired - Fee Related CN208484828U (en) | 2018-05-10 | 2018-05-10 | A kind of Fixed Wing AirVehicle of energy VTOL |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208484828U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109080824A (en) * | 2018-08-24 | 2018-12-25 | 中国民航大学 | A kind of Fixed Wing AirVehicle with tilted propeller |
| CN112009680A (en) * | 2020-08-26 | 2020-12-01 | 中国民航大学 | Double-duct fan vertical take-off and landing aircraft |
| CN112357049A (en) * | 2020-11-30 | 2021-02-12 | 中国特种飞行器研究所 | Carbon fiber reinforced aluminum alloy laminated plate impact-resistant unmanned aerial vehicle front cover structure |
-
2018
- 2018-05-10 CN CN201820696063.9U patent/CN208484828U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109080824A (en) * | 2018-08-24 | 2018-12-25 | 中国民航大学 | A kind of Fixed Wing AirVehicle with tilted propeller |
| CN112009680A (en) * | 2020-08-26 | 2020-12-01 | 中国民航大学 | Double-duct fan vertical take-off and landing aircraft |
| CN112009680B (en) * | 2020-08-26 | 2022-11-01 | 中国民航大学 | Double-duct fan vertical take-off and landing aircraft |
| CN112357049A (en) * | 2020-11-30 | 2021-02-12 | 中国特种飞行器研究所 | Carbon fiber reinforced aluminum alloy laminated plate impact-resistant unmanned aerial vehicle front cover structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190212 Termination date: 20190510 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |