CN210971492U - Aircraft with a flight control device - Google Patents

Abstract

The utility model discloses an aircraft, include: fuselage, fixed wing and fin part. The fixed wing links to each other with the fuselage, and the fin part is located the rear side of fuselage, and the fin part is including tail stay bar subassembly and the fin that links to each other, and the tail stay bar subassembly passes through the wing arm and links to each other with the fixed wing, and the fin links to each other with tail stay bar subassembly detachably, and tail stay bar subassembly rotationally links to each other or detachably links to each other with the wing arm. According to the utility model discloses the aircraft through linking to each other fin and tail boom assembly detachably, can make things convenient for the installation of fin, dismantlement and accomodating to rotationally link to each other or detachably links to each other through with tail boom assembly and wing arm, also made things convenient for accomodating of tail boom assembly, thereby made things convenient for the transportation and the depositing of aircraft, shared space when reducing the aircraft transportation and depositing.

Description

Aircraft with a flight control device

Technical Field

The utility model belongs to the technical field of the aircraft technique and specifically relates to an aircraft is related to.

Background

Among the correlation technique, fixed wing unmanned vehicles's volume is great, carries for the user and brings great puzzlement for the user, and the aircraft occupies great space when the transportation for the transportation is inconvenient.

SUMMERY OF THE UTILITY MODEL

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, an object of the utility model is to provide an aircraft, the fin of aircraft can be dismantled, and the tail stay subassembly can be dismantled or can be folded, has made things convenient for the transportation and the depositing of aircraft.

According to the utility model discloses aircraft, include: a body; the fixed wing is connected with the fuselage; the tail wing part, the tail wing part is located the rear side of fuselage, the tail wing part is including tail stay bar subassembly and the fin that links to each other, the tail stay bar subassembly pass through the wing arm with the fixed wing links to each other, the fin with tail stay bar subassembly detachably links to each other, the tail stay bar subassembly with the wing arm rotationally links to each other or detachably links to each other.

According to the utility model discloses the aircraft through linking to each other fin and tail boom assembly detachably, can make things convenient for the installation of fin, dismantlement and accomodating to rotationally link to each other or detachably links to each other through with tail boom assembly and wing arm, also made things convenient for accomodating of tail boom assembly, thereby made things convenient for the transportation and the depositing of aircraft, shared space when reducing the aircraft transportation and depositing.

According to some embodiments of the invention, the tail boom assembly is rotatably connected to the wing arm, the tail boom assembly is rotatable between a stowed position and a deployed position, the tail boom assembly extends in a side-to-side or fore-and-aft direction when the tail boom assembly is in the stowed position; the tail boom assembly extends in a fore-aft direction when the tail boom assembly is in the deployed position.

According to some optional embodiments of the utility model, be equipped with first pin joint spare on the wing arm, be equipped with second pin joint spare on the tail boom subassembly, first pin joint spare with the second pin joint spare rotationally links to each other.

Optionally, one of the first pivot member and the second pivot member is provided with a buckle, and the other is provided with a clamping groove matched with the buckle.

Furthermore, be equipped with on the first pin joint piece the buckle, be equipped with on the second pin joint piece the draw-in groove, the buckle with the first pin joint piece with the rotation hookup location of second pin joint piece sets up relatively, the draw-in groove with the rotation hookup location of first pin joint piece with the second pin joint piece sets up relatively.

Furthermore, be equipped with the location lug on the first pin joint piece, the location lug is located keeping away from of buckle one side at the center of first pin joint piece, be equipped with on the second pin joint piece with location lug complex location breach, the location breach is located keeping away from of draw-in groove one side at the center of second pin joint piece.

According to some embodiments of the utility model, the fin with be equipped with on one of the tail boom assembly peg graft protruding and be equipped with on the other with the protruding complex spliced eye of pegging graft.

According to some optional embodiments of the utility model, the tail vaulting pole subassembly includes tail vaulting pole and tail vaulting seat, the first end of tail vaulting pole with the wing arm links to each other, the tail vaulting seat cover is established the second end of tail vaulting pole, be formed with on the fin the grafting is protruding, be formed with on the tail vaulting seat the spliced eye.

According to some embodiments of the utility model, the tail stay bar subassembly is two and establishes respectively the left and right sides of fin, the fin is including two tail wing boards that link to each other, every the first end of tail wing board with correspond tail stay bar subassembly detachably links to each other, two the second end of tail wing board rotationally links to each other.

According to some embodiments of the utility model, the fin part is including establishing movable control surface on the fin, be equipped with on the tail stay subassembly and be used for the drive movable control surface pivoted steering wheel, the output shaft of steering wheel with movable control surface detachably links to each other.

According to some optional embodiments of the invention, the tail section comprises: the first connecting piece is provided with a first connecting groove and connected to one end, close to the movable control surface, of the steering engine, the end, close to the movable control surface, of the steering engine is accommodated in the first connecting groove, and an output shaft of the steering engine is detachably connected with the first connecting piece.

Further, the tail section includes: the output shaft of the steering engine is connected with the second connecting piece, one of the second connecting piece and the first connecting piece is provided with a clamping protrusion, and the other one of the second connecting piece and the first connecting piece is provided with a clamping groove matched with the clamping protrusion.

According to some embodiments of the utility model, inject in the fuselage and hold the chamber, the bottom of fuselage is formed with the intercommunication hold the heat dissipation channel of chamber and external environment.

According to some optional embodiments of the utility model, heat dissipation channel is a plurality of and a plurality of heat dissipation channel is arranged, every along controlling the direction interval heat dissipation channel extends along the fore-and-aft direction.

According to some optional embodiments of the utility model, the unit is established to the electricity of aircraft is transferred the unit hold the intracavity and be close to heat dissipation channel sets up.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is a perspective view of an aircraft according to some embodiments of the present invention;

FIG. 2 is an enlarged view at A in FIG. 1;

FIG. 3 is an enlarged view at B in FIG. 1;

FIG. 4 is a perspective view of the tail of the aircraft of FIG. 1, the tail being in a deployed state;

FIG. 5 is an enlarged view of C in FIG. 4;

FIG. 6 is a perspective view of the tail wing of the aircraft of FIG. 1, the tail wing being in a folded condition;

FIG. 7 is a schematic illustration of the connection of the first pivot and the second pivot of the aircraft of FIG. 1;

FIG. 8 is a perspective view of the first pivot member of FIG. 7;

FIG. 9 is a perspective view of the second pivot member of FIG. 7;

FIG. 10 is a perspective view of another angle of the aircraft of FIG. 1;

FIG. 11 is an enlarged view of D in FIG. 10;

FIG. 12 is a perspective view of a portion of the structure of the aircraft of FIG. 1;

FIG. 13 is an exploded schematic view of a stationary wing of the aircraft of FIG. 1;

FIG. 14 is a schematic view of the second panel of FIG. 13 engaged with the first connector;

FIG. 15 is a perspective view of the second panel of FIG. 13;

FIG. 16 is a perspective view of the first connector of FIG. 13;

FIG. 17 is a perspective view of the second connector of FIG. 13;

FIG. 18 is a schematic illustration of a portion of the structure of the aircraft of FIG. 1;

figure 19 is a perspective view of a fixed part of the aircraft in figure 18;

FIG. 20 is a perspective view of another angle of the stationary portion of the aircraft of FIG. 18;

FIG. 21 is a perspective view of a suspension frame of the aircraft of FIG. 1, with electronic components housed within the suspension frame;

FIG. 22 is a perspective view of the first suspension frame of FIG. 21;

FIG. 23 is a perspective view of the second suspension frame of FIG. 21;

figure 24 is an exploded view of a second power component of the aircraft of figure 1.

Reference numerals:

an aircraft 100;

a body 1; a body shell 11; a first mounting opening 111; a body upper cover 12; a body lower cover 13; a lower cover body 131; heat sinks 132; a heat dissipation channel 133; a first fixed frame 14; a second fixed frame 15; a first suspension frame 16; a bottom plate 161; a first peripheral plate 162; a second perimeter plate 164; a second suspension frame 17;

a fixed wing 2; a first wing panel 21; a support bar 211; a second wing section 22; a connecting rod 221; a fixed portion 23; a first connection hole 231; the second connection hole 232; the ailerons 24; a third connecting member 25; a fitting groove 251; a fourth connecting member 26; a fitting projection 261; a second connecting groove 262;

a wing arm 3; a first pivot member 31; a buckle 311; a positioning projection 312;

a tail fin 4; a tail wing plate 41; an insertion projection 411; a movable control surface 42; a first connecting member 43; a snap-fit projection 431; a first connecting groove 432; a second connecting member 44; a clip groove 441;

a tail stay bar 5; a second pivot member 51; a card slot 511; a positioning notch 512;

a tail stay seat 6;

a first power member 71; a first power unit 711; a first propeller 712; a second power component 72; a fixed seat 721; a mounting cavity 7211; an electrical tuning device 722; a second power unit 723; a second propeller 724;

a battery 81; a flight control unit 82; an electric tuning unit 83; a communication module 84; an aerial photography module 85.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.

An aircraft 100 according to an embodiment of the invention is described below with reference to fig. 1-24. This aircraft 100 can be unmanned vehicles, and this aircraft 100 can be used to fields such as aerial photography survey and drawing, electric power patrol and examine, environmental monitoring and disaster patrol. The aircraft 100 can take off and land at zero speed, has hovering capability and high horizontal flying speed, and can fly horizontally in a fixed wing flying mode.

As shown in fig. 1, 4 and 10, an aircraft 100 according to an embodiment of the invention includes: fuselage 1, fixed wing 2 and empennage part.

The fixed wings 2 are connected to the fuselage 1, for example, the fixed wings 2 may be two and two fixed wings 2 are respectively connected to the left and right sides of the fuselage 1, and the fixed wings 2 may lift the flight lift for the aircraft 100.

Alternatively, the fixed wing 2 may be detachably connected to the fuselage 1, so that when the aircraft 100 is not in use (for example, when the aircraft 100 is transported or stored), the fixed wing 2 may be detached from the fuselage 1, thereby reducing the occupied space of the aircraft 100 and facilitating the transportation and storage of the aircraft 100.

Further, the fixed wing 2 can include the wing section that the multistage connects gradually, and every two adjacent wing sections can be detachably continuous, can disassemble the separation to the fixed wing 2 from this for the fixed wing 2 can be disassembled into the multistage wing section, has reduced the occupation space of fixed wing 2 when not user state, thereby has further reduced the occupation space of aircraft 100 when not user state, has further made things convenient for the transportation and the depositing of aircraft 100.

The empennage part is positioned at the rear side of the fuselage 1 and comprises a tail stay rod assembly and an empennage 4 which are connected, the tail stay rod assembly is connected with the fixed wing 2 through a wing arm 3, the empennage 4 is detachably connected with the tail stay rod assembly, and the tail stay rod assembly is rotatably connected with the wing arm 3 or detachably connected. Thus, by detachably connecting the rear wing 4 to the tail stay assembly, the mounting, dismounting, maintenance, replacement, etc. of the rear wing 4 are facilitated. Moreover, the tail stay rod assembly is rotatably or detachably connected with the wing arm 3, so that the tail stay rod assembly is convenient to store.

When the aircraft 100 is not in use (for example, during transportation and storage of the aircraft 100), the tail fin 4 can be detached, and the tail stay rod assembly can be detached or folded by rotation, so that the overall occupied space of the aircraft 100 is reduced, and the transportation and storage of the aircraft 100 are facilitated. Of course, when the aircraft 100 is to be used, the tail boom assembly may be mounted to the wing arms 3 or rotated from the stowed position to the deployed position and the tail wing 4 mounted to the tail boom assembly.

Further, the aircraft 100 may further include a power assembly, the power assembly includes a first power member 71, the first power member 71 is connected to the fixed wing 2 through the wing arm 3, and the power assembly may provide flight power for the aircraft 100. For example, the power assembly includes four first power components 71 and the four first power components 71 are evenly distributed around the fuselage 1.

According to the utility model discloses aircraft 100 through linking to each other fin 4 and tail boom assembly detachably, can make things convenient for the installation of fin 4, dismantle and accomodate to rotationally link to each other or detachably links to each other through with tail boom assembly and wing arm 3, also made things convenient for accomodating of tail boom assembly, thereby made things convenient for aircraft 100's transportation and deposit, shared space when reducing aircraft 100 transportation and depositing.

According to some embodiments of the present invention, referring to fig. 1, 4 and 6, one of the tail fin 4 and the tail stay assembly is provided with an insertion protrusion 411 and the other is provided with an insertion hole engaged with the insertion protrusion 411. For example, when the tail fin 4 is provided with the insertion projection 411, the tail stay rod assembly is provided with an insertion hole; when the empennage 4 is provided with the inserting hole, the tail stay rod component is provided with an inserting bulge 411. Therefore, the empennage 4 and the tail stay rod assembly are connected through the matching of the inserting protrusion 411 and the inserting hole, the installation and the disassembly of the empennage 4 are further facilitated, the disassembling and assembling efficiency is high, and the connection reliability of the empennage 4 and the tail stay rod assembly can be ensured.

According to some optional embodiments of the utility model, referring to fig. 1, 4 and 6, the tail boom assembly includes tail boom 5 and tail boom seat 6, and the first end of tail boom 5 links to each other with wing arm 3, and the second end at tail boom 5 is established to tail boom seat 6 cover, is formed with grafting arch 411 on fin 4, is formed with the spliced eye on the tail boom seat 6. From this, through set up tail boom seat 6 on tail boom 5, and set up the spliced eye on tail boom seat 6, at the in-process of tail 4 and the many times dismouting of tail boom assembly, can avoid the wearing and tearing that tail boom 5 caused to damage even, tail boom seat 6 can play the effect of protection tail boom 5.

According to some embodiments of the present invention, referring to fig. 1, 4 and 6, the tail stay rod assemblies are two and are respectively disposed at the left and right sides of the tail wing 4, the tail wing 4 includes two tail wing plates 41 connected to each other, a first end of each tail wing plate 41 is detachably connected to the corresponding tail stay rod assembly, and second ends of the two tail wing plates 41 are rotatably connected to each other. Thus, by providing the tail wing 4 to include two tail wing plates 41 rotatably connected, after the tail wing 4 is detached, the two tail wing plates 41 can be disposed on top of each other by rotation, so that the tail wing 4 can be folded, further reducing the space occupied when the aircraft 100 is transported and stored.

According to some embodiments of the present invention, referring to fig. 1, 3, 7-9, the tail boom assembly is rotatably connected to the wing arm 3, the tail boom assembly is rotatable between a stowed position and a deployed position, and the tail boom assembly extends in a left-right direction or a fore-aft direction when the tail boom assembly is in the stowed position. When the tail boom assembly is in the storage position, the tail boom assembly can rotate to extend along the left-right direction, and at the moment, the tail boom assembly and the fixed wing 2 can be arranged approximately in parallel and close to the fixed wing 2, so that the occupied space of the aircraft 100 can be reduced; when the tail boom assembly is in the storage position, if above-mentioned fixed wing 2 sets up to include the multistage wing section that can dismantle the connection in proper order, can pull down the wing section that is located the fuselage 1 one side of tail boom assembly of fixed wing 2, the rear end of tail boom assembly can rotate to the front side this moment so that the tail boom assembly is close to the part that fixed wing 2 did not dismantle along the fore-and-aft direction, and the tail boom assembly extends along the fore-and-aft direction this moment, also can reduce aircraft 100's occupation space. When the tail boom assembly is in the deployed position, the tail boom assembly extends in the fore-aft direction, allowing for normal flight of the aircraft 100. Thus, by rotatably connecting the tail boom assembly to the wing arm 3, deployment and storage of the tail boom assembly may be conveniently achieved by rotating the tail boom assembly, further reducing the space occupied by the aircraft 100 when transported and stored.

According to some optional embodiments of the present invention, referring to fig. 1, fig. 3, fig. 7-fig. 9, the wing arm 3 is provided with a first pivot 31, the tail stay rod assembly is provided with a second pivot 51, and the first pivot 31 is rotatably connected to the second pivot 51. From this, through set up first pin joint piece 31 on wing arm 3, and set up second pin joint piece 51 on the tail boom subassembly simultaneously, conveniently realize wing arm 3 and tail boom subassembly and rotate to be connected to can avoid many times to rotate the wearing and tearing of in-process to wing arm 3 and tail boom subassembly.

Alternatively, referring to fig. 7-9, one of the first pivot member 31 and the second pivot member 51 is provided with a latch 311, and the other is provided with a slot 511 for engaging with the latch 311. For example, when the first pivot member 31 is provided with the buckle 311, the second pivot member 51 is provided with the slot 511; when the first pivot member 31 is disposed with the slot 511, the second pivot member 51 is disposed with the latch 311. Therefore, when the first pivoting piece 31 and the second pivoting piece 51 are rotatably connected, the connection strength and the connection reliability of the first pivoting piece 31 and the second pivoting piece 51 can be ensured through the matching of the arranged buckle 311 and the clamping groove 511, and the unlocking and the locking of the rotation between the first pivoting piece 31 and the second pivoting piece 51 are facilitated.

For example, when the tail boom assembly needs to be rotated from the unfolding position to the storage position, the buckle 311 and the slot 511 may be disengaged, and at this time, the second pivot 51 may rotate relative to the first pivot 31, so that the tail boom assembly may be rotated to the storage position relative to the wing arm 3; when the need rotated the tail boom assembly to the expansion position by the storage position, because buckle 311 and draw-in groove 511 are the disengaged state, second pivot 51 can rotate first pivot 31 relatively this moment, thereby can realize that the relative wing arm 3 of tail boom assembly rotates to the expansion position, then make buckle 311 and draw-in groove 511 cooperation, thereby can lock second pivot 51 relative first pivot 31, also can make the relative wing arm 3 of tail boom assembly lock, guarantee the reliable connection between tail boom assembly and the wing arm 3.

Further, referring to fig. 7-9, a buckle 311 is disposed on the first pivot member 31, a slot 511 is disposed on the second pivot member 51, the buckle 311 is disposed opposite to the rotational connection position of the first pivot member 31 and the second pivot member 51, and the slot 511 is disposed opposite to the rotational connection position of the first pivot member 31 and the second pivot member 51. Therefore, the connecting structure between the first pivot part 31 and the second pivot part 51 can be arranged in a balanced manner, and the reliable connection between the first pivot part 31 and the second pivot part 51 can be further ensured, so that the reliable connection between the tail stay rod component and the wing arm 3 can be further ensured.

Further, referring to fig. 7-9, the first pivot member 31 is provided with a positioning protrusion 312, the positioning protrusion 312 is located on a side of the buckle 311 away from the center of the first pivot member 31, the second pivot member 51 is provided with a positioning notch 512 engaged with the positioning protrusion 312, and the positioning notch 512 is located on a side of the slot 511 away from the center of the second pivot member 51. Therefore, through the arrangement of the positioning bump 312 and the positioning notch 512, in the process of connecting and fixing the first pivot part 31 and the second pivot part 51 through the matching of the buckle 311 and the slot 511, the positioning bump 312 and the positioning notch 512 are quickly and accurately matched, so that the guiding and positioning functions can be provided for the matching of the slot 511 and the buckle 311, the accurate matching between the buckle 311 and the slot 511 is ensured, and the reliability of the connection between the first pivot part 31 and the second pivot part 51 can be further enhanced.

According to some embodiments of the present invention, referring to fig. 1, 2, 4-6, the tail part includes a movable control surface 42 provided on the tail 4, and a steering engine for driving the movable control surface 42 to rotate is provided on the tail stay assembly, so as to control the flight attitude of the aircraft 100 by controlling the rotation angle of the movable control surface 42, and the output shaft of the steering engine is detachably connected to the movable control surface 42. From this, through being used for driving movable rudder face 42 pivoted steering wheel setting on the tail stay assembly, and link to each other the output shaft and the movable rudder face 42 detachably of steering wheel simultaneously, when dismantling fin 4 from the tail stay assembly or when installing fin 4 to the tail stay assembly, make things convenient for steering wheel and movable rudder face 42 to separate fast and be connected, avoided setting up the communication cable on fin 4, fin 4's processing cost has been reduced, fin 4 and tail stay assembly are avoided at the in-process of dismouting simultaneously, need increase the communication cable joint between fin 4 and tail stay assembly, greatly increased aircraft 100's reliability.

According to some alternative embodiments of the invention, with reference to fig. 1, 2, 4-6, the tail part comprises: the first connecting piece 43 is provided with a first connecting groove 432, the first connecting piece 43 is connected to one end, adjacent to the steering engine, of the movable control surface 42, one end, adjacent to the steering engine, of the movable control surface 42 is accommodated in the first connecting groove 432, and an output shaft of the steering engine is detachably connected with the first connecting piece 43. From this, through set up first connecting piece 43 in the one end of the neighbouring steering wheel of activity rudder face 42, and make the one end of the neighbouring steering wheel of activity rudder face 42 hold in first connecting groove 432, make the output shaft of steering wheel and first connecting piece 43 detachably link to each other simultaneously, can strengthen the joint strength of steering wheel and activity rudder face 42. Alternatively, the first connecting member 43 may be a metal member.

Further, with reference to fig. 1, 2, 4-6, the tail section comprises: and an output shaft of the steering engine is connected with the second connecting piece 44, one of the second connecting piece 44 and the first connecting piece 43 is provided with a clamping protrusion 431, and the other one is provided with a clamping groove 441 matched with the clamping protrusion 431. For example, when the second connecting member 44 is provided with the clamping protrusion 431, the first connecting member 43 is provided with the clamping groove 441; when the second connecting member 44 is provided with the engaging groove 441, the first connecting member 43 is provided with an engaging protrusion 431. Therefore, when the steering engine works, the steering engine drives the second connecting piece 44 to rotate, and the movable control surface 42 can be driven to rotate due to the fact that the second connecting piece 44 is matched with the first connecting piece 43 through the clamping protrusion 431 and the clamping groove 441. The connection strength of the steering engine and the movable control surface 42 can be further enhanced through the arranged second connecting piece 44. The clamping protrusion 431 can be fixed relative to the clamping groove 441, and the clamping protrusion 431 can be movable in the clamping groove 441.

For example, in the example of fig. 2 and 5, the second connecting member 44 has a flat plate shape, one end of the second connecting member 44 is provided with a shaft hole engaged with an output shaft of a steering engine that drives the movable control surface 42, the other end of the second connecting member 44 is provided with a locking groove 441, the locking groove 441 extends in a direction from the one end of the second connecting member 44 to the other end of the second connecting member 44, the first connecting member 43 is provided with a locking protrusion 431, and the locking protrusion 431 is engaged in the locking groove 441. In the direction by the one end of second connecting piece 44 to the other end of second connecting piece 44, the size of joint groove 441 is greater than the protruding 431's of joint size, conveniently insert the protruding 431 of joint to joint groove 441 from this in, avoid appearing because the machining precision is not in place and lead to the protruding 431 of joint to be unable with the cooperation of joint groove 441, can reduce the machining precision to protruding 431 of joint and joint groove 441, reduce the processing cost.

According to some embodiments of the present invention, referring to fig. 10 and 11, a containing cavity is defined in the body 1, and a heat dissipation channel 133 communicating the containing cavity and the external environment is formed at the bottom of the body 1. Therefore, by arranging the heat dissipation channel 133 at the bottom of the fuselage 1, the heat in the accommodating cavity can be discharged to the external environment through the heat dissipation channel 133 by flowing air flow during the flight of the aircraft 100, and the heat dissipation performance of the fuselage 1 is improved.

For example, electronic components such as the electrical tilt unit 83 and the communication module 84 of the aircraft 100 are installed in the accommodating cavity of the fuselage 1, and heat generated by the electrical tilt unit 83 and the communication module 84 can be rapidly discharged to the external environment through the heat dissipation channel 133 by setting the heat dissipation channel 133 at the bottom of the fuselage 1. Wherein, when establishing the intracavity with the unit 83 of electrically tuning of aircraft 100, can be with the adjacent heat dissipation channel 133 setting of electrically tuning unit 83, electrically tuning unit 83 is used for controlling power component, and the heat of production is great, through setting up the adjacent heat dissipation channel 133 of unit 83 with electrically tuning, can discharge the heat that electrically tuning unit 83 produced to external environment through heat dissipation channel 133 fast.

According to some optional embodiments of the present invention, referring to fig. 10 and 11, the heat dissipation channel 133 is a plurality of heat dissipation channels 133, and each heat dissipation channel 133 extends along the front-back direction. Therefore, by arranging the plurality of heat dissipation channels 133, the heat dissipation area is increased, and the heat in the accommodating cavity can be quickly discharged. Also, by extending each heat dissipation channel 133 in the fore-aft direction, the airflow generated when flying with the aircraft 100 is in the fore-aft direction, and the airflow passing through this direction further quickly discharges the heat inside the accommodation chamber through the heat dissipation channel 133.

In the present invention, "a plurality" means two or more.

It should be noted that the directions "front, back, left, right, up, and down" of the present invention are relative to the flight direction of the aircraft 100.

An aircraft 100 according to an embodiment of the invention is described below with reference to fig. 1-24. The aircraft 100 is an unmanned aircraft.

Referring to fig. 1 and 10, in the present embodiment, the aircraft 100 is a bilaterally symmetric structure, and the aircraft 100 includes: fuselage 1, fixed wing 2, wing arm 3, power assembly, tail components, battery 81, flight control unit 82, electrical tilt unit 83, aerial photography module 85 and communication module 84.

Referring to fig. 1, 10, 12 and 13, the fixed wing 2 is two and is respectively disposed at the left and right sides of the fuselage 1, the power assembly includes four first power components 71 and one second power component 72, the four first power components 71 are uniformly distributed around the fuselage 1, each first power component 71 is connected with the fixed wing 2 through a wing arm 3, each wing arm 3 extends along the front-rear direction, two of the first power components 71 are distributed at the front and rear sides of the fixed wing 2 located at the left side, the other two first power components 71 are distributed at the front and rear sides of the fixed wing 2 located at the right side, and one second power component 72 is connected at the rear end of the fuselage 1. The empennage part is arranged at the rear side of the fuselage 1 and is positioned at the rear side of the second power part 72, the empennage part comprises two tail stay rod assemblies and an empennage 4, the two tail stay rod assemblies are respectively positioned at the left side and the right side of the empennage 4, and the two tail stay rod assemblies are respectively connected with the two wing arms 3 positioned at the rear side of the fixed wing 2.

Referring to fig. 10, 12, 13 and 18, a housing cavity is defined in the main body 1, and a battery 81, a flight control unit 82, an electric tilt unit 83 and a communication module 84 may be provided in the housing cavity, and an aerial photography module 85 is provided at a front side of the main body 1 and connected to the main body 1.

Specifically, referring to fig. 10, 12, 13 and 18, the fuselage 1 includes a solid fuselage frame and a fuselage shell 11 wrapped outside the fuselage frame, the fuselage frame defines the above-mentioned accommodating cavity therein, and the fuselage shell 11 is streamlined to reduce the flight resistance of the aircraft 100. The fuselage frame includes fixed frame and connects the suspension frame in fixed frame below. The fixing frame includes a first fixing frame 14 and a second fixing frame 15 which are coupled to each other in a fore-and-aft direction, and the battery 81 is accommodated in a space defined by the first fixing frame 14.

Referring to fig. 21 to 23, the hanging frame is located below the second fixing frame 15 and connected to the second fixing frame 15, the hanging frame includes a first hanging frame 16 and a second hanging frame 17 which are arranged and connected up and down, the first hanging frame 16 includes a bottom plate 161, a first peripheral plate 162 and a second peripheral plate 164, the first peripheral plate 162 and the second peripheral plate 164 are respectively located at upper and lower sides of the bottom plate 161, and the first peripheral plate 162 and the second peripheral plate 164 both extend around the circumference of the bottom plate 161. A first housing cavity with an open upper end is defined between the first peripheral plate 162 and the bottom plate 161, the communication module 84 is housed in the first housing cavity, a second housing cavity with an open lower end is defined between the second peripheral plate 164 and the bottom plate 161, and the flight control unit 82 is housed in the second housing cavity. The second suspension frame 17 is formed with a third accommodation chamber with an open upper end, and the electric tilt unit 83 is accommodated in the third accommodation chamber.

Referring to fig. 1, 10 to 13, the top and bottom of the body housing 11 are formed with a first mounting opening 111 and a second mounting opening, respectively, wherein the first mounting opening 111 corresponds to the first fixing frame 14, and the battery 81 received in the first fixing frame 14 can be taken out of the first mounting opening 111 or be mounted in the first fixing frame 14 from the first mounting opening 111. The second mounting opening is arranged opposite to the second hanging frame 17, so that the electric tuning unit 83 in the second hanging frame 17 and the communication module 84 in the first hanging frame 16 can be conveniently mounted and taken out.

Further, referring to fig. 10 to 13, the first mounting opening 111 is covered with a body upper cover 12, the body upper cover 12 is detachably connected to the body housing 11, and the second mounting opening is covered with a body lower cover 13, the body lower cover 13 is detachably connected to the body housing 11. The lower body cover 13 includes a lower cover body 131 and a plurality of cooling fins 132, a ventilation opening is formed on the lower cover body 131, the plurality of cooling fins 132 are installed at the ventilation opening and are arranged at intervals in the left-right direction, a cooling channel 133 is defined between two adjacent cooling fins 132, so that a plurality of cooling channels 133 arranged at intervals in the left-right direction can be defined, and each cooling channel 133 extends in the front-back direction. Wherein, a plurality of fin 132 all can with the diapire contact of second suspension frame 17 to can derive the heat that the electricity accent unit 83 that holds in the third holding intracavity produced to the outside of fuselage 1 fast. Alternatively, the heat sink 132 may be a metal plate, so that the heat dissipation effect may be enhanced, and a heat conductive silicone or a heat conductive silicone grease may be filled between the heat sink 132 and the bottom wall of the second suspension frame 17, so that the heat sink 132 is in sufficient contact with the bottom wall of the second suspension frame 17, and the heat dissipation effect is further improved.

Referring to fig. 12 to 15 and 18 to 20, each fixed wing 2 includes a first wing section 21 and a second wing section 22 connected to each other, and the first wing section 21 and the second wing section 22 are connected to each other by a fixing portion 23. Be equipped with two bracing pieces 211 and two bracing pieces 211 on first wing panel 21 and run through first wing panel 21 along left right direction, the one end of the neighbouring fuselage 1 of first wing panel 21 passes through bracing piece 211 and fuselage 1 detachably links to each other, the one end of keeping away from fuselage 1 of first wing panel 21 passes through bracing piece 211 and fixed part 23 detachably links to each other, be equipped with on the fixed part 23 with two bracing pieces 211 respectively two first connecting holes 231 of complex.

One end of the second wing section 22 adjacent to the body 1 is detachably connected to the fixing portion 23, two connecting rods 221 are arranged on the second wing section 22, and two second connecting holes 232 respectively matched with the two connecting rods 221 are arranged on the fixing portion 23. From this, through linking fixed wing 2 with fuselage 1 detachably, and fixed wing 2 sets up to include two wing sections that can dismantle the linking to each other, when aircraft 100 is in the non-use state, can pull down fixed wing 2 to can further split fixed wing 2 into two parts, thereby can reduce aircraft 100's occupation space, make things convenient for aircraft 100's transportation and deposit. One end of the second wing section 22, which is far away from the fuselage 1, is provided with a wingtip winglet, and the wingtip winglet and the second wing section 22 form an included angle so as to block the air bypass flow on the upper surface and the lower surface of the second wing section 22, thereby reducing the damage of the bypass flow to the lift force.

Among the four wing arms 3, two of the wing arms 3 are connected to the front and rear sides of one of the fixing portions 23, and the other two wing arms 3 are connected to the front and rear sides of the other fixing portion 23.

Alternatively, the airfoil of the fixed wing 2 may be of a lightweight material such as foam to reduce the weight of the aircraft 100. During production and processing, the airfoil surface of the fixed wing 2 and the fuselage shell 11 can be integrally formed, and streamline transition is formed between the airfoil surface of the fixed wing 2 and the fuselage shell 11, so that air resistance in flight can be reduced.

Further, a pitot tube may be disposed along the front edge of the first wing section 21, and the pitot tube may be used to measure the air flow rate of the aircraft 100 during flight to provide flight parameters for the flight of the aircraft 100. A communication cable is also connected between the first wing section 21 and the fuselage 1 so that the pitot tube on the first wing section 21 can be communicatively connected to the electronics on the fuselage 1. Preferably, the communication cable not only enables communication between the stationary wing 2 and the fuselage 1 but also provides power to the first power component 71 on the stationary wing 2.

Referring to fig. 12-15, an aileron 24 is further disposed at the trailing edge of the second wing section 22, and the aileron 24 can be flipped up and down relative to the fixed wing 2 to control the flight attitude of the aircraft 100. The flap 24 includes opposing upper and lower surfaces, the upper surface of the flap 24 being substantially flush with the top surface of the second section 22 and the lower surface of the flap 24 being substantially flush with the bottom surface of the second section 22. A steering engine for driving the ailerons 24 to turn is arranged in the first wing section 21 or on the fixing part 23, and the steering engine can control the wing surfaces of the ailerons 24, so that the flight direction of the aircraft 100 can be controlled. Specifically, a steering engine for driving the aileron 24 to turn is arranged in the first wing section 21 or on the fixing part 23, and an output shaft of the steering engine penetrates out along the side wall of the fixing part 23 and is connected with the aileron 24 through a connecting assembly so as to drive the aileron 24 to rotate.

Referring to fig. 13-17, the attachment assembly includes a third attachment member 25 attached to the output shaft of the steering engine and a fourth attachment member 26 secured to the aileron 24. Wherein, a matching groove 251 is formed on the third connecting piece 25, a matching protrusion 261 matched with the matching groove 251 is formed on one side of the fourth connecting piece 26, which faces the third connecting piece 25, which is fixed on the aileron 24, the fourth connecting piece 26 is provided with a second connecting groove 262, the fourth connecting piece 26 is connected at one end of the aileron 24, which is close to the steering engine, and one end of the aileron 24, which is close to the steering engine, is accommodated in the second connecting groove 262. When the first wing section 21 and the second wing section 22 are connected, the matching groove 251 on the third connecting piece 25 is matched with the matching protrusion 261 of the fourth connecting piece 26, so that the connection of a steering engine for driving the aileron 24 to rotate and the aileron 24 is conveniently realized.

In this embodiment, through setting up the steering wheel that is used for driving aileron 24 to rotate in first wing section 21 or on fixed part 23, the output shaft of this steering wheel wears out and is connected with aileron 24 through coupling assembling and rotates with drive aileron 24 along the fixed part 23 lateral wall, set up the communication cable on second wing section 22 has been avoided, the processing cost of second wing section 22 has been reduced, first wing section 21 and second wing section 22 have been avoided at the in-process of dismouting simultaneously, it connects to need increase the communication cable between first wing section 21 and second wing section 22, greatly increased aircraft 100's reliability.

Referring to fig. 1 and 10, the first power component 71 is used for providing the flight power for vertical take-off and landing of the unmanned aerial vehicle 100, so that the unmanned aerial vehicle 100 can be vertically taken off and landed. Specifically, the first power member 71 includes a first power unit 711 connected to the wing arm 3 and a first propeller 712 connected to the first power unit 711. Further, a wiring channel is provided in each wing arm 3 for accommodating a cable connected between the first power unit 711 and the first wing section 21, so as to supply power to the first power unit 711 through an electric circuit in the first wing section 21. In addition, the cable may further include a communication cable, and the communication cable may be connected to allow the main body 1 to acquire information such as the rotational speed of the first propeller 712.

Referring to fig. 1, 10 and 24, the second power unit 72 includes a fixed base 721, a second power unit 723 provided on the fixed base 721, and a second propeller 724 connected to the second power unit 723. The fixing seat 721 is integrally formed in a housing of a pillar shape to be adapted to the shape of the body housing 11. A mounting cavity 7211 is formed in the fixing seat 721, and the electric adjusting device 722 for adjusting the second power unit 723 may be disposed in the mounting cavity 7211. The fixing seat 721 is adapted to be fixed to the rear end of the second fixing frame 15.

Referring to fig. 1, 4-6, each tail boom assembly includes a tail boom 5 and a tail boom seat 6 extending in the front-rear direction, the tail boom seat 6 is sleeved on the rear end of the tail boom 5, and the front end of the tail boom 5 is connected to the corresponding wing arm 3. The empennage 4 comprises two empennage plates 41 which are arranged in an inverted V shape, the inverted V-shaped empennage 4 has the functions of a vertical tail and a horizontal tail of a common fixed wing, the structure weight is small, and the control efficiency is high. The first end of each tail wing plate 41 is provided with two insertion projections 411, and the corresponding tail stay seat 6 is provided with insertion holes respectively matched with the two insertion projections 411, so that the tail wing 4 can be detached to reduce the occupied space of the aircraft 100. Further, the second ends of the two tail wings 41 are rotatably connected, thereby allowing the two tail wings 41 to be folded with each other, and reducing the storage space of the detached tail wing 4.

Referring to fig. 1, 3, 7-9, two wing arms 3 located at the rear side of the fixed wing 2 are respectively provided with a first pivot piece 31, the front end of each tail stay 5 is provided with a second pivot piece 51, the first pivot piece 31 is rotatably connected with the second pivot piece 51, the first pivot piece 31 is provided with a buckle 311, the second pivot piece 51 is provided with a slot 511, and the buckle 311 and the slot 511 are both arranged opposite to the rotating connection positions of the first pivot piece 31 and the second pivot piece 51. Thus, after the tail wing 4 is removed, rotation of the tail boom assembly relative to the wing arms 3 may be achieved by relatively rotating the second pivot 51 and the first pivot 31, such that the tail boom assembly rotates to the stowed position to further reduce the footprint of the aircraft 100.

Further, referring to fig. 1, 2, 4-6, the tail wing part further includes a movable control surface 42 provided on the tail wing 4, a steering engine for driving the movable control surface 42 to rotate is provided in the tail support seat 6, the flying attitude of the aircraft 100 can be controlled by controlling the rotation angle of the movable control surface 42, and an output shaft of the steering engine passes through the side wall of the tail support seat 6 and is detachably connected with the movable control surface 42. From this, through being used for driving movable rudder face 42 pivoted steering wheel setting on the tail stay assembly, and link to each other the output shaft and the movable rudder face 42 detachably of steering wheel simultaneously, when dismantling fin 4 from the tail stay assembly or when installing fin 4 to the tail stay assembly, make things convenient for steering wheel and movable rudder face 42 to separate fast and be connected, avoided setting up the communication cable on fin 4, fin 4's processing cost has been reduced, fin 4 and tail stay assembly are avoided at the in-process of dismouting simultaneously, need increase the communication cable joint between fin 4 and tail stay assembly, greatly increased aircraft 100's reliability.

In particular, with reference to fig. 2, 4-6, the tail section comprises: the first connecting piece 43 is provided with a first connecting groove 432, the first connecting piece 43 is connected to one end, close to the steering engine, of the movable control surface 42, the end, close to the steering engine, of the movable control surface 42 is accommodated in the first connecting groove 432, and a clamping protrusion 431 is arranged on the first connecting piece 43. The output shaft of steering wheel links to each other with second connecting piece 44, is equipped with on the second connecting piece 44 with the protruding 431 complex joint groove 441 of joint. Therefore, when the steering engine works, the steering engine drives the second connecting piece 44 to rotate, and the movable control surface 42 can be driven to rotate due to the fact that the second connecting piece 44 is matched with the first connecting piece 43 through the clamping protrusion 431 and the clamping groove 441.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims (15)

1. An aircraft, characterized in that it comprises:

a body;

the fixed wing is connected with the fuselage;

the tail wing part, the tail wing part is located the rear side of fuselage, the tail wing part is including tail stay bar subassembly and the fin that links to each other, the tail stay bar subassembly pass through the wing arm with the fixed wing links to each other, the fin with tail stay bar subassembly detachably links to each other, the tail stay bar subassembly with the wing arm rotationally links to each other or detachably links to each other.

2. The aircraft of claim 1, wherein the tail boom assembly is rotatably connected to the wing arm, the tail boom assembly being rotatable between a stowed position and a deployed position, the tail boom assembly extending in a side-to-side or fore-aft direction when the tail boom assembly is in the stowed position; the tail boom assembly extends in a fore-aft direction when the tail boom assembly is in the deployed position.

3. The aircraft of claim 2, wherein the wing arms are provided with a first pivot, the tail boom assembly is provided with a second pivot, and the first pivot and the second pivot are rotatably connected.

4. The aircraft of claim 3, wherein one of the first pivot and the second pivot is provided with a catch and the other is provided with a catch cooperating with the catch.

5. The aircraft of claim 4, wherein the first pivot is provided with the buckle, the second pivot is provided with the slot, the buckle is disposed opposite to the rotational connection position of the first pivot and the second pivot, and the slot is disposed opposite to the rotational connection position of the first pivot and the second pivot.

6. The aircraft of claim 5, wherein the first pivot is provided with a positioning protrusion, the positioning protrusion is located on one side of the buckle away from the center of the first pivot, the second pivot is provided with a positioning notch matched with the positioning protrusion, and the positioning notch is located on one side of the clamping groove away from the center of the second pivot.

7. The aircraft of claim 1 wherein one of said tail fin and said tail boom assembly is provided with an insertion projection and the other is provided with an insertion hole for engaging said insertion projection.

8. The aircraft of claim 7, wherein the tail boom assembly comprises a tail boom and a tail boom seat, a first end of the tail boom is connected to the wing arm, the tail boom seat is sleeved on a second end of the tail boom, the tail wing is formed with the insertion protrusion, and the tail boom seat is formed with the insertion hole.

9. The vehicle of claim 1, wherein said tail boom assemblies are two and disposed on respective left and right sides of said tail wing, said tail wing including two tail wing panels connected together, a first end of each of said tail wing panels being removably connected to a corresponding said tail boom assembly, and a second end of each of said tail wing panels being rotatably connected.

10. The aircraft of claim 1, wherein the tail wing part comprises a movable control surface arranged on the tail wing, a steering engine for driving the movable control surface to rotate is arranged on the tail stay assembly, and an output shaft of the steering engine is detachably connected with the movable control surface.

11. The aircraft of claim 10, wherein the tail section comprises: the first connecting piece is provided with a first connecting groove and connected to one end, close to the movable control surface, of the steering engine, the end, close to the movable control surface, of the steering engine is accommodated in the first connecting groove, and an output shaft of the steering engine is detachably connected with the first connecting piece.

12. The aircraft of claim 11 wherein the tail section comprises: the output shaft of the steering engine is connected with the second connecting piece, one of the second connecting piece and the first connecting piece is provided with a clamping protrusion, and the other one of the second connecting piece and the first connecting piece is provided with a clamping groove matched with the clamping protrusion.

13. The aircraft according to any one of claims 1 to 12, characterized in that a housing cavity is defined in said fuselage, the bottom of said fuselage being formed with a heat dissipation channel communicating said housing cavity with the external environment.

14. The aircraft of claim 13, wherein the heat dissipation channel is plural and the plural heat dissipation channels are arranged at intervals in the left-right direction, and each of the heat dissipation channels extends in the front-rear direction.

15. The aircraft of claim 13, wherein the aircraft electrical tilt unit is disposed within the containment cavity and adjacent to the heat dissipation channel.

Images