CN208181395U

CN208181395U - A kind of automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box

Info

Publication number: CN208181395U
Application number: CN201820711323.5U
Authority: CN
Inventors: 胡铃心; 李金龙
Original assignee: Tian Chang Aeronautical Technology Co Ltd
Current assignee: Tian Chang Aeronautical Technology Co Ltd
Priority date: 2018-05-14
Filing date: 2018-05-14
Publication date: 2018-12-04
Anticipated expiration: 2028-05-14

Abstract

The utility model relates to multi-rotor unmanned aerial vehicle technical fields, specifically, it is related to a kind of automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box, body housing including polygon, fuselage load box and battery frame have been sequentially arranged in the body housing, the body housing upper end is additionally provided with upper flap, carry plate is arranged in body housing lower end, undercarriage is arranged on carry plate, it directly avoids undercarriage and body housing is directly rigidly connected, it and is elastic connection between the upper connecting rod and lower connecting rod on undercarriage, in multi-rotor unmanned aerial vehicle descent, it can be mediated according to different road conditions, to reduce in descent, impact of the undercarriage to body housing, improve the service life of the utility model.

Description

A kind of automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box

Technical field:

The utility model relates to multi-rotor unmanned aerial vehicle technical fields, and in particular, to a kind of more rotors of automatic adaptation cushion formula Unmanned aerial vehicle body box.

Background technique:

Multi-rotor unmanned aerial vehicle is that there are two rotary wing aircrafts more than rotor shaft for a kind of tool.By the motor of each shaft end Rotation drives rotor to generate lifting power.The angle of rotor is fixed variable like that rather than helicopter.By changing not It can change the torque of propulsive force with the relative velocity between rotor, to control the running track of aircraft.Due to more rotors Fairly simple stabilization, currently practiced Multi-axis aircraft external form is much smaller with respect to for aircraft, thus is suitble to amateurish use.Because Multi-axis aircraft is easy to manufacture and controls, so being commonly used to production model and remotely-piloted vehicle.It common are four axis, six axis, eight Axis aircraft.Its small in size, light-weight therefore easy to carry, the various adverse circumstances that can be not easily accessible easily into people.Hair By now, the aerial missions such as film of taking photo by plane finds a view, monitors in real time, landform is explored have can be performed in Multi-axis aircraft for exhibition.

With the development of electronic multi-rotor unmanned aerial vehicle, the application field of multi-rotor unmanned aerial vehicle is more and more wider, the ruler of unmanned plane Very little and weight is also stepped up, and the performance requirement unmanned plane overall structure rigidity of multi-rotor unmanned aerial vehicle flight control computer is good at present Good, in order to meet rigidity requirement, current most of multi-rotor unmanned aerial vehicle fuselages use circular layout mode, use shell in structure The mode of whole load uses carbon fibre composite on material more.

It has been observed that most of electronic multi-rotor unmanned aerial vehicle fuselages use circular layout type at present, used in structure outer The mode of shell entirety load uses carbon fibre composite on material more.This master-plan has the disadvantage in that

1, power battery shape is Cubic at this stage, places space utilization rate not in ball or circular arc type fuselage It is high.

2, due to fuselage interior space utilization rate bottom, cause airborne equipment installation dispersion, need many cables to equipment into Row connection, increases the weight of cable.

3, fuselage is by the way of shell entirety load, and in order to ensure stiffness of fuselage, body shell is very thick, increases structure Weight.

4, it in order to install airborne equipment, needs to beat mounting hole on fuselage cover, destroys shell load path, reduce Structural strength.

5, round fuselage soaks that area is excessive, is easy the interference by prominent wind, reduces the safety of aircraft.

6, the undercarriage of multi-rotor unmanned aerial vehicle is usually and is directly installed in body housing, and undercarriage is in multi-rotor unmanned aerial vehicle Stress is larger during playing landing, and undercarriage is directly installed in body housing to will lead to body housing stress larger, reduces fuselage Shell itself service life reduces the safety coefficient of multi-rotor unmanned aerial vehicle fuselage box, meanwhile, existing landing gear structure is simple, is meeting It is high to complex road condition landing difficulty.

Utility model content:

The utility model overcomes the deficiencies of existing technologies, and provides a kind of automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box.

Technical problem to be solved in the utility model is implemented with the following technical solutions: a kind of automatic adaptation cushion formula mostly rotation Wing unmanned aerial vehicle body box, the body housing including polygon have been sequentially arranged fuselage load box and battery frame, institute in the body housing It states body housing upper end and is additionally provided with upper flap, the body housing bottom end is additionally provided with carry plate, the opening that carry plate two sides are equipped with Slot is for arranging undercarriage；The undercarriage includes fixing end, and the fixing end is hinged in open slot, is also set in fixing end There is back-shaped spring, fixing end lower end is fixedly connected with connecting rod, and the connecting rod is pierced by via open slot, and connecting rod is far from fixing end One end is also horizontal to be equipped with support rod, and the connecting rod includes upper connecting rod and lower connecting rod, and the upper connecting rod is far from fixing end One end there are also spring retention chamber, the lower connecting rod is slidably arranged in that spring retention is intracavitary, and the spring retention is intracavitary also sets There is spring, the spring one end is pressed on spring retention chamber bottom end, and the spring other end is pressed on the upper end of lower connecting rod.

Preferably, the body housing is hexagonal structure, and body housing includes fuselage frame and covering, and the covering is coated on Fuselage outer frame surface, the inwardly protruding formation carrier strip in fuselage frame lower end, the carrier strip is two, and the symmetrical cloth of carrier strip It sets in fuselage frame bottom two sides, each carrier strip one end close to each other is additionally provided with flange, and the fuselage load box is equipped with Connecting plate stick on flange.

Preferably, the frame of the fuselage load box generally hexagon shape, fuselage load box are integrally embedded in body housing Interior, fuselage load box side wall corresponding with the carrier strip bottom end is equipped with and the lower fixed strip of carrier strip cooperation, the connection Lower fixed strip side close to each other is arranged in plate, and fuselage load box upper end and lower fixed strip opposite position are additionally provided with fixation Item, fixed item and battery frame lower end connect firmly.

Preferably, fuselage frame side, which is additionally provided with, engraves hole for reducing own wt.

Preferably, integrally hexagonal frame structure, battery frame upper end are additionally provided with embedded in battery frame one end the battery frame Rectangular bearing frame, on rectangular bearing frame between upper fixed strip corresponding section and upper fixed strip via carbon pipe and hexagonal cup head Screw connects firmly, and through-hole is additionally provided on the battery frame side wall, the corresponding arrangement of the through-hole on the through-hole and fuselage shell side wall, described Rectangular bearing frame upper end is additionally provided with partition, and the rectangular space that each partition and fuselage shell side wall are enclosed is for installing electricity Pond.

Preferably, a gram horse button is additionally provided on the lateral wall of the body housing upper end, the upper flap is buckled in via a gram horse buckle Body housing upper end.

Compared with prior art, the application has the beneficial effect that

1, in the application, carry plate is arranged in body housing lower end, and undercarriage is arranged on carry plate, directly avoids Undercarriage and body housing are directly rigidly connected, and are elastic connection between the upper connecting rod and lower connecting rod on undercarriage, revolve more In wing unmanned plane descent, it can be mediated according to different road conditions, to reduce in descent, undercarriage is to body housing Impact, improve the service life of the utility model；

2, in the application, hexagon has effectively contained power battery, improves inner space utilization rate；

3, in the application, the design of unmanned aerial vehicle body box makes primary load bearing component be reduced to covering, fuselage load box, battery Frame, three parts are successively nested to be glued, and compared to more traditional fuselage interior frame structure, is greatly simplified mounting process, is dropped Low production cost；

4, in the application, since the body volume of hexagon reduces, fuselage interior equipment centralized arrangement is below battery frame Fuselage load box in, therefore can effectively shorten the overall length of fuselage interior cable, alleviate weight；

5, in the application, the boxlike load-carrying construction and small fuselage being made of fuselage frame and covering soak area can It is effective to mitigate construction weight.Actual weight measurement structure is shown: using the multi-rotor unmanned aerial vehicle of boxlike load-carrying construction, 1.2 In the case where rice wheelbase, it is capable of multi-rotor unmanned aerial vehicle construction weight of the fuselage of ratio by the way of shell entirety load and mitigates three / mono-, it is shown in Table 1.

6, in the application, in the case where accommodating the battery of same volume, the fuselage of hexagon compares round fuselage, soaks Area reduces 29.7%, reduces interference of the prominent wind to flight attitude, sees Fig. 8；

Detailed description of the invention:

FIG. 1 is a schematic structural view of the utility model；

Fig. 2 is Fig. 1 structural front view；

Fig. 3 is Fig. 2A-location A cross-sectional view；

Fig. 4 is body housing structural schematic diagram；

Fig. 5 is fuselage load case structure schematic diagram；

Fig. 6 is battery frame structural schematic diagram；

Fig. 7 is the application assembling schematic diagram；

Fig. 8 is round body housing and hexagon body housing and battery frame structural schematic diagram；

Fig. 9 is carry plate and landing gear structure schematic diagram；

In figure: 10~body housing；11~fuselage frame；12~carrier strip；13~flange；14~gram horse button；20~fuselage is held Power box；21~lower fixed strip；22~connecting plate；23~go up fixed strip；30~battery frame；31~rectangular bearing frame；32~carbon pipe； 40~upper flap；50~carry plate；51~open slot；60~undercarriage；61~fixing end；62~connecting rod；63~support rod； 64~upper connecting rod；65~spring retention chamber；66~lower connecting rod；67~spring.

Specific embodiment:

In order to be easy to understand the technical means, creative features, achievement of purpose, and effectiveness of the utility model, under Face combination is specifically illustrating and embodiment, furthers elucidate the utility model.

Embodiment 1:

As shown in Fig. 1~3, Fig. 7 and Fig. 9, a kind of automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box, including polygon Body housing 10 has been sequentially arranged fuselage load box 20 and battery frame 30 in body housing 10, and 10 upper end of body housing is additionally provided with upper flap 40,10 bottom end of body housing is additionally provided with carry plate 50, and the open slot 51 that 50 two sides of carry plate are equipped with is for arranging undercarriage 60；It rises and falls Frame 60 includes fixing end 61, and fixing end 61 is hinged in open slot 51, and back-shaped spring, fixing end lower end are additionally provided in fixing end 61 It is fixedly connected with connecting rod 62, connecting rod 62 is pierced by via open slot 51, and the one end of connecting rod 62 far from fixing end 61 also level is equipped with Support rod 63, connecting rod 62 include upper connecting rod 64 and lower connecting rod 66, and the one end of upper connecting rod 64 far from fixing end 61 is also Spring retention chamber 65, lower connecting rod 66 are slidably arranged in spring retention chamber 65, and spring 67, bullet are additionally provided in spring retention chamber 65 67 one end of spring is pressed on 65 bottom end of spring retention chamber, and 67 other end of spring is pressed on the upper end of lower connecting rod 66.

In the prior art, the undercarriage of multi-rotor unmanned aerial vehicle is usually and is directly installed in body housing, and undercarriage is more Rotor wing unmanned aerial vehicle rise landing during stress it is larger, undercarriage is directly installed in body housing will lead to body housing stress compared with Greatly, body housing itself service life is reduced, the safety coefficient of multi-rotor unmanned aerial vehicle fuselage box is reduced, meanwhile, existing undercarriage knot Structure is simple, and encountering, complex road condition landing difficulty is high, and in the application, for the setting of carry plate in body housing lower end, undercarriage 60 is to set It sets on carry plate 50, directly avoids undercarriage 60 and body housing 10 is directly rigidly connected, and the upper company on undercarriage 60 It is elastic connection between extension bar 64 and lower connecting rod 66, in multi-rotor unmanned aerial vehicle descent, can be carried out according to different road conditions It reconciles, to reduce in descent, impact of the undercarriage to body housing improves the service life of the utility model.

As shown in figure 4, body housing 10 is hexagonal structure, body housing 10 includes fuselage frame 11 and covering, and covering is coated on 11 outer surface of fuselage frame, the inwardly protruding formation carrier strip 12 in 11 lower end of fuselage frame, carrier strip 12 is two, and carrier strip 12 is symmetrical 11 two sides of the bottom of fuselage frame are arranged in, each carrier strip 12 one end close to each other is additionally provided with flange 13, sets on fuselage load box 20 Some connecting plates 22 stick on flange 13, in this way, the boxlike load-carrying construction and small machine that are made of fuselage frame 11 and covering Body, which soaks area, can effectively mitigate construction weight, and actual weight measurement structure is shown: using more rotations of boxlike load-carrying construction Wing unmanned plane is capable of multi-rotor unmanned aerial vehicle of the fuselage of ratio by the way of shell entirety load in the case where 1.2 meters of wheelbases Construction weight mitigates one third, is shown in Table 1.

As shown in figure 5, the frame of the generally hexagon shape of fuselage load box 20, fuselage load box 20 is whole to be embedded in fuselage In shell 10, the lower fixed strip 21 that 20 side wall corresponding with carrier strip 12 bottom end of fuselage load box is equipped with and carrier strip 12 cooperates, Lower fixed strip 21 side close to each other, 20 upper end of fuselage load box and lower 21 opposite position of fixed strip is arranged in connecting plate 22 It is additionally provided with fixed strip 23, upper fixed strip 23 and 30 lower end of battery frame connect firmly, and 11 side of fuselage frame is additionally provided with for reducing itself Weight engraves hole, in this way, since the body volume of hexagon reduces, fuselage interior equipment centralized arrangement is in battery in the application It in the fuselage load box 20 of 30 lower section of frame, therefore can effectively shorten the overall length of fuselage interior cable, alleviate weight.

As shown in fig. 6, the whole hexagonal frame structure of battery frame 30,30 upper end of battery frame is additionally provided with embedded in battery frame 30 The rectangular bearing frame 31 of one end, on rectangular bearing frame 31 between upper 23 corresponding section of fixed strip and upper fixed strip 23 via carbon Pipe 32 and hexagonal hexagonal socket head cap screw connect firmly, and through-hole, the through-hole pair on 10 side wall of through-hole and body housing are additionally provided on 30 side wall of battery frame It should arrange, rectangular 31 upper end of bearing frame is additionally provided with partition, and the rectangular space that each partition is enclosed with 10 side wall of body housing is used for Battery is installed and improves inner space utilization rate in this way, hexagon has effectively contained power battery.

Embodiment 2:

As shown in Figure 1, the present embodiment structure and the structure of embodiment one are essentially identical, something in common is repeated no more, different Place is: a gram horse button 14 is additionally provided on 10 upper end lateral wall of body housing, upper flap 40 is buckled in body housing via a gram horse button 14 10 upper ends, it is so easier for installation.

The measurement comparison of 1 1.2m unmanned plane construction weight of table

The characteristics of basic principles and main features and the utility model of the utility model have been shown and described above.Current row The technical staff of industry is described in above embodiments and description it should be appreciated that the present utility model is not limited to the above embodiments Only illustrate the principles of the present invention, on the premise of not departing from the spirit and scope of the utility model, the utility model is also It will have various changes and improvements, these changes and improvements are both fallen in the range of claimed invention.This is practical new The claimed range of type is defined by the appending claims and its equivalent thereof.

Claims

1. a kind of automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box, which is characterized in that the body housing (10) including polygon, institute It states in body housing (10) and has been sequentially arranged fuselage load box (20) and battery frame (30), body housing (10) upper end is additionally provided with Lid (40)；

Body housing (10) bottom end is additionally provided with carry plate (50), and the open slot (51) that carry plate (50) two sides are equipped with is used for It arranges undercarriage (60)；The undercarriage (60) includes fixing end (61), and the fixing end (61) is hinged on open slot (51) It is interior, back-shaped spring is additionally provided in fixing end (61), fixing end lower end is fixedly connected with connecting rod (62), and the connecting rod (62) is via opening Mouth slot (51) is pierced by, and the one end of connecting rod (62) far from fixing end (61) is also horizontal to be equipped with support rod (63), the connecting rod It (62) include upper connecting rod (64) and lower connecting rod (66), there are also bullets for the one end of the upper connecting rod (64) far from fixing end (61) Spring accommodating cavity (65), the lower connecting rod (66) are slidably arranged in spring retention chamber (65), in the spring retention chamber (65) It is additionally provided with spring (67), described spring (67) one end is pressed on spring retention chamber (65) bottom end, and spring (67) other end is pressed on The upper end of lower connecting rod (66).

2. automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box according to claim 1, which is characterized in that the fuselage Shell (10) is hexagonal structure, and body housing (10) includes fuselage frame (11) and covering, and the covering is coated on fuselage frame (11) outside Surface, the inwardly protruding formation carrier strip (12) in fuselage frame (11) lower end, the carrier strip (12) is two, and carrier strip (12) fuselage frame (11) two sides of the bottom are arranged symmetrically in, each carrier strip (12) one end close to each other is additionally provided with flange (13), the connecting plate (22) that the fuselage load box (20) is equipped with sticks on flange (13).

3. automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box according to claim 2, which is characterized in that the fuselage is held The frame of power box (20) generally hexagon shape, fuselage load box (20) are integrally embedded in body housing (10), and the fuselage is held Power box (20) side wall corresponding with carrier strip (12) bottom end is equipped with and the lower fixed strip (21) of carrier strip (12) cooperation, the company The side close to each other in lower fixed strip (21) is arranged in fishplate bar (22), and fuselage load box (20) upper end and lower fixed strip (21) are opposite Position is answered to be additionally provided with fixed strip (23), fixed item (23) and battery frame (30) lower end connect firmly.

4. automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box according to claim 3, which is characterized in that the fuselage frame (11) side, which is additionally provided with, engraves hole for reducing own wt.

5. automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box according to claim 3, which is characterized in that the battery frame (30) whole hexagonal frame structure, battery frame (30) upper end is additionally provided with the rectangular bearing frame embedded in battery frame (30) one end (31), on rectangular bearing frame (31) between upper fixed strip (23) corresponding section and upper fixed strip (23) via carbon pipe (32) and Hexagonal hexagonal socket head cap screw connects firmly, and is additionally provided with through-hole on battery frame (30) side wall, on the through-hole and body housing (10) side wall The corresponding arrangement of through-hole, rectangular bearing frame (31) upper end are additionally provided with partition, and each partition and body housing (10) side wall enclose The rectangular space of formation is for installing battery.

6. automatic adaptation cushion formula multi-rotor unmanned aerial vehicle fuselage box according to claim 1, which is characterized in that the body housing (10) a gram horse button (14) is additionally provided on the lateral wall of upper end, the upper flap (40) is buckled in body housing (10) via a gram horse button (14) Upper end.