CN107235144B - Aircraft protection casing and aircraft - Google Patents
Aircraft protection casing and aircraft Download PDFInfo
- Publication number
- CN107235144B CN107235144B CN201710579601.6A CN201710579601A CN107235144B CN 107235144 B CN107235144 B CN 107235144B CN 201710579601 A CN201710579601 A CN 201710579601A CN 107235144 B CN107235144 B CN 107235144B
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- aircraft
- grid bars
- framework
- protective cover
- flange
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
Abstract
The invention discloses an aircraft protective cover and an aircraft, comprising an upper protective cover and a lower protective cover, wherein the upper protective cover comprises a first framework and a plurality of first grid bars arranged on the first framework; the lower protective cover comprises a second framework and a plurality of second grid bars arranged on the second framework, and the second grid bars are arranged in one-to-one correspondence with the first grid bars; the cross sections of the first grid bars and the second grid bars are in wing shapes, the front edges of the wing shapes face upwards, the tail edges of the wing shapes face downwards, and the cross sections of the first grid bars and the second grid bars comprise gradually-expanded front portions and gradually-contracted rear portions along the flowing direction of fluid. The cross section shape of the wing profile and the arrangement form of the first grid bars and the second grid bars can effectively reduce the obstruction and turbulent flow of the aircraft protective cover to the airflow, reduce the power loss of the blade, prolong the endurance time of the battery, improve the blade efficiency and reduce the blade noise. The aircraft provided by the invention adopts the aircraft protective cover, so that the obstruction and turbulence to air flow are reduced, and the efficiency of the aircraft is improved.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft protective cover and an aircraft applying the protective cover.
Background
With the increasing development of aircraft technology, aircraft are widely used in the fields of aeronautical measurement, safety monitoring and the like. The propeller is an important component of an aircraft, and refers to a device for converting engine rotation power into propulsion by rotating blades in air or water. With the wider and wider application fields of aircrafts, the safety problem of the aircrafts is paid attention to, the full-protection type protective cover can fully protect the propellers of the aircrafts, but after the full-protection type protective cover is added to the aircrafts, the flow of fluid can be blocked, the efficiency of the blades is greatly reduced, and the power loss of the blades is increased. Because blade power loss is serious, the motor rotating speed is increased on the premise of the same thrust-weight ratio, so that the motor current is indirectly increased, the battery endurance is shortened, the endurance capacity is reduced, the blade noise is increased, and the customer experience is influenced.
Disclosure of Invention
The invention aims to provide an aircraft protective cover, which aims to solve the technical problems of low blade efficiency, high blade power loss, high motor current, short battery endurance and high blade noise caused by the fact that the protective cover influences fluid flow in the prior art.
The technical scheme adopted by the invention is as follows:
an aircraft shield comprising:
the upper protective cover comprises a first framework and a plurality of first grid bars arranged on the first framework;
the lower protective cover comprises a second framework and a plurality of second grid bars arranged on the second framework, and the second grid bars are arranged in one-to-one correspondence with the first grid bars;
the cross section shapes of the first grid bars and the second grid bars are wing shapes, the front edges of the wing shapes face upwards, the tail edges of the wing shapes face downwards, and the cross sections of the first grid bars and the cross sections of the second grid bars comprise gradually-expanded front portions and gradually-contracted rear portions along the flowing direction of fluid.
The first framework is provided with a plurality of hollowed-out parts, and each hollowed-out part is internally provided with a plurality of first grid bars.
The first grid bars are arc-shaped and are distributed along the direction away from the center of the first framework.
Wherein, the upper shield with lower shield can dismantle the connection.
The positioning columns extend towards the second framework, positioning grooves matched with the positioning columns are formed in the second framework, and the positioning columns are clamped with the positioning grooves.
The flange is arranged on the second framework and matched with the flange, and when the positioning column is inserted into the positioning groove, the flange is abutted to the flange.
The flange is of a hollow structure, and a plurality of heat dissipation holes are formed in the flange.
An aircraft comprising an aircraft shield according to any one of the preceding claims.
The novel protective cover comprises a lower protective cover, and is characterized by further comprising a plurality of propellers and motors, wherein the propellers and the motors are both positioned between the upper protective cover and the lower protective cover, and the propellers are connected with the motors in one-to-one correspondence.
The propeller comprises a propeller seat and a plurality of paddles, wherein the paddles are uniformly distributed along the circumference of the propeller seat and fixedly connected with the propeller seat, and the propeller seat is fixedly connected with an output shaft of the motor.
The invention has the beneficial effects that:
the aircraft protective cover comprises an upper protective cover and a lower protective cover, wherein the upper protective cover comprises a first framework and a plurality of first grid bars arranged on the first framework; the lower protective cover comprises a second framework and a plurality of second grid bars arranged on the second framework, the second grid bars are in one-to-one correspondence with the first grid bars, the cross section shapes of the first grid bars and the second grid bars are all wing shapes, the front edges of the wing shapes are upward, the tail edges of the wing shapes are downward, the cross sections of the first grid bars and the cross sections of the second grid bars are all in the direction of fluid flow, and comprise a gradually-expanded front part and a gradually-retracted rear part, so that the obstruction and turbulent flow of the aircraft protective cover to air flow can be effectively reduced, the air flow is smooth, the power loss of the blade is reduced, the duration of the battery is prolonged, the blade efficiency is improved, and the blade noise is reduced.
According to the aircraft provided by the invention, the protective cover of the aircraft is adopted, so that the obstruction and turbulence to air flow are effectively reduced, the air flow is smooth, the power loss of the blades is reduced, the noise of the blades is reduced, the battery endurance time is prolonged, and the efficiency of the aircraft is improved.
Drawings
FIG. 1 is a front view of an aircraft shield provided by the present invention as assembled;
FIG. 2 is a top view of FIG. 1;
FIG. 3 is a schematic view of an assembled aircraft shield according to the present invention;
fig. 4 is an enlarged view at a in fig. 3;
fig. 5 is a schematic illustration of the use of the aircraft shield provided by the present invention.
In the figure:
1. an upper protective cover; 2. a lower protective cover; 3. a propeller; 4. a motor;
11. a first skeleton; 12. a first grid; 13. flanging; 131. a heat radiation hole;
21. a second skeleton; 22. a second grid; 23. and a flange.
Detailed Description
The technical scheme of the invention is further described below with reference to the attached drawings and the embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the drawings related to the present invention are shown.
Referring to fig. 1 to 5, an embodiment of the present invention provides an aircraft shield, including an upper shield 1 and a lower shield 2, the upper shield 1 including a first frame 11 and a plurality of first bars 12 disposed on the first frame 11; the lower protective cover 2 comprises a second framework 21 and a plurality of second grid bars 22 arranged on the second framework 21, and the second grid bars 22 are arranged in one-to-one correspondence with the first grid bars 12; the cross sections of the first grid 12 and the second grid 22 are in the shape of an airfoil, the front edge of the airfoil faces upwards, the tail edge of the airfoil faces downwards, and the cross sections of the first grid 12 and the second grid 22 comprise a gradually expanding front part and a gradually shrinking rear part along the flowing direction of fluid.
The arrangement of the wing shape and the arrangement form of the first grid bars 12 and the second grid bars 22 can effectively reduce the obstruction and turbulence effect of the aircraft protective cover on the air flow, so that the air flow is smooth, the power loss of the blade is reduced, the battery endurance time is prolonged, the blade efficiency is improved, and the blade noise is reduced.
In this embodiment, the cross-sectional shapes of the first grid 12 and the second grid 22 are symmetrical wing shapes, which is convenient for processing and production and ensures stable air flow.
The first framework 11 is provided with a plurality of hollowed-out parts, a plurality of first grid bars 12 are arranged in each hollowed-out part, and the first grid bars 12 are arc-shaped and are distributed along a direction away from the center of the first framework 11. Of course, the number of the hollowed-out parts and the number of the first grid bars 12 can be set according to practical situations, and the method is not limited herein. Because the second grid bars 22 are arranged in one-to-one correspondence with the first grid bars 12, a plurality of hollowed-out parts are also arranged on the second framework 21, and a plurality of second grid bars 22 are arranged in each hollowed-out part, and the second grid bars 22 are arc-shaped and are distributed along the direction far away from the center of the second framework 21.
The upper protective cover 1 is detachably connected with the lower protective cover 2. The first framework 11 is provided with a plurality of positioning columns extending towards the second framework 21, the second framework 21 is provided with positioning grooves matched with the positioning columns, and the positioning columns are clamped with the positioning grooves. The disassembly and the installation are convenient, the processing and the production are convenient, and the mass production is facilitated. Of course, the upper protective cover 1 and the lower protective cover 2 may be connected in other manners convenient for installation and detachment, which is not limited herein.
The edge of first skeleton 11 is provided with the turn-ups 13 that extend towards second skeleton 21, is provided with on the second skeleton 21 with turn-ups 13 matched with flange 23, inserts the constant head tank as the reference column, turn-ups 13 and flange 23 butt, further guarantees the location accuracy. The flange 13 is of a hollow structure, and a plurality of radiating holes 131 are formed in the flange 13 to ensure ventilation in the protective cover.
The embodiment of the invention also provides an aircraft, which comprises the aircraft protective cover, and further comprises a plurality of propellers 3 and motors 4, wherein the propellers 3 and the motors 4 are respectively positioned between the upper protective cover 1 and the lower protective cover 2, and the propellers 3 and the motors 4 are in one-to-one correspondence connection.
In this embodiment, the number of propellers 3 is four and is evenly distributed between the upper shield 1 and the lower shield 2. The number of propellers 3 is not limited here.
The propeller 3 comprises a propeller seat and a plurality of paddles, the paddles are uniformly distributed along the circumference of the propeller seat and fixedly connected with the propeller seat, and the propeller seat is fixedly connected with an output shaft of the motor 4. In the present embodiment, each propeller 3 includes three blades, and there is no limitation on the number of blades.
When the protective cover is used, the motor 4 drives the blades to rotate, and pushes air to flow along the direction indicated by the arrow in fig. 4, so that reverse thrust is generated to the aircraft, the air flows around the first grid bars 12 and the second grid bars 22 are indicated by the flow lines in fig. 4, the safety of the aircraft is improved, meanwhile, the obstruction and turbulent flow effects of the full-protection type flight cover on the air flow are effectively reduced, and the power efficiency of the aircraft is improved. Through practical analysis, the power loss of the blade is reduced by 18-23% compared with the original blade, and the battery endurance time is prolonged.
The above embodiments merely illustrate the basic principle and features of the present invention, and the present invention is not limited to the above embodiments, but may be varied and altered without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. An aircraft shield comprising:
the upper protective cover (1) comprises a first framework (11) and a plurality of first grid bars (12) arranged on the first framework (11);
the lower protective cover (2) comprises a second framework (21) and a plurality of second grid bars (22) arranged on the second framework (21), and the second grid bars (22) are arranged in one-to-one correspondence with the first grid bars (12);
the cross sections of the first grid bars (12) and the second grid bars (22) are in wing shapes, the front edges of the wing shapes are upward, the tail edges of the wing shapes are downward, and the cross sections of the first grid bars (12) and the cross sections of the second grid bars (22) comprise gradually-expanded front parts and gradually-contracted rear parts along the flowing direction of fluid;
a plurality of hollowed-out parts are arranged on the first framework (11), and a plurality of first grid bars (12) are arranged in each hollowed-out part;
the upper protective cover (1) is detachably connected with the lower protective cover (2).
2. Aircraft shield according to claim 1, characterized in that the first grid (12) is arc-shaped and arranged in a direction away from the centre of the first skeleton (11).
3. The aircraft protection cover according to claim 1, wherein a plurality of positioning columns extending towards the second framework (21) are arranged on the first framework (11), positioning grooves matched with the positioning columns are arranged on the second framework (21), and the positioning columns are clamped with the positioning grooves.
4. An aircraft protection hood according to claim 3, characterized in that a flange (13) extending towards the second frame (21) is provided at the edge of the first frame (11), and that a flange (23) cooperating with the flange (13) is provided on the second frame (21), said flange (13) abutting against the flange (23) when the positioning stud is inserted into the positioning slot.
5. The aircraft protection cover according to claim 4, wherein the flange (13) is of a hollow structure, and a plurality of heat dissipation holes (131) are formed in the flange (13).
6. An aircraft comprising an aircraft shield according to any one of claims 1 to 5.
7. The aircraft according to claim 6, further comprising a plurality of propellers (3) and motors (4), wherein the propellers (3) and the motors (4) are located between the upper shield (1) and the lower shield (2), and the propellers (3) and the motors (4) are connected in a one-to-one correspondence.
8. The aircraft according to claim 7, characterized in that the propeller (3) comprises a paddle seat and a plurality of paddles, which are uniformly distributed along the circumference of the paddle seat and are fixedly connected with the paddle seat, which is fixedly connected with the output shaft of the motor (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710579601.6A CN107235144B (en) | 2017-07-17 | 2017-07-17 | Aircraft protection casing and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710579601.6A CN107235144B (en) | 2017-07-17 | 2017-07-17 | Aircraft protection casing and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107235144A CN107235144A (en) | 2017-10-10 |
| CN107235144B true CN107235144B (en) | 2023-06-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710579601.6A Active CN107235144B (en) | 2017-07-17 | 2017-07-17 | Aircraft protection casing and aircraft |
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| Country | Link |
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| CN (1) | CN107235144B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163190B (en) * | 2017-12-19 | 2024-03-19 | 浙江大学 | Sound insulation device for four-rotor aircraft |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011087411A1 (en) * | 2010-01-14 | 2011-07-21 | Saab Ab | An aerodynamic surface with improved properties |
| EP2900557B1 (en) * | 2012-09-27 | 2017-09-13 | Shield Aerodynamics LLC | Environmental defense shield |
| KR101396290B1 (en) * | 2012-11-06 | 2014-05-19 | 한국항공우주산업 주식회사 | Blade of propeller for turboprop aircraft |
| US9290267B2 (en) * | 2014-01-22 | 2016-03-22 | David Metreveli | Vertical take-off and landing aerial rescue and firefighting platform |
| CN204473136U (en) * | 2014-12-22 | 2015-07-15 | 深圳市高巨创新科技开发有限公司 | Screw propeller Anti-bumping protection cover and four-axle aircraft |
| CN204846369U (en) * | 2015-06-19 | 2015-12-09 | 谭国荣 | Rotor unmanned aerial vehicle's rotor safety cover and rotor unmanned aerial vehicle |
| CN205440860U (en) * | 2015-12-22 | 2016-08-10 | 优利科技有限公司 | Aircraft |
| CN204871603U (en) * | 2015-08-11 | 2015-12-16 | 零度智控（北京）智能科技有限公司 | Unmanned vehicles screw safety cover |
| CN205150236U (en) * | 2015-11-20 | 2016-04-13 | 零度智控（北京）智能科技有限公司 | Screw top protection device |
| CN105667777B (en) * | 2016-03-29 | 2018-06-22 | 普宙飞行器科技（深圳）有限公司 | Four-way is stretched blade protective cover, dynamical system and unmanned vehicle |
| CN205738086U (en) * | 2016-05-13 | 2016-11-30 | 梅家崎 | A kind of rotor craft propeller protective cover and rotor craft |
| CN106410086A (en) * | 2016-11-16 | 2017-02-15 | 上海未来伙伴机器人有限公司 | Heat dissipation device for battery of aircraft |
| CN207173958U (en) * | 2017-07-17 | 2018-04-03 | 上海未来伙伴机器人有限公司 | A kind of aircraft protective cover and aircraft |
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2017
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| CN107235144A (en) | 2017-10-10 |
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