CN112173146A - Aircraft safety landing protection ball - Google Patents
Aircraft safety landing protection ball Download PDFInfo
- Publication number
- CN112173146A CN112173146A CN202011258757.2A CN202011258757A CN112173146A CN 112173146 A CN112173146 A CN 112173146A CN 202011258757 A CN202011258757 A CN 202011258757A CN 112173146 A CN112173146 A CN 112173146A
- Authority
- CN
- China
- Prior art keywords
- protection ball
- push rod
- electric push
- aircraft
- aircraft safety
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 230000001681 protective effect Effects 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims 2
- 238000003466 welding Methods 0.000 claims 2
- 239000000463 material Substances 0.000 claims 1
- 238000009434 installation Methods 0.000 description 7
- 230000035939 shock Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
- B64D45/06—Landing aids; Safety measures to prevent collision with earth's surface mechanical
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention provides an aircraft safe landing protection ball, which comprises a protection ball body, wherein the protection ball body comprises a mounting seat and an intelligent system, the intelligent system comprises an infrared sensor, a control box, an intelligent processor, a control switch, a power supply device, a direct current motor, an electric push rod I and an electric push rod II, a movable plate is mounted on the mounting seat and mounted on the mounting seat through a fixed shaft, a groove is formed in the movable plate, a hollow rubber ball is placed in the groove, the infrared sensor is mounted at one end of the movable plate, the aircraft safe landing protection ball detects the position of an aircraft through the infrared sensor, the motor is controlled to rotate through the intelligent processor, the direction of the electric push rod II is changed, the electric push rod finely adjusts the position of the mounting seat through the movable rod, and accordingly the aircraft is adjusted and used, the function is various.
Description
Technical Field
The invention relates to the field of aircraft equipment, in particular to a protective ball for safe landing of an aircraft.
Background
Along with the development of science and technology, the remote control aircraft enters into people's sight, its constitutional features of aircraft respectively is equipped with a rotor on its four angles, drive respectively by the motor, the blade can corotation, also can reverse, in order to keep the stable flight of aircraft, it constitutes inertial navigation module with 3 directional gyroscopes and 3 axle acceleration sensors to be equipped with on the aircraft, it still guarantees its fast flight through electronic control ware, current aircraft is owing to directly contact with ground in the landing of flying, produce great impact force easily, the impact force can cause the damage of aircraft internal circuit, long-term use can cause the damage of equipment, it is inconvenient to use, current equipment can't adjust the use to the different positions that the aircraft fell down, it is inconvenient to use, the function is single.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a protective ball for safe landing of an aircraft, which is used for solving the problems in the background art.
In order to achieve the purpose, the invention is realized by the following technical scheme: the utility model provides an aircraft safety descending protection ball, includes the protection ball body, the protection ball body includes mount pad and intelligent system, intelligent system includes infrared inductor, control box, intelligent processing ware, control switch, power supply unit, direct current motor, electric putter one and electric putter two, install the fly leaf on the mount pad, the fly leaf passes through the fixed axle and installs on the mount pad, it has the recess to open on the fly leaf, hollow rubber ball has been placed to the inside of recess, the one end at the fly leaf is installed to the infrared inductor, the connection hangers is installed to the bottom of fly leaf, be fixed with fixed hangers on the mount pad, electric putter one is installed on fixed hangers through the installation pole.
As a preferred embodiment of the invention, the mounting rod is mounted on the fixed suspension loop through a rotating shaft, and the top of the electric push rod I is mounted on the connecting suspension loop through the rotating shaft I.
As a preferred embodiment of the present invention, the number of the movable plates is 6, and elastic plates are installed between every two movable plates, and the elastic plates are made of rubber.
As a preferred embodiment of the present invention, a base is installed at the bottom of the installation seat, a support column is installed on the base, a roller is installed on the support column, and the roller is matched with the inner wall of the installation seat.
As a preferred embodiment of the present invention, a fixing seat is welded on the supporting column, the electric push rod two is installed on the fixing seat, a movable rod is installed on the electric push rod two, a fixed rod is welded on the movable rod, and one end of the fixed rod is fixed at the bottom of the mounting seat.
As a preferred embodiment of the present invention, the dc motor is installed inside the base, an output shaft is installed on the dc motor, and one end of the output shaft is installed at the bottom of the supporting column.
As a preferred embodiment of the present invention, the bottom of the supporting column is mounted on the base through a fixed bearing, and the output shaft is mounted on the supporting column through a bearing.
As a preferred embodiment of the present invention, a cavity is installed inside the base, the dc motor is installed inside the cavity through a limiting rod, and a heat dissipation opening is formed in the base and is matched with the dc motor.
As a preferred embodiment of the present invention, the control box includes an intelligent processor and a control switch, and the control switch is electrically connected to the intelligent processor.
In a preferred embodiment of the present invention, the power supply device is connected to the dc motor, the first electric push rod, the second electric push rod and the infrared sensor through wires.
The invention has the beneficial effects that: the invention relates to an aircraft safe landing protection ball, which comprises a mounting seat; a movable plate; a fixed shaft; a groove; a hollow rubber ball; an elastic plate; an infrared sensor; fixing the hangers; an electric push rod I; mounting a rod; a rotating shaft; connecting a hanging lug; a base; a support pillar; a roller; a fixed seat; a second electric push rod; a movable rod; fixing the rod; fixing the bearing; a direct current motor; an output shaft; a limiting rod; a control box; an intelligent processor; a control switch; and a power supply device.
1. This aircraft safety is descended protection ball aircraft can directly descend the inside to hollow rubber ball when using, and the elasticity through hollow rubber ball carries out the shock attenuation to the impact force, effectively guarantees that the aircraft does not receive the influence of impact force, guarantees the normal use of equipment.
2. This aircraft safety is descended protection ball passes through the work of intelligent treater and control switch control electric putter one, with the fly leaf ascending simultaneously, forms the parcel form, and inside hollow rubber ball is put to central point and is drawn close and increase its thickness, and abundant parcel shock attenuation when the aircraft descends is convenient for accomodate this device after drawing in, satisfies the use under the different situation.
3. This aircraft safety landing protection ball detects the position of aircraft through infrared inductor, and is rotatory through intelligent treater control motor, makes electric putter two's direction change, and fine setting about electric putter two is gone on the position of mount pad through the activity pole to adjust the use according to the position of aircraft, the function is various.
Drawings
FIG. 1 is a schematic structural view of a protective ball for safe landing of an aircraft according to the present invention;
FIG. 2 is a schematic cross-sectional view of a mounting seat and a base of a safety protection ball for aircraft landing according to the present invention;
FIG. 3 is a schematic structural diagram of an intelligent system for protecting a ball during safe landing of an aircraft according to the present invention;
in the figure: 1. a mounting seat; 2. a movable plate; 3. a fixed shaft; 4. a groove; 5. a hollow rubber ball; 6. an elastic plate; 7. an infrared sensor; 8. fixing the hangers; 9. an electric push rod I; 10. mounting a rod; 11. a rotating shaft; 12. connecting a hanging lug; 13. a base; 14. a support pillar; 15. a roller; 16. a fixed seat; 17. a second electric push rod; 18. a movable rod; 19. fixing the rod; 20. fixing the bearing; 21. a direct current motor; 22. an output shaft; 23. a limiting rod; 24. a control box; 25. an intelligent processor; 26. a control switch; 27. and a power supply device.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
Referring to fig. 1 to 3, the present invention provides a technical solution: the utility model provides an aircraft safety descending protection ball, includes the protection ball body, the protection ball body includes mount pad 1 and intelligent system, intelligent system includes infrared inductor 7, control box 24, intelligent processor 25, control switch 26, power supply unit 27, DC motor 21, electric putter 7 and electric putter two 17, install fly leaf 2 on the mount pad 1, fly leaf 2 is installed on mount pad 1 through fixed axle 3, it has recess 4 to open on fly leaf 2, hollow rubber ball 5 has been placed to recess 4's inside, infrared inductor 7 installs the one end at fly leaf 2, the connection hangers 12 is installed to the bottom of fly leaf 2, be fixed with fixed hangers 8 on mount pad 1, electric putter 9 is installed on fixed hangers 8 through installation pole 10.
In a preferred embodiment of the present invention, the mounting rod 10 is mounted on the fixing lug 8 through a rotating shaft 11, and the top of the electric push rod 7 is mounted on the connecting lug 12 through a rotating shaft I.
As a preferred embodiment of the present invention, the number of the movable plates 2 is 6, elastic plates 6 are installed between every two movable plates 2, and the elastic plates 6 are made of rubber.
As a preferred embodiment of the present invention, a base 13 is installed at the bottom of the installation base 1, a supporting column 14 is installed on the base 13, a roller 15 is installed on the supporting column 14, and the roller 15 is matched with the inner wall of the installation base 1.
As a preferred embodiment of the present invention, a fixed seat 16 is welded on the supporting column 14, the second electric push rod 17 is installed on the fixed seat 16, a movable rod 18 is installed on the second electric push rod 17, a fixed rod 19 is welded on the movable rod 18, and one end of the fixed rod 19 is fixed at the bottom of the installation seat 1.
In a preferred embodiment of the present invention, the dc motor 21 is installed inside the base 13, the output shaft 22 is installed on the dc motor 21, and one end of the output shaft 22 is installed at the bottom of the supporting column 14.
In a preferred embodiment of the present invention, the bottom of the supporting column 14 is mounted on the base 13 through a fixed bearing 20, and the output shaft 22 is mounted on the supporting column 14 through a bearing.
As a preferred embodiment of the present invention, a cavity is installed inside the base 13, the dc motor 21 is installed inside the cavity through a limiting rod 23, and a heat dissipation opening is opened on the base 13 and is matched with the dc motor 21.
In a preferred embodiment of the present invention, the control box 24 includes an intelligent processor 25 and a control switch 26, and the control switch 26 is electrically connected to the intelligent processor 25.
In a preferred embodiment of the present invention, the power supply device 27 is connected to the dc motor 21, the first electric push rod 9, the second electric push rod 17 and the infrared sensor 7 through wires.
When the device is used, the mounting seat 1 is fixed by placing the base 13 on the ground, the movable plate 2 is retracted inwards through the electric push rod I9, the movable plate 2 is opened downwards through the connecting lugs 12 and the electric push rod I9, the bottom of the movable plate 2 is limited and fixed after being contacted with the inner wall of the mounting seat 1, the horizontal fixation of the movable plate 2 is ensured, the hollow rubber ball 5 is placed in the groove 4, the descending impact force of the aircraft is weakened for use through the elasticity of the hollow rubber ball 5, when the aircraft lands on the movable plate 2 in use, the infrared sensor 7 on the movable plate 2 senses the position of the aircraft, when the position of the aircraft is at the central position of the mounting seat 1, the electric push rod I9 works when the intelligent processor 25 controls the control switch 26, the electric push rod I9 pushes the movable plate 2 to ascend, the movable plate 2 is sealed through the elastic plate 6, make inside hollow rubber ball 5 can not drop, draw in to inside simultaneously through fixed axle 3 through fly leaf 2, make hollow rubber ball 5 concentrate on central point and put the department, make thickness increase, the shock attenuation of being convenient for is used, fully protect the aircraft, it is convenient to use, in addition, after the aircraft skew, respond to through infrared inductor 7, intelligent processor 25 control electric putter two 17 removes mount pad 1, mount pad 1 removes at support column 14's gyro wheel 15, through the skew, make the position of fly leaf 2 change, thereby accept the use to the aircraft, electric putter two 17 is two-way use, it can carry out four directions and use to drive through direct current motor 21, satisfy the use under the different situation, the function is various.
While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. The utility model provides an aircraft safety landing protection ball, includes the protection ball body, its characterized in that: the protective ball body comprises a mounting seat (1) and an intelligent system, the intelligent system comprises an infrared sensor (7), a control box (24), an intelligent processor (25), a control switch (26), a power supply device (27), a direct current motor (21), a first electric push rod (7) and a second electric push rod (17), the mounting seat (1) is provided with a movable plate (2), the movable plate (2) is arranged on the mounting seat (1) through a fixed shaft (3), a groove (4) is formed on the movable plate (2), a hollow rubber ball (5) is placed in the groove (4), the infrared inductor (7) is arranged at one end of the movable plate (2), the bottom of the movable plate (2) is provided with a connecting lug (12), the mounting seat (1) is fixedly provided with a fixed hanging lug (8), and the electric push rod I (9) is mounted on the fixed hanging lug (8) through a mounting rod (10).
2. An aircraft safety landing protection ball according to claim 1, wherein: the mounting rod (10) is mounted on the fixed hanging lug (8) through a rotating shaft (11), and the top of the electric push rod I (7) is mounted on the connecting hanging lug (12) through a rotating shaft I.
3. An aircraft safety landing protection ball according to claim 1, wherein: the quantity of fly leaf (2) is 6, install elastic plate (6) between fly leaf (2) two liang, elastic plate (6) are the rubber material.
4. An aircraft safety landing protection ball according to claim 1, wherein: base (13) are installed to the bottom of mount pad (1), install support column (14) on base (13), install gyro wheel (15) on support column (14), the inner wall of gyro wheel (15) and mount pad (1) cooperatees.
5. An aircraft safety landing protection ball according to claim 4, wherein: the welding has fixing base (16) on support column (14), install on fixing base (16) electric putter two (17), install movable rod (18) on electric putter two (17), the welding has dead lever (19) on movable rod (18), the bottom at mount pad (1) is fixed to the one end of dead lever (19).
6. An aircraft safety landing protection ball according to claim 4, wherein: the direct current motor (21) is installed in the base (13), an output shaft (22) is installed on the direct current motor (21), and one end of the output shaft (22) is installed at the bottom of the supporting column (14).
7. An aircraft safety landing protection ball according to claim 6, wherein: the bottom of the supporting column (14) is installed on the base (13) through a fixed bearing (20), and the output shaft (22) is installed on the supporting column (14) through a bearing.
8. An aircraft safety landing protection ball according to claim 7, wherein: the utility model discloses a cooling device, including base (13), DC motor (21), gag lever post (23), cooling hole, the internally mounted of base (13) has the cavity, DC motor (21) passes through the gag lever post (23) and installs the inside at the cavity, it has the thermovent to open on base (13), the thermovent cooperatees with DC motor (21).
9. An aircraft safety landing protection ball according to claim 1, wherein: the control box (24) comprises an intelligent processor (25) and a control switch (26), and the control switch (26) is electrically connected with the intelligent processor (25).
10. An aircraft safety landing protection ball according to claim 1, wherein: and the power supply device (27) is connected with the direct current motor (21), the electric push rod I (9), the electric push rod II (17) and the infrared inductor through electric wires.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011258757.2A CN112173146A (en) | 2020-11-12 | 2020-11-12 | Aircraft safety landing protection ball |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011258757.2A CN112173146A (en) | 2020-11-12 | 2020-11-12 | Aircraft safety landing protection ball |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112173146A true CN112173146A (en) | 2021-01-05 |
Family
ID=73918367
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011258757.2A Withdrawn CN112173146A (en) | 2020-11-12 | 2020-11-12 | Aircraft safety landing protection ball |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112173146A (en) |
-
2020
- 2020-11-12 CN CN202011258757.2A patent/CN112173146A/en not_active Withdrawn
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20210105 |