CN111268103A - Take dual-purpose unmanned aerial vehicle in sea and air of gasbag - Google Patents
Take dual-purpose unmanned aerial vehicle in sea and air of gasbag Download PDFInfo
- Publication number
- CN111268103A CN111268103A CN202010093025.6A CN202010093025A CN111268103A CN 111268103 A CN111268103 A CN 111268103A CN 202010093025 A CN202010093025 A CN 202010093025A CN 111268103 A CN111268103 A CN 111268103A
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- air
- air bag
- control valve
- unmanned aerial
- aerial vehicle
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- 239000003795 chemical substances by application Substances 0.000 claims description 8
- 238000005474 detonation Methods 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 7
- 230000035939 shock Effects 0.000 description 3
- 239000006096 absorbing agent Substances 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/54—Floats
- B64C25/56—Floats inflatable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/008—Amphibious sea planes
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Bag Frames (AREA)
- Air Bags (AREA)
Abstract
The invention discloses a sea-air dual-purpose unmanned aerial vehicle with an air bag, which comprises a body, a horn, a wing device, the air bag, an air charging device and a controller, wherein the air bag is arranged at the bottom end of the horn, the air charging device is arranged on the horn, the power input end of the air charging device is connected with the output end of the wing device, the air outlet of the air charging device is communicated with the air bag through a control valve, the air bag is provided with a sensor for detecting the internal air pressure of the air charging device, and the controller is electrically connected with the sensor, the wing device and the control valve; before the unmanned aerial vehicle lands, the controller controls the control valve to act, the inflating device inflates air into the air bag through the control valve to expand the air bag, and when the sensor detects that the air pressure in the air bag reaches a set value, the controller controls the control valve to act to seal the air bag; after the unmanned aerial vehicle is lifted off, the controller controls the control valve to act, and the inflating device and the air bag are discharged into the atmosphere through the control valve. The invention has the advantages of simple structure, light weight, diversified functions and high applicability.
Description
Technical Field
The invention relates to an unmanned aerial vehicle, in particular to a sea-air dual-purpose unmanned aerial vehicle with an air bag.
Background
Compared with the existing man-machine, the unmanned aerial vehicle has the advantage of being unique, and the whole unmanned aerial vehicle can be smaller and more compact and can perform more complex flight actions, so that the unmanned aerial vehicle is more suitable for executing more dangerous tasks. At present, unmanned aerial vehicles are widely applied to the fields of aerial photography, forest fire fighting, transportation, disaster relief, wild animal tracking, city stability maintenance, surveying and mapping, power inspection, reconnaissance and the like.
But in current unmanned aerial vehicle technique, the landing to unmanned aerial vehicle slows down the structure, often adopts skid bumper shock absorber formula shock attenuation mode, but skid bumper shock absorber structure is complicated, and weight is great, and need set up in the unmanned aerial vehicle fuselage outside, has influenced unmanned aerial vehicle's pneumatics to this kind of land slows down the structure and can only be adapted on land, and can't realize descending on sea or the surface of water, and the structure is complicated, weight is big and the suitability is poor.
Disclosure of Invention
The invention aims to solve the problems and provides a sea-air dual-purpose unmanned aerial vehicle with an air bag, which is simple in structure, light in weight and high in applicability.
The purpose of the invention can be achieved by adopting the following technical scheme:
a sea-air dual-purpose unmanned aerial vehicle with air bags comprises a machine body, a plurality of machine arms, wing devices, air bags, an air charging device and a controller, wherein one end of each machine arm is uniformly and fixedly connected to the outer wall of the machine body, and the wing devices are arranged at the other end of each machine arm; the air bag is arranged at the bottom end of the horn, the inflation device is arranged on the horn, the power input end of the inflation device is connected with the output end of the wing device, the air outlet of the inflation device is communicated with the air bag through a control valve, the air bag is provided with a sensor for detecting the internal air pressure of the air bag, and the controller is electrically connected with the sensor, the wing device and the control valve; before the unmanned aerial vehicle lands, the controller controls the control valve to act, the inflating device inflates air into the air bag through the control valve to expand the air bag, and when the sensor detects that the air pressure in the air bag reaches a set value, the controller controls the control valve to act to seal the air bag; after the unmanned aerial vehicle is lifted off, the controller controls the control valve to act, and the inflating device and the air bag are discharged into the atmosphere through the control valve.
Preferably, the wing device comprises a motor and a blade fixedly connected to a rotating shaft of the motor, and the motor is fixedly mounted on the horn.
As a preferable scheme, the inflation device comprises a cam, an inflator and an elastic member, the cam is fixedly connected to a rotating shaft of the motor, the inflator is mounted on the horn, and the elastic member presses a piston rod of the inflator against the cam so that the piston rod of the inflator is pressed against the cam; when the rotating shaft of the motor rotates, the cam and the elastic piece drive the piston rod to reciprocate and continuously output gas.
Preferably, the control valve is provided with an ignition device, the ignition device comprises a small detonation tube and a gas generating agent, and the controller controls the detonation gas generating agent to generate gas to be filled into the air bag when the motor is damaged or the inflating device fails.
As a preferable scheme, a baffle is arranged on the horn, and two ends of the elastic piece respectively press against a piston rod and the baffle of the inflator.
Preferably, the elastic member is a compression spring.
As a preferred scheme, the controller is a single chip microcomputer.
The implementation of the invention has the following beneficial effects:
1. when the unmanned aerial vehicle lands, the controller controls the control valve to act, so that the inflating device is communicated with the air bag through the control valve, and further, gas generated by the inflating device is input into the air bag; the controller detects the air pressure in the air bag through the sensor. When atmospheric pressure in the gasbag reached the setting value, controller control valve moved once more and made the gasbag sealed to keep the gasbag in the inflation state, thereby guarantee that unmanned aerial vehicle gasbag can play the effect of buffering and landing when landing, and unmanned aerial vehicle can also descend to the surface of water through the gasbag, have simple structure, light in weight, function diversification and the high advantage of suitability.
2. When the air charging device fails to charge the air bag, the sensor detects that the air pressure in the air bag does not reach a set value. The controller controls the small detonating tube to detonate the gas generating agent to chemically inflate the air bag until the sensor detects that the air pressure in the air bag reaches a set value, and the controller controls the control valve to act to seal the air bag. Therefore, this kind of aerating device can let the unmanned aerial vehicle who drops to the aquatic float to the surface of water from the aquatic to rotation through the control motor can make unmanned aerial vehicle like unmanned ship on the water cruise.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of the air-sea dual-purpose unmanned aerial vehicle with an air bag according to the invention.
FIG. 2 is a schematic structural view of the wing assembly and inflator device of FIG. 1.
Fig. 3 is a top view of fig. 2.
Fig. 4 is a control block diagram of the air-sea dual-purpose unmanned aerial vehicle with an air bag according to the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Examples
Referring to fig. 1 to 4, the embodiment relates to a sea and air dual-purpose unmanned aerial vehicle with an airbag, which includes a machine body 1, a plurality of machine arms 2, wing devices 3, an airbag 4, an inflator 5 and a controller 6, wherein one end of each of the machine arms 2 is uniformly and fixedly connected to the outer wall of the machine body 1, and the wing devices 3 are arranged at the other end of the machine arm 2; the air bag 4 is arranged at the bottom end of the horn 2, the inflation device 5 is arranged on the horn 2, the power input end of the inflation device 5 is connected with the output end of the wing device 3, the air outlet of the inflation device 5 is communicated with the air bag 4 through a control valve 7, a sensor for detecting the internal air pressure of the air bag 4 is arranged on the air bag 4, and the controller 6 is electrically connected with the sensor, the wing device 3 and the control valve 7; before the unmanned aerial vehicle lands, the controller 6 controls the control valve 7 to act, the inflating device 5 inflates gas into the air bag 4 through the control valve 7 to expand the air bag 4, and when the sensor detects that the air pressure in the air bag 4 reaches a set value, the controller 6 controls the control valve 7 to act to seal the air bag 4; after the unmanned aerial vehicle is lifted off, the controller 6 controls the control valve 7 to act, and the inflating device 5 and the air bag 4 are discharged to the atmosphere through the control valve 7.
When the unmanned aerial vehicle lands, the controller 6 controls the control valve 7 to act, so that the inflating device 5 is communicated with the air bag 4 through the control valve 7, and further, the gas generated by the inflating device 5 is input into the air bag 4; the controller 6 detects the magnitude of the air pressure in the air bag 4 by a sensor. When atmospheric pressure in the gasbag 4 reaches the setting value, 6 control valve 7 actions once more of controller make gasbag 4 sealed to keep gasbag 4 to be in the inflation state, thereby guarantee that unmanned aerial vehicle gasbag 4 can play the effect of buffering and landing when landing, and unmanned aerial vehicle can also descend to the surface of water through gasbag 4, have simple structure, light in weight, function diversification and the high advantage of suitability.
The wing device 3 comprises a motor 31 and a blade 32 fixedly connected to a rotating shaft of the motor 31, wherein the motor 31 is fixedly arranged on the horn 2. The controller 6 controls the working state of the motor 31 to control the rotating speed and direction of the blades 32, and further controls the lifting, flying speed and direction of the whole unmanned aerial vehicle.
The inflator 5 comprises a cam 51, an inflator 52 and an elastic member 53, the cam 51 is fixedly connected to a rotating shaft of the motor 31, the inflator 52 is mounted on the horn 2, and the elastic member 53 presses a piston rod 521 of the inflator 52 against the cam 51, so that the piston rod 521 of the inflator 52 is pressed against the cam 51; when the rotating shaft of the motor 31 rotates, the cam 51 and the elastic member 53 drive the piston rod 521 to reciprocate to continuously output gas. When the motor 31 is operated, the rotating shaft of the motor 31 drives the cam 51 to rotate. Under the action of the cam 51 and the air pump 52, the piston rod 521 of the air pump 52 reciprocates to continuously output air from the air outlet, so that the aim of continuously inflating air is fulfilled.
The control valve 7 is provided with an ignition device which comprises a small detonating tube and a gas generating agent, and when the motor 31 is damaged or the inflator 5 fails, the controller 6 controls the detonating gas generating agent to generate gas to be filled into the air bag 4. When the inflator 5 fails to inflate the airbag 4, the sensor detects that the air pressure in the airbag 4 has not reached the set value. The controller 6 controls the small squib to detonate the gas generating agent to chemically inflate the airbag 4 until the sensor detects that the air pressure in the airbag 4 reaches a set value, and then the controller 6 controls the control valve 7 to operate to seal the airbag 4. Therefore, this kind of inflator 5 can let the unmanned aerial vehicle who drops to the aquatic float to the surface of water from the aquatic to can make unmanned aerial vehicle walk on the water like unmanned boat through the rotation of control motor 31.
The arm 2 is provided with a baffle 21, and two ends of the elastic member 53 respectively press against the piston rod 521 of the inflator 52 and the baffle 21. In a normal state, the elastic member 53 is compressed by the piston rod 521 of the pump 52 and the baffle 21.
The elastic member 53 is a compression spring. Of course, other elastic materials may be used for the elastic member 53.
The controller 6 is a single chip microcomputer. Of course, the controller 6 may also employ a PLC.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (7)
1. A sea-air dual-purpose unmanned aerial vehicle with an air bag is characterized by comprising a machine body, a plurality of machine arms, wing devices, the air bag, an inflating device and a controller, wherein one end of each machine arm is uniformly and fixedly connected to the outer wall of the machine body, and the wing devices are arranged at the other end of each machine arm; the air bag is arranged at the bottom end of the horn, the inflation device is arranged on the horn, the power input end of the inflation device is connected with the output end of the wing device, the air outlet of the inflation device is communicated with the air bag through a control valve, the air bag is provided with a sensor for detecting the internal air pressure of the air bag, and the controller is electrically connected with the sensor, the wing device and the control valve; before the unmanned aerial vehicle lands, the controller controls the control valve to act, the inflating device inflates air into the air bag through the control valve to expand the air bag, and when the sensor detects that the air pressure in the air bag reaches a set value, the controller controls the control valve to act to seal the air bag; after the unmanned aerial vehicle is lifted off, the controller controls the control valve to act, and the inflating device and the air bag are discharged into the atmosphere through the control valve.
2. The air-bag unmanned aerial vehicle for sea and air use of claim 1, wherein the wing device comprises a motor and a blade fixedly connected to a rotating shaft of the motor, and the motor is fixedly installed on a horn.
3. The air-bag type unmanned aerial vehicle for sea and air use as claimed in claim 2, wherein the inflation device comprises a cam, an inflator and an elastic member, the cam is fixedly connected to a rotating shaft of the motor, the inflator is mounted on the arm, and the elastic member presses a piston rod of the inflator against the cam so that the piston rod of the inflator is pressed against the cam; when the rotating shaft of the motor rotates, the cam and the elastic piece drive the piston rod to reciprocate and continuously output gas.
4. The unmanned aerial vehicle used in sea and air with an airbag as claimed in claim 1, wherein the control valve is provided with an ignition device, the ignition device comprises a small detonation tube and a gas generating agent, and when a motor is damaged or the inflator fails, the controller controls the detonation gas generating agent to generate gas to be charged into the airbag.
5. The air-bag unmanned aerial vehicle for sea and air use as defined in claim 3, wherein the arm is provided with a baffle, and two ends of the elastic member respectively press against a piston rod and the baffle of the inflator.
6. The unmanned aerial vehicle used in sea and air with an air bag as claimed in claim 1, wherein the elastic member is a compression spring.
7. The air-sea unmanned aerial vehicle with the airbag as claimed in any one of claims 1 to 6, wherein the controller is a single chip microcomputer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010093025.6A CN111268103B (en) | 2020-02-14 | 2020-02-14 | Sea-air dual-purpose unmanned aerial vehicle with air bag |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010093025.6A CN111268103B (en) | 2020-02-14 | 2020-02-14 | Sea-air dual-purpose unmanned aerial vehicle with air bag |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111268103A true CN111268103A (en) | 2020-06-12 |
| CN111268103B CN111268103B (en) | 2024-03-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010093025.6A Active CN111268103B (en) | 2020-02-14 | 2020-02-14 | Sea-air dual-purpose unmanned aerial vehicle with air bag |
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Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB777495A (en) * | 1954-12-06 | 1957-06-26 | Gq Parachute Comp Ltd | Improvements in shock-absorbing air cushions |
| DE3034551A1 (en) * | 1979-09-14 | 1981-04-02 | Texas Instruments Inc., Dallas, Tex. | RAM AND METHOD FOR OPERATING IT |
| US20080309060A1 (en) * | 2004-08-24 | 2008-12-18 | Sam Hakki | Collision air bag and flotation system |
| US20080315037A1 (en) * | 2005-12-23 | 2008-12-25 | Airbus Deutschland Gmbh | Safety System for Reducing the Impact Energy of a Container |
| CN204568058U (en) * | 2015-03-25 | 2015-08-19 | 朱威 | A kind of submersible many rotor wing unmanned aerial vehicles |
| CN104898655A (en) * | 2015-06-10 | 2015-09-09 | 浙江空行飞行器技术有限公司 | Amphibious unmanned plane |
| CN105730688A (en) * | 2016-05-09 | 2016-07-06 | 四川马可视觉网络科技有限公司 | Unmanned gyroplane capable of landing on water surface |
| CN205499330U (en) * | 2016-02-04 | 2016-08-24 | 普宙飞行器科技（深圳）有限公司 | Unmanned aerial vehicle with gasbag of saving oneself |
| CN106741879A (en) * | 2016-12-09 | 2017-05-31 | 合肥赛为智能有限公司 | A kind of unmanned plane with protection device |
| CN206336428U (en) * | 2016-12-27 | 2017-07-18 | 广州市海智谷机器人有限公司 | A kind of inflatable unmanned plane |
| CN107323193A (en) * | 2017-08-04 | 2017-11-07 | 代国栋 | One kind can fly empty land convertible car |
| CN207759043U (en) * | 2017-12-16 | 2018-08-24 | 广东容祺智能科技有限公司 | A kind of overboard protection unmanned plane horn |
| CN208021761U (en) * | 2018-03-19 | 2018-10-30 | 北京中科遥数信息技术有限公司 | A kind of unmanned plane parachute |
| CN109250082A (en) * | 2018-10-30 | 2019-01-22 | 佛山市神风航空科技有限公司 | A kind of multiaxis low latitude manned vehicle |
| CN212667645U (en) * | 2020-02-14 | 2021-03-09 | 广东工业大学 | Take dual-purpose unmanned aerial vehicle in sea and air of gasbag |
-
2020
- 2020-02-14 CN CN202010093025.6A patent/CN111268103B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB777495A (en) * | 1954-12-06 | 1957-06-26 | Gq Parachute Comp Ltd | Improvements in shock-absorbing air cushions |
| DE3034551A1 (en) * | 1979-09-14 | 1981-04-02 | Texas Instruments Inc., Dallas, Tex. | RAM AND METHOD FOR OPERATING IT |
| US20080309060A1 (en) * | 2004-08-24 | 2008-12-18 | Sam Hakki | Collision air bag and flotation system |
| US20080315037A1 (en) * | 2005-12-23 | 2008-12-25 | Airbus Deutschland Gmbh | Safety System for Reducing the Impact Energy of a Container |
| CN204568058U (en) * | 2015-03-25 | 2015-08-19 | 朱威 | A kind of submersible many rotor wing unmanned aerial vehicles |
| CN104898655A (en) * | 2015-06-10 | 2015-09-09 | 浙江空行飞行器技术有限公司 | Amphibious unmanned plane |
| CN205499330U (en) * | 2016-02-04 | 2016-08-24 | 普宙飞行器科技（深圳）有限公司 | Unmanned aerial vehicle with gasbag of saving oneself |
| CN105730688A (en) * | 2016-05-09 | 2016-07-06 | 四川马可视觉网络科技有限公司 | Unmanned gyroplane capable of landing on water surface |
| CN106741879A (en) * | 2016-12-09 | 2017-05-31 | 合肥赛为智能有限公司 | A kind of unmanned plane with protection device |
| CN206336428U (en) * | 2016-12-27 | 2017-07-18 | 广州市海智谷机器人有限公司 | A kind of inflatable unmanned plane |
| CN107323193A (en) * | 2017-08-04 | 2017-11-07 | 代国栋 | One kind can fly empty land convertible car |
| CN207759043U (en) * | 2017-12-16 | 2018-08-24 | 广东容祺智能科技有限公司 | A kind of overboard protection unmanned plane horn |
| CN208021761U (en) * | 2018-03-19 | 2018-10-30 | 北京中科遥数信息技术有限公司 | A kind of unmanned plane parachute |
| CN109250082A (en) * | 2018-10-30 | 2019-01-22 | 佛山市神风航空科技有限公司 | A kind of multiaxis low latitude manned vehicle |
| CN212667645U (en) * | 2020-02-14 | 2021-03-09 | 广东工业大学 | Take dual-purpose unmanned aerial vehicle in sea and air of gasbag |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111268103B (en) | 2024-03-05 |
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