CN204988033U - External power source power supply remote control rotor flight flail - Google Patents
External power source power supply remote control rotor flight flail Download PDFInfo
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- CN204988033U CN204988033U CN201520726326.2U CN201520726326U CN204988033U CN 204988033 U CN204988033 U CN 204988033U CN 201520726326 U CN201520726326 U CN 201520726326U CN 204988033 U CN204988033 U CN 204988033U
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- external power
- flail
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Abstract
External power source power supply remote control rotor flight flail, including fuselage, the electronic rotor of a plurality of, state of flight computer control system, radio signal receiving process transmitting facilities and remote controller, state of flight computer control system includes satellite positioning terminal, accelerometer and communication module, characterized by flight the flail contain a set of more than two with external power source with the power transmission line with electric loading component return circuit of aircraft to it gets the thunder facility to contain one make a video recording / ignition /, make a video recording / ignition / get the thunder facility and pass through interface circuit and state of flight computer control system signal connection, state that the thunder facility was got to make a video recording / ignition / is according to the change of state of flight computer control system state and the change. Make external power source pass through the power transmission line and continuously supply the electric energy, can almost unrestrictedly strengthen the empty ability that stagnates.
Description
Technical field
The utility model relates to external power source remote controlled rotary-wing flight flail.
Background technology
On Cambodia and other places, the event having land mine to hurt sb.'s feelings time so far occurs.Be a kind of well mode with remotely-piloted vehicle clearance, but when utilizing the self-contained battery flight of aircraft, the hang time is short, sometimes only has several minutes.
Summary of the invention
The purpose of this utility model is the flail that the hang time will be provided longer.
The utility model realizes the technical scheme of its object: manufacture an external power source remote controlled rotary-wing flight flail, comprise fuselage, several electronic rotors, state of flight computer control system, radio signal reception process launch facility and remote controller, state of flight computer control system comprises satellite positioning-terminal, accelerometer, magnetometer, baroceptor, gyroscope and communication module, and described flight flail adopts one group more than two to form the power transmission line in loop with the electricity consumption load of external power source and described aircraft.External power source continues the described flight flail electric energy of supply by power transmission line.And adopt one make a video recording/ignite/get thunder facility; Make a video recording/ignite/get thunder facility to be connected with state of flight computer control system signal by interface circuit, make a video recording/ignite/state of getting thunder facility changes according to the change of state of flight computer control system state.
Field condition is sent to rear and analyzes by shooting facility; Ignition facility comprises one or row's cable detonates a mine for inswept ground, and related content can with reference to prior art; Get thunder facility and comprise a pneumatic bucket, pneumatic bucket puts down from unmanned plane above and directly land mine is taken handling and destroy to appointed place; Pneumatic bucket is connected to obtain power by appendix with an external air source; Pneumatic bucket is connected with aerial described flight flail by appendix.
Two frame rotor crafts can also be adopted namely to spray medicine aircraft and assisting in flying device, and adopt a tracking dolly, follow the tracks of dolly and be mounted with automatic wire winding device, appendix automatic retraction device, external power source and external air source; Clearance aircraft adopts an appendix, appendix two ends respectively with get thunder facility and be communicated with external air source.
The above rotor craft of a three framves i.e. frame assisting in flying device can also be adopted to configure the above clearance aircraft of two framves; Also comprise a tracking dolly, follow the tracks of dolly and be mounted with automatic wire winding device, appendix automatic retraction device, external power source and external air source; Clearance aircraft adopts an appendix, appendix two ends respectively with get thunder facility and be communicated with external air source.
As required, clearance aircraft and assisting in flying device also can configure automatic wire winding device and appendix automatic retraction device.Automatic wire winding device and appendix automatic retraction device can adopt one can rotating motorized pulleys make, motorized pulleys reel power transmission line or appendix.
Rotor craft comprises a post and multiaxis rotor craft, and a post comprises single-blade and double-vane.
The beneficial effects of the utility model: adopt one group more than two to form the power transmission line in loop with the electricity consumption load of external power source and described flight instruments, make external power source continue the described flight instruments electric energy of supply by power transmission line, almost unrestrictedly can strengthen the stagnant empty ability of described flight instruments.Adopt assisting in flying device, both can share the power transmission line load of clearance aircraft; The power transmission line that can realize again clearance aircraft connects from above, greatly increases the operation free degree of clearance aircraft.
Accompanying drawing explanation
Fig. 1 is the fundamental diagram of the external power source remote controlled rotary-wing flight flail of a band appendix.
Fig. 2 is the field layout figure of an external power source remote controlled rotary-wing flight flail.
Fig. 3 is a fundamental diagram adopting pneumatic clearance grab bucket to capture land mine.
Fig. 4 is the structural representation of an ignition still.
1. clearance aircraft in figure; 2. assisting in flying device; 3. follow the tracks of dolly; 4. fuselage; 5. electronic rotor; 6. external power source; 7. power transmission line; 8. automatic wire winding device; 9. appendix; 10. automatic retraction device; 11. pneumatic supplies; 12. choose high bar; 13. pneumatic clearance grab buckets; 14. land mines; 15. clearance cables; 16. ignite still; 17. initiation bombs; 18. landing platforms.
Detailed description of the invention
Fig. 1 to Fig. 4 provides embodiment 1 jointly.
In embodiment 1, manufacture an external power source remote controlled rotary-wing flight flail, comprise four frame clearance aircraft 1 and assisting in flying devices 2, and adopt a tracking dolly 3.Clearance aircraft 1 and assisting in flying device 2 comprise fuselage 4, several electronic rotor 5, state of flight computer control system, radio signal reception process launch facility and remote controllers, and state of flight computer control system comprises satellite positioning-terminal, accelerometer, magnetometer, baroceptor, gyroscope and communication module.Described flight flail adopts one group more than two to form the power transmission line 7 in loop with the electricity consumption load of external power source 6 and aircraft 1,2.Follow the tracks of that dolly 3 is mounted with the automatic wire winding device 8 of power transmission line 7, the automatic retraction device 10 of appendix 9, external power source 6, pneumatic supply 11, choose high bar 12 and landing platform 18.Flight flail adopts its two ends to grab bucket with pneumatic clearance respectively 13 appendixs 9 be communicated with pneumatic supply 11.Follow the tracks of dolly 3 from motion tracking assisting in flying device 2.External power source 6 continues supply aircraft electric energy by power transmission line 7.Pneumatic clearance grab bucket 13 is connected with state of flight computer control system signal by interface circuit, and the state of pneumatic clearance grab bucket 13 changes according to the change of state of flight computer control system state.
Choose high bar 12 upwards the highest stretch out 6 meters, stretch out at most 5 meters to side.Choose high bar 12 and obviously can shorten power transmission line 7 and the skyborne length of carrier pipe assembly 9.Choose high bar 12 and have multiple robotic arm, its state can adjust.The content of robotic arm can with reference to prior art.
The brief introduction of work principle of embodiment 1 is: the self-inspection of external power source remote controlled rotary-wing flight flail system boot, and assisting in flying device 2 and spray medicine aircraft 1 successively stop from landing platform 18 hovering that rises; Then follow the tracks of dolly 3 to follow clearance unit and reach the spot.First enable that detection facility comprises image pick-up device, radar detedtor, magnetic detector, ultrasonic detector carry out detection to the removal of mines land mine 14 in region and whole topography and geomorphology and reconnoitre and transmit rear and analyze and data processing, comprise and position mark is carried out to all land mines 14 and suspicious item.Then according to action scheme, operation part is changed to clearance aircraft 1, be included in clearance aircraft 1 to hang clearance cable 15 or hang and ignite still 16.Ignite still 16 and comprise a remote-controlled detonation bullet 17.Then detonate a mine 14 with clearance cable 15 at the scene as requested, and carry out shooting, record comprises recording and checks has ignited altogether how many land mines and explosion equivalent thereof and position thereof.For the doubtful land mine of failing to ignite, adopt pneumatic clearance to grab bucket and 13 carry out taking and move to assigned address and dispose separately or is directly destroyed with gas flame cuttiug machine people and to ignite or employing ignition still is ignited.In this process, other process means can also be adopted to comprise the process means of prior art.
And then removal of mines region is carried out detection and reconnoitred, and doubtful land mine is ignited again or removes, until be sure of that the removal of mines completes.Then on-the-spot walking test is carried out with simulation soldier and vehicle, and plug penoncel to the removal of mines region mark the mobile terminal simultaneously walkable region being inputted computer and soldier, domain of dependence is monitored simultaneously, prevent new land mine from being dropped or otherwise enter removal of mines region once again.Then, be worth aircraft to drop on landing platform 18 and to recall storehouse.To the average wide 20 meters long regions of 2000 meters, above-mentioned removal of mines process can complete in 10 minutes.
Obviously, on some region such as hillside, only use a frame clearance aircraft 1 and band to choose the tracking dolly 3 of high bar 12, and order is followed the tracks of dolly 3 and is positioned at higher position and also can implements detection to lower and reconnoitre and mine-clearing operation.
In addition, the remotely-piloted vehicle that detection task of reconnoitring also can give the flight of self battery of existing dependence is served as.
Adopt the unit of a frame assisting in flying device 1 and multi rack clearance aircraft 2 composition, operating efficiency significantly improves.For the scene needing different work, adopt the division of labor mine-clearing operation of Various Complex can be completed with the speed that a strong wind scattering the last clouds.
Claims (3)
1. external power source remote controlled rotary-wing flight flail, comprise fuselage, several electronic rotors, state of flight computer control system, radio signal reception process launch facility and remote controller, state of flight computer control system comprises satellite positioning-terminal, accelerometer, magnetometer, baroceptor, gyroscope and communication module, it is characterized in that described flight flail contains one group more than two and form the power transmission line in loop with the electricity consumption load of external power source and described aircraft, and contain one make a video recording/ignite/get thunder facility; Make a video recording/ignite/get thunder facility to be connected with state of flight computer control system signal by interface circuit, make a video recording/ignite/state of getting thunder facility changes according to the change of state of flight computer control system state.
2. according to external power source remote controlled rotary-wing flight flail according to claim 1, it is characterized in that comprising two frame rotor crafts and clearance aircraft and assisting in flying device, also comprise a tracking dolly, follow the tracks of dolly and be mounted with automatic wire winding device, appendix automatic retraction device, external power source and external air source; Clearance aircraft adopts an appendix, appendix two ends respectively with get thunder facility and be communicated with external air source.
3., according to external power source remote controlled rotary-wing flight flail according to claim 1, it is characterized in that comprising the above rotor craft of a three framves i.e. frame assisting in flying device configures the above clearance aircraft of two framves; Also comprise a tracking dolly, follow the tracks of dolly and be mounted with automatic wire winding device, appendix automatic retraction device, external power source and external air source; Clearance aircraft adopts an appendix, appendix two ends respectively with get thunder facility and be communicated with external air source.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520726326.2U CN204988033U (en) | 2015-09-18 | 2015-09-18 | External power source power supply remote control rotor flight flail |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520726326.2U CN204988033U (en) | 2015-09-18 | 2015-09-18 | External power source power supply remote control rotor flight flail |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204988033U true CN204988033U (en) | 2016-01-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520726326.2U Expired - Fee Related CN204988033U (en) | 2015-09-18 | 2015-09-18 | External power source power supply remote control rotor flight flail |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204988033U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110044213A (en) * | 2019-03-27 | 2019-07-23 | 中国人民解放军国防科技大学 | Mine sweeping device |
-
2015
- 2015-09-18 CN CN201520726326.2U patent/CN204988033U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110044213A (en) * | 2019-03-27 | 2019-07-23 | 中国人民解放军国防科技大学 | Mine sweeping device |
| CN110044213B (en) * | 2019-03-27 | 2024-02-09 | 中国人民解放军国防科技大学 | Mine sweeping device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160120 Termination date: 20170918 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |