CN204399484U - Unmanned plane fuel-feed system - Google Patents
Unmanned plane fuel-feed system Download PDFInfo
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- CN204399484U CN204399484U CN201420843890.8U CN201420843890U CN204399484U CN 204399484 U CN204399484 U CN 204399484U CN 201420843890 U CN201420843890 U CN 201420843890U CN 204399484 U CN204399484 U CN 204399484U
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- fuel
- tank
- unmanned plane
- main oil
- additional fuel
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Abstract
The utility model discloses a kind of unmanned plane fuel-feed system, comprise main oil tank, additional fuel tank, fuel feed pipe and oil suction pipe, top or the top of described main oil tank are provided with vent, one end of described fuel feed pipe is through main oil tank top or top, and the bottom of main oil tank inner fluid is sunk to by weight, the other end of fuel feed pipe enters the top in additional fuel tank through the top of additional fuel tank or top, top or the top of additional fuel tank are passed in one end of oil suction pipe, and the bottom of additional fuel tank inner fluid is sunk to by weight, and under remaining in pasta when UAV Maneuver, the other end of oil suction pipe is connected with the oil suction of the Oil sucking device of driving engine.The utility model solves small-sized long endurance unmanned aircraft under low pasta during large angle maneuver, may failure of fuel system be there is in existing fuel-feed system, cause the problem of engine off and air crash, there is fuel feeding failure-free advantage, for the safe flight of unmanned plane adds guarantee.
Description
Technical field
The utility model relates to unmanned plane fuel-feed system.
Background technology
At present, small-sized long endurance unmanned aircraft all uses fuel engines, and stablizing with reliable of fuel delivery, directly has influence on the work of fuel engines and the flight safety of unmanned plane.At present, most of small-sized long endurance unmanned aircraft all adopts weight to sink to the single fuel tank of assimilating type fuel feeding.Under the low oil mass state of unmanned plane, when operator operation unmanned plane does large angle maneuver, because flight attitude changes, fuel tank IFO intermediate fuel oil liquid level also changes thereupon, may occur that weight exposes pasta situation, cannot complete oil suction, cause engine off, unmanned plane crashes.
Utility model content
For solving small-sized long endurance unmanned aircraft under low pasta during large angle maneuver, may there is failure of fuel system in existing fuel-feed system, cause the problem of engine off and air crash, and the utility model provides a kind of unmanned plane fuel-feed system.
The technical solution of the utility model is as follows:
A kind of unmanned plane fuel-feed system, comprise main oil tank, additional fuel tank, fuel feed pipe and oil suction pipe, top or the top of described main oil tank are provided with vent, one end of described fuel feed pipe is through main oil tank top or top, and the bottom of main oil tank inner fluid is sunk to by weight, the other end of fuel feed pipe enters the top in additional fuel tank through the top of additional fuel tank or top, top or the top of additional fuel tank are passed in one end of oil suction pipe, and the bottom of additional fuel tank inner fluid is sunk to by weight, and under remaining in pasta when UAV Maneuver, the other end of oil suction pipe is connected with the oil suction of the Oil sucking device of driving engine,
Preferably, top or the top of described additional fuel tank are provided with pouring orifice, described pouring orifice are provided with sealing plug cock or seal cover cap.
Preferably, top or the top of main oil tank are provided with pouring orifice, described pouring orifice are provided with sealing plug cock or seal cover cap.
Preferably, described vent is connected with breather pipe.
Preferably, described breather pipe is provided with roundabout right-angle bending.
The utility model, by being connected in series an additional fuel tank between the existing fuel tank of unmanned plane and driving engine, makes unmanned plane when maneuvering flight, under the pasta that the weight end of oil suction pipe remains in additional fuel tank.When unmanned plane normal flight, under the weight end of fuel feed pipe is positioned at the pasta of main oil tank, driving engine is from while oil suction in additional fuel tank, oil in main oil tank is also inhaled in additional fuel tank, now, actual to the oil of driving engine confession is oil in main oil tank, and additional fuel tank only plays intermediation; When unmanned plane large angle maneuver causes the weight end of fuel feed pipe to expose the pasta in main oil tank, weight starts to suck air, and main oil tank cannot complete fuel feeding, and now, the additional fuel tank of fuel-feed system is actual is engine oil, continues to ensure engine operation.When unmanned plane gets back to normal attitude flight, under the weight of fuel feed pipe sinks to pasta, main oil tank continues as engine oil.
Therefore, the utility model solves small-sized long endurance unmanned aircraft under low pasta during large angle maneuver, and existing fuel-feed system may occur failure of fuel system, causes the problem of engine off and air crash, there is fuel feeding failure-free advantage, for the safe flight of unmanned plane adds guarantee.
Accompanying drawing explanation
Fig. 1 is the structural principle schematic diagram of the utility model one embodiment;
Fig. 2 is the structural representation of the breather pipe with roundabout right-angle bending;
In figure: 1, main oil tank; 2, additional fuel tank; 3, fuel feed pipe; 4, oil suction pipe; 5, weight; 6, breather pipe; 7, oiling tube.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in further detail.
As shown in Figure 1, the unmanned plane fuel-feed system of the present embodiment comprises main oil tank 1, additional fuel tank 2, fuel feed pipe 3 and oil suction pipe 4, the top of main oil tank 1 is provided with vent, one end of fuel feed pipe 3 is through main oil tank 1 top, and the bottom of main oil tank 1 inner fluid is sunk to by weight 5, the other end of fuel feed pipe 3 enters the top in additional fuel tank 2 through the top of additional fuel tank 2, the top of additional fuel tank 2 is passed in one end of oil suction pipe 4, and the bottom of additional fuel tank 2 inner fluid is sunk to by weight 5, and under remaining in pasta when UAV Maneuver, the other end of oil suction pipe 4 is connected with the oil suction of the Oil sucking device of driving engine.
For ease of oiling, top or the top of additional fuel tank 2 are provided with pouring orifice, and pouring orifice is provided with sealing plug cock or seal cover cap, top or the top of main oil tank 1 are provided with pouring orifice, pouring orifice are provided with sealing plug cock or seal cover cap.During oiling, oiling tube 7 can be inserted at pouring orifice and carry out oiling, after oiling completes, pull out oiling tube 7, build sealing plug cock or seal cover cap.
For while the ventilation of guarantee main oil tank, the fluid in main oil tank can not flow out easily, vent is connected with breather pipe 6, is promoted the height of vent by breather pipe 6, and the fluid in main oil tank is not easily flowed out.
Further, roundabout right-angle bending also can be set on breather pipe 6 and flow out to prevent fluid, as shown in Figure 2.
The utility model solves small-sized long endurance unmanned aircraft under low pasta during large angle maneuver, may failure of fuel system be there is in existing fuel-feed system, cause the problem of engine off and air crash, there is fuel feeding failure-free advantage, for the safe flight of unmanned plane adds guarantee.
Although be below described the utility model in conjunction with the preferred embodiments, but it should be appreciated by those skilled in the art, method and system described in the utility model is not limited to the embodiment described in detailed description of the invention, when not deviating from the utility model spirit and scope be defined by the appended claims, can various amendment, increase be made to the utility model and replace.
Claims (5)
1. a unmanned plane fuel-feed system, it is characterized in that: comprise main oil tank, additional fuel tank, fuel feed pipe and oil suction pipe, top or the top of described main oil tank are provided with vent, one end of described fuel feed pipe is through main oil tank top or top, and the bottom of main oil tank inner fluid is sunk to by weight, the other end of fuel feed pipe enters the top in additional fuel tank through the top of additional fuel tank or top, top or the top of additional fuel tank are passed in one end of oil suction pipe, and the bottom of additional fuel tank inner fluid is sunk to by weight, and under remaining in pasta when UAV Maneuver, the other end of oil suction pipe is connected with the oil suction of the Oil sucking device of driving engine.
2. unmanned plane fuel-feed system according to claim 1, is characterized in that: top or the top of described additional fuel tank are provided with pouring orifice, described pouring orifice is provided with sealing plug cock or seal cover cap.
3. unmanned plane fuel-feed system according to claim 1, is characterized in that: top or the top of described main oil tank are provided with pouring orifice, described pouring orifice is provided with sealing plug cock or seal cover cap.
4. unmanned plane fuel-feed system according to claim 1, is characterized in that: described vent is connected with breather pipe.
5. unmanned plane fuel-feed system according to claim 4, is characterized in that: described breather pipe is provided with roundabout right-angle bending.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420843890.8U CN204399484U (en) | 2014-12-25 | 2014-12-25 | Unmanned plane fuel-feed system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420843890.8U CN204399484U (en) | 2014-12-25 | 2014-12-25 | Unmanned plane fuel-feed system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204399484U true CN204399484U (en) | 2015-06-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201420843890.8U Active CN204399484U (en) | 2014-12-25 | 2014-12-25 | Unmanned plane fuel-feed system |
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| CN (1) | CN204399484U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106241719A (en) * | 2016-09-23 | 2016-12-21 | 江西洪都航空工业集团有限责任公司 | A kind of vapour-pressure type fuel tank refueling control system |
-
2014
- 2014-12-25 CN CN201420843890.8U patent/CN204399484U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106241719A (en) * | 2016-09-23 | 2016-12-21 | 江西洪都航空工业集团有限责任公司 | A kind of vapour-pressure type fuel tank refueling control system |
| CN106241719B (en) * | 2016-09-23 | 2018-04-06 | 江西洪都航空工业集团有限责任公司 | A kind of vapour-pressure type fuel tank refueling control system |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |