CN113212772A - Fuel device of jet power flight knapsack - Google Patents
Fuel device of jet power flight knapsack Download PDFInfo
- Publication number
- CN113212772A CN113212772A CN202110543217.7A CN202110543217A CN113212772A CN 113212772 A CN113212772 A CN 113212772A CN 202110543217 A CN202110543217 A CN 202110543217A CN 113212772 A CN113212772 A CN 113212772A
- Authority
- CN
- China
- Prior art keywords
- oil
- fuel
- pipe
- air
- frame
- 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.)
- Pending
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 57
- 239000003921 oil Substances 0.000 claims abstract description 93
- 239000000295 fuel oil Substances 0.000 claims abstract description 61
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 51
- 230000006835 compression Effects 0.000 claims abstract description 32
- 238000007906 compression Methods 0.000 claims abstract description 32
- 230000007246 mechanism Effects 0.000 claims abstract description 28
- 238000007789 sealing Methods 0.000 claims description 8
- 239000012528 membrane Substances 0.000 claims description 7
- 238000001914 filtration Methods 0.000 claims description 6
- 230000001105 regulatory effect Effects 0.000 claims description 6
- 230000009189 diving Effects 0.000 abstract description 4
- 239000007788 liquid Substances 0.000 description 10
- 230000009471 action Effects 0.000 description 6
- 230000013011 mating Effects 0.000 description 4
- 239000003502 gasoline Substances 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
- B64D37/10—Constructional adaptations thereof to facilitate fuel pressurisation
-
- 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Closures For Containers (AREA)
Abstract
The invention discloses a fuel device of a jet power flight backpack, which relates to the technical field of jet flight backpacks and comprises a first box frame, a second box frame, a clamping block and wings, wherein a wind power mechanism is arranged in the middle of one end of the first box frame and comprises a wind pressure pipe, a supporting frame, a central shaft, an impeller, an air compression impeller assembly and a guide pipe. According to the invention, the impeller is driven by the air flow to rotate at a high speed, the impeller and the air compression impeller component share the central shaft, so that the air compression impeller component rotates at a high speed, the air compression impeller component compresses the air flow, the compressed air flow transmits the compressed air flow into the fuel oil cavity through the guide pipe, the high-pressure air flow drives the oil stabilizing plate of the oil stabilizing mechanism to be always attached to the fuel oil in the fuel oil cavity, and further, when the aircraft flies in a diving mode or a side flying mode, the fuel oil is effectively prevented from deviating from the fuel oil pipe or even being separated from the fuel oil pipe, so that the fuel oil can be supplied to an engine all the time.
Description
Technical Field
The invention relates to the technical field of jet flying backpacks, in particular to a fuel device of a jet power flying backpack.
Background
The jet flying backpack is propelled by a rocket propeller, controls the magnitude of jet thrust through a controller button to control the flying speed and height, and can also be used for soft landing by reducing the jet thrust.
The jet flying backpack mainly uses high-strength light carbon fibers to manufacture main components of the jet backpack, a small amount of fibers are added in raw materials, so that the added materials are firmer, and a two-liter and two-hundred-horsepower gasoline engine is arranged to provide energy power for two huge rotor wing engines on two sides of a pilot, wherein the gasoline engine needs an oil tank to supply oil to the gasoline engine.
In the prior art, after a pilot bears a jet flight backpack and descends at high altitude, fuel oil is provided for four groups of engines below two groups of wings on two sides of the pilot by an oil tank, the engines acquire power to generate thrust, after the pilot flies for a period of time, the fuel oil in the oil tank is consumed to a certain extent, the fuel oil in the oil tank can be separated from an oil outlet pipe, the oil supply amount to the engines is reduced, and the power of the engines is reduced.
Disclosure of Invention
Based on the above, the invention aims to provide a fuel device of a jet power flight backpack, so as to solve the technical problem that in the prior art, when a pilot carries the jet power flight backpack in flight, fuel oil cannot be supplied to an engine in time, so that the power of the engine is reduced.
In order to achieve the purpose, the invention provides the following technical scheme: a fuel device of a jet power flight backpack comprises a first box frame, a second box frame, a clamping block and wings, wherein a wind power mechanism is arranged in the middle of one end of the first box frame and comprises a wind pressure pipe, a supporting frame, a central shaft, an impeller, an air compression impeller assembly and a flow guide pipe;
the top end and the bottom end of the interior of the air pressure pipe are fixedly provided with support frames, the interiors of the two groups of support frames are rotatably connected with a central shaft, an impeller and an air compression impeller component are sequentially arranged on the outer side of the central shaft from top to bottom, and the bottom of the air pressure pipe is provided with a flow guide pipe extending into the fuel oil cavity;
and an oil stabilizing mechanism matched with the fuel oil cavity is arranged in the second tank bracket, and an oil stabilizing plate is connected in the fuel oil cavity in a sliding manner.
By adopting the technical scheme, when a pilot flies at high altitude by bearing the jet flying backpack, in the early stage of flight, fuel in the fuel tank is sufficient, the fuel can be consumed to a certain extent along with the increase of the flying time, at the moment, air airflow enters the wind pressure pipe of the wind mechanism through the wind cap, the air airflow drives the impeller to rotate at high speed, the air compression impeller component rotates at high speed because the impeller and the air compression impeller component share the central shaft, the air compression impeller component compresses the air airflow, the compressed airflow is transmitted into the fuel cavity through the guide pipe, the high-pressure air airflow drives the oil stabilizing plate of the oil stabilizing mechanism to be always attached to the top of the fuel liquid level in the fuel cavity, the oil stabilizing plate descends along with the descending of the fuel liquid level under the action of the air airflow pressure, and further during the diving flight or the side flight, the fuel is always positioned at the bottom of the fuel cavity, so that the fuel is effectively prevented from deviating from the fuel outlet pipe or even separating from the fuel outlet pipe, the fuel can be supplied to the engine of the engine all the time, and the problem of power reduction of the engine is avoided.
The invention is further provided that the wind power mechanism further comprises a filtering membrane, a first one-way valve, a wind cap, a bearing, overflow valves and overflow air pipes, wherein the wind cap is fixedly arranged at the top end of the wind pressure pipe, the filtering membrane is fixedly arranged in the wind pressure pipe and positioned below the air compression impeller assembly, the first one-way valves extending into the fuel oil cavity are arranged at the tail ends of the two groups of flow guide pipes, the overflow air pipes extending into the wind pressure pipe are transversely arranged on two sides of the outside of the wind pressure pipe, and the overflow valves extending into the overflow air pipes are arranged on the outer sides of the two groups of overflow air pipes.
By adopting the technical scheme, the two sides of the bottom of the wind pressure pipe are transversely provided with the overflow pipes, the two groups of overflow pipes are both provided with overflow valves in a matching way, when the oil stabilizing plate is attached to the liquid level of the fuel oil, the output quantity of the fuel oil is a fixed quantity under the action of the two groups of flow regulating valves, so that the fuel oil can not increase the output quantity of the fuel oil under the pressure of the oil stabilizing plate, so that the honeycomb duct can not continuously inject high-pressure air into the fuel cavity, at the moment, the air compression impeller component continuously compresses the air flow, the pressure of the air flow after continuous compression reaches the pressure value set by the overflow valve, and the compressed air flow is transmitted to the interior of the engine through the two groups of overflow air pipes, so that the air inflow of the engine during working is further improved, the air inflow is increased, the working efficiency of the engine is higher, and the power of the engine is further improved.
The invention is further provided that both sides of the top of the first box frame and the second box frame are provided with air inlets matched with the flow guide pipe, and the impeller and the central shaft are rotatably connected through a bearing.
Through adopting above-mentioned technical scheme, the air inlet is convenient to be admitted air to the fuel pocket inside, and the setting of bearing makes the impeller rotate more smoothly.
The invention is further arranged in a way that a fuel cavity is formed between the first tank frame and the second tank frame, a plurality of groups of clamping blocks are uniformly and fixedly arranged on two sides of the first tank frame and the second tank frame, and two sides of the clamping blocks are connected with two groups of wings in a clamping way.
Through adopting above-mentioned technical scheme, the multiunit fixture block can carry out the block to two sets of wings and connect, and the installation is dismantled conveniently.
The oil stabilizing mechanism further comprises an oil stabilizing plate, a second one-way valve, a corrugated pipe, an oil filling pipe, a sealing plug, a matching groove and a limiting slide block.
By adopting the technical scheme, the oil stabilizing mechanism can stabilize the fuel oil in the fuel oil cavity, and the phenomenon that the fuel oil shifts along with the change of flight action is avoided.
The oil stabilizing plate is characterized in that a second one-way valve is fixedly arranged at the central position in the oil stabilizing plate, a corrugated pipe is fixedly arranged at the top of the second one-way valve, oil filling pipes positioned in the first box frame and the second box frame are fixedly arranged at the top of the corrugated pipe, and sealing plugs matched with the oil filling pipes are arranged in the oil filling pipes.
Through adopting above-mentioned technical scheme, when steady oily board goes up and down, through setting up the bellows, can not influence oiling to the inside of fuel pocket.
The oil stabilizing plate is further provided with matching grooves matched with the first check valve on two sides inside the oil stabilizing plate, one end of the oil stabilizing plate is fixedly provided with a limiting slide block extending into the second box frame, and one end inside the second box frame is provided with a sliding groove matched with the limiting slide block.
Through adopting above-mentioned technical scheme, the cooperation groove can play the mating reaction with first check valve, and spacing slider makes steady oilboard more stable when burning the lift of oil intracavity portion, can not take place to rock the phenomenon of skew.
The invention is further provided with a first matching frame matched with the wind pressure pipe arranged in the middle of one end of the first box frame, and second matching frames matched with the flow guide pipe are arranged on two sides of the first matching frame at one end of the first box frame.
Through adopting above-mentioned technical scheme, first cooperation frame plays the fixed limiting displacement to the wind pressure pipe, and the second cooperation frame plays the fixed limiting displacement to the honeycomb duct.
The fuel oil tank is characterized in that an oil outlet pipe is fixedly arranged at the bottom of the second tank frame, flow regulating valves matched with the second tank frame are fixedly arranged on two sides of the bottom of the second tank frame, and the top of the oil outlet pipe extends to the bottom end inside the fuel oil cavity.
By adopting the technical scheme, the engine can be conveniently supplied with oil, and the flow of the oil supply can be controlled.
In summary, the invention mainly has the following beneficial effects:
1. when the invention flies at high altitude by carrying the jet flying backpack on the pilot, the air current enters the wind pressure pipe of the wind mechanism through the hood, the air current drives the impeller to rotate at high speed, because the impeller and the air compression impeller component share the central shaft, the air compression impeller component rotates at high speed, the air compression impeller component compresses air flow, the compressed air flow transmits the compressed air flow into the fuel oil cavity through the flow guide pipe, the high-pressure air flow drives the oil stabilizing plate of the oil stabilizing mechanism to be always attached to the fuel oil in the fuel oil cavity, further, when the aircraft flies in a diving way or a side flight way, the fuel oil is always positioned at the bottom of the fuel oil cavity, thereby effectively avoiding the fuel oil from deviating from the oil outlet pipe or even separating from the oil outlet pipe, the fuel can be supplied to the engine all the time, so that the problem of power reduction of the engine is solved;
2. according to the invention, the overflow air pipes are transversely arranged on two sides of the bottom of the air pressure pipe, the two groups of overflow air pipes are provided with the overflow valves in a matched manner, when the oil stabilizing plate is attached to the liquid level of fuel oil, the guide pipe cannot continuously inject high-pressure air into the fuel oil cavity, at the moment, the air compression impeller assembly continuously compresses the air flow, the pressure of the air flow after continuous compression reaches the set pressure value of the overflow valves, and then the compressed air flow is transmitted into the engine through the two groups of overflow air pipes, so that the air inflow of the engine during operation is further improved, the air inflow is increased, the working efficiency of the engine is higher, and the power of the engine is further improved.
Drawings
FIG. 1 is a front view of the present invention in an assembled configuration;
FIG. 2 is an exploded view of the present invention from a first perspective;
FIG. 3 is an exploded view of the present invention from a second perspective;
FIG. 4 is a side cross-sectional view of the present invention;
FIG. 5 is an exploded view of the wind mechanism of the present invention;
FIG. 6 is an exploded view of the oil stabilizing mechanism of the present invention;
FIG. 7 is a partial cross-sectional view of the present invention;
FIG. 8 is a cross-sectional view of the oil stabilization mechanism of the present invention;
fig. 9 is a schematic view of the back side assembly of the present invention.
In the figure: 1. a first case frame; 2. a second cabinet frame; 3. a clamping block; 4. an airfoil; 5. a fuel oil chamber; 6. a wind power mechanism; 601. a wind pressure pipe; 602. a support frame; 603. a central shaft; 604. an impeller; 605. air compressing the impeller assembly; 606. a filtration membrane; 607. a flow guide pipe; 608. a first check valve; 609. a hood; 610. a bearing; 611. an overflow valve; 612. an overflow gas pipe; 7. an oil stabilizing mechanism; 701. an oil stabilizing plate; 702. a second one-way valve; 703. a bellows; 704. an oil filling pipe; 705. a sealing plug; 706. a mating groove; 707. a limiting slide block; 8. a first mating frame; 9. an air inlet; 10. a chute; 11. an oil outlet pipe; 12. a flow regulating valve; 13. and a second mating frame.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
The following describes an embodiment of the present invention based on its overall structure.
A fuel device of a jet power flying backpack is shown in figures 1, 2, 4, 5 and 6 and comprises a first box frame 1, a second box frame 2, a clamping block 3 and an airfoil 4, wherein a wind power mechanism 6 is arranged in the middle of one end of the first box frame 1, and the wind power mechanism 6 comprises a wind pressure pipe 601, a support frame 602, a central shaft 603, an impeller 604, an air compression impeller assembly 605 and a flow guide pipe 607;
the top end and the bottom end of the interior of the wind pressure pipe 601 are fixedly provided with support frames 602, the interior of the two groups of support frames 602 is rotatably connected with a central shaft 603, the support frames 602 play a role of supporting the central shaft 603, and are rotatably connected with the central shaft 603, so that the central shaft 603 can conveniently rotate, an impeller 604 and an air compression impeller assembly 605 are sequentially arranged from top to bottom outside the central shaft 603, the impeller 604 is driven by external air flow to rotate so as to drive the air compression impeller assembly 605 to rotate, the bottom of the wind pressure pipe 601 is provided with a flow guide pipe 607 extending to the interior of the fuel oil cavity 5, the flow guide pipe 607 transmits the compressed air flow into the interior of the fuel oil cavity 5, the wind mechanism 6 further comprises a filter membrane 606, a first check valve 608, a wind cap 609, a bearing 610, an overflow valve 611 and an overflow pipe 612, the top end of the wind pressure pipe 601 is fixedly provided with a wind cap 609, the interior of the wind pressure pipe 601 is fixedly provided with the filter membrane 606 below the air compression impeller assembly, the ends of the two groups of flow guide pipes 607 are provided with first check valves 608 extending into the fuel oil cavity 5, two sides of the outside of the air pressure pipe 601 are transversely provided with overflow air pipes 612 extending into the inside of the air pressure pipe 601, the outsides of the two groups of overflow air pipes 612 are provided with overflow valves 611 extending into the inside of the two groups of overflow air pipes, when the oil stabilizing plate 701 is attached to the liquid level of the fuel oil, the output quantity of the fuel oil of the oil outlet pipe 11 is fixed under the action of the two groups of flow regulating valves 12, so that the fuel oil can not increase the output quantity of the fuel oil under the pressure of the oil stabilizing plate 701, so that the flow guide pipe 607 can not continuously inject high-pressure air into the fuel oil cavity 5, at this time, the air compression impeller assembly 605 continuously compresses the air flow, the pressure of the air flow after continuous compression reaches the pressure value set by the overflow valves 611, and the compressed air flow is transmitted into the engine through the two groups of overflow air pipes 612, thereby further improving the air intake amount of the engine during operation, the working efficiency of the engine is higher when the air inflow is increased, and the power of the engine is further improved;
an oil stabilizing mechanism 7 matched with the fuel cavity 5 is arranged in the second tank bracket 2, an oil stabilizing plate 701 is connected in the fuel cavity 5 in a sliding manner, the oil stabilizing mechanism 7 comprises an oil stabilizing plate 701, a second one-way valve 702, a corrugated pipe 703, an oil filling pipe 704, a sealing plug 705, a matching groove 706 and a limiting slide block 707, the second one-way valve 702 is fixedly arranged at the central position in the oil stabilizing plate 701, the second one-way valve 702 effectively prevents air entering the fuel cavity 5 from escaping, the corrugated pipe 703 is fixedly arranged at the top of the second one-way valve 702, the corrugated pipe 703 can be extended and retracted, the oil filling pipe 704 positioned in the first tank bracket 1 and the second tank bracket 2 is fixedly arranged at the top of the corrugated pipe 703, the matching groove 706 matched with the first sealing plug 608 is arranged in the oil stabilizing plate 701, the limiting slide block 707 extending to the second tank bracket 2 is fixedly arranged at one end of the oil stabilizing plate 701, one end of the interior of the second box frame 2 is provided with a sliding groove 10 matched with the limiting sliding block 707.
Referring to fig. 2, 3 and 6, the air inlets 9 matched with the flow guide pipe 607 are disposed on both sides of the top of the first box frame 1 and the second box frame 2, and the impeller 604 and the central shaft 603 are rotatably connected through a bearing 610. By the arrangement of the structure, compressed air flow can conveniently enter the fuel oil cavity 5, and the oil stabilizing plate 701 is compressed to move downwards.
Referring to fig. 1 and 9, a fuel cavity 5 is formed between the first tank frame 1 and the second tank frame 2, a plurality of clamping blocks 3 are uniformly and fixedly arranged on two sides of the first tank frame 1 and the second tank frame 2, and two sides of the plurality of clamping blocks 3 are connected with two sets of wings 4 in a clamping manner. By the arrangement of the structure, the wing is convenient to disassemble and assemble.
Referring to fig. 2 and 3, a first fitting frame 8 fitted with the wind pressure pipe 601 is disposed at a middle position of one end of the first box frame 1, and second fitting frames 13 fitted with the wind guide pipe 607 are disposed at two sides of the first fitting frame 8 at one end of the first box frame 1. By the arrangement of the structure, the wind pressure pipe 601 and the flow guide pipe 607 can be conveniently supported and fixed.
Referring to fig. 2, 4 and 5, the oil outlet pipe 11 is fixedly disposed at the bottom of the second tank frame 2, the flow control valve 12 matched with the second tank frame 2 is fixedly disposed at two sides of the bottom of the second tank frame 2, and the top of the oil outlet pipe 11 extends to the bottom end inside the fuel oil cavity 5. By the arrangement of the structure, oil can be conveniently supplied to the engine of the engine.
The working principle of the invention is as follows: when the jet power flight backpack is used, an external engine is arranged at the bottoms of the two groups of wings, the two groups of oil outlet pipes 11 are communicated with an oil inlet pipe of the engine through an external pipeline, and the two groups of overflow air pipes 612 are communicated with an air inlet pipe of the engine;
firstly, fuel needs to be added before flying, an initial state of the oil stabilizing plate 701 is located at the bottom end inside the fuel cavity 5, an external oil filling pipe is communicated with an oil filling pipe 704 by unscrewing a sealing plug 705, the fuel enters the bottom of the oil stabilizing plate 701 through a corrugated pipe 703 and a second one-way valve 702, along with the increase of oil filling, the liquid surface at the top of the fuel jacks up the oil stabilizing plate 701, the oil stabilizing plate 701 slides upwards inside the fuel cavity 5, and after the fuel inside the fuel cavity 5 is filled, the oil stabilizing plate 701 is jacked to the top end inside the fuel cavity 5 by the liquid surface at the top of the fuel to be fixed;
when a pilot flies at high altitude by carrying the jet flying backpack, fuel in the fuel tank is sufficient in the early stage of flight, and the fuel can be consumed to a certain extent along with the increase of the flight time, at the moment, air flow enters the air pressure pipe 601 of the wind mechanism 6 through the hood 609, drives the impeller 604 to rotate at high speed through the air flow, and further, the air compression impeller component 605 rotates at high speed because the impeller 604 and the air compression impeller component 605 share the central shaft 603, the air compression impeller component 605 compresses the air flow, the compressed air flow is transmitted into the fuel cavity 5 through the guide pipe 607, the high-pressure air flow drives the fuel stabilizing plate 701 of the fuel stabilizing mechanism 7 to be always attached to the top of the fuel liquid level in the fuel cavity 5, and the fuel stabilizing plate 701 descends along with the descending of the fuel liquid level under the action of the air flow pressure, when the aircraft flies in a diving mode or a side-flying mode, the fuel oil is always positioned at the bottom of the fuel oil cavity 5, so that the fuel oil is effectively prevented from deviating from the oil outlet pipe 11 and even being separated from the oil outlet pipe 11, the fuel oil can be supplied to an engine of the engine all the time, and the problem that the power of the engine is reduced is solved;
furthermore, the top end of the oil outlet pipe 11 extends to the bottom end inside the fuel oil cavity 5, and the oil outlet pipe 11 is in a one-in two-out oil supply mode and can supply oil to engine engines on two sides of the wing;
the blast cap 609 is positioned at the top of the wind pressure pipe 601, and a plurality of groups of filtering holes are uniformly formed in the surface of the blast cap 609, so that impurities in the air flow can be filtered to a certain degree by the blast cap 609, the air flow entering the wind pressure pipe 601 cannot contain large-particle impurity dust, the service lives of the impeller 604 and the air compression impeller assembly 605 are further protected, and abrasion is reduced;
still further, a first one-way valve 608 is disposed between the ends of the two sets of flow guide pipes 607 and the air inlet 9, and the first one-way valve 608 only allows compressed air to enter the fuel oil chamber 5, but does not allow the air pressure in the area above the oil stabilizing plate 701 in the fuel oil chamber 5 to be discharged from the fuel oil chamber 5.
Although embodiments of the present invention have been shown and described, it is intended that the present invention should not be limited thereto, that the particular features, structures, materials or characteristics described may be combined in any suitable manner in any one or more embodiments or examples, and that modifications, substitutions, variations or the like, which are not inventive and may be made by those skilled in the art without departing from the principle and spirit of the present invention and without departing from the scope of the claims.
Claims (9)
1. The utility model provides a fuel device of jet-propelled power flight knapsack, includes first tank tower (1), second tank tower (2), fixture block (3) and wing (4), its characterized in that: a wind power mechanism (6) is arranged in the middle of one end of the first box frame (1), and the wind power mechanism (6) comprises a wind pressure pipe (601), a support frame (602), a central shaft (603), an impeller (604), an air compression impeller assembly (605) and a guide pipe (607);
the top end and the bottom end of the interior of the air pressure pipe (601) are fixedly provided with supporting frames (602), the interiors of the two groups of supporting frames (602) are rotatably connected with a central shaft (603), an impeller (604) and an air compression impeller assembly (605) are sequentially arranged on the outer side of the central shaft (603) from top to bottom, and the bottom of the air pressure pipe (601) is provided with a flow guide pipe (607) extending to the interior of the fuel oil cavity (5);
the oil stabilizing mechanism (7) matched with the fuel oil cavity (5) is arranged inside the second tank frame (2), and an oil stabilizing plate (701) is connected inside the fuel oil cavity (5) in a sliding mode.
2. A fuel assembly for a jet-powered flying backpack according to claim 1 wherein: the wind power mechanism (6) further comprises a filtering membrane (606), a first one-way valve (608), a hood (609), a bearing (610), an overflow valve (611) and an overflow air pipe (612), the hood (609) is fixedly arranged at the top end of the wind pressure pipe (601), the filtering membrane (606) is fixedly arranged below the air compression impeller assembly (605) inside the wind pressure pipe (601), the first one-way valve (608) extending to the inside of the fuel oil cavity (5) is arranged at the tail end of the draft pipe (607), the overflow air pipes (612) extending to the inside of the wind pressure pipe (601) are transversely arranged on two sides of the outside of the wind pressure pipe (601), and the overflow valve (611) extending to the inside of the overflow air pipes is arranged on the outer side of the two groups of the overflow air pipes (612).
3. A fuel assembly for a jet-powered flying backpack according to claim 2 wherein: the two sides of the tops of the first box frame (1) and the second box frame (2) are provided with air inlets (9) matched with the flow guide pipe (607), and the impeller (604) and the central shaft (603) are rotatably connected through a bearing (610).
4. A fuel assembly for a jet-powered flying backpack according to claim 1 wherein: constitute between first tank tower (1) and second tank tower (2) fuel chamber (5), first tank tower (1) and second tank tower (2) both sides are evenly fixed and are provided with multiunit fixture block (3), multiunit fixture block (3) both sides all the block is connected with two sets of wings (4).
5. A fuel assembly for a jet-powered flying backpack according to claim 1 wherein: the oil stabilizing mechanism (7) comprises an oil stabilizing plate (701), a second one-way valve (702), a corrugated pipe (703), an oil filling pipe (704), a sealing plug (705), a matching groove (706) and a limiting sliding block (707).
6. A fuel assembly for a jet-powered flying backpack according to claim 5 wherein: a second one-way valve (702) is fixedly arranged at the center position in the oil stabilizing plate (701), a corrugated pipe (703) is fixedly arranged at the top of the second one-way valve (702), an oil filling pipe (704) located in the first box frame (1) and the second box frame (2) is fixedly arranged at the top of the corrugated pipe (703), and a sealing plug (705) matched with the oil filling pipe (704) is arranged in the oil filling pipe (704).
7. A fuel assembly for a jet-powered flying backpack according to claim 5 wherein: and the two sides in the oil stabilizing plate (701) are provided with matching grooves (706) matched with the first check valves (608), one end of the oil stabilizing plate (701) is fixedly provided with a limiting sliding block (707) extending to the inside of the second box frame (2), and one end in the inside of the second box frame (2) is provided with a sliding groove (10) matched with the limiting sliding block (707).
8. A fuel assembly for a jet-powered flying backpack according to claim 1 wherein: the middle position department of first tank tower (1) one end is provided with first cooperation frame (8) with wind pressure pipe (601) matched with, first tank tower (1) one end is located first cooperation frame (8) both sides and all is provided with second cooperation frame (13) with honeycomb duct (607) matched with.
9. A fuel assembly for a jet-powered flying backpack according to claim 1 wherein: the fuel oil tank is characterized in that an oil outlet pipe (11) is fixedly arranged at the bottom of the second tank frame (2), flow regulating valves (12) matched with the second tank frame (2) are fixedly arranged on two sides of the bottom of the second tank frame (2), and the top of the oil outlet pipe (11) extends to the bottom end inside the fuel oil cavity (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110543217.7A CN113212772A (en) | 2021-05-19 | 2021-05-19 | Fuel device of jet power flight knapsack |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110543217.7A CN113212772A (en) | 2021-05-19 | 2021-05-19 | Fuel device of jet power flight knapsack |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113212772A true CN113212772A (en) | 2021-08-06 |
Family
ID=77092862
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110543217.7A Pending CN113212772A (en) | 2021-05-19 | 2021-05-19 | Fuel device of jet power flight knapsack |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113212772A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB742700A (en) * | 1951-04-16 | 1955-12-30 | Mini Of Supply | Improvements in or relating to aircraft fuel systems |
| CN102808711A (en) * | 2012-08-14 | 2012-12-05 | 李恒 | Compressed-air oil tank oil supply system |
| US20140345700A1 (en) * | 2013-05-22 | 2014-11-27 | Hamilton Sundstrand Corporation | Pressure monitoring system for a fuel tank and method |
| CN109915262A (en) * | 2017-12-12 | 2019-06-21 | 中电科特种飞机***工程有限公司 | A kind of aero-engine and its wind power boosting device |
| CN110466786A (en) * | 2019-08-20 | 2019-11-19 | 陶水芳 | A kind of airborne pressure maintaining fuel tank |
| CN110949675A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Auxiliary oil supply device for airplane negative overload |
| CN112249344A (en) * | 2020-10-10 | 2021-01-22 | 西安爱生技术集团公司 | High-altitude air-entraining and pressurizing system and method for unmanned aerial vehicle oil tank |
-
2021
- 2021-05-19 CN CN202110543217.7A patent/CN113212772A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB742700A (en) * | 1951-04-16 | 1955-12-30 | Mini Of Supply | Improvements in or relating to aircraft fuel systems |
| CN102808711A (en) * | 2012-08-14 | 2012-12-05 | 李恒 | Compressed-air oil tank oil supply system |
| US20140345700A1 (en) * | 2013-05-22 | 2014-11-27 | Hamilton Sundstrand Corporation | Pressure monitoring system for a fuel tank and method |
| CN109915262A (en) * | 2017-12-12 | 2019-06-21 | 中电科特种飞机***工程有限公司 | A kind of aero-engine and its wind power boosting device |
| CN110466786A (en) * | 2019-08-20 | 2019-11-19 | 陶水芳 | A kind of airborne pressure maintaining fuel tank |
| CN110949675A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Auxiliary oil supply device for airplane negative overload |
| CN112249344A (en) * | 2020-10-10 | 2021-01-22 | 西安爱生技术集团公司 | High-altitude air-entraining and pressurizing system and method for unmanned aerial vehicle oil tank |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106988926B (en) | Whirlpool axis turbofan combined cycle engine | |
| CN101134508B (en) | Fan exhaust nozzle for turbofan engine | |
| US20120056034A1 (en) | Variable cycle vtol powerplant | |
| CN101649781A (en) | Jet engine | |
| CN110985215B (en) | Integrated system for starting of micro turbojet engine | |
| GB900903A (en) | Vehicle capable of flight within the ground cushion and of free flight | |
| CN207701226U (en) | A kind of gas turbine fuel service system | |
| CN113202655B (en) | Solid-liquid stamping combined engine | |
| US20190186418A1 (en) | Multi-Hybrid Aircraft Engine | |
| US3699771A (en) | Rotary wing aircraft lift and propulsion method and systems | |
| CN107905899A (en) | A kind of gas turbine fuel service system and its control method | |
| CN211494470U (en) | Foldable device of seed launching tube of dibble seeding unmanned aerial vehicle | |
| CN109899177A (en) | Multicore scheming band after-burner turbofan aeropropulsion system and aircraft | |
| CN113212772A (en) | Fuel device of jet power flight knapsack | |
| CN107021235A (en) | A kind of low-to-medium altitude aircraft driving device, driving method and low-to-medium altitude aircraft | |
| RU86560U1 (en) | VERTICAL TAKEOFF AND LANDING FLIGHT | |
| CN103615367B (en) | A kind of energy storage declines head fluid energy pumping system | |
| CN107524526A (en) | Compressor blowdown gas-turbine unit | |
| CN203094443U (en) | Mixed lifting system for fixed duct | |
| CN114738115A (en) | Gas turbine engine with contra-rotating centrifugal compressor driven by contra-rotating centripetal turbine | |
| CN110433574A (en) | A kind of forced-ventilated fuel oil bubble stripper for Micro-Aviation Engine | |
| CN2646046Y (en) | Novel helicopter | |
| CN101576021A (en) | Spiral type thrust engine | |
| CN112483275B (en) | Propeller and aircraft | |
| CN102588303A (en) | Axial-flow compressor with air-supplying and pressurizing function |
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 |