CN209617518U - A kind of miniature drone configuring hybrid power - Google Patents
A kind of miniature drone configuring hybrid power Download PDFInfo
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- CN209617518U CN209617518U CN201821993103.2U CN201821993103U CN209617518U CN 209617518 U CN209617518 U CN 209617518U CN 201821993103 U CN201821993103 U CN 201821993103U CN 209617518 U CN209617518 U CN 209617518U
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Abstract
The utility model proposes a kind of miniature drone for configuring hybrid power, the fuselage including flying control module, more rotor propulsive mechanisms, jet propulsion mechanism and bar shaped；Fly control module be set to fuselage at and with more rotor propulsive mechanisms and rocket engine configuration interaction；More rotor propulsive mechanisms include more pieces of electronic rotors for surrounding fuselage setting；The injecting type propulsive mechanism is set at fuselage and nozzle is located at the tail end of fuselage；When unmanned plane low-speed operations, electronic rotor spin generates flying power and is adjusted in the case where flying control module control to unmanned plane during flying posture；When unmanned plane needs high-speed flight, injecting type propulsive mechanism sprays working medium to push unmanned plane during flying；The winged control module controls the nozzle direction and thrust of injecting type propulsive mechanism；This product can be according to real needs, and the high efficiency propeller being made into using liquid fuel or solid fuel is supplemented as the power of miniature drone, and Lai Zengjia voyage endurance or the enough power of instantaneous burst complete target.
Description
Technical field
The utility model relates to vehicle technology field, especially a kind of miniature drone for configuring hybrid power.
Background technique
Miniature drone (Miniature Unmanned Aerial Vehicle, abbreviation MUAV) refer to size relative to
Lesser aircraft for large-scale military unmanned air vehicle or fixed-wing large size unmanned plane.
Develop can long endurance, the miniature drone that can play predictive role be faced with many technologies and engineering problem.
Maximum difficulty is dynamical problem.It must generate enough energy in minimum volume, it is changed into thrust, can support
The enough voyages of miniature drone or endurance simultaneously can provide enough power for airborne equipment and not increase entire fuselage excessive
Weight.
Current miniature drone mostly uses multi-rotor unmanned aerial vehicle greatly in order to reduce equipment cost and maintenance cost, miniature
Multi-rotor unmanned aerial vehicle mostly uses greatly battery driven motor to obtain lifting force and advance and retreat power at present, in freight weight limit condition of itself taking off
It cannot be equipped with high capacity cell in so small space, limit the voyage or endurance of miniature drone in this way.
With current technical conditions, miniature multi-rotor unmanned aerial vehicle can not be using liquid or the conventional gas and oil of gaseous fuel-driven
Engine operation obtains power, besides it is with high costs, maintenance is cumbersome, be less able to satisfy take-off weight limitation and voyage endurance
Contradiction.
Current miniature drone cannot be next simply by battery capacity is further added by the basis of existing battery sizes
Increase voyage or endurance, because battery capacity increases self weight and also will increase, and miniature drone is various from figure because being limited to
Part has stringent take-off weight limitation.
Current battery-driven miniature drone can not be in the enough power of a direction instantaneous burst, to complete such as
The high speed motions such as underriding.
Summary of the invention
The utility model proposes a kind of miniature drone for configuring hybrid power, can be according to real needs, using liquid
The high efficiency propeller that fuel or solid fuel are made into is supplemented as the power of miniature drone, and Lai Zengjia voyage endurance or moment are quick-fried
Send out power enough to complete target.
The utility model uses following technical scheme.
A kind of miniature drone configuring hybrid power, the unmanned plane include flying control module, more rotor propulsive mechanisms, spray
Penetrate the fuselage of propulsive mechanism and bar shaped；The winged control module be set to fuselage at and with more rotor propulsive mechanisms and jet propulsion mechanism
Interaction；More rotor propulsive mechanisms include more pieces of electronic rotors for surrounding fuselage setting；The jet propulsion mechanism is set
At fuselage and nozzle is located at the tail end of fuselage；When unmanned plane low-speed operations, electronic rotor spin generates flying power simultaneously
Unmanned plane during flying posture is adjusted in the case where flying control module control；When unmanned plane needs high-speed flight, injecting type propulsive mechanism
Working medium is sprayed to push unmanned plane during flying；The winged control module controls the nozzle direction and thrust of injecting type propulsive mechanism
System.
When unmanned plane needs high-speed flight, electronic rotor blows lower rotation in windstream, is by gyroplane lift principle
Unmanned plane provides auxiliary lifting.
The jet propulsion mechanism has tubular propulsion casing；The nozzle is set to tubular one end for promoting casing；It pushes away
Fuel compartment and jet pipe are equipped in into casing；Jet pipe both ends communicate to form propulsion unit with fuel compartment and nozzle respectively；When injection pushes away
Into mechanism propulsion unit work when, fly control module and send fuel in instruction pilot fuel cabin, being generated in a manner of detonation can be from
The propulsive working medium of nozzle injection is to generate thrust.
Fuel is stored in the fuel compartment with multiple micro combustors；It is equipped at the locular wall of micro combustor for fire ring to be isolated
The explosion-proof thermal insulation mechanism in border；When the explosion-proof thermal insulation mechanism opening of micro combustor, the indoor fuel of micro-combustion is in shape to be fired
State.
The winged control module is in the micro combustor quantity of state to be fired by changing, to control injecting type propulsive mechanism
The thrust generated when igniting.
The fuel compartment is in the tubular being unidirectionally open, and the opening of tubular fuel compartment is communicated with jet pipe；The micro combustor exists
It is arranged in a straight line in fuel compartment；The ignition order of each micro combustor is from tubular fuel compartment open end to tubular fuel compartment closed end.
It is equipped with miniature initiator at the explosion-proof thermal insulation mechanism of micro combustor, is equipped with electronic ignition device in micro combustor；Institute
It states miniature initiator and electronic ignition device and has control address code and can be flown control module and started in a manner of automatically controlled；Institute
It states and flies the miniature initiator detonation of control module control to open explosion-proof thermal insulation mechanism, enable micro combustor through fuel compartment cavity and jet pipe
It communicates, the indoor fuel of micro-combustion can be flown the electronic ignition device that control module controls and be ignited.
The fuel is solid fuel；The micro combustor locular wall is with the molding of high-strength heat-insulation explosion-proof lamp.
The jet propulsion mechanism fits in formation assembly at unmanned aerial vehicle body；The assembly shape is similar to high-speed rail
The sub warhead streamlined contour or drip type streamlined contour of train are to reduce air drag；It is equipped in the jet propulsion mechanism
More than one propulsion unit.
The unmanned aerial vehicle body head is equipped with image identification module；When injecting type propulsive mechanism pushes unmanned plane high speed to fly
When going, and needing that unmanned aerial vehicle body is made to be accurately directed to target, flies control module control unmanned plane and be in diving flight posture.
The beneficial effects of the utility model are；Utility model device scheme mature and feasible uses easy understandable, human nature
Change；Utility model device unique design and exploitativeness are high, can effectively solve deficiency of the miniature drone in voyage endurance
And cannot moment high-speed mobile the problem of.Will greatly play the wider purposes of miniature drone, it is especially military, anti-
Probably aspect.
Detailed description of the invention
With reference to the accompanying drawings and detailed description to the further details of explanation of the utility model:
Attached drawing 1 is the schematic diagram of the utility model；
Attached drawing 2 is the cut-away illustration of injecting type propulsive mechanism propulsion unit；
In figure: the electronic rotor of 1-；2- fuselage；3- jet propulsion mechanism；4- nozzle；5- micro combustor；6- explosion-proof thermal insulation machine
Structure；7- electronic ignition device；The miniature initiator of 8-；9- fuel.
Specific embodiment
As shown in Figs. 1-2, a kind of miniature drone configuring hybrid power, the unmanned plane include flying control module, more rotations
The fuselage 2 of wing propulsive mechanism, jet propulsion mechanism 3 and bar shaped；The winged control module be set to fuselage at and with more rotor pushers
Structure and rocket engine configuration interaction；More rotor propulsive mechanisms include more pieces of electronic rotors 1 for surrounding fuselage setting；Institute
Jet propulsion mechanism 3 is stated at fuselage 2 and nozzle 4 is located at the tail end of fuselage；When unmanned plane low-speed operations, electronic rotor
Spin generates flying power and is adjusted in the case where flying control module control to unmanned plane during flying posture；When unmanned plane needs high-speed flight
When, working medium is sprayed to push unmanned plane during flying by jet propulsion mechanism；Nozzle court of the winged control module to injecting type propulsive mechanism
To and thrust controlled.
When unmanned plane needs high-speed flight, electronic rotor blows lower rotation in windstream, is by gyroplane lift principle
Unmanned plane provides auxiliary lifting.
The jet propulsion mechanism has tubular propulsion casing；The nozzle is set to tubular one end for promoting casing；It pushes away
Fuel compartment and jet pipe are equipped in into casing；Jet pipe both ends communicate to form propulsion unit with fuel compartment and nozzle respectively；When injection pushes away
Into mechanism propulsion unit work when, fly control module and send fuel 9 in instruction pilot fuel cabin, being generated in a manner of detonation can be from
The propulsive working medium that nozzle 4 sprays is to generate thrust.
Fuel is stored in the fuel compartment with multiple micro combustors 5；It is equipped at the locular wall of micro combustor for burning to be isolated
The explosion-proof thermal insulation mechanism 6 of environment；When the explosion-proof thermal insulation mechanism opening of micro combustor, the indoor fuel of micro-combustion is in be fired
State.
The winged control module is in the micro combustor quantity of state to be fired by changing, to control injecting type propulsive mechanism
The thrust generated when igniting.
The fuel compartment is in the tubular being unidirectionally open, and the opening of tubular fuel compartment is communicated with jet pipe；The micro combustor exists
It is arranged in a straight line in fuel compartment；The ignition order of each micro combustor is from tubular fuel compartment open end to tubular fuel compartment closed end.
It is equipped with miniature initiator 8 at the explosion-proof thermal insulation mechanism of micro combustor, is equipped with electronic ignition device 7 in micro combustor；
The miniature initiator and electronic ignition device have control address code and can be flown control module to be started in a manner of automatically controlled；
The winged control module controls miniature initiator detonation to open explosion-proof thermal insulation mechanism, enables micro combustor through fuel compartment cavity and spray
Pipe communicates, and the indoor fuel of micro-combustion can be flown the electronic ignition device that control module controls and be ignited.
The fuel is solid fuel；The micro combustor locular wall is with the molding of high-strength heat-insulation explosion-proof lamp.
The jet propulsion mechanism fits in formation assembly at unmanned aerial vehicle body；The assembly shape is similar to high-speed rail
The sub warhead streamlined contour or drip type streamlined contour of train are to reduce air drag；It is equipped in the jet propulsion mechanism
More than one propulsion unit.
The unmanned aerial vehicle body head is equipped with image identification module；When injecting type propulsive mechanism pushes unmanned plane high speed to fly
When going, and needing that unmanned aerial vehicle body is made to be accurately directed to target, flies control module control unmanned plane and be in diving flight posture.
Embodiment:
Under regular situation, miniature drone is gone up and down by battery driven motor, flown or turned to.When battery exhausts fastly (can be with
A value is set, just as can make a return voyage automatically when unmanned plane at present on the market, which presets battery, there remains 10%) or receive manipulation
After hand telecommand, the propeller of unmanned plane liquid fuel (or solid fuel) driving can start the igniting of the first combustion chamber of igniting
Device (electronic ignition device), and explosion-proof thermal insulation plate (explosion-proof thermal insulation mechanism) and point of the detonation between combustion chamber as needed
Igniter is fired, can detonate as needed and lights single or multiple liquid or solid Bunkers and adjusts nozzle direction.Nothing
Flight control system on man-machine can be according to prior preset programme path or the energy of preset target and propeller output
Size coordinates the operations of unmanned plane all parts.
The utility model can install one or more sets propellers in different angle on demand.The institute of the utility model propeller
Propellant can be divided into liquid fuel or solid fuel, comprising power resources of the gunpowder as propeller can be used.
Address code is all had positioned at the miniature igniter of micro combustor and the miniature initiator between combustion chamber,
Electric start mode is all used, is provided with explosion-proof thermal insulation device between each micro combustor, is located at each combustion chamber explosion-proof thermal insulation
After miniature initiator between device is detonated by electronics, explosion-proof thermal insulation device can be opened.(one can be set when battery exhausts fastly
It is value, the same just as that can make a return voyage automatically when unmanned plane at present on the market, which presets battery, there remains 10%) or receive manipulation hand and be remotely controlled and refer to
After order, the igniter in the first combustion chamber of the propeller of unmanned plane solid fuel driving can be by electronic ignition, propellant quilt
It lights, indoor pressure of burning increases, and after the high-temperature, high pressure fluid of generation is expanded by tapered divergent nozzle, speed sharply increases
Add, generates thrust and momentum.As needed can automatic or remote initiation be located at the first combustion chamber heat isolation explosion proof plate and second and fire
Burn the first miniature initiator between room heat isolation explosion proof plate and the second igniter of the second combustion chamber of electronic ignition, and so on
It can detonate and light multiple micro combustors to obtain enough flying powers and high speed impulse force.
Flight control system on the hybrid power unmanned plane of utility model device can according to prior preset programme path or
Preset target and the energy size of propeller output coordinate the operations of unmanned plane all parts, realize micro-unmanned
The high-precision orientation holding of machine, gesture stability, speed adjustment, gravity compensation and course line adjustment.
The utility model preferably uses solid fuel, and the burning of solid fuel is a kind of from the high-level energy of small size acquisition
Plain mode.The energy density of one typical solid propellant is about 5 times of the energy density of typical traditional lithium battery.
Therefore, filling fuel of the solid propellant particularly suitable as unmanned plane propeller, meeting micromass culture system needs can be very short
Time in the requirement of thrust and momentum is provided rapidly.In addition, solid fuel propeller does not need liquid or gaseous propellant pushes away
The equipment of the complexity such as pump needed for into device, valve and burning line, whole system are simple and compact for structure.Because without moving parts,
A possibility that friction loss is small, propellant leakage is also relatively low, is conducive to the integration of whole system.It can be by the way that micromass culture be arranged
The structure and size and propellant type, content of device, obtain the thrust and momentum of needs.
The micro combustor of utility model device need to select the material that high temperature resistant, pyroconductivity are small and weight is light.Micro- combustion
The environment of high pressure-temperature in sustained combustion and micro combustor will be realized by burning indoor propellant, and this requires the intensity of combustion chamber wall surface
It is larger, to prevent from rupturing.Material can generally select silicon, heat resistant glass, silicon nitride etc..
The front end of solid fuel propeller in utility model device and body may be designed to be similar to high-speed rail " bullet
Head " and " dripping " fairshaped shape, more meet aerodynamics in this way.Be conducive to the rising and advance of hybrid power unmanned plane
Flight.
Propeller in utility model device can according to need and be designed to various shapes, and centre is gathered multiple micro- combustions
Room, micro- initiator, microdot firearm and the nozzle that two or more directions are set are burnt, and by process control, electronics fire point
Fire, to generate thrust and impulse force in different directions.
Utility model device is equipped with face identification system and micro high explosives, by locking mesh after recognition of face
Mark, starts solid fuel propulsion system, and fast dive rushes at target and ignites micro high explosives.Make in military and anti-probably field
With huge.
Claims (9)
1. a kind of miniature drone for configuring hybrid power, it is characterised in that: the unmanned plane is pushed away including winged control module, more rotors
Into the fuselage of mechanism, jet propulsion mechanism and bar shaped；The winged control module be set to fuselage at and with more rotor propulsive mechanisms and spray
Penetrate propulsive mechanism interaction；More rotor propulsive mechanisms include more pieces of electronic rotors for surrounding fuselage setting；The injection
Propulsive mechanism is set at fuselage and nozzle is located at the tail end of fuselage.
2. a kind of miniature drone for configuring hybrid power according to claim 1, it is characterised in that: electronic rotor can be
Windstream blows lower rotation, provides auxiliary lifting by gyroplane lift principle for unmanned plane.
3. a kind of miniature drone for configuring hybrid power according to claim 1, it is characterised in that: the jet propulsion
Mechanism has tubular propulsion casing；The nozzle is set to tubular one end for promoting casing；Promote casing in be equipped with fuel compartment and
Jet pipe；Jet pipe both ends communicate to form propulsion unit with fuel compartment and nozzle respectively；Fly the transmittable instruction pilot fuel cabin of control module
Interior fuel generates the propulsive working medium that can be sprayed from nozzle in a manner of detonation to generate thrust.
4. a kind of miniature drone for configuring hybrid power according to claim 3, it is characterised in that: in the fuel compartment
Fuel is stored with multiple micro combustors；The explosion-proof thermal insulation mechanism for burning situation to be isolated is equipped at the locular wall of micro combustor；When
When the explosion-proof thermal insulation mechanism opening of micro combustor, the indoor fuel of micro-combustion is in state to be fired.
5. a kind of miniature drone for configuring hybrid power according to claim 4, it is characterised in that: the fuel compartment is in
The opening of the tubular being unidirectionally open, tubular fuel compartment is communicated with jet pipe；The micro combustor is arranged in a straight line in fuel compartment；It is each micro-
The ignition order of combustion chamber is from tubular fuel compartment open end to tubular fuel compartment closed end.
6. a kind of miniature drone for configuring hybrid power according to claim 5, it is characterised in that: micro combustor is prevented
It is equipped with miniature initiator at quick-fried heat-shield mechanism, is equipped with electronic ignition device in micro combustor；The miniature initiator and electronics point
Fiery device has control address code and can be flown control module to be started in a manner of automatically controlled.
7. a kind of miniature drone for configuring hybrid power according to claim 4, it is characterised in that: the fuel is solid
Fluid fuel；The micro combustor locular wall is with the molding of high-strength heat-insulation explosion-proof lamp.
8. a kind of miniature drone for configuring hybrid power according to claim 3, it is characterised in that: the jet propulsion
Mechanism fits in formation assembly at unmanned aerial vehicle body；The sub warhead that the assembly shape is similar to high-speed rail train is streamlined outer
Shape or drip type streamlined contour are to reduce air drag；More than one propulsion unit is equipped in the jet propulsion mechanism.
9. a kind of miniature drone for configuring hybrid power according to claim 3, it is characterised in that: the unmanned plane machine
Body head is equipped with image identification module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821993103.2U CN209617518U (en) | 2018-11-30 | 2018-11-30 | A kind of miniature drone configuring hybrid power |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821993103.2U CN209617518U (en) | 2018-11-30 | 2018-11-30 | A kind of miniature drone configuring hybrid power |
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| CN209617518U true CN209617518U (en) | 2019-11-12 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109335004A (en) * | 2018-11-30 | 2019-02-15 | 福建星图智控科技有限公司 | A kind of miniature drone configuring hybrid power |
| CN111907710A (en) * | 2020-08-17 | 2020-11-10 | 来宾市农业科学院 | Sugarcane medicament spraying system |
-
2018
- 2018-11-30 CN CN201821993103.2U patent/CN209617518U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109335004A (en) * | 2018-11-30 | 2019-02-15 | 福建星图智控科技有限公司 | A kind of miniature drone configuring hybrid power |
| CN109335004B (en) * | 2018-11-30 | 2024-04-26 | 福建星图智控科技有限公司 | Micro unmanned aerial vehicle equipped with hybrid power |
| CN111907710A (en) * | 2020-08-17 | 2020-11-10 | 来宾市农业科学院 | Sugarcane medicament spraying system |
| CN111907710B (en) * | 2020-08-17 | 2021-08-20 | 来宾市农业科学院 | Sugarcane medicament spraying system |
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