CN206520738U - Emission type unmanned plane and its system - Google Patents
Emission type unmanned plane and its system Download PDFInfo
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- CN206520738U CN206520738U CN201720013493.1U CN201720013493U CN206520738U CN 206520738 U CN206520738 U CN 206520738U CN 201720013493 U CN201720013493 U CN 201720013493U CN 206520738 U CN206520738 U CN 206520738U
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- 239000002360 explosive Substances 0.000 claims description 5
- 238000000034 method Methods 0.000 abstract description 9
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Abstract
The utility model provides emission type unmanned plane and its system, is related to emission type unmanned air vehicle technique field.The emission type unmanned plane has different state of flights in launching phase, autonomous flight stage, the unmanned plane can reduce flying speed by the power and/or resistance structure of itself setting, so as to enter inverse launching phase state of flight from launching phase state of flight；After inverse launching phase, the unmanned plane enter the autonomous flight stage, reach or close to destination in the case of, be changed into can lean on self power fly state of flight.The difference physically and/or on power is presented in different phase in unmanned plane of the present utility model, that is, is easy to storage to transport and launch, and is easy to scout positioning again, the flight, scouting, fight capability of unmanned plane under complex environment are improved to a certain extent.
Description
Technical field
The utility model is related to emission type unmanned air vehicle technique field.
Background technology
Unmanned plane (UAV) is the abbreviation of " UAV ", relies primarily on wireless remotecontrol or by automatic Pilot
The modes such as instrument realize that autonomous control is flown.It is one of current advanced technological arms, is widely used in battle reconnaissance, electronics pair
Many military operations such as anti-, air attack, are described as the " prying eyes " and " trump card " of modern battlefield.The launching phase of unmanned plane
In one of most difficult, most critical stage often referred to as in unmanned plane tactics method, the launching phase of unmanned plane is directly affected
War skill index and the requirements such as maneuverability, Local Adaptation, reusability and the survival ability of UAS operation.
For emission type unmanned plane, conventional emission system is mainly using the transmitting such as hydraulic pressure, pneumatic, ejection, rocket assist
Mode, its emission process can be typically summarized as follows：Emission type unmanned plane is placed on launcher, by launcher to unmanned plane
Accelerated, unmanned plane is accelerated to after safe take-off speed, departed from launcher, target position, realize transmitting.Transmitting
Afterwards, often high-speed flight can carry out selective self-destruction after the completion of target location, reconnaissance mission and attack to reaching aircraft to target
Or parachuting landing is reclaimed or autonomous flight is maked a return voyage.During target position, the flying speed of unmanned plane is often quickly, no
Positioned beneficial to scouting.
The content of the invention
The purpose of this utility model is：The deficiencies in the prior art are overcome to adjust state of flight there is provided one kind with suitable
The emission type unmanned plane and its system of different mission phases are answered, the unmanned plane improves the flexibility of unmanned plane during flying.
To realize above-mentioned target, the utility model provides following technical scheme：
A kind of emission type unmanned plane, has different state of flights, the unmanned plane in launching phase, autonomous flight stage
Flying speed can be reduced by the power and/or resistance structure of itself setting, so as to enter from launching phase state of flight
Inverse launching phase state of flight；After inverse launching phase, the unmanned plane enters the autonomous flight stage, is reaching or close to mesh
Ground in the case of, be changed into can lean on self power fly state of flight.
Further, in launching phase, the state of flight for physically meeting mission need is presented in unmanned plane.
Further, unmanned plane uses morphing, in launching phase, and the morphing folds after-contraction in body.
Further, unmanned plane reduces flying speed by way of reverse launching objects.
Further, the object inversely launched is that can launch the explosive of after-explosion.
Further, be provided with reaction power unit on unmanned plane, the reaction power unit can by jet to
Unmanned plane provides reverse power, reduces flying speed.
Further, drag parachute unit is provided with unmanned plane, the drag parachute unit can be opened inversely, reduces flight speed
Degree.
Further, state of flight adjustment unit is provided with unmanned plane, for adjusting unmanned plane during flying state to adapt to not
Same mission phase.
Further, position detection unit is provided with unmanned plane, the position detection unit is used for the ground for gathering unmanned plane
Positional information and/or flying distance information are managed, and the information of acquisition is sent to state of flight adjustment unit；The state of flight
Adjustment unit according to the information of reception, determine whether to meet it is default the need for carry out state of flight adjustment geographical position and/or
Distance；In the case where judging to meet, triggering unmanned plane carries out body adjustment and power adjustment.
Further, timing unit is provided with unmanned plane, the timing unit is used for the temporal information for gathering unmanned plane, and
The information of acquisition is sent to state of flight adjustment unit；The state of flight adjustment unit is according to the information of reception, judgement
It is no meet it is default the need for carry out time of state of flight adjustment；In the case where judging to meet, triggering unmanned plane carries out body
Adjustment and power adjustment.
Further, wireless signal Transmit-Receive Unit is provided with unmanned plane, the wireless signal Transmit-Receive Unit can connect control
Signal, and the control signal of acquisition is sent to state of flight adjustment unit；The state of flight adjustment unit is according to reception
Control signal, triggering unmanned plane carries out body adjustment and power adjustment.
Further, state of flight monitoring unit is provided with unmanned plane, the state of flight monitoring unit is used to monitor nothing
Man-machine state of flight information, and the state of flight information of acquisition is sent to state of flight adjustment unit；The state of flight
Adjustment unit according to the information of reception, judge unmanned plane in the horizontal direction and/or vertical direction movement velocity, according to default
The velocity standard of progress state of flight adjustment is needed, triggering unmanned plane carries out body adjustment and power adjustment.
Further, state of flight adjustment unit in the following way in one or more adjustment state of flights：Mode one,
Adjust position, area and/or the angle of wing；Mode two, adjusts shape, size and/or the angle of fuselage；Mode three, is abandoned
Default transition structure in unmanned plane.
The utility model additionally provides a kind of system for launching unmanned plane, including：Foregoing emission type unmanned plane；Transmitting dress
Put there is provided transmitting unmanned plane power.
Further, the emitter includes transmitter unit, brake unit, control unit, described control unit control institute
State transmitter unit and brake unit.
Further, the power of transmitter unit uses blasting type launch power, electromagnetic type launch power, vapour-pressure type launch power
Or elastic emission power.
The utility model compared with prior art, as an example, has the following advantages that due to using above technical scheme
And good effect：Using the utility model, emission type unmanned plane can adjust state of flight to adapt to different mission phases,
Launching phase, the kinetic energy applied by emitter is moved, and the form for meeting mission need is presented in unmanned plane；Inverse transmitting rank
Section, unmanned plane is slowed down in the air by itself applying reverse power, in order to which unmanned plane enters follow-up autonomous flight rank
Section；In the autonomous flight stage, changed by the unmanned plane of foregoing inverse launching phase and obtained, reached or close to the situation of destination
Under, unmanned plane is changed into the state of flight that self power can be leaned on to fly.Due to flying in launching phase, inverse launching phase and independently
The difference physically and/or on power is presented in row order section, unmanned plane, in this way, being easy to storage to transport and launch, is easy to scout again
Positioning, improves the flight, scouting, fight capability of unmanned plane under complex environment to a certain extent.
Brief description of the drawings
State of flight schematic diagram of the emission type unmanned plane that Fig. 1 is provided for the utility model embodiment in launching phase.
State of flight schematic diagram of the emission type unmanned plane that Fig. 2 is provided for the utility model embodiment in inverse launching phase
One.
State of flight schematic diagram of the emission type unmanned plane that Fig. 3 is provided for the utility model embodiment in inverse launching phase
Two.
State of flight of the emission type unmanned plane that Fig. 4 is provided for the utility model embodiment in the autonomous flight stage is illustrated
Figure.
The function structure chart for the emission type unmanned plane that Fig. 5 provides for the utility model embodiment.
The flow chart of the implementation method for the emission type unmanned plane that Fig. 6 provides for the utility model embodiment.
Description of reference numerals：
Emission type unmanned plane 100；Head 110, spray-hole 111；Front wing 120, front wing expansion retaining mechanism 121；Rear wing
130, rear wing expansion retaining mechanism 131；Empennage 140, rear wing expansion retaining mechanism 141；Flying power unit 150；It is jet-propelled dynamic
Power unit 160；Drag parachute 170；State of flight adjustment unit 180；Position detection unit 190；
Explosive 200；
Gas 300.
Embodiment
The emission type unmanned plane and its system provided below in conjunction with the drawings and specific embodiments the utility model is made into one
Step is described in detail.It should be noted that the combination of technical characteristic or technical characteristic described in following embodiments should not be by
It is considered isolated, they can be mutually combined to reach superior technique effect.In the accompanying drawing of following embodiments, respectively
The identical label that accompanying drawing occurs represents identical feature or part, can be applied in not be the same as Example.Therefore, once it is a certain
It is defined, then it need not be further discussed in subsequent accompanying drawing in Xiang Yi accompanying drawing.
It should be noted that, depicted structure, ratio, size etc. in this specification institute accompanying drawing, only to coordinate explanation
Content disclosed in book, so that those skilled in the art is understood with reading, is not limited to the enforceable limit of utility model
Fixed condition, the modification of any structure, the change of proportionate relationship or the adjustment of size, in the work(for not influenceing utility model can be generated
Under effect and the purpose that can reach, it all should fall in the range of the technology contents disclosed in utility model can be covered.This practicality
The scope of new preferred embodiment includes other realization, wherein described or discussion order can not be pressed, including root
According to involved function by it is basic simultaneously in the way of or in the opposite order, carry out perform function, this should be by reality of the present utility model
A person of ordinary skill in the field is applied to be understood.
It may be not discussed in detail for technology, method and apparatus known to person of ordinary skill in the relevant, but suitable
In the case of, the technology, method and apparatus should be considered as authorizing a part for specification.Institute that is shown here and discussing
Have in example, any occurrence should be construed as merely exemplary, not as limitation.Therefore, exemplary embodiment
Other examples can have different values.
Embodiment
A kind of emission type unmanned plane, can adjust state of flight to adapt to different mission phases, the unmanned plane at least has
There are launching phase state of flight, inverse launching phase state of flight and autonomous flight stage state of flight, in different mission phases,
The difference physically and/or on power is presented in unmanned plane.
Launching phase state of flight is presented in launching phase in unmanned plane.Launching phase, the power of unmanned plane during flying comes from
The kinetic energy that emitter applies.In launching phase, unmanned plane physically meets mission need.
After launching phase, unmanned plane is by the power and/or resistance structure set by itself, to reduce flying speed,
Enter inverse launching phase.Inverse launching phase, the power that unmanned plane is applied by itself is the resistance as flight, winged for reducing
Scanning frequency degree, with launching phase emitter apply flying power effect it is opposite (launching phase, emitter apply power use
In raising flying speed).In inverse launching phase, inverse launching phase state of flight is presented in unmanned plane.
Inverse launching phase is described after inverse launching phase as launching phase and the transition stage in autonomous flight stage
Unmanned plane can enter the autonomous flight stage.The autonomous flight stage is changed by foregoing inverse launching phase to be obtained, and is being reached
Or close in the case of destination, unmanned plane is changed into the state of flight that self power can be leaned on to fly, into autonomous flight rank
Section.
In this example, in launching phase, the state of flight for physically meeting mission need is presented in unmanned plane.It is preferred that, than
Body such as unmanned plane is integrally presented streamlined so as to fit aerial high-speed flight in the stage, simultaneously as the stage flies
Action edge is come from and emitter, and the body of unmanned plane should be matched with emitter, in order to which emitter accelerates to it.As
For example and not limitation, such as body is tried one's best contraction, and wing is tried one's best folding.In this example, by taking morphing unmanned plane as an example, nothing
The morphing that man-machine use wing can deploy or withdraw with respect to body, in launching phase, the morphing is received after folding
Shrink in body.
Unrestricted as an example, shown in Figure 1, the emission type unmanned plane 100 in this example, body includes head
110th, be provided with fuselage, fuselage can deploy or fold with respect to fuselage for a pair front wing 120, a pair can relative fuselage expansion
Or fold rear wing 130, a pair can relative fuselage deploy or folding empennage 140, and be arranged on the spiral of afterbody
Oar (not shown), the propeller as unmanned plane flying power unit, using the teaching of the invention it is possible to provide unmanned plane autonomous flight it is dynamic
Power.Described head 110 is mechanically connected with fuselage by flange, and described front wing 120, rear wing 130 and empennage 140 passes through machine
Span open locking mechanism is connected with fuselage.Wing expansion retaining mechanism includes front wing expansion retaining mechanism 121, rear wing expansion locking
Mechanism 131, rear wing expansion retaining mechanism 141.Described unmanned plane wing can be using tandem layout, front wing, rear wing, arrangement
Below fuselage, retaining mechanism, rear wing expansion retaining mechanism are deployed by front wing respectively and are connected with fuselage.Forward and backward wing left and right
It is laminated or is arranged in juxtaposition；Empennage is placed in afterbody and is symmetrically arranged, and deploy retaining mechanism by empennage is connected with fuselage.Spiral shell
Revolve oar and be arranged on unmanned aerial vehicle body afterbody, thrust is provided for unmanned plane autonomous flight.
Emitter, the power for providing transmitting unmanned plane.It is preferred that, in this example, emitter can include hair
Unit, brake unit, control unit are penetrated, described control unit controls the transmitter unit and brake unit.
Unrestricted as an example, transmitter unit can include launching tube and launch power unit.The power of launching tube can
With using blasting type launch power, electromagnetic type launch power, vapour-pressure type launch power or elastic emission power, in the present embodiment
In, using blasting type launch power.Following structure can specifically be used.The two ends of the cylinder of launching tube are respectively arranged with upper end cover
And bearing base, the glass-reinforced plastic material of the use high intensity of cylinder preferably, cylinder back-end is by being threadably mounted on bearing base.
Rear end isolation in slide rail, cylinder is provided with cylinder inboard wall and is provided with low-pressure chamber, holes and hyperbaric chamber, is opened from cylinder back-end portion
Begin, forward end sets gradually and is provided with transmitting push pedal above hyperbaric chamber, holes, low-pressure chamber, the front end of low-pressure chamber；Low-pressure chamber and height
Pressure chamber is by holes UNICOM, and hyperbaric chamber bottom is placed with the fire in a stove before fuel is added and transmitting explosion medicine, and the fire in a stove before fuel is added is connected with electric signal transmitting terminal.
After igniting, gas pressure is delivered on the unmanned plane in cylinder by launching push pedal, unmanned plane is along cylinder inwall
Slide rail is launched after cylinder, and the body for physically meeting mission need is still presented, and keeps form during transmitting to be flown.
It is preferred that, can also set to have to prevent unmanned plane from rotating in launching tube, in the cylinder of launching tube prevents nothing
Spin-ended piece rotated when unmanned plane is launched in people's machine barrel.
Brake unit can be braked to emitter when needed, it is possible to increase the security of emitter.
Unmanned plane holding launching phase state of flight was flown after a period of time, and inverse launching phase is adjusted into as needed.
It is preferred that, state of flight adjustment unit is provided with this example, on unmanned plane, for adjusting unmanned plane during flying state to adapt to
Different mission phases.
State of flight adjustment is triggered, can be in the following way in the way of realizing mission phase transformation.
Mode based on positional information.Such as, position detection unit, the position detection unit are provided with unmanned plane
Geographical location information and/or flying distance information for gathering unmanned plane, and the information of acquisition is sent to state of flight tune
Whole unit；The state of flight adjustment unit according to the information of reception, determine whether to meet it is default the need for carry out state of flight
The geographical position of adjustment and/or distance；In the case where judging to meet, triggering unmanned plane carries out body adjustment and power adjustment.
Or, the mode based on temporal information.Such as, timing unit is provided with unmanned plane, the timing unit is used for
The temporal information of unmanned plane is gathered, and the information of acquisition is sent to state of flight adjustment unit；The state of flight adjustment is single
Member according to the information of reception, determine whether to meet it is default the need for carry out time of state of flight adjustment；The feelings met in judgement
Under condition, triggering unmanned plane carries out body adjustment and power adjustment.
Or, the mode of the active control based on control signal.Such as, wireless signal transmitting-receiving is provided with unmanned plane single
Member, the wireless signal Transmit-Receive Unit can connect control signal, and the control signal of acquisition is sent into state of flight adjustment list
Member；The state of flight adjustment unit is according to the control signal of reception, and triggering unmanned plane carries out body adjustment and power is adjusted.Institute
Control signal is stated, emitter can be carried out, be can be from the remote terminal of other associations.
Or, based on intelligent decision of the unmanned plane to itself state of flight.Such as, state of flight prison is provided with unmanned plane
Unit is surveyed, the state of flight monitoring unit is used for the state of flight information for monitoring unmanned plane, and the state of flight of acquisition is believed
Breath is sent to state of flight adjustment unit；The state of flight adjustment unit judges unmanned plane in level according to the information of reception
Direction and/or the movement velocity of vertical direction, according to the velocity standard that state of flight adjustment is carried out the need for default, trigger nobody
Machine carries out body adjustment and power adjustment.It is unrestricted as an example, the speed cone of state of flight adjustment is carried out the need for presetting
Standard, can be when collecting unmanned plane in the vertical direction to do descending motion.At this point it is possible to by judging unmanned plane in vertical side
Upward movement velocity be on the occasion of or negative value, judge unmanned plane whether be in landing state, when judge unmanned plane landing feelings
Under condition, body adjustment and power adjustment are carried out.
Using aforesaid way, unmanned plane can enter inverse launching phase from launching phase, enter autonomous from inverse launching phase
Mission phase.
The adjustment of state of flight includes body adjustment and power adjustment.Described body adjustment, that is, change the shape of unmanned plane
Shape, it is unrestricted as an example, such as deploy by the wing section of folding or fully.Described power adjustment, that is, change and fly
Capable power, unrestricted as an example, such as the clamping impelling object to outside fuselage, the reaction force of clamping impelling object is applied to fuselage.
Specifically, state of flight adjustment unit in the following way in one or more adjustment state of flights：Mode one,
Adjust position, area and/or the angle of wing；Mode two, adjusts shape, size and/or the angle of fuselage；Mode three, is abandoned
Default transition structure in unmanned plane.The transition structure, includes but is not limited to be previously used in inverse launching phase to outside fuselage
The object of projectile.
Unmanned plane enters the mode of inverse launching phase from launching phase, can be side of the unmanned plane by reverse launching objects
Formula reduces flying speed.It is preferred that, the object inversely launched is that can launch the explosive of after-explosion.Referring to Fig. 2
It is shown, illustrate state of flight of the emission type unmanned plane in inverse launching phase, the spray-hole that unmanned plane passes through the front end of head 110
111 to motion front launching objects, object fly out spray-hole 111 when, can to head apply an opposition, the effect
Power can be opposite with the heading of unmanned plane, i.e., there is provided one reverse power of unmanned plane, nobody is reduced with this
The flying speed of machine.When the object inversely launched is can launch the explosive 200 of after-explosion, due to pushing away that blast is produced
Power also further can provide a reverse power to unmanned plane.
Aforesaid way is unrestricted as an example to can also be other structures there is provided the mode of reverse power.Referring to Fig. 3 institutes
Show, such as reaction power unit (not shown) is provided with unmanned plane, and the reaction power unit can pass through
Jet provides reverse power to unmanned plane, reduces flying speed.It is preferred that, the fumarole of reaction power unit is arranged on head
110 front end.
Or, drag parachute unit 170, the drag parachute energy of the drag parachute unit 170 can also be provided with unmanned plane
It is enough to eject and open from the afterbody rear end of fuselage.The direction opened due to drag parachute and the heading of unmanned plane are on the contrary, therefore
It can be described as reverse opening.After drag parachute expansion, it can provide reverse power to unmanned plane, so as to reduce the flight speed of unmanned plane
Degree.
Inverse launching phase is as launching phase and the transition stage in autonomous flight stage, after inverse launching phase, nobody
The flying speed of machine reduces, and the unmanned plane can enter the autonomous flight stage.The autonomous flight stage passes through foregoing inverse transmitting rank
Section transformation obtain, reach or close to destination in the case of, unmanned plane be changed into can lean on self power fly flight shape
State, into the autonomous flight stage.State of flight adjustment is triggered, in the way of realizing mission phase transformation, foregoing base can be used
Mode in positional information, the mode based on temporal information, the mode of active control based on control signal or based on unmanned plane
The modes such as the intelligent decision to itself state of flight, will not be repeated here.
It is shown in Figure 4, under being state of flight of the emission type unmanned plane 100 in the autonomous flight stage, the state of flight, nothing
It is man-machine to be deployed by folded state above.Unrestricted as an example, described unmanned plane wing is laid out using tandem, front wing
120th, rear wing 130 is arranged in below fuselage, is deployed retaining mechanism, rear wing by front wing respectively and is deployed retaining mechanism and fuselage company
Connect.Forward and backward wing left and right stacking is arranged in juxtaposition；Empennage 140 is placed in afterbody and is symmetrically arranged, and deploys to lock by empennage
Tight mechanism is connected with fuselage.The structure of three class wings expansion locking device is identical, and size is different.During expansion, front wing 120,
Rear wing 130 by correspondence wing deploy retaining mechanism in flexible member drive, to fuselage both sides using deploy retaining mechanism axis as
Symmetrically deploy in axle center.When wing expansion in place when, front wing 120, rear wing 130 left and right wing wing root respectively with front wing limiting block
Block, the contact of rear wing positive stop, so as to limit its expanded angle, collaboration wing expansion retaining mechanism locks wing.Empennage 140
It is that axle center is deployed clockwise respectively in accordance with empennage expansion retaining mechanism axis, can be limited when deploying in place by empennage block
Position, while wing retaining mechanism locks empennage.Propeller (not shown) is arranged on unmanned aerial vehicle body afterbody, is unmanned plane
Autonomous flight provides power.Unmanned plane can carry out autonomous flight in the autonomous flight stage by the power set of itself.
Referring to Fig. 5, a kind of function structure chart for emission type unmanned plane that another embodiment of the present utility model is provided.The hair
Emitting unmanned plane 100 includes body, and morphing, flying power unit 150, reaction power unit 160, drag parachute 170 flies
Row state adjustment unit 180, position detection unit 190.Body include head 110 and fuselage, morphing include front wing 120,
Rear wing 130 and empennage 140.Specifically, be provided with fuselage a pair can with respect to fuselage deploy or fold front wing 120, a pair
The rear wing 130 that can deploy or fold with respect to fuselage, a pair can the relative fuselage empennage 140 that deploys or fold, and set
In the propeller of afterbody, the propeller as unmanned plane flying power unit, using the teaching of the invention it is possible to provide unmanned plane autonomous flight
Power.Described head 110 is mechanically connected with fuselage by flange, and described front wing 120, rear wing 130 and empennage 140 leads to
Wing expansion retaining mechanism is crossed to be connected with fuselage.In different mission phases, the difference physically and/or on power is presented in unmanned plane
It is different.
In the embodiment, the adjustment of triggering state of flight is to be based on positional information in the way of realizing mission phase transformation.
Be provided with position detection unit on unmanned plane, the position detection unit be used for the geographical location information for gathering unmanned plane and/or
Flying distance information, and the information of acquisition is sent to state of flight adjustment unit；The state of flight adjustment unit is according to connecing
The information of receipts, determine whether to meet it is default the need for carry out geographical position and/or the distance of state of flight adjustment；Judging to meet
In the case of, triggering unmanned plane carries out body adjustment and power adjustment.
In the embodiment, mode of the unmanned plane from launching phase into inverse launching phase is unmanned plane by inversely launching
The mode of object reduces flying speed.Reaction power unit 150, the reaction power unit are provided with unmanned plane
150 can reduce flying speed by jet to the reverse power of unmanned plane offer.It is preferred that, the jet of reaction power unit
Hole is arranged on the front end of head.Meanwhile, drag parachute unit 170, the drag parachute list are additionally provided with the embodiment, on unmanned plane
The drag parachute of member 170 can be ejected and opened from the afterbody rear end of fuselage.Due to the direction of drag parachute opening and flying for unmanned plane
Therefore line direction on the contrary, can be described as reverse opening.After drag parachute expansion, it can provide reverse power to unmanned plane, so as to enter
One step reduces the flying speed of unmanned plane.
Another embodiment of the present utility model there is provided a kind of system for launching unmanned plane, including foregoing emission type without
It is man-machine, and emitter, the emitter, the power for providing transmitting unmanned plane.
The emitter can include transmitter unit, brake unit, control unit, and described control unit controls the hair
Penetrate unit and brake unit.Emitter, the power for providing transmitting unmanned plane.It is preferred that, in this example, emitter can
So that including transmitter unit, brake unit, control unit, described control unit controls the transmitter unit and brake unit.
Unrestricted as an example, transmitter unit can include launching tube and launch power unit.The power of launching tube can
With using blasting type launch power, electromagnetic type launch power, vapour-pressure type launch power or elastic emission power, in the present embodiment
In, using blasting type launch power.It is preferred that, transmitter unit can use following structure.The two ends difference of the cylinder of launching tube
Upper end cover and bearing base are provided with, the glass-reinforced plastic material of the use high intensity of cylinder preferably, cylinder back-end is installed by screw thread
On bearing base.Rear end isolation in slide rail, cylinder is provided with cylinder inboard wall and is provided with low-pressure chamber, holes and hyperbaric chamber, from
Cylinder back-end portion starts, and forward end sets gradually hyperbaric chamber, holes, low-pressure chamber, and the front end top of low-pressure chamber is provided with transmitting and pushed away
Plate；Low-pressure chamber and hyperbaric chamber are by holes UNICOM, and hyperbaric chamber bottom is placed with the fire in a stove before fuel is added and transmitting explosion medicine, and the fire in a stove before fuel is added is sent out with electric signal
End is penetrated to be connected.
Referring to Fig. 6, another embodiment of the present utility model there is provided a kind of implementation method of emission type unmanned plane, including
Following steps.
S100, unmanned plane is launched by emitter, and unmanned plane enters launching phase state of flight.
S200, unmanned plane reduces flying speed by the power and/or resistance structure itself set, from launching phase flight
State enters inverse launching phase state of flight.
S300, after inverse launching phase, the unmanned plane enters the autonomous flight stage, is reaching or close to destination
In the case of, it is changed into the state of flight that self power can be leaned on to fly.
It is preferred that, between step S100 and step S200, in addition to triggering unmanned plane turns from launching phase state of flight
The step of changing to inverse launching phase state of flight.
And, between step S200 and step S300, in addition to triggering unmanned plane turns from inverse launching phase state of flight
The step of changing to autonomous flight stage state of flight.
Specifically, by way of triggering the state of flight of unmanned plane and adjusting transformation, positional information can be based on using foregoing
Mode, the mode based on temporal information, the mode of active control based on control signal or itself is flown based on unmanned plane
The modes such as the intelligent decision of state.
Specifically, the geographical location information and/or flying distance information of such as collection unmanned plane, according to the information of acquisition,
Determine whether to meet it is default the need for carry out geographical position and/or the distance of state of flight adjustment；In the case where judging to meet,
Trigger unmanned plane and carry out body adjustment and power adjustment.
Or, gather the temporal information of unmanned plane, according to the information of acquisition, determine whether to meet it is default the need for flown
The time of row state adjustment；In the case where judging to meet, triggering unmanned plane carries out body adjustment and power adjustment.
Or, control signal is received by wireless signal Transmit-Receive Unit, according to the control signal of reception, triggering unmanned plane enters
Row body is adjusted and power adjustment.The control signal, can carry out emitter, can be from the long-range end of other associations
End.
Or, monitor unmanned plane state of flight information, judge unmanned plane in the horizontal direction and/or vertical direction motion
Speed, according to the velocity standard that state of flight adjustment is carried out the need for default, triggering unmanned plane carries out body adjustment and power is adjusted
It is whole.
Foregoing description is only the description to the utility model preferred embodiment, not to any limit of the utility model scope
Fixed, the scope of preferred embodiment of the present utility model includes other realization, wherein can not by it is described go out or discuss it is suitable
Sequence carrys out perform function.Any change, modification that the those of ordinary skill in the utility model field does according to the disclosure above content,
Belong to the protection domain of claims.
Claims (10)
1. a kind of emission type unmanned plane, has different state of flights in launching phase, autonomous flight stage, it is characterised in that：
The unmanned plane can reduce flying speed by the power and/or resistance structure of itself setting, so as to fly from launching phase
Row state enters inverse launching phase state of flight；After inverse launching phase, the unmanned plane enter the autonomous flight stage, up to
Arrive or close in the case of destination, being changed into state of flight that self power can be leaned on to fly.
2. emission type unmanned plane according to claim 1, it is characterised in that：In launching phase, unmanned plane is presented physically
Meet the state of flight of mission need.
3. emission type unmanned plane according to claim 1, it is characterised in that：Unmanned plane is by way of reverse launching objects
To reduce flying speed, the object inversely launched is that can launch the explosive of after-explosion.
4. emission type unmanned plane according to claim 1, it is characterised in that：Reaction power list is provided with unmanned plane
Member, the reaction power unit can reduce flying speed by jet to the reverse power of unmanned plane offer.
5. emission type unmanned plane according to claim 1, it is characterised in that：State of flight adjustment is provided with unmanned plane single
Member, for adjusting unmanned plane during flying state to adapt to different mission phases.
6. emission type unmanned plane according to claim 5, it is characterised in that：Position detection unit is provided with unmanned plane,
The position detection unit is used to gathering the geographical location information and/or flying distance information of unmanned plane, and by the information of acquisition
It is sent to state of flight adjustment unit；The state of flight adjustment unit determines whether to meet default according to the information of reception
Need geographical position and/or the distance of progress state of flight adjustment；In the case where judging to meet, triggering unmanned plane carries out body
Adjustment and power adjustment.
7. emission type unmanned plane according to claim 5, it is characterised in that：Timing unit is provided with unmanned plane, it is described
Timing unit is used for the temporal information for gathering unmanned plane, and the information of acquisition is sent into state of flight adjustment unit；It is described to fly
Row state adjustment unit according to the information of reception, determine whether to meet it is default the need for carry out time of state of flight adjustment；
In the case that judgement meets, triggering unmanned plane carries out body adjustment and power adjustment.
8. emission type unmanned plane according to claim 5, it is characterised in that：Wireless signal transmitting-receiving is provided with unmanned plane single
Member, the wireless signal Transmit-Receive Unit can connect control signal, and the control signal of acquisition is sent into state of flight adjustment list
Member；The state of flight adjustment unit is according to the control signal of reception, and triggering unmanned plane carries out body adjustment and power is adjusted.
9. emission type unmanned plane according to claim 5, it is characterised in that：State of flight monitoring is provided with unmanned plane single
Member, the state of flight monitoring unit is used for the state of flight information for monitoring unmanned plane, and the state of flight information of acquisition is sent out
Give state of flight adjustment unit；The state of flight adjustment unit judges unmanned plane in the horizontal direction according to the information of reception
And/or the movement velocity of vertical direction, according to the velocity standard that state of flight adjustment is carried out the need for default, triggering unmanned plane enters
Row body is adjusted and power adjustment.
10. a kind of system for launching unmanned plane, it is characterised in that including：
Emission type unmanned plane any one of claim 1-9；
There is provided the power of transmitting unmanned plane for emitter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720013493.1U CN206520738U (en) | 2017-01-03 | 2017-01-03 | Emission type unmanned plane and its system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720013493.1U CN206520738U (en) | 2017-01-03 | 2017-01-03 | Emission type unmanned plane and its system |
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| Publication Number | Publication Date |
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| CN206520738U true CN206520738U (en) | 2017-09-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720013493.1U Expired - Fee Related CN206520738U (en) | 2017-01-03 | 2017-01-03 | Emission type unmanned plane and its system |
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| CN (1) | CN206520738U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741847A (en) * | 2017-01-03 | 2017-05-31 | 上海量明科技发展有限公司 | Emission type unmanned plane and its system, implementation method |
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2017
- 2017-01-03 CN CN201720013493.1U patent/CN206520738U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741847A (en) * | 2017-01-03 | 2017-05-31 | 上海量明科技发展有限公司 | Emission type unmanned plane and its system, implementation method |
| CN106741847B (en) * | 2017-01-03 | 2023-10-13 | 上海量明科技发展有限公司 | Transmitting type unmanned aerial vehicle, system and implementation method thereof |
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Granted publication date: 20170926 |