CN106741847A - Emission type unmanned plane and its system, implementation method - Google Patents
Emission type unmanned plane and its system, implementation method Download PDFInfo
- Publication number
- CN106741847A CN106741847A CN201710001206.XA CN201710001206A CN106741847A CN 106741847 A CN106741847 A CN 106741847A CN 201710001206 A CN201710001206 A CN 201710001206A CN 106741847 A CN106741847 A CN 106741847A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- flight
- state
- adjustment
- unit
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 19
- 230000010006 flight Effects 0.000 claims abstract description 3
- 230000002441 reversible effect Effects 0.000 claims description 20
- 238000001514 detection method Methods 0.000 claims description 10
- 230000002123 temporal effect Effects 0.000 claims description 9
- 230000033001 locomotion Effects 0.000 claims description 8
- 238000004880 explosion Methods 0.000 claims description 6
- 239000002360 explosive Substances 0.000 claims description 5
- 238000012544 monitoring process Methods 0.000 claims description 5
- 230000001960 triggered effect Effects 0.000 claims 1
- 230000007246 mechanism Effects 0.000 description 20
- 238000005422 blasting Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 230000007704 transition Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 239000003814 drug Substances 0.000 description 2
- 239000011152 fibreglass Substances 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/14—Attitude, flight direction, or altitude control by jet reaction the jets being other than main propulsion jets
-
- 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
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Toys (AREA)
Abstract
The invention provides emission type unmanned plane and its system, implementation method, it is related to emission type unmanned air vehicle technique field.The emission type unmanned plane, there are different state of flights in launching phase, autonomous flight stage, the unmanned plane can reduce flying speed by the power of itself setting and/or resistance structure, so as to enter inverse launching phase state of flight from launching phase state of flight；By after inverse launching phase, the unmanned plane enters the autonomous flight stage, is reaching or close in the case of destination, is being changed into the state of flight that self power can be leaned on to fly.Unmanned plane of the invention is presented the difference physically and/or on power in different phase, that is, be easy to storage to transport and launch, and is easy to scout positioning again, and flight, scouting, the fight capability of unmanned plane under complex environment are improve to a certain extent.
Description
Technical field
The present invention relates 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 requirement such as maneuverability, Local Adaptation, reusability and 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 typically be summarized as follows：Emission type unmanned plane is placed on launcher, by launcher to unmanned plane
Accelerated, after unmanned plane accelerates to safe take-off speed, departed from launcher, target position, realized transmitting.Transmitting
Afterwards, often high-speed flight, to target location is reached, can carry out selective self-destruction attack to aircraft to target after the completion of reconnaissance mission
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
It is an object of the invention to：Overcome the deficiencies in the prior art, there is provided one kind can adjust state of flight to adapt to not
The emission type unmanned plane of same mission phase, and corresponding system and implementation method, the unmanned plane at least have launching phase
State of flight, inverse launching phase state of flight and autonomous flight stage state of flight, in different mission phases, unmanned plane is presented
Difference physically and/or on power.In this way, being easy to storage to transport, it is easy to scout positioning again, improves to a certain extent
Flight, scouting, the fight capability of unmanned plane under complex environment.
To realize above-mentioned target, the invention 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 of itself setting and/or resistance structure, so as to enter from launching phase state of flight
Inverse launching phase state of flight；By 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, unmanned plane is presented the state of flight for physically meeting mission need.
Further, unmanned plane uses morphing, and in launching phase, the morphing folds after-contraction in body.
Further, unmanned plane reduces flying speed by way of reverse launching objects.
Further, the object of the reverse transmitting 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 to gather the ground of unmanned plane
Reason positional information and/or flying distance information, and the information of acquisition is sent to state of flight adjustment unit；The state of flight
Adjustment unit according to the information for receiving, 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 to gather the temporal information of unmanned plane, and
The information of acquisition is sent to state of flight adjustment unit；According to the information for receiving, judgement is the state of flight adjustment unit
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 judges unmanned plane in the horizontal direction and/or the movement velocity of vertical direction, according to default according to the information for receiving
Need to carry out the velocity standard of state of flight adjustment, 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 flight：Mode one,
Adjust position, area and/or the angle of wing；Mode two, adjusts shape, size and/or the angle of fuselage；Mode three, abandons
Default transition structure in unmanned plane.
Present invention also offers a kind of system for launching unmanned plane, including：Foregoing emission type unmanned plane；Emitter,
The power of transmitting unmanned plane is provided.
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.
Present invention also offers a kind of implementation method of emission type unmanned plane, comprise the following steps：Sent out by emitter
Unmanned plane is penetrated, unmanned plane enters launching phase state of flight；Unmanned plane is reduced by the power and/or resistance structure for itself setting
Flying speed, inverse launching phase state of flight is entered from launching phase state of flight；By after inverse launching phase, the unmanned plane
Into the autonomous flight stage, reaching or close in the case of destination, be changed into the flight shape that self power can be leaned on to fly
State.
Further, the geographical location information and/or flying distance information of collection unmanned plane, according to the information for obtaining, judge
Whether the geographical position and/or the distance that preset the need for carry out state of flight adjustment is met；In the case where judging to meet, triggering
Unmanned plane carries out body adjustment and power adjustment.
Further, gather the temporal information of unmanned plane, according to the information for obtaining, determine whether to meet it is default the need for carry out
The time of state of flight adjustment；In the case where judging to meet, triggering unmanned plane carries out body adjustment and power adjustment.
Further, control signal is received by wireless signal Transmit-Receive Unit, according to the control signal for receiving, triggers unmanned plane
Carry out body adjustment and power adjustment.
Further, the state of flight information of unmanned plane is monitored, unmanned plane is judged in the horizontal direction and/or the fortune of vertical direction
Dynamic speed, according to the velocity standard that state of flight adjustment is carried out the need for presetting, triggering unmanned plane carries out body adjustment and power
Adjustment.
The present invention compared with prior art, as an example, has the following advantages that and accumulates due to using above technical scheme
Pole effect：Using the present invention, emission type unmanned plane can adjust state of flight to adapt to different mission phases, in transmitting rank
Section, the kinetic energy applied by emitter is moved, and unmanned plane is presented the form for meeting mission need；Inverse launching phase, nothing
It is man-machine to be slowed down in the air by itself applying reverse power, enter the follow-up autonomous flight stage in order to unmanned plane；From
Main mission phase, is changed by the unmanned plane of foregoing inverse launching phase and obtained, reaching or close in the case of destination, nobody
Machine is changed into the state of flight that self power can be leaned on to fly.Due in launching phase, inverse launching phase and autonomous flight stage,
Unmanned plane is presented the difference physically and/or on power, in this way, being easy to storage to transport and launch, is easy to scout positioning again,
Flight, scouting, the fight capability of unmanned plane under complex environment are improve to a certain extent.
Brief description of the drawings
Fig. 1 is state of flight schematic diagram of the emission type unmanned plane provided in an embodiment of the present invention in launching phase.
Fig. 2 is state of flight schematic diagram one of the emission type unmanned plane provided in an embodiment of the present invention in inverse launching phase.
Fig. 3 is state of flight schematic diagram two of the emission type unmanned plane provided in an embodiment of the present invention in inverse launching phase.
Fig. 4 is state of flight schematic diagram of the emission type unmanned plane provided in an embodiment of the present invention in the autonomous flight stage.
Fig. 5 is the function structure chart of emission type unmanned plane provided in an embodiment of the present invention.
Fig. 6 is the flow chart of the implementation method of emission type unmanned plane provided in an embodiment of the present invention.
Description of reference numerals：
Emission type unmanned plane 100；Head 110, spray-hole 111；Front wing 120, front wing launches retaining mechanism 121；Rear wing
130, rear wing launches retaining mechanism 131；Empennage 140, rear wing launches 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.
Specific embodiment
Emission type unmanned plane and its system, the implementation method work provided the present invention below in conjunction with the drawings and specific embodiments
Further describe.It should be noted that the combination of the technical characteristic or technical characteristic described in following embodiments should not
When being considered as isolated, they can be mutually combined so as to reach superior technique effect.In the accompanying drawing of following embodiments
In, the identical label that each accompanying drawing occurs represents identical feature or part, in can be applied to different embodiments.Therefore, one
It is defined in a certain Xiang Yi accompanying drawing of denier, then it need not be further discussed in subsequent accompanying drawing.
It should be noted that, depicted structure, ratio, size etc. in this specification institute accompanying drawing are only used to coordinate explanation
Content disclosed in book, so that those skilled in the art understands and reads, is not limited to invent enforceable restriction bar
Part, the modification of any structure, the change of proportionate relationship or the adjustment of size are not influenceing to invent effect and the institute's energy that can be generated
Under the purpose reached, all should fall in the range of the technology contents disclosed in invention to be covered.The side of being preferable to carry out of the invention
The scope of formula includes other realization, wherein the order of described or discussion can not be pressed, including function involved by basis is pressed
Basic mode simultaneously or in the opposite order, carrys out perform function, and this should be by the skill of embodiments of the invention art
Art personnel understood.
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, and 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,
Unmanned plane is presented the difference physically and/or on power.
Unmanned plane is presented launching phase state of flight in launching phase.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 reduces flying speed by the power and/or resistance structure set by itself,
Enter inverse launching phase.Inverse launching phase, unmanned plane is winged for reducing by the resistance that the power that itself applies is as flight
Scanning frequency degree, opposite with the effect of the flying power that launching phase emitter applies (launching phase, the power that emitter applies is used
In raising flying speed).In inverse launching phase, unmanned plane is presented inverse launching phase state of flight.
Inverse launching phase is described by 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 changes acquisition by foregoing inverse launching phase, is reaching
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, unmanned plane is presented the state of flight for physically meeting mission need.Preferably, 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 comes from and emitter, and the body of unmanned plane should match with emitter, it is accelerated in order to emitter.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 launch or withdraw with respect to body, in launching phase, the morphing is received after folding
In shrinking in body.
Unrestricted as an example, shown in Figure 1, the emission type unmanned plane 100 in this example, body includes head
110th, fuselage, a pair are provided with fuselage fuselage can launch relatively with respect to the front wing 120 of fuselage expansion or folding, a pair
Or fold rear wing 130, a pair can relative fuselage launch or folding empennage 140, and the spiral for being arranged on 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 pass through machine
Span open locking mechanism is connected with fuselage.Wing launches retaining mechanism includes that front wing launches retaining mechanism 121, rear wing and launches locking
Mechanism 131, rear wing launches retaining mechanism 141.Described unmanned plane wing can be laid out using tandem, front wing, rear wing, arrangement
In fuselage lower section, retaining mechanism, rear wing expansion retaining mechanism are launched by front wing respectively and is 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 launch retaining mechanism by empennage is connected with fuselage.Spiral shell
Rotation oar is arranged on unmanned aerial vehicle body afterbody, for unmanned plane autonomous flight provides thrust.
Emitter, the power for providing transmitting unmanned plane.Preferably, 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, preferably using the glass-reinforced plastic material of high intensity, cylinder back-end is by being threadably mounted on bearing base for cylinder.
Slide rail is provided with cylinder inboard wall, rear end isolation is provided with low-pressure chamber, holes and hyperbaric chamber in cylinder, is opened from cylinder back-end portion
Begin, forward end sets gradually hyperbaric chamber, holes, low-pressure chamber, the front end top of low-pressure chamber is provided with transmitting push pedal；Low-pressure chamber and height
By holes UNICOM, hyperbaric chamber bottom is placed with the fire in a stove before fuel is added and transmitting explosion medicine to pressure chamber, 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
After slide rail launches cylinder, the body for physically meeting mission need is still presented, keeps form during transmitting to be flown.
Preferably, can also set to have to prevent unmanned plane from being rotated in launching tube, in the cylinder of launching tube and prevent 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.
After unmanned plane is kept for launching phase state of flight flight a period of time, inverse launching phase is adjusted into as needed.
Preferably, in this example, state of flight adjustment unit is provided with unmanned plane, for adjusting unmanned plane during flying state to adapt to
Different mission phases.
Triggering state of flight adjustment, in the way of realizing that mission phase changes, can be in the following way.
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 for receiving, 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
Unit according to the information for receiving, determine whether to meet it is default the need for carry out time of state of flight adjustment；In the feelings that judgement meets
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
Unit, the wireless signal Transmit-Receive Unit can connect control signal, and it is single that the control signal of acquisition is sent into state of flight adjustment
Unit；According to the control signal for receiving, triggering unmanned plane carries out body adjustment and power adjustment to the state of flight adjustment unit.Institute
Control signal is stated, emitter can be carried out, it is also possible to come from the remote terminal of other associations.
Or, based on unmanned plane to the intelligent decision of 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 to monitor the state of flight information of unmanned plane, and the state of flight letter that will be obtained
Breath is sent to state of flight adjustment unit；The state of flight adjustment unit judges unmanned plane in level according to the information for receiving
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 presetting, 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 pass through to judge unmanned plane in side vertically
Upward movement velocity be on the occasion of or negative value, whether unmanned plane is judged in landing state, when the feelings for judging unmanned plane landing
Under condition, body adjustment and power adjustment are carried out.
Using aforesaid way, unmanned plane can enter inverse launching phase, enter autonomous from inverse launching phase from 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 launch by the wing section of folding or fully.Described power adjustment, that is, change and fly
Capable power, unrestricted as an example, such as, to clamping impelling object 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 flight：Mode one,
Adjust position, area and/or the angle of wing；Mode two, adjusts shape, size and/or the angle of fuselage；Mode three, abandons
Default transition structure in unmanned plane.The transition structure, includes but is not limited to be previously used for outside inverse launching phase is to 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.Preferably, the object of the reverse transmitting 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 of reverse transmitting be can be when the explosive 200 of after-explosion be launched, 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, there is provided the mode of reverse power can also be other structures.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.Preferably, 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 conversely, therefore
Can be described as reverse opening.After drag parachute launches, it can provide reverse power to unmanned plane, so as to reduce the flight speed of unmanned plane
Degree.
Inverse launching phase as launching phase and the transition stage in autonomous flight stage, by 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 is by foregoing inverse transmitting rank
Section transformation is obtained, and is being reached or close in the case of destination, unmanned plane is changed into the flight shape that self power can be leaned on to fly
State, into the autonomous flight stage.Triggering state of flight adjustment, in the way of realizing that mission phase changes, can use foregoing base
Mode in positional information, the mode based on temporal information, the mode of the 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, it is state of flight of the emission type unmanned plane 100 in the autonomous flight stage, under the state of flight, nothing
It is man-machine to be launched 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 fuselage lower section, launches retaining mechanism, rear wing by front wing respectively and launches 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 launches to lock by empennage
Tight mechanism is connected with fuselage.The structure that three class wings launch locking device is identical, and size is different.During expansion, front wing 120,
The flexible member that rear wing 130 is launched in retaining mechanism by correspondence wing drives, and is to launch retaining mechanism axis to fuselage both sides
Symmetrically launch in axle center.When wing launches in place, 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 launches retaining mechanism and locks wing.Empennage 140
Launch retaining mechanism axis to launch clockwise in axle center respectively in accordance with empennage, can be limited by empennage block when launching in place
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.
A kind of function structure chart of the emission type unmanned plane provided referring to Fig. 5, another embodiment of the present invention.The emission type
Unmanned plane 100 includes body, morphing, flying power unit 150, reaction power unit 160, drag parachute 170, flight shape
State adjustment unit 180, position detection unit 190.Body includes head 110 and fuselage, and morphing includes front wing 120, rear wing
130 and empennage 140.Specifically, be provided with fuselage can launch or fold with respect to fuselage for a pair front wing 120, a pair can be with
The rear wing 130 that launches with respect to fuselage or fold, a pair can the relative fuselage empennage 140 that launches or fold, and be arranged on machine
The propeller of body afterbody, 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 pass through machine
Span open locking mechanism is connected with fuselage.In different mission phases, unmanned plane is presented the difference physically and/or on power.
In the embodiment, the adjustment of triggering state of flight is based on positional information in the way of realizing that mission phase changes.
Be provided with position detection unit on unmanned plane, the position detection unit be used to gather unmanned plane geographical location information 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, unmanned plane enters the mode of inverse launching phase from launching phase, is that unmanned plane is launched by reverse
The mode of object reduces flying speed.Reaction power unit 150, the reaction power unit are provided with unmanned plane
150 can provide reverse power by jet to unmanned plane, reduce flying speed.Preferably, 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 unit 170 can be ejected and opened from the afterbody rear end of fuselage.Because the direction that drag parachute is opened is winged with unmanned plane
Therefore line direction conversely, can be described as reverse opening.After drag parachute launches, 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 invention, there is provided a kind of system of transmitting unmanned plane, including foregoing emission type unmanned plane,
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.Preferably, 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.Preferably, 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, cylinder preferably using the glass-reinforced plastic material of high intensity, by screw thread installed by cylinder back-end
On bearing base.Slide rail is provided with cylinder inboard wall, rear end isolation is provided with low-pressure chamber, holes and hyperbaric chamber in cylinder, 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 pushes away
Plate；, by holes UNICOM, hyperbaric chamber bottom is placed with the fire in a stove before fuel is added and transmitting explosion medicine for low-pressure chamber and hyperbaric chamber, and the fire in a stove before fuel is added is sent out with electric signal
End is penetrated to be connected.
It is referring to Fig. 6, another embodiment of the present invention, there is provided a kind of implementation method of emission type unmanned plane including as follows
Step.
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 for itself setting, from launching phase flight
State enters inverse launching phase state of flight.
S300, by 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.
Preferably, between step S100 and step S200, also turn from launching phase state of flight including triggering unmanned plane
The step of changing to inverse launching phase state of flight.
And, between step S200 and step S300, also turn from inverse launching phase state of flight including triggering unmanned plane
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, can use foregoing based on positional information
Mode, the mode based on temporal information, the mode of the active control based on control signal or based on unmanned plane to itself fly
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 for obtaining,
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,
Triggering unmanned plane carries out body adjustment and power adjustment.
Or, gather the temporal information of unmanned plane, according to the information for obtaining, 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 for receiving, triggering unmanned plane enters
Row body is adjusted and power adjustment.The control signal, can carry out emitter, it is also possible to come from the long-range end of other associations
End.
Or, the state of flight information of unmanned plane is monitored, judge unmanned plane in the horizontal direction and/or the motion of vertical direction
Speed, according to the velocity standard that state of flight adjustment is carried out the need for presetting, triggering unmanned plane carries out body adjustment and power is adjusted
It is whole.
Foregoing description is only the description to present pre-ferred embodiments, not to any restriction of the scope of the invention, this hair
The scope of bright preferred embodiment includes other realization, wherein can not by it is described go out or the order that discusses perform work(
Energy.Any change, modification that the those of ordinary skill in field of the present invention does according to the disclosure above content, belong to claims
Protection domain.
Claims (15)
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 of itself setting and/or resistance structure, so as to fly from launching phase
Row state enters inverse launching phase state of flight；By after inverse launching phase, the unmanned plane enters the autonomous flight stage, is reaching
To or close in the case of destination, being changed into the 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 of the reverse transmitting is can be in the explosive of transmitting after-explosion.
4. emission type unmanned plane according to claim 1, it is characterised in that：Reaction power list is provided with unmanned plane
Unit, the reaction power unit can provide reverse power by jet to unmanned plane, reduce flying speed.
5. emission type unmanned plane according to claim 1, it is characterised in that：State of flight adjustment is provided with unmanned plane single
Unit, 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 gather the geographical location information and/or flying distance information of unmanned plane, and the information that will be obtained
It is sent to state of flight adjustment unit；The state of flight adjustment unit determines whether to meet default according to the information for receiving
Need to carry out geographical position and/or the distance of 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 to gather the temporal information of 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 for receiving, 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
Unit, the wireless signal Transmit-Receive Unit can connect control signal, and it is single that the control signal of acquisition is sent into state of flight adjustment
Unit；According to the control signal for receiving, triggering unmanned plane carries out body adjustment and power adjustment to the state of flight adjustment unit.
9. emission type unmanned plane according to claim 5, it is characterised in that：State of flight monitoring is provided with unmanned plane single
Unit, the state of flight monitoring unit is used to monitor the state of flight information of unmanned plane, and the state of flight information hair that will be obtained
Give state of flight adjustment unit；The state of flight adjustment unit judges unmanned plane in the horizontal direction according to the information for receiving
And/or the movement velocity of vertical direction, according to the velocity standard that state of flight adjustment is carried out the need for presetting, triggering unmanned plane enters
Row body is adjusted and power adjustment.
10. it is a kind of launch unmanned plane system, it is characterised in that including：
Emission type unmanned plane any one of claim 1-9；
Emitter, there is provided the power of transmitting unmanned plane.
11. systems according to claim 10, it is characterised in that：The emitter include transmitter unit, brake unit,
Control unit, described control unit controls the transmitter unit and brake unit.
12. a kind of implementation methods of emission type unmanned plane, it is characterised in that comprise the following steps：
Unmanned plane is launched by emitter, unmanned plane enters launching phase state of flight；
Unmanned plane reduces flying speed by the power and/or resistance structure for itself setting, and enters from launching phase state of flight
Inverse launching phase state of flight；
By after inverse launching phase, the unmanned plane enters the autonomous flight stage, is reaching or close in the case of destination, is turning
It is changed into the state of flight that self power can be leaned on to fly.
13. methods according to claim 12, it is characterised in that：Gather geographical location information and/or the flight of unmanned plane
Range information, according to the information for obtaining, 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.
14. methods according to claim 12, it is characterised in that：The temporal information of unmanned plane is gathered, according to the letter for obtaining
Breath, determine whether to meet it is default the need for carry out time of state of flight adjustment；In the case where judging to meet, unmanned plane is triggered
Carry out body adjustment and power adjustment.
15. methods according to claim 12, it is characterised in that：The state of flight information of unmanned plane is monitored, nobody is judged
Machine in the horizontal direction and/or vertical direction movement velocity, 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 adjustment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710001206.XA CN106741847B (en) | 2017-01-03 | 2017-01-03 | Transmitting type unmanned aerial vehicle, system and implementation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710001206.XA CN106741847B (en) | 2017-01-03 | 2017-01-03 | Transmitting type unmanned aerial vehicle, system and implementation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106741847A true CN106741847A (en) | 2017-05-31 |
| CN106741847B CN106741847B (en) | 2023-10-13 |
Family
ID=58952161
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710001206.XA Active CN106741847B (en) | 2017-01-03 | 2017-01-03 | Transmitting type unmanned aerial vehicle, system and implementation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741847B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114590417A (en) * | 2022-03-24 | 2022-06-07 | 武昌理工学院 | Method and device for controlling catapult takeoff of unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6923404B1 (en) * | 2003-01-10 | 2005-08-02 | Zona Technology, Inc. | Apparatus and methods for variable sweep body conformal wing with application to projectiles, missiles, and unmanned air vehicles |
| CN102173310A (en) * | 2004-04-14 | 2011-09-07 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| CN103587686A (en) * | 2013-12-02 | 2014-02-19 | 哈尔滨工业大学 | Catapulted folding wing flying robot |
| CN104691748A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Gun-launched unmanned helicopter and expansion method thereof |
| CN105035321A (en) * | 2015-07-08 | 2015-11-11 | 中国电子科技集团公司第二十七研究所 | Miniature cylindrical launched unmanned plane and launcher |
| CN206520738U (en) * | 2017-01-03 | 2017-09-26 | 上海量明科技发展有限公司 | Emission type unmanned plane and its system |
-
2017
- 2017-01-03 CN CN201710001206.XA patent/CN106741847B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6923404B1 (en) * | 2003-01-10 | 2005-08-02 | Zona Technology, Inc. | Apparatus and methods for variable sweep body conformal wing with application to projectiles, missiles, and unmanned air vehicles |
| CN102173310A (en) * | 2004-04-14 | 2011-09-07 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| CN103587686A (en) * | 2013-12-02 | 2014-02-19 | 哈尔滨工业大学 | Catapulted folding wing flying robot |
| CN104691748A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Gun-launched unmanned helicopter and expansion method thereof |
| CN105035321A (en) * | 2015-07-08 | 2015-11-11 | 中国电子科技集团公司第二十七研究所 | Miniature cylindrical launched unmanned plane and launcher |
| CN206520738U (en) * | 2017-01-03 | 2017-09-26 | 上海量明科技发展有限公司 | Emission type unmanned plane and its system |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114590417A (en) * | 2022-03-24 | 2022-06-07 | 武昌理工学院 | Method and device for controlling catapult takeoff of unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106741847B (en) | 2023-10-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107985605B (en) | Control system of surrounding scouting and batting integrated airplane | |
| CN111670063B (en) | Fire resistant aircraft for suppressing a wide range of fires | |
| CN108482635B (en) | Inflator wing type aircraft capable of being parked | |
| CN106516144A (en) | Recovery method for small and medium-sized fixed-wing unmanned aerial vehicle | |
| CN103043214A (en) | Folding type unmanned plane | |
| US20160178317A1 (en) | Payload launch system and method | |
| CN110065634A (en) | Unmanned flight robot based on the cold power-assisted transmitting of compressed gas | |
| RU2684160C1 (en) | Deck-based aircraft unmanned anti-submarine complex (dauac) | |
| RU2721808C1 (en) | Surface-submerged ship with deck air strike complex | |
| US20210237872A1 (en) | Launch system | |
| CN109229363A (en) | A kind of double hair hand throwing fixed-wing unmanned planes | |
| WO2008073069A2 (en) | Unmanned aerial vehicle | |
| RU2708782C1 (en) | Unmanned aircraft-helicopter-missile carrier | |
| RU2768999C1 (en) | Coastal air-rocket reusable autonomous complex | |
| CN203020540U (en) | Folding unmanned aerial vehicle | |
| CN206520738U (en) | Emission type unmanned plane and its system | |
| RU2720592C1 (en) | Adaptive airborne missile system | |
| CN106741847A (en) | Emission type unmanned plane and its system, implementation method | |
| WO2016079747A1 (en) | Delivery of intelligence gathering devices | |
| RU2711430C2 (en) | Flying robot-carrier of shipborne and airborne missiles | |
| RU2721803C1 (en) | Aircraft-missile strike system | |
| RU2745590C1 (en) | Method for capture of air target with a net | |
| RU2733678C1 (en) | Unmanned impact helicopter aircraft | |
| CN110940236B (en) | Non-aiming intelligent patrol projectile | |
| RU2725372C1 (en) | Unobtrusive aircraft-missile system |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |