CN108204768A - Four duct electric power rockets, emitter and launching technique - Google Patents
Four duct electric power rockets, emitter and launching technique Download PDFInfo
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- CN108204768A CN108204768A CN201810081500.0A CN201810081500A CN108204768A CN 108204768 A CN108204768 A CN 108204768A CN 201810081500 A CN201810081500 A CN 201810081500A CN 108204768 A CN108204768 A CN 108204768A
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- 230000001105 regulatory effect Effects 0.000 claims abstract description 36
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 27
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- 230000033001 locomotion Effects 0.000 description 4
- 238000004064 recycling Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H11/00—Defence installations; Defence devices
- F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/68—Line-carrying missiles, e.g. for life-saving
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a kind of four duct electric power rockets, emitter and launching technique, the rocket includes housing, case top is hinged with radome fairing, outside is equipped with distance measuring sensor and image recognizer, bottom is surrounded by four symmetrical duct motors, it is internally provided with Electromagnetical ejector, electric-control system and flight control system, Electromagnetical ejector is equipped with intercept net bullet, electric-control system respectively with distance measuring sensor, image recognizer, Electromagnetical ejector, flight control system connects, flight control system is connect respectively with four duct motors, radome fairing is connect by connecting line with Electromagnetical ejector；The emitter includes launch angle regulating mechanism and rotating mechanism, launch angle regulating mechanism is fixed on rotating mechanism, for placing rocket, and adjust the launch angle of rocket, rotating mechanism is used to that launch angle regulating mechanism to be driven to rotate horizontally launch angle regulating mechanism.The present invention can accurate delivery rocket whenever and wherever possible, improve attack precision.
Description
Technical field
The present invention relates to a kind of electric power rocket and its emitter, especially a kind of four duct electric power rockets, transmitting
Device and launching technique belong to aircraft field.
Background technology
At present, with remote sensing technology, the continuous maturation of airmanship and electronic technology, the cost of manufacture of small aircraft is got over
Come lower, gradually expand with range using scale.In recent years, small aircraft brings work, agriculture production and other field
Facility, but also bring great hidden danger to public safety.
Although relevant department is provided with no-fly zone for small aircraft, and has gradually put into effect related management method, small
The thing that type aircraft malice upsets the public happens occasionally, and needs the mandatory interception of small aircraft and captures.Due to
Low latitude small aircraft is small, at low cost, flight path is flexible, is not suitable for using general military ground-to-air blocking apparatus, special
It is not to require radio interference the stringent more unsuitable use in place on airport etc..
Existing small aircraft blocking apparatus has unmanned plane electromagnetic signal to interfere vehicle, unmanned aerial vehicle catching net transmitter
Wait several types, generally existing range is shorter, can not real-time tracking target, the shortcomings of electromagnetic interference is stronger, application scenario is more
Limitation, use cost is higher, can not promote on a large scale.
Invention content
The defects of first purpose of the present invention is to solve the above-mentioned prior art provides a kind of four duct electric power fire
Arrow, the autonomous trace trap target of the rocket are driven using four duct motors, can be turned by each duct motor of independent control
Speed controls rocket posture and running track, it can be achieved that being precisely controlled, and ensure that the flexibility of rocket flight.
Second object of the present invention is to provide a kind of emitter of above-mentioned rocket, and the device is easy to carry, motor-driven
Property is strong, can accurate delivery rocket whenever and wherever possible, not only increase attack precision, and facilitate the operation and use of user.
Third object of the present invention is to provide a kind of launching technique based on above-mentioned emitter.
First purpose of the present invention can be reached by adopting the following technical scheme that：
Four duct electric power rockets, including housing, the case top is hinged with radome fairing, and hull outside is passed equipped with ranging
Sensor and image recognizer, housing bottom are surrounded by four symmetrical duct motors, and enclosure interior is equipped with electromagnetic launch
Device, electric-control system and flight control system, the Electromagnetical ejector be equipped with intercept net bullet, the electric-control system respectively with ranging
Sensor, image recognizer, Electromagnetical ejector, flight control system connection, the flight control system respectively with four ducts
Motor connects, and the radome fairing is connect by connecting line with Electromagnetical ejector.
Further, the enclosure interior is divided into upper and lower two parts, and top is divided into electromagnetic launch cabin, and lower part is divided into electricity
Cabin is controlled, the Electromagnetical ejector and intercept net bullet are arranged in electromagnetic launch cabin, and the electric-control system and flight control system are set
It puts in automatically controlled cabin.
Further, the distance measuring sensor is arranged on the outside of housing central section, and described image identifier is arranged on housing
On the outside of portion.
Second object of the present invention can be reached by adopting the following technical scheme that：
The emitter of above-mentioned rocket, including launch angle regulating mechanism and rotating mechanism, the launch angle adjusts machine
Structure is fixed on rotating mechanism, and launch angle regulating mechanism is for placing rocket, and adjust the launch angle of rocket, the rotation
Mechanism is used to that launch angle regulating mechanism to be driven to rotate horizontally.
Further, the launch angle regulating mechanism includes stent, launching trajectory cabin and the first motor, and the stent is consolidated
It is scheduled on rotating mechanism, for placing rocket, first motor is arranged on stent, and pass through shaft in the launching trajectory cabin
It is connect with launching trajectory cabin, for launching trajectory cabin to be driven to swing, so as to adjust the launch angle of rocket.
Further, the launching trajectory cabin is cross space orbit cabin.
Further, the swaying direction both sides in the launching trajectory cabin are respectively equipped with limiting plate.
Further, the rotating mechanism includes rotary shaft tray, the first support base and the second motor, the launch angle
Regulating mechanism is fixed on the first support base, and first support base is fixed on rotary shaft tray, the second motor setting
It is connect on the first support base, and with the first support base, for the first support base to be driven to rotate horizontally, so as to drive launch angle
Regulating mechanism rotates horizontally.
Further, the emitter further includes the second support base, and second support base is arranged on rotating mechanism
Bottom.
Further, the bottom of second support base is equipped with universal wheel.
Third object of the present invention can be reached by adopting the following technical scheme that：
Based on the launching technique of above-mentioned emitter, the method includes：
It is captured in spatial domain when the target that is captured enters, rocket is placed on launch angle regulating mechanism；
By the launch angle and the direction of the launch of launch angle regulating mechanism and rotating mechanism co- controlling rocket, make rocket
Top towards being captured target direction, realize the initial alignment of rocket；
Start rocket, rocket is made to launch from launch angle regulating mechanism；
Rocket tracking after transmitting is captured target, when rocket will be contacted with the target that is captured, by intercept net bullet from
It is ejected at the top of rocket, enwinds the target that is captured.
Further, the rocket after the transmitting tracks the target that is captured, when rocket will be contacted with the target that is captured,
Intercept net bullet at the top of rocket is ejected, the target that is captured is enwinded, specifically includes：
Rocket after transmitting by image recognizer identification be captured target and by distance measuring sensor measure rocket with
Be captured the distance between target, and then transmits signals to flight control system by electric-control system；
By the rotating speed and thrust of each duct motor of flight control system independent control, according to the position for the target that is captured
Situation of change constantly adjusts the running track and flight attitude of rocket, makes to be directed at the target that is captured at the top of rocket always；
When rocket will be contacted with the target that is captured, electric control system controls Electromagnetical ejector is started to work, at this time electromagnetism
Ejector is in ejection status, pulls connecting line, radome fairing is opened, and then intercept net bullet is ejected at the top of rocket；
It is opened after the release of intercept net bullet, enwinds the target that is captured.
The present invention has following advantageous effect relative to the prior art：
1st, rocket of the invention is pure electric vehicle rocket, and safety is higher, and mobility is stronger, and controllability is stronger, power section
It is driven using four duct motors, can rocket posture and running track be controlled by the rotating speed of each motor of independent control, it can
Realization is precisely controlled, compared to traditional steering mechanism turned to by rudder face, precision and controllability higher；It uses electromagnetic launch
Device discharges intercept net bullet, has and is quick on the draw, and reliability is high, it is reusable the advantages that；It is realized by image recognizer to quilt
It captures the tracking of target and the relative position for the target that is captured is obtained by distance measuring sensor, pass through distance measuring sensor in addition
The distance between rocket and ground signal can also be transmitted, and then four duct motors is controlled to cooperate, realizes that rocket steadily drops
Receipts are dropped back into, reduce use cost.
2nd, it is divided into upper and lower two parts inside storepipe of the invention, top is divided into electromagnetic launch cabin, and lower part is divided into electricity
The intercept net bullet of control cabin, Electromagnetical ejector and its filling is arranged in electromagnetic launch cabin, and electric-control system and flight control system are set
It puts in automatically controlled cabin, by setting electromagnetic launch cabin and automatically controlled cabin, ejection part and control section is separated, preferably to pacify
Dress and maintenance.
3rd, emitter of the invention devises launch angle regulating mechanism and rotating mechanism, and machine is adjusted by launch angle
Structure can place rocket, and adjust the launch angle of rocket, launch angle regulating mechanism can be driven horizontal by rotating mechanism
Rotation to adjust the direction of the launch of rocket, has three degree of freedom, it can be achieved that more accurately rocket initial alignment function.
4th, in emitter of the invention, the launching trajectory cabin of launch angle regulating mechanism is a cross space orbit
Cabin, rocket can smoothly slide in launching trajectory cabin, and rocket can further be helped to realize initial alignment.
It 5th, can be in the launching trajectory cabin swaying direction both sides of launch angle regulating mechanism point in emitter of the invention
Limiting plate is not set, to limit the swing angle in launching trajectory cabin so that rocket can emit or tilt upward hair straight up
It penetrates, ensures that rocket directive is aerial.
6th, in emitter of the invention, a support base can be set in the bottom of rotating mechanism, which can be with
The weight of launch angle regulating mechanism and rotating mechanism is supported, and the bottom of the support base can also set universal wheel, pass through
Universal wheel can easily carry out the carrying and movement of emitter.
Description of the drawings
Fig. 1 is the three-dimensional structure diagram of four duct electric power rockets of the embodiment of the present invention 1.
Fig. 2 is the sectional structure chart of four duct electric power rockets of the embodiment of the present invention 1.
Fig. 3 is the emitter structure chart of the embodiment of the present invention 1.
Fig. 4 is that the emitter of the embodiment of the present invention 1 places the schematic diagram of rocket.
Wherein, 1- housings, 2- radome fairings, 3- distance measuring sensors, 4- image recognizers, 5- duct motors, 6- electromagnetic launches
Device, 7- electric-control systems, 8- flight control systems, 9- connecting lines, 10- intercept net bullets, 11- electromagnetic launches cabin, the automatically controlled cabins of 12-, 13-
Power battery, 14- stents, 15- launching trajectories cabin, the first motors of 16-, 17- rotary shaft trays, the first support bases of 18-, 19-
Two motors, 20- first rotating shafts, the second shafts of 21-, 22- limiting plates, the second support bases of 23-, 24- universal wheels.
Specific embodiment
With reference to embodiment and attached drawing, the present invention is described in further detail, but embodiments of the present invention are unlimited
In this.
Embodiment 1：
As depicted in figs. 1 and 2, a kind of four duct electric power rockets are present embodiments provided, which can be used for intercepting
Small aircraft, including housing 1, radome fairing 2, distance measuring sensor 3, image recognizer 4, duct motor 5, Electromagnetical ejector 6,
Electric-control system 7 and flight control system 8, wherein radome fairing 2, distance measuring sensor 3, image recognizer 4, duct motor 5 are housing 1
External structure, Electromagnetical ejector 6, electric-control system 7 and flight control system 8 be housing 1 internal structure.
The housing 1 is identical with the outer housing of traditional power rocket, is all cylindrical structure, and open top.
The radome fairing 2 is mounted on 1 top of housing, hinged with 1 top of housing, can open more easily radome fairing 2,
Radome fairing 2 is also connect by connecting line 9 with Electromagnetical ejector 6, and the folding of radome fairing 2 is controlled by Electromagnetical ejector 6.
The distance measuring sensor 3 is mounted on 1 middle part outside of housing preferably using distance measuring sensor, and with electric-control system 7
Connection is mainly used for measuring rocket and the distance between the target (such as small aircraft) that is captured, obtains the phase for the target that is captured
To position；In addition, when rocket enters recycling state, the distance between rocket and ground can be transmitted by distance measuring sensor 3
Signal, and then duct motor 5 is controlled to cooperate, it realizes the recycling of rocket stable landing, reduces use cost.
Described image identifier 4 is mounted on 1 upper outside of housing, and is connect with electric-control system 7, for identifying the mesh that is captured
Mark, realizes the tracking to the target that is captured.
There are four the duct motors 5, and four duct motors 5 symmetrically are mounted on 1 bottom surrounding of housing, and with flying
Row control system 8 connects, and by flight control system 8, can be controlled with the rotating speed and thrust of each duct motor 5 of independent control
Rocket flight track and flight attitude are, it can be achieved that be precisely controlled, compared to traditional steering mechanism turned to by rudder face, precision and
Controllability higher.
The Electromagnetical ejector 6 is arranged on inside housing 1, and is connect with electric-control system 7, the ejection portion of Electromagnetical ejector 6
Intercept net bullet 10 is filled on position, and during rocket original state, Electromagnetical ejector 6 be in compressive state, and intercept net bullet 10 is in closing
Conjunction state, when the order that Electromagnetical ejector 6 receives electric-control system 7 is started to work, Electromagnetical ejector 6 can be in catapult like
State, after starting ejection, connecting line 2 is tightened up, and then opens radome fairing 1, and intercept net bullet 10 will be popped up by Electromagnetical ejector 6,
And then the target that is captured is captured.
The electric-control system 7 is arranged on inside housing 1, and is connect with flight control system 8, for collecting distance measuring sensor
3 and the signal that transmits of image recognizer 4, and transmit signals to flight control system 8.
The flight control system 8 is arranged on inside housing 1, what flight control system 8 was transmitted by receiving electric-control system 7
Signal, the rotating speed and thrust of each duct motor 5 of independent control, and then change rocket flight track and flight attitude, control fire
Arrow precisely tracks target.
Preferably, upper and lower two parts are divided into inside the housing 1 of the present embodiment, top is divided into electromagnetic launch cabin 11, lower part
It is divided into automatically controlled cabin 12, Electromagnetical ejector 6 and its intercept net bullet 10 loaded are arranged in electromagnetic launch cabin 11,7 He of electric-control system
Flight control system 8 is arranged in automatically controlled cabin 12, by setting electromagnetic launch cabin 11 and automatically controlled cabin 12, by ejection part and control
Part separates, and so as to preferably installation and maintenance, further, power battery 13, power battery 13 is additionally provided in automatically controlled cabin 12
Can be all electrical equipment power supplies in rocket.
In conclusion the rocket of the present invention is pure electric vehicle rocket, safety is higher, and mobility is stronger, and controllability is stronger, moves
Power part is driven using four duct motors, can control rocket posture and operation rail by the rotating speed of each motor of independent control
Road is, it can be achieved that be precisely controlled, compared to traditional steering mechanism turned to by rudder face, precision and controllability higher；It uses electricity
Magnetic ejector discharges intercept net bullet, has and is quick on the draw, and reliability is high, it is reusable the advantages that；Pass through image recognizer reality
The now tracking to the target that is captured and the relative position for the target that is captured by distance measuring sensor acquisition, pass through ranging in addition
Sensor can also transmit with ground distance signal, and then four duct motors is controlled to cooperate, realizes that rocket stable landing returns
It receives, reduces use cost.
As shown in figure 3, the present embodiment additionally provides a kind of emitter of above-mentioned rocket, which includes the angle of departure
Regulating mechanism and rotating mechanism are spent, launch angle regulating mechanism includes stent 14,15 and first motor 16 of launching trajectory cabin, rotation
Mechanism includes rotary shaft tray 17, the first support base 18 and the second motor 19.
Further, stent 14 is fixed on the first support base 18, is made of two symmetrical upright bars；Emit rail
Road cabin 15 is for placing rocket, as shown in figure 4, launching trajectory cabin 15 is preferably a cross space orbit cabin, rocket can be
It is smoothly slid in launching trajectory cabin 15, the effect in launching trajectory cabin 15 can help rocket to realize initial alignment, improve and capture hit
Rate；First motor 16 is set on the support 14, is specifically located on the inside of a upright bar of stent 14, from the figure, it can be seen that this
Embodiment is arranged on the inside of the upright bar of the right, and is passed through first rotating shaft 20 and connect with the right side in launching trajectory cabin 15, is sent out for driving
15 swing of orbital module is penetrated, so as to adjust the launch angle of rocket.
In order to improve the swing effect in launching trajectory cabin 15, another upright bar of stent 14, i.e. left side upright bar passes through second
Shaft 21 is connect with the left side in launching trajectory cabin 15, and stent 14 can support transmitting rail by first rotating shaft 20, the second shaft 21
Road cabin 15, after the first motor 16 is driven by first rotating shaft 20, the second shaft 21 also plays the effect of transmission, smoothly drives hair
Penetrate 15 swing of orbital module.
Further, since the necessary directive of rocket is aerial, rocket can only emit or tilt upward transmitting straight up, level hair
It is all unnecessary, therefore the present embodiment is (i.e. front and rear in the swaying direction both sides in launching trajectory cabin 15 to penetrate and emit diagonally downward
Position) limiting plate 22 is respectively equipped with, to limit the swing angle in launching trajectory cabin 15, the limiting plate 22 also the first support base 18
On.
Further, the first support base 18 is fixed on rotary shaft tray 17, and the second motor 19 is arranged on the first support base
It on 18, and is connect with the first support base 18, due to the effect of rotary shaft tray 17, the second motor 19 can pass through gear, belt
Etc. modes the first support base 18 is driven to rotate horizontally, so as to which stent 14 be driven to rotate horizontally, to adjust the direction of the launch of rocket.
Preferably, the emitter of the present embodiment further includes the second support base 23, and the second support base 23 is arranged on whirler
The bottom of structure, it is specific mounted on the bottom of rotary shaft tray 17, the weight of launch angle regulating mechanism and rotating mechanism can be supported
Amount；In addition, the bottom of the second support base 23 can also set universal wheel 24, the 23 rectangular knot of the second support base of the present embodiment
Structure, correspondingly, universal wheel 24 are also provided with four, and four universal wheels 24 are arranged on four angles of the second support base 23, pass through ten thousand
The carrying and movement of emitter can be easily carried out to wheel 24.
It is controlled while launch angle regulating mechanism and rotating mechanism to realize, it can be by the first motor 16 and the second electricity
Machine 19 is connect with same control unit, which can be provided in the controller on emitter, the controller collection into
Microprocessor (such as microcontroller), motor driver or the computer being arranged on outside emitter, computer
Slot is inserted into motion control card, motion control card connection motor driver.
As shown in Figure 1 to 4, the concrete principle of the emitter four duct electric power rockets of transmitting of the present embodiment is as follows：
S1, it is captured in spatial domain when the target that is captured (such as small aircraft) enters, rocket is placed in launch angle is adjusted
In the launching trajectory cabin 15 of mechanism.
S2, pass through the first motor 16 of launch angle regulating mechanism and the 19 co- controlling rocket of the second motor of rotating mechanism
Launch angle and the direction of the launch, the top of rocket is made to realize the initial alignment of rocket towards the target direction that is captured.
S3, start rocket, rocket is made to launch from the launching trajectory cabin 15 of launch angle regulating mechanism.
Rocket after S4, transmitting is captured by the identification of image recognizer 4 and target and is measured by distance measuring sensor 3
Rocket and the distance between the target that is captured, and then flight control system 8 is transmitted signals to by electric-control system 7.
S5, rotating speed and thrust by each duct motor 5 of 8 independent control of flight control system, according to the target that is captured
Change in location situation constantly adjust the running track and flight attitude of rocket, alignment always is made at the top of rocket to be captured target；
S6, when rocket will be contacted with the target that is captured, illustrate rocket be captured the distance between target be less than set
Fixed distance threshold, electric-control system 7 control Electromagnetical ejector 6 to start to work, and Electromagnetical ejector 6 is in ejection status at this time, draw
Dynamic connecting line, radome fairing is opened, and then intercept net bullet 10 is ejected at the top of rocket；
S7, intercept net bullet 10 are opened after discharging, and enwind the target that is captured, and the target that makes to be captured runs out of steam and manipulation work(
It can and then fall.
After S8, interception work, rocket enters recycling state, and flight control system 8 can control four duct motors 5,
The rotating speed for making four duct motors 5 is identical with thrust, keeps the vertical of storepipe, is landed with slower speed, realizes recycling.
In conclusion the emitter of the present invention devises launch angle regulating mechanism and rotating mechanism, pass through the angle of departure
Degree regulating mechanism can place rocket, and adjust the launch angle of rocket, launch angle can be driven to adjust by rotating mechanism
Mechanism rotates, and to adjust the direction of the launch of rocket, has three degree of freedom, it can be achieved that more accurately rocket initial alignment work(
Energy.
The above, patent preferred embodiment only of the present invention, but the protection domain of patent of the present invention is not limited to
This, any one skilled in the art is in the range disclosed in patent of the present invention, according to the skill of patent of the present invention
Art scheme and its inventive concept are subject to equivalent substitution or change, belong to the protection domain of patent of the present invention.
Claims (10)
1. four duct electric power rockets, it is characterised in that：Including housing, the case top is hinged with radome fairing, hull outside
Equipped with distance measuring sensor and image recognizer, housing bottom is surrounded by four symmetrical duct motors, and enclosure interior is set
There are Electromagnetical ejector, electric-control system and flight control system, the Electromagnetical ejector is equipped with intercept net bullet, the electric-control system
It is connect respectively with distance measuring sensor, image recognizer, Electromagnetical ejector, flight control system, the flight control system difference
It is connect with four duct motors, the radome fairing is connect by connecting line with Electromagnetical ejector.
2. four ducts electric power rocket according to claim 1, it is characterised in that：The enclosure interior is divided into upper and lower two
A part, top are divided into electromagnetic launch cabin, and lower part is divided into automatically controlled cabin, and the Electromagnetical ejector and intercept net bullet are arranged on electromagnetism bullet
It penetrates in cabin, the electric-control system and flight control system are arranged in automatically controlled cabin.
3. the emitter of rocket described in claims 1 or 2, it is characterised in that：Including launch angle regulating mechanism and whirler
Structure, the launch angle regulating mechanism are fixed on rotating mechanism, and launch angle regulating mechanism is used to place rocket, and adjust fire
The launch angle of arrow, the rotating mechanism are used to that launch angle regulating mechanism to be driven to rotate horizontally.
4. emitter according to claim 3, it is characterised in that：The launch angle regulating mechanism includes stent, hair
Orbital module and the first motor are penetrated, the stent is fixed on rotating mechanism, and the launching trajectory cabin is for placing rocket, and described the
One motor is arranged on stent, and is passed through shaft and connect with launching trajectory cabin, for launching trajectory cabin to be driven to swing, so as to adjust
The launch angle of rocket.
5. emitter according to claim 4, it is characterised in that：The launching trajectory cabin is cross space orbit
Cabin.
6. emitter according to claim 3, it is characterised in that：The rotating mechanism includes rotary shaft tray, first
Support base and the second motor, the launch angle regulating mechanism are fixed on the first support base, and first support base is fixed on
On rotary shaft tray, second motor is arranged on the first support base, and is connect with the first support base, for driving first
It supports seat to rotate horizontally, so as to which launch angle regulating mechanism be driven to rotate horizontally.
7. according to claim 3-6 any one of them emitters, it is characterised in that：The emitter further includes second
Seat is supportted, second support base is arranged on the bottom of rotating mechanism.
8. emitter according to claim 7, it is characterised in that：The bottom of second support base is equipped with universal wheel.
9. the launching technique based on any one of the claim 4-8 emitters, it is characterised in that：The method includes：
It is captured in spatial domain when the target that is captured enters, rocket is placed on launch angle regulating mechanism；
By the launch angle and the direction of the launch of launch angle regulating mechanism and rotating mechanism co- controlling rocket, make the top of rocket
The initial alignment of rocket is realized towards the target direction that is captured in portion；
Start rocket, rocket is made to launch from launch angle regulating mechanism；
Rocket tracking after transmitting is captured target, when rocket will be contacted with the target that is captured, by intercept net bullet from rocket
Top ejects, and enwinds the target that is captured.
10. launching technique according to claim 9, it is characterised in that：Rocket after the transmitting tracks the target that is captured,
When rocket will be contacted with the target that is captured, intercept net bullet at the top of rocket is ejected, the target that is captured is enwinded, has
Body includes：
Rocket after transmitting is identified by image recognizer to be captured target and measures rocket with being caught by distance measuring sensor
The distance between target is caught, and then flight control system is transmitted signals to by electric-control system；
By the rotating speed and thrust of each duct motor of flight control system independent control, according to the change in location for the target that is captured
Situation constantly adjusts the running track and flight attitude of rocket, makes to be directed at the target that is captured at the top of rocket always；
When rocket will be contacted with the target that is captured, electric control system controls Electromagnetical ejector is started to work, at this time electromagnetic launch
Device is in ejection status, pulls connecting line, radome fairing is opened, and then intercept net bullet is ejected at the top of rocket；
It is opened after the release of intercept net bullet, enwinds the target that is captured.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810081500.0A CN108204768A (en) | 2018-01-29 | 2018-01-29 | Four duct electric power rockets, emitter and launching technique |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810081500.0A CN108204768A (en) | 2018-01-29 | 2018-01-29 | Four duct electric power rockets, emitter and launching technique |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108204768A true CN108204768A (en) | 2018-06-26 |
Family
ID=62605001
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810081500.0A Pending CN108204768A (en) | 2018-01-29 | 2018-01-29 | Four duct electric power rockets, emitter and launching technique |
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| CN109200597A (en) * | 2018-11-26 | 2019-01-15 | 桂林航天工业学院 | Miniature solid rocket system |
| CN110553548A (en) * | 2019-08-30 | 2019-12-10 | 江西洪都航空工业集团有限责任公司 | anti-unmanned aerial vehicle system based on fixed wing platform |
| CN111272019A (en) * | 2020-03-27 | 2020-06-12 | 牛三库 | Intelligent elastic net |
| CN111653174A (en) * | 2020-05-26 | 2020-09-11 | 南京航空航天大学 | Rocket model stable control demonstration device applied to science popularization education |
| CN114705080A (en) * | 2022-02-11 | 2022-07-05 | 广东空天科技研究院 | Deformable and recyclable rocket aircraft aerial launching system |
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| CN114705080B (en) * | 2022-02-11 | 2023-09-29 | 广东空天科技研究院 | Deformable and recyclable rocket type aircraft air launching system |
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