CN110329515A - It is a kind of to examine the design method and system for making integrated aircraft - Google Patents
It is a kind of to examine the design method and system for making integrated aircraft Download PDFInfo
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- CN110329515A CN110329515A CN201910688211.1A CN201910688211A CN110329515A CN 110329515 A CN110329515 A CN 110329515A CN 201910688211 A CN201910688211 A CN 201910688211A CN 110329515 A CN110329515 A CN 110329515A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
Abstract
Dozen design method and system of integrated aircraft is examined the invention discloses a kind of, it is that will examine that beat integrated airplane design be that introduce except photoelectronic reconnaissance in addition to include technology investigation with long-range including radar-reconnaissance and reconnaissance equipment round the clock, the comprehensive strike of progress is interacted with a variety of weapons；Course line is designed as using 8 word course line orbits aerial to one of specific direction or a group or ground sea-surface target is persistently hit；Air weapon is designed as usually being built in engine room inside.Outstanding feature of the present invention is to realize the theaomni-directional transmission of emission type weapon by installing weapon carrier.It examines dozen aircraft and target is persistently directed toward, it can be achieved that the basic patterns of warfare beaten are examined by continuous omnidirectional using the orbit and air weapon in 8 word course lines.It is such as 135 degree of the biggish angle of departure even more big, it supports aircraft to turn around to implement 8 shorter word course lines of course line in time, biggish maneuver warfare efficiency can be won.
Description
Technical field
The multitask aircraft technical field scouted and fought the invention belongs to aviation field especially has to examine and beats one use
Aircraft technology field is driven in manned aircraft, UAV system and the conjunction on way.
Background technique
Omnidirectional examines dozen integrated aircraft abbreviation omnidirectional and examines dozen aircraft, including unmanned plane and manned aircraft or other.Tradition
It examines and beats the weapon strike of integrated unmanned plane is how much weapon no matter to be hung, to preceding to mesh based on to the strike before flight to target
The occupy-place time for marking strike is fewer, is suitble to low-intensity confrontation on the battlefield or fight-terrorism warfare.Meanwhile tradition examines the scouting for making aircraft
Lower with strike efficiency, photoelectronic reconnaissance distance about 10km or so, round-the-clock operations be restricted, and lacks photoelectronic reconnaissance in addition and can
The servo-actuated technical method with strike；Tradition examine beat integrated unmanned plane weapon it is substantially plug-in under the wings of an airplane or under fuselage, influence nothing
Man-machine aeroperformance, this design scheme are suitable only for ceiling and speed and use than lower unmanned plane.
Applicant submit on November 30th, 2017 application application No. is 201711241305.1, invention and created name is
A kind of be disclosed in detail in the application documents for examining the control method and system of making integrated aircraft surround or omnidirectional examines and makes aircraft
Technological maheup, equally, applicant submits another innovation and creation of application, application No. is 201811107991.8, invention wound
It makes a kind of entitled omnidirectional and examines the transmission ammunition belt system for making aircraft, the technology of weapon transmission ammunition belt system is mainly proposed in content
Method, examining the technical solution beaten in omnidirectional does not include examining in this two parts of patent applications without reference to omnidirectional to aerial target
The design method for playing aircraft weapon hanger, does not introduce technology investigation and examining for radar-reconnaissance beats technical application, does not provide yet
The technical solution that air-to-surface multiple and different targets are scouted and hit simultaneously.Therefore, it is necessary to this two parts of patent applications
Involved in technical solution carry out further creative expansion and perfect, could constitute and air-to-surface omnidirectional be examined dozen and to more
The fairly perfect novel omnidirectional that target is hit simultaneously, which is examined, beats aircraft system, can further significantly improve omnidirectional and examine dozen aircraft
Fighting efficiency.
Summary of the invention
It is an object of the invention to propose that a kind of examine beats the design method and system of integrated aircraft, to overcome the prior art to deposit
Deficiency.
Detailed technology explanation:
Of the invention examines the design method for making integrated aircraft, is that will examine to beat integrated airplane design to introduce in addition to photoelectronic reconnaissance
Long-range and reconnaissance equipment round the clock including technology investigation and radar-reconnaissance, interacts that progress is comprehensive to beat with a variety of weapons
It hits；Course line is designed as can be used that 8 word course line orbits are aerial to one of specific direction or a group or ground sea mesh
The lasting strike of mark；Air weapon is designed as usually built-in in engine room inside.
The omnidirectional designed according to the method described above, which is examined, beats integrated aircraft system, including Flight Vehicle Structure, on Flight Vehicle Structure
The weapon carrier of installation, installs air weapon on weapon carrier, the scouting load installed on Flight Vehicle Structure and airborne system
System, and ground monitoring matched with airborne system station.
Flight Vehicle Structure is divided into fuselage compartment, head front deck, machine speedpak and machine back cabin.Design scheme can hold participation
Before the fuselage cabin structure of power power transmission is divided into, in, rear body, wing and empennage；Head front deck is connected to forebody course front end；
Machine speedpak is connected to the lower section of middle fuselage；Machine back cabin is connected to the top of middle fuselage.Machine speedpak is readily modified as other use
On the way, such as cargo compartment, pesticide cabin, target drone nacelle.
Weapon carrier is mountable on Flight Vehicle Structure, including head front deck, machine speedpak and machine back cabin and fuselage
Under the wing in cabin.
The design of weapon carrier includes: hanging rack structure, can install more pieces of weapons thereon, and can be layered installation, especially
All types of weapons are mixed and are installed；The radome fairing being mounted on hanging rack structure can install included see in radome fairing and take aim at irradiation
Device or electronic control unit；The hangers of air weapon is installed；The elevating mechanism that weapon carrier is connect with Flight Vehicle Structure；Electric-controlled box and with
Dynamic servo mechanism.Included see can be designed on weapon carrier and takes aim at illuminator and electronic control unit, and dual drive can be performed in weapon carrier
It is dynamic: target component being handed over into electronic control unit to servo-actuated lock onto target first is that receiving scouting load, then controls weapon carrier
Sight is taken aim at illuminator and is persistently tracked to target lock-on, and the double drive to weapon carrier is constituted；Second is that the included sight of weapon carrier is taken aim at
Illuminator and electronic control unit can independently guide driving weapon carrier surely to take aim at target following, realize multiple target tracking.
For weapon carrier on Flight Vehicle Structure in mount scheme, being typically designed is that weapon carrier is mounted on Flight Vehicle Structure
Immediate vicinity, or design the design scheme of a kind of adaptation air weapon transmitting and adjustable Flight Vehicle Structure center of gravity, or to a left side
The weapon of right front and back installation carries out transmitting management to guarantee gravity balance.Equally, wake flame caused by the transmitting to air weapon
Flame air deflector can be designed.
Air weapon is mounted on weapon carrier and is arranged in one or more positions of Flight Vehicle Structure, including before head
Under the wing of cabin, machine speedpak and machine back cabin and fuselage compartment；Three classes, which are matched, for weapon carrier is suitble to the main of theaomni-directional transmission
Air weapon, first is that can be with the emission type guided missile such as laser irradiation type or radar guidance type guided missile of the servo-actuated transmitting of weapon carrier, boat
Empty machine gun, second is that the electromagnetic jammer in the mountable cabin before the handpiece of antenna.
The design scheme at each position is: the mountable miniature missile of the upper space in cabin or electromagnetic jammer day before the handpiece
Line；In the inside and outside space of machine speedpak, mountable emission type guided missile, guidance or non-guided bomb, airborne machine gun and sky
Unmanned plane is thrown, wherein the weapon carrier with the servo-actuated servo mechanism of two dimension may be selected in installation airborne machine gun, in addition, machine speedpak
When weapon carrier is used for forward emitted, it can increase and select laser-guided or bookbinding coordinates of targets guided bomb, and launch
Type weapon；In the inside and outside space in machine back cabin, the weapon carrier of the servo-actuated servo mechanism of two dimension can be selected；In machine back cabin
Inner space, the combination of simplify the internal structure of an organization the i.e. guided missile and its firing box of Vertical Launch of installation weapon carrier structure may be selected,
By opening the cabin or rupture of membranes launches cabin；Weapon carrier, mountable and machine speedpak same type are connected under the wing of fuselage compartment
Air weapon.
Scout the optional O-E Payload of load；Skill detects load；Radar load；A kind of or three kinds combinations are therefrom selected to be mounted on winged
In row device structure.
Each control unit for scouting load all supports the control of aforementioned weapon carrier, that is, supports to a target or same
When multiple target omnidirectionals are hit and avoid hitting identical target.Wherein, O-E Payload, skill detects load and radar load
Signal processing and SERVO CONTROL effect control unit, connect respectively with the electric-controlled box of weapon carrier with cable, when each
After the locking parameter of selected target is passed to electric-controlled box by the control unit of scouting load, electric-controlled box presses the coordinate of selected target
Guidance directly drives weapon carrier alignment target and in servo-actuated emission state, waits pending airborne system instruction issue weapon；
Or guidance sight takes aim at illuminator and continues surely to take aim at the target following, control weapon carrier continues alignment target and in servo-actuated transmitting
State waits pending airborne system instruction issue weapon, and illuminator is taken aim in the sight on different weapon carriers and electronic control unit can
It is surely taken aim at and emission state independently to carry out continuing locking tracking to selected target, while to realize to multiple targets；Therefore,
A kind of relevant action for scouting load and electronic control unit, may be constructed the double drive to weapon carrier；Directly drive above and
Target information is all passed back the subsystem such as flight subsystem of airborne system by double drive process, then is thus distributed to ground
Monitoring station is completed to hit " people the is online " weapon delivery of target to be closed.
A kind of design scheme of step of transmitting of transmitting process is divided into: 1) being pressed by the flight subsystem of airborne system
According to predetermined transmitting process according to the received target information of ground monitoring station, " people is online " determines launching time and issues instruction concurrently
The electric-controlled box for being sent to weapon carrier executes transmitting, or according to the target information for scouting load, " people is offline " automatically generates transmitting
Instruction is transported to the electric-controlled box of weapon carrier and executes transmitting, so as to one or more targets, separately or concurrently independent omnidirectional
Transmitting strike；And necessary launching condition is set to avoid transmitting obstacle；2) by the electric-controlled box of weapon carrier according to target with
The information of track be sent to the flight subsystem of airborne system and be transmitted to ground monitoring station obtain " people is online " transmitting refer to
It enables and transmitting strike is controlled by electric-controlled box again；Or firing order is directly generated according to the predetermined transmitting criterion of electric-controlled box and executes hair
It penetrates；Necessary launching condition is also provided with to avoid transmitting obstacle.
The flight subsystem of airborne system is connect with the electric-controlled box for scouting load and weapon carrier by cable, structure
It is directly driven and the information of double drive and instruction connection at aforementioned.Flight subsystem connection weapon management subsystem with
The electric-controlled box for scouting load and weapon carrier is connected by cable, configuration information and instruction connection.
To the flight subsystem and navigation subsystem of airborne system, data-link subsystem is respectively as this is designed
Change:
1) for flight subsystem, no matter its original computer module is single redundancy system structure or redundance
System structure, this introduces new departure of flight management module+flight control modules Dual module redundant system structure, wherein
Both the design scheme of flight management module and flight control modules, the prefabricated function of flight manipulation and emergency disposal can be used
Warm back-up；Stress man-machine interface with flight management module is with auxiliary monitoring flight and the process management and monitoring of task execution
It is main；Stress flight manipulation with flight control modules and receive based on the regulation of flight management module instruction or parameter；Meanwhile it introducing
Cover the inspection software of identical airborne sensor, jointly construct two modules be in communication with each other+inspection software auxiliary judgement it is remaining
Spend system structure.
2) navigation data information is introduced flight management for navigation subsystem by the change for adapting to flight subsystem
In module and flight control modules, and depth coupling application is carried out to navigation data information in flight management module；To shorten
Navigation and the resolving time delay of flight control data improve calculation accuracy, can be by high performance navigational computer as flight management mould
Block is applied.
3) to airborne data link, using parallel data chain, it can divide the work or work alternatively with the parallel data-link of toilet；Branch
Hold a station multimachine or a machine multistation Universal Data Link and the time-division or frequency division coding support a station multimachine data-link.
The parallel data chain of ground monitoring station installation and data-link subsystem phase one used by the aforementioned change of airborne system
It causes；Operation interface supports manual command's manipulation, or the process monitoring that authorization airborne system " people is offline " automatically controls to control with emergency
The application of a station multimachine or a machine multistation is supported in the operation of system；What the configurable non-military operations for supporting daily workout used
ADS-B ground base station.
The above design scheme is applied to UAV system, to piloted vehicle by adding repacking weapon carrier and fitting
Airborne system and become Special Aircraft.Suitable for army and People's Armed Police, the anti-terrorism or operation of land and sea border defense.
The present invention proposes a kind of design side for being suitble to implement to scout and hit to aircraft peripheral space or comprehensive target
Method and system, in addition to photoelectronic reconnaissance, the investigation of introducing technology and radar-reconnaissance etc. are mutual with a variety of weapons remotely with reconnaissance equipment round the clock
It is dynamic to carry out comprehensive strike.Especially aircraft can be aerial to one of specific direction or a group using 8 word course line orbits
Or ground sea-surface target is persistently hit, and can hit multiple and different targets simultaneously, is suitble to high intensity confrontation on the battlefield, is also suitble to general strong
Spend confrontation on the battlefield or fight-terrorism warfare.Air weapon is usually built-in inside machine speedpak, and the influence to flying quality reduces.
Detailed description of the invention
Fig. 1 is the weapon carrier diagram for horizontally rotating servo-actuated servo mechanism, single layer guided missile, front view；
Fig. 2 is the weapon carrier diagram for horizontally rotating servo-actuated servo mechanism, single layer guided missile, attached view；
Fig. 3 is the weapon carrier diagram for horizontally rotating servo-actuated servo mechanism, the double-deck rail guided missile, front view；
Fig. 4 is the weapon carrier diagram for horizontally rotating servo-actuated servo mechanism, the double-deck rail guided missile, attached view；
Fig. 5 is the weapon carrier diagram for horizontally rotating horizontal servo mechanism, double-layer barrel guided missile, front view；
Fig. 6 is the weapon carrier diagram for horizontally rotating horizontal servo mechanism, double-layer barrel guided missile, attached view；
Fig. 7 is that the weapon carrier of the servo-actuated servo mechanism of horizontal and pitch rotation illustrates, front view, (pitch rotation mechanism
Shaft is near weapon carrier center of gravity section)；
Fig. 8 is that the weapon carrier of the servo-actuated servo mechanism of horizontal and pitch rotation illustrates, attached view, (pitch rotation mechanism
Shaft is near weapon carrier center of gravity section)；
Fig. 9 is that the weapon carrier of the servo-actuated servo mechanism of horizontal and pitch rotation illustrates, front view, (pitch rotation mechanism
Front end of the shaft in weapon carrier center of gravity section)；
Figure 10 is that the weapon carrier of the servo-actuated servo mechanism of horizontal and pitch rotation illustrates, attached view, (pitch rotation mechanism
Front end of the shaft in weapon carrier center of gravity section)；
Figure 11 is the installation diagram of the weapon carrier on aircraft wing；
Figure 12 is the position of centre of gravity diagram for installing multiple weapon carriers out of my cabin under midwing monoplane ventral；
Figure 13 is upper and lower weapon carrier/cabin of haveing hair hang down/O-E Payload installation site diagram；
Figure 14 is that each position of Flight Vehicle Structure divides diagram.
The label in accompanying drawing is: 1- elevating mechanism, 2- is servo-actuated servo mechanism, and 3- horizontally rotates hanger and hanging rack structure, 4-
Illuminator, 7- pitch rotation mechanism and hanging rack structure, 8- electronic control unit, 9- pitch rotation are taken aim in radome fairing, 5- air weapon, 6- sight
Mechanism driving hinge, 10- weapon carrier transmission chain, 11- transmission chain control mechanism, the machine back cabin 12- and weapon carrier, 13- fuselage
Cabin, 14- have hair hang down guided missile and cabin of haveing hair hang down, 15- O-E Payload, 16- weapon carrier, 17- flame air deflector, 18- hangers, 19- electricity
Control box, 20- head front deck, 21- machine back cabin, cabin under 22- fuselage, 23- wing, 24- empennage.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation " " is set
Be equipped with ", " be arranged/connect ", " connection " etc., shall be understood in a broad sense, such as " connection ", may be a fixed connection, be also possible to removable
Connection is unloaded, or is integrally connected；It can be mechanical connection, be also possible to be electrically connected；It can be directly connected, it can also be in
Between medium be indirectly connected, can be the connection inside two elements.It for the ordinary skill in the art, can be specific
Situation understands the concrete meaning of above-mentioned term in the present invention.
The embodiment of the present invention:
As shown in figures 1-13: the design method for making integrated aircraft is examined by a kind of omnidirectional and system includes Flight Vehicle Structure；Flying
The weapon carrier 16 installed in row device structure, the air weapon 5 installed on weapon carrier 16, is installed on Flight Vehicle Structure
Scout load and airborne system, and the ground monitoring station being adapted to airborne system.Airborne system is pacified on Flight Vehicle Structure
Other function systems in addition to weapon carrier 16 and air weapon 5 and other than scouting load of dress, including but not limited to such as lead
Boat and flight subsystem, sensor subsystem, data-link subsystem, power subsystem.
Flight Vehicle Structure is divided into fuselage compartment 13, head front deck, machine speedpak and machine back cabin.Design scheme can will participate in
13 structure of fuselage compartment of load power transmission middle rear body, wing and empennage before being divided into, wherein preceding middle rear body structure can be set by their entirety
Meter, middle fuselage include fuselage compartment 13, machine speedpak and machine back cabin, can be collectively referred to as fuselage compartment 13.The main molecules system of airborne system
System is mounted on fuselage compartment 13, and the layout designs of wing meet the installation of weapon carrier 16 and the transmitting of air weapon 5 subtracts as far as possible
Few structural member blocks；Head front deck is connected to forebody course front end, and reconnaissance equipment uses semi-buried installation head front deck
It is interior, it is downwardly projected blocking for the transmitting of air weapon 5 to machine speedpak to reduce, the upper space in cabin can carry additionally machine before the handpiece
Carry weapon 5；The lower section of machine speedpak middle rear body before being connected to, does not undertake the load power transmission of fuselage compartment 13, in design with side
Just change structure space, be mainly used for that weapon carrier 16 and rail are installed and cartridge type class is launched a guided missile, guidance and coordinate class are launched
Bomb and skill, which are detectd, scouts load with radar class；Machine back cabin be connected to before in rear body top, do not undertake in design or
Part undertakes the load power transmission of fuselage compartment 13, reserves suitable space and is mainly used for installing the weapon carrier 16 of two-dimensional rotary and prevent
Empty weapon installs have hair hang down guided missile and cabin 14 of haveing hair hang down.Machine speedpak is readily modified as other purposes, such as cargo compartment, pesticide cabin, target drone
Nacelle.
Weapon carrier 16 is mounted on Flight Vehicle Structure, including head front deck, machine speedpak and machine back cabin and fuselage
Under the wing in cabin 13.
The design of weapon carrier 16 includes:
Hanging rack structure is mainly manufactured using light material and structure, can install more pieces of weapons thereon, and can be layered installation
Especially all types of weapons are mixed and are installed, it is quasi- if irradiation type or conductivity type processed load in mixture such as more pieces of single layer or double-deck more pieces of the installation
The option of weapon delivery is instructed by the weapon management subsystem of airborne system and is completed；
With the radome fairing 4 of hanging rack structure cooperation, included see can be installed in radome fairing 4 and take aim at illuminator 6 or electronic control unit
8；Shown in attached drawing 7-10.
The weapon hangers 18 for installing air weapon 5, may be designed as the structure of quick despatch；
The elevating mechanism 1 that weapon carrier 16 is connect with Flight Vehicle Structure can drive 16 phase of weapon carrier by motor drive mechanism
Horizontal vertical lifting made to the plane of 13 horizontal datum of fuselage compartment, vertical lift function can be used for the collection of weapon carrier 16 with
Reduce aerodynamic drag, it can also be used to aerial to launch weapon carrier 16；1 design scheme of optional elevating mechanism is relatively more, can be used
Parallelogram adds power cylinder mechanism, electric cylinders mobile mechanism, electric gear worm and screw mechanism, liquid electric moveable mechanism, electronic steel
Restrict mechanism；Shown in attached drawing 1-2.
Electric-controlled box 19 and the order parameter and the servo-actuated servo of instruction motor structure control that scouting load is received by electric-controlled box 19
Mechanism 2 drives weapon carrier 16 to make horizontal angle or pitch angle rotation, and horizontal angle rotation is opposite 13 horizontal datum of fuselage compartment
Plane makees parallel 360 degree rotation, provides the azimuth of 5 theaomni-directional transmission of air weapon, is turned by the level being connected on elevating mechanism 1
Motivation structure 2 is executed with hanger 3 is horizontally rotated；Pitch angle rotation is that the plane of opposite 13 horizontal datum of fuselage compartment makees pitch angle turn
It is dynamic, about 45 degree upward or downward of general pitch range, turned by being mounted on the pitching horizontally rotated on hanger and hanging rack structure 3
Motivation structure and hanging rack structure 7 execute；The design scheme of pitch rotation mechanism and hanging rack structure 7 can be divided into two kinds, first is that pitching turns
Moving axis is arranged near 16 center of gravity section of weapon carrier, drives design scheme such as motor, shown in attached drawing 7-8, second is that pitching turns
Moving axis is arranged in the front end in 16 center of gravity section of weapon carrier, design scheme such as electric cylinders is driven, shown in attached drawing 9-10；It is optional servo-actuated
The driving design scheme of servo mechanism is relatively more, can be used all types of motors, rack-and-pinion chain, electric cylinders or the driving of liquid voltage
Rocker-arm, electromagnetic drive；
Included see can be designed on weapon carrier 16 to take aim at illuminator 6 and carry out photoelectric observing and take aim to take aim at the sight of the auxiliary of laser irradiation
System, and the mating controllable electronic control unit 8 that target following sight is taken aim at.Shown in attached drawing 7-10.
Therefore, two kinds of driving method alignment target weapon deliveries can be performed in weapon carrier 16: first is that double drive mode, i.e.,
Receive to scout load and target component is handed over into electronic control unit 8 be servo-actuated lock onto target, then controls the sight of weapon carrier 16 and take aim at irradiation
Device 6 persistently tracks target lock-on, constitutes the double drive alignment target to weapon carrier 16；Second is that direct drive mode, i.e.,
Target component is handed over to electronic control unit 8 and is servo-actuated alignment target by receiving scouting load, or is taken aim at by the included sight of weapon carrier 16
Illuminator 6 and electronic control unit 8 can independently guide driving weapon carrier 16 surely to take aim at simultaneously alignment target to target following.
Weapon carrier 16 in mount scheme, will control after air weapon 5 emits to Flight Vehicle Structure on Flight Vehicle Structure
Mass centre changing, be typically designed be weapon carrier 16 is mounted on the immediate vicinity of Flight Vehicle Structure (1) so as not to by or reduce
Mass centre changing after the transmitting of air weapon 5；Attached drawing 12 designs a kind of transmitting of adaptation air weapon 5 and adjusts Flight Vehicle Structure center of gravity
Design scheme: the center of gravity of the more than one piece weapon carrier 16 of machine speedpak installation with weight after arm discharge change and can it is automatic before
It is moved afterwards to adjust the center of gravity of airplane, the movement of 16 center of gravity of weapon carrier is designed as individually or what is interconnected automatically moves mode；
To under 13 wing of fuselage compartment install weapon carrier 16 on air weapon 5 shooting sequence and quantity by gravity balance requirement into
Row selects bullet transmitting management；Or the weapon carrier 16 after transmitting air weapon 5 can be launched by the principle driver of gravity balance, it can
Mitigate weight or reduces aerodynamic drag.Equally, wake flame caused by the transmitting of air weapon 5 can design the solution of flame air deflector 17
Certainly, the installation site of flame air deflector 17 is shown in that attached drawing 13 illustrates.In short, installation of the weapon carrier 16 on Flight Vehicle Structure, is answered
Meet periphery intervisibility, gravity balance impacts lossless, the harmless flight of wake flame and lift-off technology requirement.
Air weapon 5 is mounted on weapon carrier 16 and can be arranged in flight (by handling characteristics) together with weapon carrier 16
Under the wing of one or more positions of device structure, including head front deck, machine speedpak and machine back cabin and fuselage compartment 13；
The main air weapon 5 that three classes are suitble to theaomni-directional transmission is matched for weapon carrier 16, first is that can be with the servo-actuated transmitting of weapon carrier 16
Irradiation type or conductivity type guided missile processed, with the airborne machine gun that sight is taken aim at, laser irradiation device, antiradiation missile or sky penetrate unmanned plane, second is that military
The i.e. Vertical-launched Missile that simplifies the internal structure of an organization of device hanging rack structure alerts display shell or infrared flare, third is that antenna is mountable in machine
Head before to electromagnetic jammer.
The design scheme at each position is, before the handpiece transmitting range 2-5km in the mountable air weapon 5 of the upper space in cabin
Miniature missile or electromagnetic jammer antenna；Rail in the inside and outside space of machine speedpak, mountable air weapon 5
Formula or the guided missile of wound packages transmitting, guidance or non-guided bomb, airborne machine gun and air-drop unmanned plane, wherein can for installation airborne machine gun
It selects the weapon carrier 16 with the servo-actuated servo mechanism 2 of two dimension and the reduction aerodynamic drag of radome fairing 4 can be designed, in addition, under ventral
When the weapon carrier 16 in cabin is used for forward emitted, it can increase and select laser-guided or bookbinding coordinates of targets guided bomb, with
And dispensing type weapon；In the inside and outside space in machine back cabin, the weapon carrier of the servo-actuated servo mechanism 2 of two dimension can be preferentially selected
16 and select installation barreled guided missile or airborne machine gun execute level orientation rotation and certain pitch angle theaomni-directional transmission, for protrusion
The two-dimentional weapon carrier 16 or air weapon 5 in machine back cabin can be used radome fairing 4 and reduce aerodynamic drag；It is empty inside machine back cabin
Between, the combination of the guided missile and its firing box of installation Vertical Launch also may be selected, open the cabin by opening combination hatch door, or puncture anti-
Film that dirt discharges water and rupture of membranes, and then cabin of launching a guided missile out, the air defence missile transmitting range for Small object are not less than 2km；?
Weapon carrier 16, the mountable air weapon 5 with machine speedpak same type are connected under the wing of fuselage compartment 13.
The optional O-E Payload 15 of load is scouted, by the mechanical movement of photoelectricity servo mechanism, recognition and tracking lock onto target is matched
Laser ranging and irradiation are closed, target component is generated；Skill detects load, passes through the active or passive detection of antenna and the place of echo signal
Reason generates target component；Radar load generates target component by the direction of antenna to target active detection and signal processing；
A kind of or three kinds combinations are therefrom selected to be mounted on Flight Vehicle Structure；The other types for being suitble to install in Flight Vehicle Structure can be chosen to install
Scouting load.
Each control unit for scouting load all supports the control of weapon carrier 16 above-mentioned, (supports to a mesh
Mark or multiple target omnidirectionals are hit simultaneously and avoid hitting identical target), wherein the signal processing of O-E Payload 15 with watch
The photo-electric control unit of control is taken, skill detects the signal processing of load and servo-controlled skill detects control unit, the letter of radar load
Number processing with servo-controlled radar control unit, connect respectively with 19 cable of electric-controlled box of weapon carrier 16, scout load
After the locking parameter of target selection is passed to electric-controlled box 19 by each control unit, electric-controlled box 19 can directly drive weapon extension
Frame 16 is servo-actuated alignment target and is in emission state, or takes aim at illuminator 6 two times drivings by sight and continue to be in target following control
Emission state；And target information is passed to the subsystem such as flight subsystem of airborne system back, then be thus distributed to ground prison
Control station；Wherein, O-E Payload 15 and skill detect load can the pitch angle to lock onto target give electric-controlled box 19 handover parameter information, from
And transmitting strike can be carried out to the extraterrestrial target of 13 horizontal datum above and below of fuselage compartment, radar load is only to locking mesh
The target angle of depression gives electric-controlled box 19 handover parameter information, thus only sends out 13 horizontal datum of fuselage compartment extraterrestrial target below
Penetrate strike；For the extraterrestrial target near 13 horizontal datum of fuselage compartment can control Flight Vehicle Structure carry out surrounding target or from
The light grade for opening target spirals to carry out transmitting strike.
A kind of design of transmitting process is divided into: 1) by the flight subsystem of airborne system according to predetermined transmitting process
According to the received target information of ground monitoring station, " people is online " determines launching time and issues to instruct and be sent to weapon carrier 16
Electric-controlled box 19 execute transmitting, or according to the target information for scouting load, " people is offline " automatically generates firing order and is transported to
The electric-controlled box 19 of weapon carrier 16 executes transmitting, so as to which to one or more targets, separately or concurrently independent theaomni-directional transmission is beaten
It hits；Wherein, necessary launching condition is set to avoid transmitting obstacle, such as the vertical fin or undercarriage of fuselage compartment 13；2) it is hung by weapon
The electric-controlled box 19 of frame 16 is according to the flight subsystem for being sent to airborne system to the information of target following and is transmitted to ground prison
The firing order that control station obtains " people is online " controls transmitting strike by electric-controlled box again；Or according to the pre- of airborne system or electric-controlled box 19
Surely transmitting criterion directly generates firing order and executes transmitting；Wherein, necessary launching condition is also provided with to avoid transmitting obstacle.
Scout load and electric-controlled box 19 directly drive and double drive, especially skill detect the offer of load and radar load
Double drive, change it is traditional examine the strike mode that the integrated single forward direction of unmanned plane aims at transmitting of beating, provide abundant
It is suitble to the strike mode of theaomni-directional transmission.
The electric-controlled box 19 of load and weapon carrier 16 is scouted by the flight subsystem cable connection of airborne system,
It constitutes aforementioned directly drive to connect with the information of double drive and instruction, target position or orientation is sent to weapon carrier 16 and carried out
Digital guiding.The electric-controlled box of load and weapon carrier 16 is scouted by the weapon management subsystem cable connection in airborne system
19, configuration information and instruction connect, and are selected and appointed to every weapon and carry out powering on lower electricity and transmitting management, and beaten for weapon
Hit the position coordinates or target pattern of bookbinding target.
To the flight subsystem and navigation subsystem of airborne system, data-link subsystem is respectively as this is designed
Change, other molecular systems are then adjusted according to the principle being adapted to these molecular system interfaces, the constant still edge of interface
With.
1) for flight subsystem, no matter its original computer module is single redundancy system structure or redundance
System structure, this introduces new departure of flight management module+flight control modules Dual module redundant system structure, wherein
Stressing man-machine interface with flight management module and assisting in flying controls, including navigation warm back-up, course line is calculated binds with new course line,
Flying area limitation, the monitoring of course line navigation attitude and regulation and task execution, including course line task switch, payload interface adaptation with
Switch, loading area, load data distribution, weapon manipulation instruction simultaneously support the process management of double drive and monitoring is
It is main；Stress flight manipulation with flight control modules and receive based on the regulation of flight management module instruction or parameter；Meanwhile it introducing
Cover the inspection software of identical airborne sensor, jointly construct two modules be in communication with each other+inspection software auxiliary judgement it is remaining
Spend system structure.
2) navigation data information is introduced flight management for navigation subsystem by the change for adapting to flight subsystem
In module and flight control modules, and depth coupling application is carried out to navigation data information in flight management module；To shorten
Navigation and the resolving time delay of flight control data improve calculation accuracy, can be by high performance navigational computer as flight management mould
Block is applied.
3) one group of branch is increased using the original long-range sighting distance of one group of unmanned plane and over the horizon data-link to airborne data link
The short range sighting distance broadband ad hoc network Universal Data Link or 4/5G communication chain for holding a station multimachine or a machine multistation, may be selected to be further added by one
Group laser communication chain, by designing a kind of parallel data chain that switchgear composition can divide the work or work alternatively；And the time-division or
Frequency division coding supports the data-link of a station multimachine.Ground monitoring station is also accordingly changed.So-called long-range finger is greater than 100km, short range
Refer to about 30km.
It, can for the former technical solution of the data-link subsystem of flight subsystem and navigation subsystem and narrowband
It can arrangement as one kind.
The parallel data chain of ground monitoring station installation is consistent with the data-link subsystem that the aforementioned change of airborne system uses,
And pass through radio connection；Operation interface is supported to manipulate the manual command of weapon carrier 16 and air weapon 5, or issues authorization
Airborne system people automatically generates the operation of the process monitoring and emergency flight control of control instruction offline, supports a station multimachine or a machine more
The application stood；The ADS-B ground base station that the configurable non-military operations for supporting daily workout use.
Outstanding feature of the present invention is to realize the theaomni-directional transmission of emission type weapon by installing weapon carrier 16.It examines and makes aircraft
Target is persistently directed toward using the orbit in 8 word course lines and air weapon 5, it can be achieved that the basic work beaten is examined by continuous omnidirectional
War pattern.It is such as 135 degree of the biggish angle of departure even more big, it supports aircraft to turn around to implement 8 shorter word course lines of course line in time, can win
Obtain biggish maneuver warfare efficiency.
The present invention has the advantage that weapon loads in mixture: loading in mixture for air weapon 5 is difficult point and bright spot.First is that ground-to-air
Weapon loads in mixture, second is that the weapon of cartridge type transmitting emitted with non-cartridge type loads in mixture, third is that the weapon of similar length loads in mixture.
Case study on implementation 1:
A kind of omnidirectional, which is examined, beats integrated UAV system, as shown in figure 12, and machine speedpak only install before and after 2 weapon carriers
16.2 sets of weapon carriers 16 totally 4 × 2 pieces of laser-guided bombs, effective range 12km are installed before and after machine speedpak；1 frame of centre installation
Radiation protection unmanned plane；1 set of weapon carrier 16 and 4 piece Minitype infrared seeker is installed in machine back cabin, and effective range 5km is (in figure
Head front deck weapon and machine are carried on the back combination of haveing hair hang down and are ignored), weapon weight about 320kg；Maximum take-off weight 1800kg, flying speed is about
180km/h.Head front deck installs a set of O-E Payload 15, and 1 set of skill of installation detects load (not shown) in fuselage compartment 13.Nobody
Cruise-out altitude 5000km is flat after machine takes off flies, and skill detects load first discovery target bearing 2 o'clock direction, and distance 200km is preliminary to know
It is not armored motorcade and command post, is traveling at training.1 hour approaches target.It is known that nearby there is command post in armored motorcade,
Rear about 400km has other side airport.Identified confirmation, target is 8 armored personnel carrier teams, and identifies aerial accompanying flying miniature self-service
Machine is more gyroplanes, about 3 framves, flying height 500m.Ground monitoring station determines unmanned plane in the safe distance away from fleet 15km, master
Dynamic flight positive about 20 degree of side orientation in front of fleet, avoids the multidirectional attack of surface-to-air ballistic missile.Unmanned plane lifting height simultaneously
To 6000m, 8 letter disks, which revolve horizontal distance target about 8km, initiates strike.O-E Payload 15 locks front truck, the preposition weapon of machine speedpak
The 1st piece of laser-guided bomb of servo-actuated transmitting of hanger 16 is simultaneously surely taken aim at device tracking radiation by this hanger, meanwhile, O-E Payload 15 locks vehicle
Team's intermediate car also transfers machine speedpak postposition weapon carrier 16 to and surely takes aim at device tracking radiation by this hanger.First-round hit, vehicle
Team's evacuation, Optic-electronic Stabilization Sight device persistently lock wherein 1 vehicle and continue irradiation strike.O-E Payload 15 is locked again from scattered fleet
Fixed 1 vehicle tracking.2nd vehicle is hit, and command post's goal activities frequently detect excitation equivalence by skill, emits radiation protection unmanned plane.
For about 5 minutes in the rotation of 8 letter disks, 5 vehicles, the recession of remaining vehicle are hit one by one.Command post's signal weakens, but does not have for recession
Approach scouting assessment.
If to strike before traditional, it is contemplated that attack was more than 5 minutes every time.Period, the more people of other side leave panzer and use shoulder
Boosted missile hits this unmanned plane, and distance and height ensure that the safety of unmanned plane.The drone flying height gone out before other side is lower,
The machine back weapon carrier 16 of unmanned plane can not aim at.Due to target is smaller and threaten less, front deck O-E Payload 15 also not from
It opens panzer and specially it is aimed at, strike of not launching a guided missile to it.In operation, skill is detectd the load discovery other side someone that takes off and is driven
It sails operational aircraft and estimates 2 framves, it is contemplated that reach scene after 30 minutes.Unmanned plane withdraws from battlefield and makes a return voyage, and the our surface-to-air ballistic missile that flies back is protected
Protect airspace.Avoid unmanned plane may pursue and attack panzer by shoulder-fired missiles take this opportunity low coverage attack.
Case study on implementation 2:
With the unmanned plane of case study on implementation 1, subtracts dress weapon load and install fuel oil additional, cruise duration is for 24 hours.Machine speedpak is reequiped micro-
Light video, the mapping load of laser camera and digital camera combination, provides maritime search and rescue application.By machine speedpak space, add
Fill the weight such as several life jackets and lifesaving smoke generator about 200kg.The merchant ship position and letter are received by UAV system AIS system
Breath, height 2000m is orbitinged after the machine flies to target area, confirms 1 freighter of suspending.By understand the freighter oil leakage fault without
Method navigation, not yet generation critical conditions.Unmanned plane, which takes pictures to freighter, collects evidence and sends back to bank base headquarter, and completion task is maked a return voyage, separately
Rescue is gone to by other ships.Such as Hainan rescue situations, unmanned plane will approach the extreme low-altitude dispensing lifesaving appliance of target.
Although the present invention is described in detail referring to the foregoing embodiments, for those skilled in the art,
It is still possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is carried out etc.
With replacement, all within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in this
Within the protection scope of invention.
Claims (8)
1. a kind of examine the design method for making integrated aircraft, it is characterised in that: will examine and beat integrated airplane design is in addition to photoelectronic reconnaissance
The long-range and reconnaissance equipment round the clock including including technology investigation and radar-reconnaissance is introduced, it is comprehensive that progress is interacted with a variety of weapons
Strike；Course line is designed as using 8 word course line orbits aerial to one of specific direction or a group or ground sea mesh
The lasting strike of mark；Air weapon (5) is designed as usually built-in in engine room inside.
2. one kind, which is examined, beats integrated aircraft system, it is characterised in that: including Flight Vehicle Structure, the weapon installed on Flight Vehicle Structure
Hanger (16), the air weapon (5) installed on weapon carrier (16) are equipped on Flight Vehicle Structure and scout load and airborne
System, and ground monitoring matched with airborne system station.
3. according to claim 2 examine beats integrated aircraft system, it is characterised in that: Flight Vehicle Structure is divided into fuselage compartment
(13), head front deck, machine speedpak and machine back cabin；Machine after in front of fuselage compartment (13) structure for participating in load power transmission is divided into
Body, wing and empennage；Head front deck is connected to forebody course front end；The lower section of machine speedpak middle rear body before being connected to；
The top of machine back cabin middle rear body before being connected to.
4. according to claim 2 examine beats integrated aircraft system, it is characterised in that: weapon carrier (16) is mounted on aircraft
In structure, installation site includes under the wing of head front deck, machine speedpak and machine back cabin and fuselage compartment (13)；
Weapon carrier (16) includes: hanging rack structure installs more pieces of weapons thereon, and is layered installation or mixes all types of weapons and pacify
Dress；The radome fairing (4) being mounted on hanging rack structure, included see of installation takes aim at illuminator (6) or electronic control unit in radome fairing (4)
(8)；The hangers (18) of air weapon (5) is installed；The elevating mechanism (1) that weapon carrier (16) is connect with Flight Vehicle Structure；It is automatically controlled
Box (19) and servo-actuated servo mechanism (2).
5. according to claim 2 examine beats integrated aircraft system, it is characterised in that: air weapon (5) is mounted on weapon extension
On frame (16) and it is arranged in one or more positions of Flight Vehicle Structure, including head front deck, machine speedpak and machine back cabin, with
And under the wing of fuselage compartment (13)；The air weapon (5) that three classes are suitble to theaomni-directional transmission is matched for weapon carrier (16), first is that can be with
With emission type guided missile such as laser irradiation type or radar guidance type guided missile or airborne machine gun of weapon carrier (16) servo-actuated transmitting, two
Be antenna may be mounted at before head to miniature missile or electromagnetic jammer；
The design scheme at each position is: the upper space installation miniature missile or electromagnetic jammer antenna in cabin before the handpiece；In machine
Emission type guided missile, guidance or non-guided bomb, airborne machine gun and air-drop unmanned plane are installed in the inside and outside space of speedpak,
Wherein the selection of installation airborne machine gun has the weapon carrier (16) of two dimension servo-actuated servo mechanism (2), in addition, the weapon of machine speedpak
When hanger (16) is used for forward emitted, increases and select laser irradiation or bookbinding coordinates of targets guided bomb and dispensing type
Weapon；In the inside and outside space in machine back cabin, the weapon carrier (16) of two dimension servo-actuated servo mechanism (2) is selected；It is carried on the back in machine
The group of simplify the internal structure of an organization the i.e. guided missile and its firing box of Vertical Launch of installation weapon carrier (16) may be selected in the inner space of upper-deck cabin
It closes, by opening the cabin or rupture of membranes launches cabin；Weapon carrier (16) are connected under the wing of fuselage compartment (13), installation and machine speedpak
The air weapon (5) of same type.
6. according to claim 2 examine beats integrated aircraft system, it is characterised in that: the scouting load selects O-E Payload
(15)；Skill detects load；Radar load；A kind of or three kinds combinations are therefrom selected to be mounted on Flight Vehicle Structure；The scouting load
Each control unit all support to the servo antrol of weapon carrier (16) and be directed toward selected target；Wherein, O-E Payload
(15), skill detect load and radar load signal processing and SERVO CONTROL effect control unit, respectively with weapon carrier
(16) electric-controlled box (19) is connected with cable, when the control unit that each scouts load passes the locking parameter of selected target
After passing electric-controlled box (19), electric-controlled box (19) directly drives weapon carrier (16) alignment target by the guidance of selected coordinates of targets；Or
Person's guidance sight takes aim at illuminator (6) and continues surely to take aim at the target following, and the lasting alignment target of control weapon carrier (16), which is in, to be servo-actuated
Emission state；And illuminator (6) is taken aim in the sight on different weapon carriers (16) and electronic control unit (8) can be independent to selected target
It carries out continuing locking tracking, surely be taken aim at and emission state while to realize to multiple targets；Therefore, a kind of scouting load and electricity
The relevant action for controlling unit (8), may be constructed the double drive to weapon carrier (16)；It directly drives above and double drive mistake
Target information is all passed back the subsystem such as flight subsystem of airborne system by journey, then is thus distributed to ground monitoring station, from
And it is closed and completes to hit the online weapon delivery of the people of target.
7. according to claim 2 examine beats integrated aircraft system, it is characterised in that: the flight subsystem of airborne system
It is connect with the electric-controlled box (19) for scouting load and weapon carrier (16) by cable, constitutes the letter directly driven with double drive
Breath and instruction connection；The weapon management subsystem of flight subsystem connection and the electricity for scouting load and weapon carrier (16)
It controls box (19) to connect by cable, configuration information and instruction connection.
8. according to claim 2 examine beats integrated aircraft system, it is characterised in that: the parallel data of ground monitoring station installation
Chain is consistent with the data-link subsystem that airborne system uses；Operation interface supports manual command's manipulation, or authorization airborne system
The operation of process monitoring and emergency flight control that people automatically controls offline, supports the application of a station multimachine or a machine multistation；Configuration branch
Hold the ADS-B ground base station that the non-military operations of daily workout use.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111489610A (en) * | 2020-05-06 | 2020-08-04 | 西安爱生技术集团公司 | Anti-radiation unmanned aerial vehicle simulation training system |
| CN111750741A (en) * | 2020-06-17 | 2020-10-09 | 江西洪都航空工业集团有限责任公司 | Distributed plug-in management system of training machine |
| CN112114668A (en) * | 2020-09-02 | 2020-12-22 | 北京捷安申谋军工科技有限公司 | AR individual soldier accompanying reconnaissance unmanned aerial vehicle system based on digital twins and reconnaissance method thereof |
| CN113247262A (en) * | 2021-07-05 | 2021-08-13 | 天津天羿科技有限公司 | Multipurpose aircraft |
| CN113602499A (en) * | 2021-09-15 | 2021-11-05 | 尚之灏 | Multipurpose attack and transportation integrated aircraft |
| CN113985926A (en) * | 2021-10-22 | 2022-01-28 | 航天科工通信技术研究院有限责任公司 | Unmanned aerial vehicle guidance missile attack system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107261479A (en) * | 2017-07-24 | 2017-10-20 | 陈建生 | True man's military game system |
| CN107792373A (en) * | 2017-11-01 | 2018-03-13 | 陶文英 | A kind of aircraft reclaims the method and its system of unmanned plane in the air |
| CN107985605A (en) * | 2017-11-30 | 2018-05-04 | 陶文英 | It is a kind of to surround the control method and system examined and make integral aircraft |
| CN109387113A (en) * | 2018-09-21 | 2019-02-26 | 陶文英 | The transmission ammunition belt system of dozen aircraft is examined by a kind of omnidirectional |
| CN210364404U (en) * | 2019-07-29 | 2020-04-21 | 陶文英 | Investigation and beating integrated airplane |
-
2019
- 2019-07-29 CN CN201910688211.1A patent/CN110329515A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107261479A (en) * | 2017-07-24 | 2017-10-20 | 陈建生 | True man's military game system |
| CN107792373A (en) * | 2017-11-01 | 2018-03-13 | 陶文英 | A kind of aircraft reclaims the method and its system of unmanned plane in the air |
| CN107985605A (en) * | 2017-11-30 | 2018-05-04 | 陶文英 | It is a kind of to surround the control method and system examined and make integral aircraft |
| CN109387113A (en) * | 2018-09-21 | 2019-02-26 | 陶文英 | The transmission ammunition belt system of dozen aircraft is examined by a kind of omnidirectional |
| CN210364404U (en) * | 2019-07-29 | 2020-04-21 | 陶文英 | Investigation and beating integrated airplane |
Non-Patent Citations (4)
| Title |
|---|
| 任宏光;刘颖;: "无人机侦察打击一体化武器系统发展", 飞航导弹, no. 06, pages 49 - 51 * |
| 刘洋;李一波;王扬扬;: "从"捕食者"看高空长航时察打一体化无人机的特点", 国际航空, no. 12, pages 28 - 30 * |
| 吴涛等: "《天行"捕食者"》", 《现代武器》, pages 14 - 19 * |
| 欧阳平等: "《捕食者系列无人机及其武器配置》", 《教练机》, pages 34 - 37 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111489610A (en) * | 2020-05-06 | 2020-08-04 | 西安爱生技术集团公司 | Anti-radiation unmanned aerial vehicle simulation training system |
| CN111750741A (en) * | 2020-06-17 | 2020-10-09 | 江西洪都航空工业集团有限责任公司 | Distributed plug-in management system of training machine |
| CN112114668A (en) * | 2020-09-02 | 2020-12-22 | 北京捷安申谋军工科技有限公司 | AR individual soldier accompanying reconnaissance unmanned aerial vehicle system based on digital twins and reconnaissance method thereof |
| CN112114668B (en) * | 2020-09-02 | 2024-04-19 | 北京捷安申谋科技有限公司 | Digital twinning-based AR individual soldier accompanying reconnaissance unmanned aerial vehicle system and reconnaissance method thereof |
| CN113247262A (en) * | 2021-07-05 | 2021-08-13 | 天津天羿科技有限公司 | Multipurpose aircraft |
| CN113247262B (en) * | 2021-07-05 | 2021-09-28 | 天津天羿科技有限公司 | Multipurpose aircraft |
| CN113602499A (en) * | 2021-09-15 | 2021-11-05 | 尚之灏 | Multipurpose attack and transportation integrated aircraft |
| CN113602499B (en) * | 2021-09-15 | 2023-09-19 | 尚之灏 | Multipurpose attack transportation integrated aircraft |
| CN113985926A (en) * | 2021-10-22 | 2022-01-28 | 航天科工通信技术研究院有限责任公司 | Unmanned aerial vehicle guidance missile attack system |
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