CN205396525U - Many rotors armed helicopter - Google Patents
Many rotors armed helicopter Download PDFInfo
- Publication number
- CN205396525U CN205396525U CN201620107434.6U CN201620107434U CN205396525U CN 205396525 U CN205396525 U CN 205396525U CN 201620107434 U CN201620107434 U CN 201620107434U CN 205396525 U CN205396525 U CN 205396525U
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- CN
- China
- Prior art keywords
- catapult
- hatch door
- fuselage
- sidespin wing
- launching gear
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model discloses a many rotors armed helicopter, pop out constitutions such as device and controller including fuselage, top main rotor, afterbody rotor, sidespin wing business turn over device, plate armour. Wherein armoured jettison device includes that the platform is deposited to rope constriction device fixed station, rope constriction device, rope, pulling end, connecting axle, jettison device workstation, expanding spring, armoured heavy object, heavy object and the impact is held. Sidespin wing telecontrol equipment includes telescopic link, revoliving arm, the sidespin wing, sidespin wing telecontrol equipment workstation, flexible arm and the fixed boss of flexible arm. The utility model discloses a cooperation work that many rotors armed helicopter popped out the device through controller control sidespin wing business turn over device, plate armour to guarantee that a many rotors armed helicopter still can descend safely when being caused quick -witted bulk damage by the attack in the smooth flight, the injury that caused by the attack is fallen into minimumly.
Description
Technical field
This utility model relates to a kind of multi-rotor aerocraft, and specifically, this utility model relates to a kind of many rotors armed helicopter.Belong to vehicle technology field.
Background technology
Armed helicopter is widely used among war, existing armed helicopter generally only has top rotor and anti-torque rotor, injury is produced when armed helicopter fuselage or machine rotor suffer to attack, armed helicopter just cannot smooth flight normally, extremely it is susceptible to the danger of air crash, causes personal safety and helicopter double loss.
Summary of the invention
In order to overcome existing armed helicopter suffer attack produce injury, just cannot smooth flight normally, be extremely susceptible to air crash danger problem.This utility model provides a kind of many rotors armed helicopter, this many rotors armed helicopter by top main rotor, anti-torque rotor, can telescopic folding sidespin swing device and armoring device for ejecting form, the collaborative work of many rotors, armoring device for ejecting is coordinated to eject armoring weight, to ensure that this many rotors armed helicopter still is able to smooth flight safe falling when being caused body injury by attack.
This utility model solves its technical problem and be the technical scheme is that
nullA kind of many rotors armed helicopter，Including: helicopter agent structure、Main rotor、Anti-torque rotor 3、Sidespin wing telecontrol equipment 17、Armoring catapult-launching gear 16 and controller 15，Described helicopter agent structure includes fuselage 1、Tail 2 and empennage 10，Fuselage 1 top is provided with main rotor fixed station 9，Main rotor is arranged on main rotor fixed station 9，Main rotor is by main rotor blade 7、Main rotor propeller hub 8 and main rotor shaft 14 form，Main rotor blade 7 is fixed on main rotor propeller hub 8，Main rotor propeller hub 8 is arranged on main rotor fixed station 9 by main rotor shaft 14，The empennage 10 of fuselage 1 afterbody is provided with anti-torque rotor 3，Described sidespin wing telecontrol equipment 17 and armoring catapult-launching gear 16 control by controller 15，Controller 15 controls to be arranged on armoring catapult-launching gear 16 cooperation of fuselage 1 both sides and realizes work.
Preferably, described fuselage 1 two sides are respectively symmetrically and are provided with sidespin wing turnover hatch door 12 and catapult-launching gear hatch door 13, fuselage 1 side disposes two sidespin wing turnover hatch doors 12 and a catapult-launching gear hatch door 13 altogether, one catapult-launching gear hatch door 13 is located between two sidespin wing turnover hatch doors 12, main rotor top is provided with radar 11, main rotor installation direction adopts mode upward, and anti-torque rotor installation direction adopts the mode towards side.
Preferably, described catapult-launching gear hatch door 13 adopts catapult-launching gear hatch door hinge 31 and fuselage hinge A32 connected mode on fuselage 1, catapult-launching gear hatch door 13 can along two chain connection center rotatings, sidespin wing turnover hatch door 12 adopts sidespin wing in-out apparatus hatch door hinge 33 and fuselage hinge B34 connected mode, and sidespin wing turnover hatch door 12 can along two chain connection center rotatings.
nullPreferably，Described fuselage 1 internal symmetry is provided with two armoring catapult-launching gears 16，Installation site is corresponding with both sides catapult-launching gear hatch door 13，Armoring catapult-launching gear 16 includes rope constriction device fixed station 35、Rope constriction device 21、Rope 22、Pull end 23、Connect axle 24、Catapult-launching gear workbench 25、Coil tension spring 26、Armoring weight 27、Weight lodging bench 28 and impact end 36，It is internal that described rope constriction device fixed station 35 is fixedly installed in fuselage 1，Rope constriction device fixed station 35 top is provided with rope constriction device 21，Rope constriction device 21 is the housing of internal cavities，Inside has rope 22 internal along the winding of rope constriction device 21 central shaft at rope constriction device 21，Rope 22 is made up of nonelastic flexible material，The internal actuator being provided with rope constriction device 21 of rope constriction device fixed station 35，The controlled device 15 of actuator controls，Controller 15 controls rope constriction device 21 and internal rope 22 is wound around contracted open procedure.
Preferably, the other end of described rope 22 is fixed with pulling end 23, described pull end 23, impact end 36 and two to connect axle 24 to form the entirety of a shape such as Roman number " II ", pull end 23, connect axle 24 and impact end 36) it is installed in catapult-launching gear workbench 25 entirely through connection axle 24, being placed in the weight resettlement groove of catapult-launching gear workbench 25, entirety can along connecting axle 24 mounting axis direction easy slide.
Preferably, described two connection axles 24 are all cased with spring 26, spring 26 one end props up impact end 36, the other end is against on the end face of weight resettlement groove of catapult-launching gear workbench 25, catapult-launching gear workbench 25 is provided with weight near catapult-launching gear hatch door 13 side and launches mouth 30, armoring weight 27 can launch mouth 30 by the impact of impact end 36 from weight and launch away, and described weight lodging bench 28 is placed with the armoring weight 27 that several size same rule shape is identical.
Preferably, also include sidespin wing turnover hatch door 12, described fuselage 1 internal symmetry is provided with four sidespin wing telecontrol equipments 17, it is corresponding that sidespin wing telecontrol equipment 17 installation site passes in and out hatch door 12 with the sidespin wing, sidespin wing telecontrol equipment 17 is separately mounted to the both sides of armoring catapult-launching gear 16, and described sidespin wing telecontrol equipment 17 includes expansion link 4, revoliving arm 5, the sidespin wing 6, sidespin wing telecontrol equipment workbench 18, telescopic arm 19 and telescopic arm fixing lug boss 20.
Preferably, it is internal that described sidespin wing telecontrol equipment workbench 18 is fixedly installed in fuselage 1, sidespin wing telecontrol equipment workbench 18 is provided with telescopic arm fixing lug boss 20 near fuselage 1 inside upper part, telescopic arm 19 one end is fixedly installed in telescopic arm fixing lug boss 20, expansion link 4 is installed on telescopic arm 19 in one end of fuselage 1, and expansion link 4 can along telescopic arm 19 installation direction easy slide.
Preferably, described expansion link 4 is provided with hinge at the other end of fuselage 1 and is connected with revoliving arm 5 by hinge, revoliving arm 5 can along chain connection center steering certain angle, the other end of revoliving arm 5 is provided with the sidespin wing 6, described telescopic arm 19, expansion link and revoliving arm 5 are installed point-blank, upwards, sidespin wing turnover hatch door 12 is provided with the anti-gear mouth 29 of hatch door to the described sidespin wing 6 installation direction.
Preferably, the internal movement executing mechanism being provided with expansion link 4, revoliving arm 5 and the sidespin wing 6 of described sidespin wing telecontrol equipment workbench 18, movement executing mechanism is controlled by controller 15, and controller 15 controls sidespin wing turnover hatch door 12 and opens or closes along installing hinge axis revolution.
The beneficial effects of the utility model are, a kind of many rotors armed helicopter when attacking generation injury, still can keep normal smooth flight, will suffer from attacking the injury caused and drop into minimum.
Accompanying drawing explanation
This specification includes the following drawings, it is shown that content respectively:
Fig. 1 is all rotor duty top views of this utility model；
Fig. 2 is all rotor duty side views of this utility model；
Fig. 3 is all rotor duty front views of this utility model；
Fig. 4 is this utility model section view internal structure schematic diagram；
Fig. 5 is catapult-launching gear structural representation；
Fig. 6 is catapult-launching gear structural representation；
Fig. 7 is utility model works view；
Fig. 8 is that this utility model sidespin wing turnover hatch door opens operating diagram；
Fig. 9 is sidespin wing in-out apparatus operating diagram；
Figure 10 is that this utility model sidespin wing turnover hatch door closes operating diagram；
Figure 11 is that this utility model device for ejecting hatch door closes operating diagram；
Figure 12 is section view internal structure schematic diagram；
Figure 13 is section view internal structure schematic diagram；
Figure is labeled as:
1, fuselage；2, tail；3, anti-torque rotor；4, expansion link；5, revoliving arm；6, the sidespin wing；7, main rotor blade；8, main rotor propeller hub；9, main rotor fixed station；10, empennage；11, radar；12, sidespin wing turnover hatch door；13, catapult-launching gear hatch door；14, main rotor shaft；15, controller；16, armoring catapult-launching gear；17, sidespin wing telecontrol equipment；18, sidespin wing telecontrol equipment workbench；19, telescopic arm；20, telescopic arm fixing lug boss；21, rope constriction device；22, rope；23, end is pulled；24, axle is connected；25, catapult-launching gear workbench；26, coil tension spring；27, armoring weight；28, weight lodging bench；29, the anti-gear mouth of hatch door；30, weight launches mouth；31, catapult-launching gear hatch door hinge；32, fuselage hinge A；33, sidespin wing in-out apparatus hatch door hinge；34, fuselage hinge B；35, rope constriction device fixed station；36, impact end.
Detailed description of the invention
Below against accompanying drawing, by the description to embodiment, detailed description of the invention of the present utility model is described in further detail, it is therefore an objective to help those skilled in the art that design of the present utility model, technical scheme are had more complete, accurate and deep understanding, and contribute to its enforcement.
As shown in Figures 1 to 4, this utility model includes helicopter agent structure, main rotor, anti-torque rotor 3, sidespin wing telecontrol equipment 17, armoring catapult-launching gear 16 and controller 15 etc..
Specifically, helicopter agent structure includes fuselage 1, tail 2, empennage 10 and many prior art parts composition.Fuselage 1 top is provided with main rotor fixed station 9, and main rotor is made up of with main rotor shaft 14 main rotor blade 7, main rotor propeller hub 8.Main rotor top is provided with radar 11, is used for reconnoitring and protecting.Main rotor blade 7 is fixed on main rotor propeller hub 8, and main rotor propeller hub 8 is then arranged on main rotor fixed station 9 by main rotor shaft 14, and rotor installation direction adopts mode upward.The empennage 10 of fuselage 1 afterbody is provided with anti-torque rotor 3, and rotor installation direction adopts the mode towards side.With reference to Figure 12, fuselage 1 two sides are respectively symmetrically and are provided with sidespin wing turnover hatch door 12 and catapult-launching gear hatch door 13, fuselage 1 side disposes two sidespin wing turnover hatch doors 12 and a catapult-launching gear hatch door 13 altogether, and a catapult-launching gear hatch door 13 is located between two sidespin wing turnover hatch doors 12.Catapult-launching gear hatch door 13 preferentially adopts catapult-launching gear hatch door hinge 31 and fuselage hinge A32 connected mode on fuselage 1, and catapult-launching gear hatch door 13 can along two chain connection center rotatings.Sidespin wing turnover hatch door 12 preferentially adopts sidespin wing in-out apparatus hatch door hinge 33 and fuselage hinge B34 connected mode, and sidespin wing turnover hatch door 12 can along two chain connection center rotatings.
As shown in Figures 5 to 7, fuselage 1 internal symmetry is provided with two armoring catapult-launching gears 16, and installation site is corresponding with both sides catapult-launching gear hatch door 13.With reference to Figure 12, armoring catapult-launching gear 16 by rope constriction device fixed station 35, rope constriction device 21, rope 22, pull end 23, connect axle 24, catapult-launching gear workbench 25, coil tension spring 26, armoring weight 27, weight lodging bench 28, impact end 36 form.
Wherein rope constriction device fixed station 35 is fixedly installed in fuselage 1 inside, rope constriction device fixed station 35 top is provided with rope constriction device 21, rope constriction device 21 is the housing of internal cavities, inside has rope 22 internal along the winding of rope constriction device 21 central shaft at rope constriction device 21, and rope 22 is made up of nonelastic flexible material.And the internal actuator being provided with rope constriction device 21 of rope constriction device fixed station 35, the controlled device 15 of actuator controls, and controller 15 controls rope constriction device 21 and internal rope 22 is wound around contracted open procedure.The other end of rope 22 is fixed with pulling end 23, wherein pull end 23, impact end 36 is connected axle 24 with two and can form a whole, shape such as Roman number " II ", pull end 23, connect axle 24, this overall this of impact end 36 is installed in catapult-launching gear workbench 25 by connecting axle 24, it is placed in the weight resettlement groove of catapult-launching gear workbench 25, entirety can along connecting axle 24 mounting axis direction easy slide, and two connection axles 24 are all cased with spring 26, spring 26 one end props up impact end 36, the other end is against on the end face of weight resettlement groove of catapult-launching gear workbench 25.With reference to Figure 11, catapult-launching gear workbench 25 is provided with weight and launches mouth 30 near catapult-launching gear hatch door 13 side, and armoring weight 27 can launch mouth 30 by the impact of impact end 36 from weight and launch away.Weight lodging bench 28 is placed with the armoring weight 27 that several size same rule shape is identical.In this plate armour catapult-launching gear 16, controller 15 controls the actuator of rope constriction device 21, and when not working, rope constriction device 21 is in the state of tightening up, and rope 22 tightens up, and pulls end 23 guarantee impact end 36 not contact armoring weight 27.When needs eject armoring weight 27, controller 15 first controls to open catapult-launching gear hatch door 13, controller 15 controls rope constriction device 21 again and works, rope 22 moment unclamps, the entirety pull end 23, connecting axle 24, impact end 36 and forming skids off along connecting the direction abrupt release of axle 24 mounting axis under the effect of spring 26 elastic force, and impact end 36 has enormous impact power and from the weight catapult-launching gear workbench 25, armoring weight 27 is launched mouth 30 ejects.Controller 15 controls rope constriction device 21 and works afterwards, and rope 22 moment tightens up, and launches after an armoring weight 27 of mouth 30 is ejected now close to weight, and the armoring weight 27 being and then placed on weight lodging bench 28 falls successively as launching use next time.
As shown in Figure 4, fuselage 1 internal symmetry is provided with four sidespin wing telecontrol equipments 17, and it is corresponding that sidespin wing telecontrol equipment 17 installation site passes in and out hatch door 12 with the sidespin wing, and sidespin wing telecontrol equipment 17 is separately mounted to the both sides of armoring catapult-launching gear 16.With reference to shown in Fig. 7, this position is that sidespin wing telecontrol equipment 17 works the sidespin wing 6 is stretched out operating position.Sidespin wing telecontrol equipment 17 is made up of expansion link 4, revoliving arm 5, the sidespin wing 6, sidespin wing telecontrol equipment workbench 18, telescopic arm 19, telescopic arm fixing lug boss 20.
It is internal that sidespin wing telecontrol equipment workbench 18 is fixedly installed in fuselage 1, sidespin wing telecontrol equipment workbench 18 is provided with telescopic arm fixing lug boss 20 by fuselage 1 inside upper part, telescopic arm 19 one end is by being fixedly installed in telescopic arm fixing lug boss 20, expansion link 4 is installed on telescopic arm 19 in one end of fuselage 1 such as telescopic hydraulic cylinder mounting means, and expansion link 4 can along telescopic arm 19 installation direction easy slide.Expansion link 4 is provided with hinge at the other end of fuselage 1 and is connected with revoliving arm 5 by hinge, and revoliving arm 5 can along chain connection center steering certain angle, and the other end of revoliving arm 5 is provided with the sidespin wing 6.During sidespin wing telecontrol equipment 17 duty, telescopic arm 19, expansion link and revoliving arm 5 are installed point-blank, and the sidespin wing 6 installation direction is upwards.With reference to shown in Fig. 8, wherein sidespin wing turnover hatch door 12 is provided with the anti-gear mouth 29 of hatch door, in order to when ensureing that sidespin wing telecontrol equipment 17 works, sidespin wing turnover hatch door 12 does not cause with expansion link 4 and touches gear.With reference to, shown in Figure 12, being provided with the movement executing mechanism of expansion link 4, revoliving arm 5 and the sidespin wing 6 inside sidespin wing telecontrol equipment workbench 18, movement executing mechanism is controlled by controller 15.With reference to Fig. 8 to shown in 10, when sidespin wing telecontrol equipment 17 is without working, controller 15 controls sidespin wing turnover hatch door 12, and sidespin wing turnover hatch door 12 is opened along installing hinge axis revolution,
The sidespin wing 6 stops the rotation, controller 15 controls revoliving arm 5 and returns and turn 90 degrees along being connected hinge central axis with expansion link 4, and then controller 15 controls expansion link 4 along telescopic arm 19 installation direction to fuselage 1 inner slide, and controller 15 controls sidespin wing turnover hatch door 12 and cuts out.
nullComprehensive all diagrams，One many rotors Armored Helicopter of the present utility model is when normal flight，Main rotor and anti-torque rotor 3 rotary motion，When a kind of many rotors Armored Helicopter suffer to attack fuselage 1 is impaired and person's main rotor impaired cannot normal rotational movement time，Sidespin wing telecontrol equipment 17 controls by controller 15 with armoring catapult-launching gear 16，Controller 15 controls armoring catapult-launching gear 16 cooperation of both sides and realizes work，Such as impaired on the left of fuselage 1，A kind of many rotors Armored Helicopter tilts to the right when left side weight saving，The armoring catapult-launching gear 16 in now controller 15 control right side works，Eject the armoring weight 27 of appropriate weight，Simultaneously，Controller 15 controls sidespin wing telecontrol equipment 17 cooperation of four and realizes work，Fuselage 1 is impaired with main rotor，Sidespin wing telecontrol equipment 17 realizes work，Controller 15 controls multiple sidespin wing 6 and rotates and rotary speed.Armoring catapult-launching gear 16 achieves the still smooth flight when fuselage 1 is impaired and main rotor is impaired of a kind of many rotors Armored Helicopter with sidespin wing telecontrol equipment 17 cooperation under the control of controller 15.
Above in association with accompanying drawing, this utility model is exemplarily described.Obviously, this utility model implements and is not subject to the restrictions described above.As long as have employed the improvement of the various unsubstantialities that method of the present utility model design carries out with technical scheme；Or not improved, above-mentioned design of the present utility model and technical scheme are directly applied to other occasion, all within protection domain of the present utility model.
Claims (10)
- null1. rotor armed helicopter more than a kind，It is characterized in that，Including: helicopter agent structure、Main rotor、Anti-torque rotor (3)、Sidespin wing telecontrol equipment (17)、Armoring catapult-launching gear (16) and controller (15)，Described helicopter agent structure includes fuselage (1)、Tail (2) and empennage (10)，Fuselage (1) top is provided with main rotor fixed station (9)，Main rotor is arranged on main rotor fixed station (9)，Main rotor is by main rotor blade (7)、Main rotor propeller hub (8) and main rotor shaft (14) composition，Main rotor blade (7) is fixed on main rotor propeller hub (8)，Main rotor propeller hub (8) is arranged on main rotor fixed station (9) by main rotor shaft (14)，The empennage (10) of fuselage (1) afterbody is provided with anti-torque rotor (3)，Described sidespin wing telecontrol equipment (17) and armoring catapult-launching gear (16) control by controller (15)，Controller (15) controls to be arranged on armoring catapult-launching gear (16) cooperation of fuselage (1) both sides and realizes work.
- 2. armed helicopter according to claim 1, it is characterized in that, described fuselage (1) two sides are respectively symmetrically and are provided with sidespin wing turnover hatch door (12) and catapult-launching gear hatch door (13), fuselage (1) side disposes two sidespin wings turnover hatch door (12) and a catapult-launching gear hatch door (13) altogether, one catapult-launching gear hatch door (13) is located between two sidespin wings turnover hatch door (12), main rotor top is provided with radar (11), main rotor installation direction adopts mode upward, anti-torque rotor installation direction adopts the mode towards side.
- 3. armed helicopter according to claim 2, it is characterized in that, described catapult-launching gear hatch door (13) adopts upper fuselage hinge A (32) connected mode of catapult-launching gear hatch door hinge (31) and fuselage (1), catapult-launching gear hatch door (13) can along two chain connection center rotatings, sidespin wing turnover hatch door (12) adopts sidespin wing in-out apparatus hatch door hinge (33) and fuselage hinge B (34) connected mode, and sidespin wing turnover hatch door (12) can along two chain connection center rotatings.
- null4. the armed helicopter according to claim 1-3 any one，It is characterized in that，Described fuselage (1) internal symmetry is provided with two armoring catapult-launching gears (16)，Installation site is corresponding with both sides catapult-launching gear hatch door (13)，Armoring catapult-launching gear (16) includes rope constriction device fixed station (35)、Rope constriction device (21)、Rope (22)、Pull end (23)、Connect axle (24)、Catapult-launching gear workbench (25)、Coil tension spring (26)、Armoring weight (27)、Weight lodging bench (28) and impact end (36)，It is internal that described rope constriction device fixed station (35) is fixedly installed in fuselage (1)，Rope constriction device fixed station (35) top is provided with rope constriction device (21)，The housing that rope constriction device (21) is internal cavities，Inside has rope (22) internal along the winding of rope constriction device (21) central shaft at rope constriction device (21)，Rope (22) is made up of nonelastic flexible material，The internal actuator being provided with rope constriction device (21) of rope constriction device fixed station (35)，The controlled device of actuator (15) controls，Controller (15) controls rope constriction device (21) and internal rope (22) is wound around contracted open procedure.
- 5. armed helicopter according to claim 4, it is characterized in that, the other end of described rope (22) is fixed with pulling end (23), described pull end (23), impact end (36) and two entirety connecting axle (24) composition one shape such as Roman number " II ", pull end (23), connect axle (24) and impact end (36) and be installed in catapult-launching gear workbench (25) entirely through connecting axle (24), it is placed in the weight resettlement groove of catapult-launching gear workbench (25), entirety can along connecting axle (24) mounting axis direction easy slide.
- 6. armed helicopter according to claim 5, it is characterized in that, described two connections axle (24) are all cased with spring (26), spring (26) one end props up impact end (36), the other end is against on the end face of the weight resettlement groove of catapult-launching gear workbench (25), catapult-launching gear workbench (25) is provided with weight near catapult-launching gear hatch door (13) side and launches mouth (30), armoring weight (27) can be launched mouth (30) by the impact of impact end (36) from weight and be launched away, described weight lodging bench (28) is placed with the armoring weight (27) that several size same rule shape is identical.
- 7. the armed helicopter according to claim 1-3 any one, it is characterized in that, also include sidespin wing turnover hatch door (12), described fuselage (1) internal symmetry is provided with four sidespins wing telecontrol equipment (17), it is corresponding that sidespin wing telecontrol equipment (17) installation site passes in and out hatch door (12) with the sidespin wing, sidespin wing telecontrol equipment (17) is separately mounted to the both sides of armoring catapult-launching gear (16), described sidespin wing telecontrol equipment (17) includes expansion link (4), revoliving arm (5), the sidespin wing (6), sidespin wing telecontrol equipment workbench (18), telescopic arm (19) and telescopic arm fixing lug boss (20).
- 8. armed helicopter according to claim 7, it is characterized in that, it is internal that described sidespin wing telecontrol equipment workbench (18) is fixedly installed in fuselage (1), sidespin wing telecontrol equipment workbench (18) is provided with telescopic arm fixing lug boss (20) near fuselage (1) inside upper part, telescopic arm (19) one end is fixedly installed in telescopic arm fixing lug boss (20), expansion link (4) is installed on telescopic arm (19) in one end of fuselage (1), and expansion link (4) can along telescopic arm (19) installation direction easy slide.
- 9. armed helicopter according to claim 8, it is characterized in that, described expansion link (4) is provided with hinge at the other end of fuselage (1) and is connected with revoliving arm (5) by hinge, revoliving arm (5) can along chain connection center steering certain angle, the other end of revoliving arm (5) is provided with the sidespin wing (6), described telescopic arm (19), expansion link and revoliving arm (5) are installed point-blank, upwards, sidespin wing turnover hatch door (12) is provided with the anti-gear mouth (29) of hatch door to the described sidespin wing (6) installation direction.
- 10. armed helicopter according to claim 9, it is characterized in that, the internal movement executing mechanism being provided with expansion link (4), revoliving arm (5) and the sidespin wing (6) of described sidespin wing telecontrol equipment workbench (18), movement executing mechanism is controlled by controller (15), and controller (15) controls sidespin wing turnover hatch door (12) and opens or closes along installing hinge axis revolution.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620107434.6U CN205396525U (en) | 2016-01-29 | 2016-01-29 | Many rotors armed helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620107434.6U CN205396525U (en) | 2016-01-29 | 2016-01-29 | Many rotors armed helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205396525U true CN205396525U (en) | 2016-07-27 |
Family
ID=56450124
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620107434.6U Withdrawn - After Issue CN205396525U (en) | 2016-01-29 | 2016-01-29 | Many rotors armed helicopter |
Country Status (1)
| Country | Link |
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| CN (1) | CN205396525U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730684A (en) * | 2016-01-29 | 2016-07-06 | 安徽工程大学 | Multi-rotor gunship helicopter |
-
2016
- 2016-01-29 CN CN201620107434.6U patent/CN205396525U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730684A (en) * | 2016-01-29 | 2016-07-06 | 安徽工程大学 | Multi-rotor gunship helicopter |
| CN105730684B (en) * | 2016-01-29 | 2018-02-02 | 安徽工程大学 | A kind of more rotor armed helicopters |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160727 Effective date of abandoning: 20180202 |
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| AV01 | Patent right actively abandoned |