CN105539849A - External mounting type aviation electric pod and using method thereof - Google Patents
External mounting type aviation electric pod and using method thereof Download PDFInfo
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- CN105539849A CN105539849A CN201511023374.6A CN201511023374A CN105539849A CN 105539849 A CN105539849 A CN 105539849A CN 201511023374 A CN201511023374 A CN 201511023374A CN 105539849 A CN105539849 A CN 105539849A
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- 238000000034 method Methods 0.000 title claims description 22
- 238000004804 winding Methods 0.000 claims abstract description 28
- 230000007246 mechanism Effects 0.000 claims description 118
- 239000004744 fabric Substances 0.000 claims description 40
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 claims description 9
- 238000011084 recovery Methods 0.000 claims description 6
- 230000001105 regulatory effect Effects 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 230000009471 action Effects 0.000 abstract description 3
- 238000005299 abrasion Methods 0.000 abstract 1
- 230000006835 compression Effects 0.000 abstract 1
- 238000007906 compression Methods 0.000 abstract 1
- 230000003247 decreasing effect Effects 0.000 abstract 1
- 230000009347 mechanical transmission Effects 0.000 abstract 1
- 238000005096 rolling process Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 206010008190 Cerebrovascular accident Diseases 0.000 description 1
- 208000033999 Device damage Diseases 0.000 description 1
- 208000006011 Stroke Diseases 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
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- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
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- 230000008569 process Effects 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses an external mounting type aviation electric pod. The external mounting type aviation electric pod comprises a pod core and a shell. The pod core is arranged in the shell. High-automation-degree operating design is adopted for the external mounting type aviation electric pod. All operation actions can be completed just through one pilot in a part-time job manner, and therefore the pod can be used for all aircraft with a single seat and multiple seats. Because no hydraulic and air compression systems are arranged, mechanical transmission parts are reduced by 80%, mechanical abrasion is greatly reduced, and the system is single and simplified; rolling of a winch and cable distributing and dragging winding and unwinding speed control precision can be improved, and therefore the fault rate is greatly decreased; and because a cable dragging automatic locking device is arranged, part of cable dragging force is transmitted to a pod body structure, loads on the winch are relieved, and using reliability is greatly improved. A more advanced thin-shell structure is adopted for a pod body, the ratio of strength to weight and the material utilizing rate are greatly increased.
Description
Technical field
The application relates to aviation field, particularly relates to the electronic gondola of a kind of external hanging type aviation and using method.
Background technology
Aviation plug-in winch cabin is a kind of rectification type nacelle hanging on aircraft all-wing aircraft or ventral, in order to install a certain functional component of aircraft as electronic machine, weapon and trailing type target etc., existing plug-in winch cabin, classification is numerous, but be all mechanical winch cabin, mechanical type cabin is by mechanical gear and chain gear, also hydraulic pressure will be furnished with, pressurized air and the system such as electric, complex structure, driving efficiency is low, serious wear, fault rate is high, especially this cover complication system must join special messenger's operation, aircraft crewmember like this for pulling must be two people, this is just inadaptable is the most generally the fighter plane adapted of single seat, also because system architecture is complicated, fault rate is also high, often there is the fault that transmission device damages and trailing cable fractures, reliability of service is low.
Summary of the invention
In order to solve the problem, the application provides the electronic gondola of a kind of external hanging type aviation and using method.
The application proposes the electronic gondola of a kind of external hanging type aviation, and the electronic gondola of described external hanging type aviation comprises gondola core and housing, and described gondola core is arranged at enclosure interior;
Described gondola core comprises: wind turbine generator group, electrical control mechanism group, trailing cable winding mechanism, sensor cloth cable control mechanism;
Described electrical control mechanism group one end is fixedly connected with described wind turbine generator group, and the described electrical control mechanism group other end is provided with described trailing cable winding mechanism, and the described trailing cable winding mechanism other end is provided with sensor cloth cable control mechanism.
Preferably, described wind turbine generator group comprises: wind turbine generator and servomotor controller;
Described wind turbine generator is arranged at described housing forefront, and described servomotor controller is arranged at the rear of described wind turbine generator and is connected with described wind turbine generator;
Described wind turbine generator is made up of impulse turbine, dynamo generator, air flow regulating damper etc.
Preferably, described electrical control mechanism group comprises: the first buncher, the second buncher, master controller and data radio station;
Described key station is connected with data radio station with described first buncher, the second buncher;
Described data radio station is connected with the second buncher with described first buncher.
Preferably, described trailing cable winding mechanism comprises: trailing cable, reel, braking mechanism and wiring unit;
Described reel comprises: towing cable spool body, plate washer, bearing seat and axle;
Described wiring unit and described reel are arranged side by side, and one section of described trailing cable is fixedly installed on reel, and the other end lays in described sensor cloth cable control mechanism by wiring unit;
Preferably, described sensor cloth cable control mechanism comprises: sensor and cloth cable control assembly;
Described cloth cable control assembly comprises: towing cable folding and unfolding drag body and Suo Lan mechanism;
Described towing cable folding and unfolding drag body comprises: energy disperser, leading sheave group, cable cutter and target are locked;
Described trailing cable lays to cable cutter by energy disperser, leading sheave group and fixing and locking device, is put into the target lock be arranged at below described housing, then lays on the object of needs towing via cable cutter cloth;
Described Suo Lan mechanism comprises: six groups of locking assembly pulleys and snap lock;
Described sensor is laid between energy disperser and cable cutter.
Preferably, described sensor comprises: tension pick-up, temperature sensor and linear transducer.
Preferably, described housing comprises: body skin and crossbeam, and described body skin is high strength alumin ium alloy thin shell structure, and body skin inwall top is located at by described crossbeam;
Described body skin is provided with through hole, and described crossbeam is provided with hanger, and described hanger stretches out body skin by through hole and is connected with aircraft hanging beam.
The application also proposes the using method of the electronic gondola of a kind of external hanging type aviation, and described method comprises:
Step R1: target is laid to designated flying zone;
Step R2: target is reclaimed and takes back ground.
Preferably, described step R1: the method laid by target to designated flying zone comprises:
Step S1: cabin body is suspended on the hanging beam of airframe or wing;
Step S2: after taking off, wind turbine generator group air door regulates air-flow, makes electrical generator send stable electric current;
Step S3: aviator presses the releasing button in passenger cabin;
Step S4: electrical control mechanism group sends signal to trailing cable winding mechanism and sensor cloth cable control mechanism;
Step S5: described trailing cable winding mechanism opens braking mechanism, described sensor cloth cable control mechanism opens target lock and Suo Lan mechanism;
Step S6: target moves backward, drives towing cable to release;
Step S7: described electrical control mechanism group and described towing cable folding and unfolding drag body control described towing cable and release with safety speed;
Step S8: described target is put into position, towing cable pins in Suo Lan mechanism.
Preferably, described step R2: target to be reclaimed and the method taking back ground comprises:
Step S101: aviator presses the recovery button in passenger cabin;
Step S102: electrical control mechanism group sends signal to trailing cable winding mechanism and sensor cloth cable control mechanism;
Step S103: open Suo Lan mechanism;
Step S104: described electrical control mechanism group and described towing cable folding and unfolding drag body control described towing cable and reclaim with safety speed;
Step S105: when recovery puts in place, described trailing cable winding mechanism locking braking mechanism, described sensor cloth cable control mechanism locking target lock and Suo Lan mechanism;
Step S106: aircraft makes a return voyage landing.
The electronic gondola of a kind of external hanging type aviation that the invention described above proposes and using method, obtain following technique effect:
1, the electronic gondola of external hanging type aviation of the application's proposition is completely without hydraulic pressure and compressed air system, have employed full electric type design, thus the operational design that degree of automation is high can be adopted, as long as aviator one people is part-time just can complete all operations action, thus this gondola can be used for the aircraft of all single seats and many.
2, the electronic gondola of external hanging type aviation that proposes of the application is due to without hydraulic pressure and compressed air system, mechanical drive department enclosure decreases 80 percent simultaneously, and mechanical wear declines greatly, and system is concisely single, fault rate also declines greatly, and reliability of service improves greatly.
3, the structure of the electronic gondola of external hanging type aviation of the application's proposition adopts more advanced thin shell structure, substantially increases the ratio of strength to weight and stock utilization.
4, the electronic gondola of external hanging type aviation of the application's proposition is owing to using full electric type cabin, so the control accuracy of the scrolling of winch and cloth cable and towing cable folding and unfolding speed all can improve, greatly alleviates the loss of towing cable.
5, the electronic gondola of external hanging type aviation of the application's proposition is owing to having set up one group of towing cable forced locking device, is delivered on section structure, alleviates the load of winch by the gradeability of part towing cable.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present application or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, the accompanying drawing that the following describes is only some embodiments recorded in the application, for those of ordinary skill in the art, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the integral structure schematic diagram of the electronic gondola of the application's external hanging type aviation;
Fig. 2 is the structural representation of the application's external hanging type aviation electronic gondola apoplexy power turbine generation unit;
Fig. 3 is the structural representation of electrical control mechanism group in the electronic gondola of the application's external hanging type aviation;
Fig. 4 is the structural representation of trailing cable winding mechanism in the electronic gondola of the application's external hanging type aviation;
Fig. 5 is the structural representation of sensor cloth cable control mechanism in the electronic gondola of the application's external hanging type aviation;
Fig. 6 is the structural representation that the application tows target;
Fig. 7 is the application's external hanging type aviation electronic gondola using method schematic flow sheet;
Fig. 8 is that target lays to designated flying zone method flow schematic diagram by the application;
Fig. 9 is that target reclaims and takes back surface process schematic flow sheet by the application.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described.
The application proposes the electronic gondola of a kind of external hanging type aviation, and as shown in Figure 1, the electronic gondola of described external hanging type aviation comprises gondola core and housing, and described gondola core is arranged at enclosure interior;
Concrete, described housing, according to theory of thin shell, is made generally in as fairing, can also makes the shape that cylinder etc. possesses streamline relationship;
More specifically, described housing comprises: body skin and crossbeam, and described body skin and described crossbeam are high strength alumin ium alloy material, and body skin inwall top is located at by described crossbeam;
Described body skin is provided with through hole, and described crossbeam is provided with hanger, and described hanger stretches out body skin by through hole and is connected with aircraft hanging beam;
More specifically, described housing is also provided with the control cables seat that can throw in.
Described gondola core comprises: wind turbine generator group 1, electrical control mechanism group 2, trailing cable winding mechanism 3, sensor cloth cable control mechanism 4;
Described electrical control mechanism group 2 one end is fixedly connected with described wind turbine generator group 1, and described electrical control mechanism group 2 other end is provided with described trailing cable winding mechanism 3, and described trailing cable winding mechanism 3 other end is provided with sensor cloth cable control mechanism 4.
Concrete, described wind turbine generator group 1, as shown in Figure 2, comprising: wind turbine generator 11 and servomotor controller 12;
Described wind turbine generator 11 is arranged at described housing forefront, and described servomotor controller 12 is arranged at the rear of described wind turbine generator 11 and is connected with described wind turbine generator 11;
Described wind turbine generator 11 is made up of impulse turbine 111, dynamo generator 112, air flow regulating damper etc.
Concrete, described electrical control mechanism group 2 as shown in Figure 3, comprising: the first buncher 21, second buncher 22, master controller 23 and data radio station 24;
Described master controller 23 is connected with data radio station 24 with described first buncher 21, second buncher 22;
More specifically, described first buncher 21 is for driving electric winch, and described second buncher 22 is for driving cloth cable device axle.
Described data radio station 24 is connected with the second buncher 22 with described first buncher 21.
Concrete, as shown in Figure 4, described trailing cable winding mechanism 3 comprises: trailing cable, reel 31, braking mechanism 32 and wiring unit 33;
Described reel comprises: towing cable spool body, plate washer, bearing seat and axle;
Described wiring unit 33 is arranged side by side with described reel 31, and one section of described trailing cable is fixedly installed on described reel 31, and the other end lays in described sensor cloth cable control mechanism 4 by wiring unit 33;
Concrete, described sensor cloth cable control mechanism 4, as shown in Figure 5, comprising: sensor 41 and cloth cable control assembly 42;
Described cloth cable control assembly 42 comprises: towing cable folding and unfolding drag body 421 and Suo Lan mechanism 422;
Described towing cable folding and unfolding drag body 421 comprises: energy disperser, leading sheave group, cable cutter and target are locked;
Described trailing cable lays to cable cutter by energy disperser, leading sheave group and fixing and locking device, is put into the target lock be arranged at below described housing, then lays on the object of needs towing, as target via cable cutter cloth;
Described Suo Lan mechanism 422 comprises: six groups of locking assembly pulleys 501 and snap lock 503;
More specifically, as shown in Figure 6, described Suo Lan mechanism is made up of 6 groups of assembly pulleys 501 and 6 groups of parallelogram connecting shaft mechanisms 502, and towing cable runs in the guide in six groups of locking assembly pulleys, and described mechanism locks 503 by an electromagnetic elasticity and controls.
Described Suo Lan mechanism 422 also comprises: lock cable mechanism shell 504, control apparatus 505 and latching device 506;
Described control apparatus 505 also comprises holding screw 5051, slidably latch segment 5052 and deep groove ball bearing 5053;
When snap lock 503 does not work, towing cable moves in pulley 501, drive pulley 501, lever due to sheave shaft mutually forms parallelogram, and at this moment each pulley 501 is all made to the motion of towing cable direction, i.e. mutual jam-packed, produce coupling mechanism force, when 503 work of electromagnetic elasticity lock, assembly pulley is separated from each other under leverage, and towing cable also just unclamps unblock.
Described sensor is laid between energy disperser and cable cutter.
More specifically, described sensor comprises: tension pick-up, temperature sensor and linear transducer.
More specifically, whether the tensile deformation of described tension pick-up for the tension force measuring towing cable and be subject to and when being subject to tension force exceeds the safety value of design;
Whether described temperature sensor meets the safety value of design for measuring the temperature of towing cable under high-altitude low temperature environment;
The towing cable length that described linear transducer is released for measuring cloth.
Describe according to Fig. 1-6 the electronic gondola of a kind of external hanging type aviation that the application proposes above, below introduce the using method of the electronic gondola of described external hanging type aviation according to Fig. 7-9.
The using method of the electronic gondola of a kind of external hanging type aviation that the application proposes, described method comprises:
Step R1: target is laid to designated flying zone;
Step R2: target is reclaimed and takes back ground.
Concrete, described step R1: the method laid by target to designated flying zone comprises:
Step S1: cabin body is suspended on the hanging beam of airframe or wing;
More specifically, cabin body hanger is hung on aircraft hanging beam, can throw and unload the control cables seat that plug inserts aircraft, and complete the suspension of cabin body.
Step S2: after taking off, wind turbine generator group air door regulates air-flow, makes electrical generator send stable electric current;
More specifically, described wind turbine generator group is in flight course, and described air flow regulating damper regulates the intake entering impulse turbine, make impulse turbine under the wind being subject to the most applicable intensity impacts, produce turning effort, band dynamotor, generation current, for miscellaneous part is powered.
Step S3: aviator presses the releasing button in passenger cabin;
Step S4: described electrical control mechanism group 2 sends signal to trailing cable winding mechanism 3 and sensor cloth cable control mechanism 4;
More specifically, when aviator presses releasing button, signal is via described control cables seat, can throw and unload the data radio station 24 that electric rubbing head is transferred to described electrical control mechanism group 2, signal is sent to master controller 23 by described data radio station 24, and signal is sent to trailing cable winding mechanism 3 and sensor cloth cable control mechanism 4 by master controller 23 again.
Step S5: described trailing cable winding mechanism opens braking mechanism, described sensor cloth cable control mechanism opens target lock and Suo Lan mechanism;
Step S6: target moves backward, drives towing cable to release;
More specifically, described target, under air resistance and gravity combined action, drives towing cable to move backward.
Step S7: described electrical control mechanism group 2 and described towing cable folding and unfolding drag body control described towing cable and release with safety speed;
More specifically, when described target drives towing cable to move backward, first buncher 21 driving electric winch of described electrical control mechanism group 2, described second buncher 22 drives and drives cloth cable device axle, application force is applied with direction, make to tow target and towing cable can not to accelerate release backward, so that when towing cable arrives length of command code, the acceleration/accel stopping winch producing suddenly is excessive and the problem that causes towing cable to rupture.
Step S8: described target is put into position, towing cable pins in Suo Lan mechanism.
More specifically, when target is put into, locking braking mechanism, the first buncher 21 and the second buncher 22 strengthen running, and make towing cable no longer continue to release, towing cable pins in Suo Lan mechanism.
Concrete, described step R2: target to be reclaimed and the method taking back ground comprises:
Step S101: aviator presses the recovery button in passenger cabin;
Step S102: electrical control mechanism group sends signal to trailing cable winding mechanism and sensor cloth cable control mechanism;
More specifically, when aviator presses releasing button, signal is via described control cables seat, can throw and unload the data radio station 24 that electric rubbing head is transferred to described electrical control mechanism group 2, signal is sent to master controller 23 by described data radio station 24, and signal is sent to trailing cable winding mechanism 3 and sensor cloth cable control mechanism 4 by master controller 23 again.
Step S103: open Suo Lan mechanism;
Step S104: described electrical control mechanism group and described towing cable folding and unfolding drag body control described towing cable and reclaim with safety speed;
More specifically, when locking cable mechanism opening, described first buncher 21 and described second buncher 22 strengthen running, make towing cable start at the uniform velocity to reclaim.
Step S105: when recovery puts in place, described trailing cable winding mechanism locking braking mechanism, described sensor cloth cable control mechanism locking target lock and Suo Lan mechanism;
Step S106: aircraft makes a return voyage landing.
The above, it is only preferred embodiment of the present invention, not any pro forma restriction is done to the present invention, although the present invention discloses as above with preferred embodiment, but and be not used to limit the present invention, any those skilled in the art, do not departing within the scope of technical solution of the present invention, make a little change when the technology contents of above-mentioned announcement can be utilized or be modified to the Equivalent embodiments of equivalent variations, in every case be the content not departing from technical solution of the present invention, according to any simple modification that technical spirit of the present invention is done above embodiment, equivalent variations and modification, all still belong in the scope of technical solution of the present invention.
Claims (10)
1. the electronic gondola of external hanging type aviation, is characterized in that:
The electronic gondola of described external hanging type aviation comprises gondola core and housing, and described gondola core is arranged at enclosure interior;
Described gondola core comprises: wind turbine generator group, electrical control mechanism group, trailing cable winding mechanism, sensor cloth cable control mechanism;
Described electrical control mechanism group one end is fixedly connected with described wind turbine generator group, and the described electrical control mechanism group other end is provided with described trailing cable winding mechanism, and the described trailing cable winding mechanism other end is provided with sensor cloth cable control mechanism.
2. the electronic gondola of external hanging type aviation as claimed in claim 1, it is characterized in that, described wind turbine generator group comprises: wind turbine generator and servomotor controller;
Described wind turbine generator is arranged at described housing forefront, and described servomotor controller is arranged at the rear of described wind turbine generator and is connected with described wind turbine generator;
Described wind turbine generator is made up of impulse turbine, dynamo generator, air flow regulating damper etc.
3. the electronic gondola of external hanging type aviation as claimed in claim 1, it is characterized in that, described electrical control mechanism group comprises: the first buncher, the second buncher, master controller and data radio station;
Described key station is connected with data radio station with described first buncher, the second buncher;
Described data radio station is connected with the second buncher with described first buncher.
4. the electronic gondola of external hanging type aviation as claimed in claim 1, it is characterized in that, described trailing cable winding mechanism comprises: trailing cable, reel, braking mechanism and wiring unit;
Described reel comprises: towing cable spool body, plate washer, bearing seat and axle;
Described wiring unit and described reel are arranged side by side, and one section of described trailing cable is fixedly installed on reel, and the other end is laid in described sensor cloth cable control mechanism by wiring unit.
5. the electronic gondola of external hanging type aviation as claimed in claim 1, it is characterized in that, described sensor cloth cable control mechanism comprises: sensor and cloth cable control assembly;
Described cloth cable control assembly comprises: towing cable folding and unfolding drag body and Suo Lan mechanism;
Described towing cable folding and unfolding drag body comprises: energy disperser, leading sheave group, cable cutter and target are locked;
Described trailing cable lays to cable cutter by energy disperser, leading sheave group and fixing and locking device, is put into the target lock be arranged at below described housing, then lays on the object of needs towing via cable cutter cloth;
Described Suo Lan mechanism comprises: six groups of locking assembly pulleys and snap lock;
Described sensor is laid between energy disperser and cable cutter.
6. the electronic gondola of external hanging type aviation as claimed in claim 5, it is characterized in that, described sensor comprises: tension pick-up, temperature sensor and linear transducer.
7. the electronic gondola of external hanging type aviation as claimed in claim 1, it is characterized in that, described housing comprises: body skin and crossbeam, and described body skin is high strength alumin ium alloy thin shell structure, and body skin inwall top is located at by described crossbeam;
Described body skin is provided with through hole, and described crossbeam is provided with hanger, and described hanger stretches out body skin by through hole and is connected with aircraft hanging beam.
8. a using method for the electronic gondola of external hanging type aviation, is characterized in that, described method comprises:
Step R1: target is laid to designated flying zone;
Step R2: target is reclaimed and takes back ground.
9. the electronic gondola of external hanging type aviation as claimed in claim 8, is characterized in that, described step R1: the method laid by target to designated flying zone comprises:
Step S1: cabin body is suspended on the hanging beam of airframe or wing;
Step S2: after taking off, wind turbine generator group air door regulates air-flow, makes electrical generator send stable electric current;
Step S3: aviator presses the releasing button in passenger cabin;
Step S4: electrical control mechanism group sends signal to trailing cable winding mechanism and sensor cloth cable control mechanism;
Step S5: described trailing cable winding mechanism opens braking mechanism, described sensor cloth cable control mechanism opens target lock and Suo Lan mechanism;
Step S6: target moves backward, drives towing cable to release;
Step S7: described electrical control mechanism group and described towing cable folding and unfolding drag body control described towing cable and release with safety speed;
Step S8: described target is put into position, towing cable pins in Suo Lan mechanism.
10. the electronic gondola of external hanging type aviation as claimed in claim 8, is characterized in that, described step R2: reclaimed by target and the method taking back ground comprises:
Step S101: aviator presses the recovery button in passenger cabin;
Step S102: electrical control mechanism group sends signal to trailing cable winding mechanism and sensor cloth cable control mechanism;
Step S103: open Suo Lan mechanism;
Step S104: described electrical control mechanism group and described towing cable folding and unfolding drag body control described towing cable and reclaim with safety speed;
Step S105: when recovery puts in place, described trailing cable winding mechanism locking braking mechanism, described sensor cloth cable control mechanism locking target lock and Suo Lan mechanism;
Step S106: aircraft makes a return voyage landing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511023374.6A CN105539849B (en) | 2015-12-31 | 2015-12-31 | A kind of electronic gondola of external hanging type aviation and application method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201511023374.6A CN105539849B (en) | 2015-12-31 | 2015-12-31 | A kind of electronic gondola of external hanging type aviation and application method |
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| CN105539849A true CN105539849A (en) | 2016-05-04 |
| CN105539849B CN105539849B (en) | 2017-11-10 |
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| CN106767181A (en) * | 2017-01-13 | 2017-05-31 | 河北环航科技股份有限公司 | A kind of plug-in target nacelle of aviation |
| CN108639351A (en) * | 2018-08-03 | 2018-10-12 | 河北环航科技股份有限公司 | A kind of protective device of aeroengine winches transmission mechanism |
| CN108946534A (en) * | 2018-08-10 | 2018-12-07 | 河北环航科技股份有限公司 | A kind of aeroengine winches |
| CN110789724A (en) * | 2019-10-12 | 2020-02-14 | 哈尔滨飞机工业集团有限责任公司 | Flexible towing nacelle retracting and releasing mechanism and method |
| CN116353869A (en) * | 2023-05-25 | 2023-06-30 | 成都庆龙航空科技有限公司 | Unmanned aerial vehicle on-board photoelectricity imaging nacelle |
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|---|---|---|---|---|
| CN106767181A (en) * | 2017-01-13 | 2017-05-31 | 河北环航科技股份有限公司 | A kind of plug-in target nacelle of aviation |
| CN108639351A (en) * | 2018-08-03 | 2018-10-12 | 河北环航科技股份有限公司 | A kind of protective device of aeroengine winches transmission mechanism |
| CN108639351B (en) * | 2018-08-03 | 2024-01-16 | 河北环航科技股份有限公司 | Protection device of aviation winch transmission mechanism |
| CN108946534A (en) * | 2018-08-10 | 2018-12-07 | 河北环航科技股份有限公司 | A kind of aeroengine winches |
| CN108946534B (en) * | 2018-08-10 | 2019-11-29 | 河北环航科技股份有限公司 | A kind of aeroengine winches |
| CN110789724A (en) * | 2019-10-12 | 2020-02-14 | 哈尔滨飞机工业集团有限责任公司 | Flexible towing nacelle retracting and releasing mechanism and method |
| CN116353869A (en) * | 2023-05-25 | 2023-06-30 | 成都庆龙航空科技有限公司 | Unmanned aerial vehicle on-board photoelectricity imaging nacelle |
| CN116353869B (en) * | 2023-05-25 | 2023-08-22 | 成都庆龙航空科技有限公司 | Unmanned aerial vehicle on-board photoelectricity imaging nacelle |
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|---|---|
| CN105539849B (en) | 2017-11-10 |
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