CN106585991B - A kind of helicopter suspension beam structure of comprehensive integration - Google Patents
A kind of helicopter suspension beam structure of comprehensive integration Download PDFInfo
- Publication number
- CN106585991B CN106585991B CN201611083583.4A CN201611083583A CN106585991B CN 106585991 B CN106585991 B CN 106585991B CN 201611083583 A CN201611083583 A CN 201611083583A CN 106585991 B CN106585991 B CN 106585991B
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- fixed
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- 239000000725 suspension Substances 0.000 title claims abstract description 36
- 230000010354 integration Effects 0.000 title claims abstract description 15
- 230000005611 electricity Effects 0.000 claims abstract description 13
- 230000005540 biological transmission Effects 0.000 claims abstract description 9
- 230000033001 locomotion Effects 0.000 claims description 6
- 238000002788 crimping Methods 0.000 claims description 4
- 238000013461 design Methods 0.000 abstract description 17
- 230000015556 catabolic process Effects 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 239000000243 solution Substances 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 210000005069 ears Anatomy 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 210000000988 bone and bone Anatomy 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
Classifications
-
- 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
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
-
- 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
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/12—Releasing
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electric Cable Installation (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The present invention provides a kind of helicopter suspension beam structures of comprehensive integration, belong to helicopter suspension design technical field.Including body drop in beam, hanging beam is extended to form for connecting body, and to the direction far from body；Arming unit is fixed in the hanging beam, and the carrier Electricity Federation with suspension；Hitch gear is fixed in the hanging beam by the hanging hook assembly that both ends are arranged, and the hitch gear is at least provided with two hanging points, for hanging carrier；Transmission mechanism is fixed in the hanging beam, and with the hitch gear Electricity Federation；Centralising device is arranged at hanging beam both ends, and is extended with crimp to the carrier direction to carry, and the crimp can be flexible by control, to compress the carrier of suspension.The present invention uses modularized design, and the division of initial breakdown interface matches with the division of production breakdown interface, and structure design uses integration as far as possible, part and connector quantity is reduced, to reduce assembly work amount.
Description
Technical field
The invention belongs to helicopter suspension design technical fields, and in particular to a kind of helicopter drop in beam knot of comprehensive integration
Structure.
Background technique
Carrier suspension arrangement will usually consider the center of gravity and stability of carry object, in the prior art, especially stability
Poor, as helicopter moves, carry object usually shakes more severity, and carry object belongs to tender, can not increase on it
Fixed device.
Summary of the invention
To solve the above-mentioned problems, the present invention provides a kind of helicopter suspension beam structures of comprehensive integration, comprising:
Body drop in beam extends to form hanging beam for connecting body, and to the direction far from body；
Arming unit is fixed in the hanging beam, and the carrier Electricity Federation with suspension；
Hitch gear is fixed in the hanging beam by the hanging hook assembly that both ends are arranged, and the hitch gear is at least set
Hanging point there are two setting, for hanging carrier；
Transmission mechanism is fixed in the hanging beam, and with the hitch gear Electricity Federation；
Centralising device is arranged and is extended with crimp, the crimp at hanging beam both ends, and to the carrier direction to carry
Can be flexible by control, to compress the carrier of suspension.
Preferably, the body drop in beam is set as arc, is articulated on fuselage by four connectors.
In above scheme preferably, crimping locking member is provided on the hanging hook assembly, the fixed institute by way of crimping
State hitch gear.
In above scheme preferably, the centralising device includes two, is separately positioned on the both ends of hanging beam.
In above scheme preferably, any centralising device include shell, setting the intracorporal mobile mechanism of shell with
And two tablettings to extension at suspension carrier, the tabletting are connected to one end of mobile mechanism, the moving machine by rocker arm
The other end of structure stretches out the shell, and threadably controls it in the intracorporal movement of shell.
It in above scheme preferably, further include parachute-opening control mechanism, for opening when helicopter launches suspension carrier
It is connected to the extension umbrella of the suspension carrier.
Key point of the present invention: on the basis of guaranteeing constant with housing construction original interface position, re-optimization design is folded
Formula carrier drop in beam designs comprehensive helicopter hanging rack system using functional module and load drop in beam integral fusion form, realizes
Carrier drop in beam is light-weight, the reasonable demand of space layout.
The characteristics of according to original helicopter suspension arrangement, eliminates traditional aluminum alloy framework form, by each functional module
Directly with combine drop in beam and carry out integrated design, front and rear connector component by 11 M8 bolts and is gone straight up in helicopter suspension arrangement
The connection of machine hanging beam, front and back retainer are connected by 8 M6 bolts with the forward and backward beam for combining drop in beam.
The synthesis helicopter hanging rack system has following advantages:
1. space utilization rate is high: meeting requirement of the fuselage unilateral side installation jettison system to body nodal point and terrain clearance；
2. simple process economy: using modularized design, the division of initial breakdown interface and the division kissing of production breakdown interface
It closes, and structure design uses integration as far as possible, part and connector quantity is reduced, to reduce assembly work amount.Part
Processing is all made of mature manufacturing process, convenient for the connection with housing construction；
3. function uses: overall structure and each functional module can realize fast quick-detach, easy to operate；
4. safety: strong, the rigidity Design of comprehensive hanging rack system have comprehensively considered helicopter and have taken off, land and maximum overload
The stress of each primary structure member under state and strain require, and use safe-life design, guarantee its function, reliable performance.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of a preferred embodiment of the helicopter suspension beam structure of comprehensive integration of the present invention.
Fig. 2 is the body drop in beam of embodiment illustrated in fig. 1 of the present invention and is hanging beam connection schematic diagram.
Fig. 3 is the hanging beam carry equipment schematic diagram of embodiment illustrated in fig. 1 of the present invention.
Wherein, 1 is body drop in beam, and 2 be hanging beam, and 4 be hitch gear, and 5 be transmission mechanism, and 6 be signal controlling machine structure, 7
It is parachute-opening control mechanism for centralising device, 8；
101 be connector；
201 be front-axle beam, and 202 be the back rest, and 203 be intermediate beam, and 204 be maintenance radome fairing
401 be hanging hook assembly, and 402 be hook, and 403 be hanging point；
701 be crimp, and 702 be shell, and 703 be rocker arm.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
The present invention is described in further details below by embodiment.
The present invention uses full modularization, integrated design, and each separate functional unit has independent interchangeability, cancels hanger bone
Frame realizes that helicopter executes task ability, mitigates overall weight to reach drop in beam and the integrated design of suspension arrangement fusion type,
Solve the problems, such as space layout.
This synthesis hanging rack system is mainly made of the part such as combination drop in beam, each module of suspension arrangement and electric appliance component, respectively
Part uses comprehensive integrated design.
The helicopter suspension beam structure of comprehensive integration specifically includes that as shown in Figures 1 and 2
Body drop in beam 1 extends to form hanging beam 2 for connecting body, and to the direction far from body；
Arming unit is fixed in the hanging beam 2, and can be with the carrier Electricity Federation of suspension；
Hitch gear 4 is fixed in the hanging beam 2, the hitch gear 4 by the hanging hook assembly 401 that both ends are arranged
At least provided with two hanging points, for hanging carrier；
Transmission mechanism 5 is fixed in the hanging beam 2, and with 4 Electricity Federation of hitch gear；
Centralising device 7 is arranged and is extended with crimp 701 at 2 both ends of hanging beam, and to the carrier direction to carry, described
Crimp can be flexible by control, to compress the carrier of suspension.
In the present embodiment, body drop in beam 1 is set as arc, to be adapted to the arcuation body fuselage with body lower end, and passes through
At least four connectors are articulated on fuselage, as shown in Figure 1, four connectors 101 are preferably arranged to ears chip architecture, each body is hung
Two are arranged on beam, and is symmetrically distributed in the both ends of arc body drop in beam.
In the present embodiment, hanging beam 2 includes front-axle beam 201, the back rest 202, intermediate beam 203 and maintenance radome fairing 204, front-axle beam
201 and the back rest 202 be main force support structure, the both ends of hanging beam 2 are set, in preferred embodiment, with 1 one of body drop in beam
Design, as the extended segment of body drop in beam 1, alternatively, it uses 7055 high-strength aluminum alloy injection moldings on body drop in beam 1.
In another embodiment of the present invention, a connector 101 of aforementioned any body drop in beam 1 and the front-axle beam 201 or the back rest of hanging beam 2
202 integrated designs only include an ears connector in left side, the ears on right side for forward body drop in beam 1 with reference to Fig. 1
The a part of connector as front-axle beam 201, meanwhile, front-axle beam 201 is fixedly connected with forward body drop in beam 1.For machine rearward
Body drop in beam 1 is also designed using such as upper type.This design load is transferred to fuselage by front-axle beam, the back rest, effectively increases structure benefit
With rate, overall weight is alleviated.
Maintenance radome fairing 204 is hinged on the side of hanging beam 2, which refers to the rectilinear direction where it after front-axle beam direction
Beam can protect hanging beam 2 by maintenance radome fairing 204 when the helicopter suspension beam structure of the comprehensive integration does not mount carrier
Intermediate beam 203 on fixed various electric utilities.
Fixed various electric utilities on intermediate beam 203 as shown in Fig. 2, mainly include hitch gear 4 and transmission mechanism 5,
Hitch gear 4 includes two hanging hook assemblies 401, can install hook 402 between two hanging hook assemblies 401, link up with to carry
Carrier direction extend there are two hanging point 403, it is fixed to carry carrier (not shown) by the hanging point, transmission mechanism 5 with
4 Electricity Federation of hitch gear is used to control hanging point 403 and discharges carrier.
It should be noted that hanging hook assembly 401 is bolted or is clamped with hook 402.Transmission mechanism 5 and hitch gear 4
Electricity Federation is substantially 402 Electricity Federations of transmission mechanism 5 and hook, and hook is laminated structure in the present embodiment, by Electronic control, rather than
The hook structure of the bending shape of conventional meaning, cannot because its name due to limiting structure.
It is understood that each communications cable of above-mentioned Electricity Federation connection is fixed on intermediate beam 203 by way of clip
On, the communications cable is mounted in comprehensive drop in beam, is connect by J599/24JE26PN socket with electric interfaces on machine.
In the present embodiment, with reference to Fig. 2, signal controlling machine structure 6 is additionally provided on intermediate beam 203, with carrier control terminal electricity
Connection, certain carriers need in advance to apply it function signal in release, such as apply image pickup signal, so that the carrier is released
It puts in descent, constantly acquisition image information, at this time, it may be necessary to open the camera function of the carrier by signal controlling machine structure 6
Switch.
Hanging beam 2 is additionally provided with centralising device 7 on the outside of front-axle beam and the back rest, is arranged at 2 both ends of hanging beam, and to carry
Carrier direction be extended with crimp 701, the crimp can be flexible by control, to compress the carrier of suspension, such as Fig. 3 institute
Show.Any centralising device 7 includes shell 702, the intracorporal mobile mechanism of shell is arranged in and extends at carrier to hanging
Two crimps 701, such as round tablet, the tabletting are connected to one end of mobile mechanism, the moving machine by rocker arm 703
The other end of structure stretches out the shell, and threadably controls it in the intracorporal movement of shell.
It is understood that mobile mechanism for example can be screw rod, it is provided with tapped channel in shell, rotates spiral shell
Bar moves it along channel, and one end of screw rod is hinged on one end of rocker arm, the fixed tabletting of the other end of rocker arm 703, rocker arm 703
It is hinged on shell, in turn, when screw rod moves downward the one end for acting on rocker arm 703, the other end of rocker arm (connects tabletting
One end) to opposite counter motion, even if two rocker arms flaring in Fig. 3 becomes larger, otherwise principle is consistent, make two in Fig. 3
Rocker arm flaring becomes smaller.
It is understood that be easy to shake when carrier carry is at hanging point 403, and two above-mentioned tablettings can compress
The both ends of carrier avoid the shaking in carry process.
In alternate embodiment, the movement of screw rod can rotate master gear by using specific purpose tool, and master gear is engagement
The screw rod, so that the rotation by master gear drives screw motion, such as move upwards, rocker arm is promoted, clamps and carry
Body.
It further include parachute-opening control mechanism 8 in the present embodiment, for when helicopter launches suspension carrier, opening to be connected to
The extension umbrella of the suspension carrier.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (5)
1. a kind of helicopter suspension beam structure of comprehensive integration characterized by comprising
Body drop in beam extends to form hanging beam for connecting body, and to the direction far from body；
Arming unit is fixed in the hanging beam, and the carrier Electricity Federation with suspension；
Hitch gear, by both ends be arranged hanging hook assembly be fixed in the hanging beam, the hitch gear at least provided with
Two hanging points, for hanging carrier, wherein crimping locking member is provided on the hanging hook assembly, the fixed institute by way of crimping
State hitch gear；
Transmission mechanism is fixed in the hanging beam, and with the hitch gear Electricity Federation；
Centralising device is arranged and is extended with crimp at hanging beam both ends, and to the carrier direction to carry, and the crimp can
It is flexible by control, to compress the carrier of suspension.
2. the helicopter suspension beam structure of comprehensive integration as described in claim 1, which is characterized in that the body drop in beam setting
For arc, it is articulated on fuselage by four connectors.
3. the helicopter suspension beam structure of comprehensive integration as described in claim 1, which is characterized in that the centralising device includes
Two, it is separately positioned on the both ends of hanging beam.
4. the helicopter suspension beam structure of comprehensive integration as described in claim 1, which is characterized in that any centralising device
Including shell, the intracorporal mobile mechanism of shell is set and to two tablettings extended at suspension carrier, the tabletting is by shaking
Arm is connected to one end of mobile mechanism, and the other end of the mobile mechanism stretches out the shell, and threadably described in control
Mobile mechanism is in the intracorporal movement of shell.
5. the helicopter suspension beam structure of comprehensive integration as described in claim 1, which is characterized in that further include parachute-opening control machine
Structure, for opening the extension umbrella for being connected to the suspension carrier when helicopter launches suspension carrier.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611083583.4A CN106585991B (en) | 2016-11-30 | 2016-11-30 | A kind of helicopter suspension beam structure of comprehensive integration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611083583.4A CN106585991B (en) | 2016-11-30 | 2016-11-30 | A kind of helicopter suspension beam structure of comprehensive integration |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106585991A CN106585991A (en) | 2017-04-26 |
| CN106585991B true CN106585991B (en) | 2019-05-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611083583.4A Active CN106585991B (en) | 2016-11-30 | 2016-11-30 | A kind of helicopter suspension beam structure of comprehensive integration |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2740324C1 (en) * | 2020-06-30 | 2021-01-13 | Акционерное общество "Вятское машиностроительное предприятие "АВИАТЕК" | Universal helical multiple rack |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108454878B (en) * | 2018-04-28 | 2020-08-18 | 成都致冠科技有限公司 | Assembly method of modular unmanned helicopter |
| CN112173066A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Turnover hidden type gunship wing |
| CN112224441A (en) * | 2020-09-25 | 2021-01-15 | 中国直升机设计研究所 | Helicopter is synthesized and is hung roof beam assembly quality |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2506540Y (en) * | 2001-11-07 | 2002-08-21 | 哈尔滨飞机工业(集团)有限责任公司 | External hanging device for helicopter |
| DE202010005311U1 (en) * | 2010-04-27 | 2010-07-29 | Sfs Intec Holding Ag | Fixing system for suspended ceiling containers |
| CN203558215U (en) * | 2013-08-30 | 2014-04-23 | 中国人民解放军海军航空工程学院青岛校区 | Anti-swing device used for helicopter |
| CN204688428U (en) * | 2015-04-27 | 2015-10-07 | 中国直升机设计研究所 | A kind of removable fixation means |
| CN105564661A (en) * | 2014-10-15 | 2016-05-11 | 哈尔滨飞机工业集团有限责任公司 | Transport helicopter task load hanging point |
-
2016
- 2016-11-30 CN CN201611083583.4A patent/CN106585991B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2506540Y (en) * | 2001-11-07 | 2002-08-21 | 哈尔滨飞机工业(集团)有限责任公司 | External hanging device for helicopter |
| DE202010005311U1 (en) * | 2010-04-27 | 2010-07-29 | Sfs Intec Holding Ag | Fixing system for suspended ceiling containers |
| CN203558215U (en) * | 2013-08-30 | 2014-04-23 | 中国人民解放军海军航空工程学院青岛校区 | Anti-swing device used for helicopter |
| CN105564661A (en) * | 2014-10-15 | 2016-05-11 | 哈尔滨飞机工业集团有限责任公司 | Transport helicopter task load hanging point |
| CN204688428U (en) * | 2015-04-27 | 2015-10-07 | 中国直升机设计研究所 | A kind of removable fixation means |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2740324C1 (en) * | 2020-06-30 | 2021-01-13 | Акционерное общество "Вятское машиностроительное предприятие "АВИАТЕК" | Universal helical multiple rack |
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| Publication number | Publication date |
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| CN106585991A (en) | 2017-04-26 |
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