CN106585991A - Comprehensively integrated helicopter suspended beam structure - Google Patents
Comprehensively integrated helicopter suspended beam structure Download PDFInfo
- Publication number
- CN106585991A CN106585991A CN201611083583.4A CN201611083583A CN106585991A CN 106585991 A CN106585991 A CN 106585991A CN 201611083583 A CN201611083583 A CN 201611083583A CN 106585991 A CN106585991 A CN 106585991A
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- Prior art keywords
- suspension beam
- carrier
- helicopter
- suspension
- hanging
- Prior art date
- 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.)
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- 239000000725 suspension Substances 0.000 claims abstract description 47
- 230000007246 mechanism Effects 0.000 claims abstract description 21
- 230000005540 biological transmission Effects 0.000 claims abstract description 9
- 230000010354 integration Effects 0.000 claims description 13
- 230000005611 electricity Effects 0.000 claims description 10
- 238000002788 crimping Methods 0.000 claims description 4
- 238000013461 design Methods 0.000 abstract description 19
- 239000000969 carrier Substances 0.000 abstract description 5
- 230000000712 assembly Effects 0.000 abstract description 3
- 238000000429 assembly Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 3
- 230000006835 compression Effects 0.000 abstract 2
- 238000007906 compression Methods 0.000 abstract 2
- 230000003247 decreasing effect Effects 0.000 abstract 2
- 238000000926 separation method Methods 0.000 abstract 2
- 238000004880 explosion Methods 0.000 abstract 1
- 230000008520 organization Effects 0.000 description 4
- 210000005069 ears Anatomy 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011435 rock Substances 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 210000000988 bone and bone Anatomy 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000000243 solution Substances 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)
- Aerials With Secondary Devices (AREA)
- Electric Cable Installation (AREA)
Abstract
The present invention provides a comprehensively integrated helicopter suspended beam structure, and belongs to the technical field of helicopter suspension design. The comprehensively integrated helicopter suspended beam structure comprises body suspended beams which are used for connecting with a body and extend in the direction away from the body to form a suspension beam; an explosion control mechanism which is fixed to the suspension beam and electrically connected to suspended carriers; a hook mechanism which is fixed to the suspension beam through hook assemblies provided on the both ends; a transmission mechanism which is fixed on the suspension beam and electrically connected with the hook mechanism; and centering devices which are provided at the both ends of the suspension beam and extend into the direction of carriers to be suspended to form compression joint parts. The hook mechanism is provided with at least two suspending points for suspending the carriers, and the compression joint parts can be controlled to be telescoped to compress the suspended carriers. The modular design is adopted, the division of the design separation surface is consistent with the division of the process separation surface, the structural design employs integrity to the maximum, the number of parts and connectors is decreased, and the assembly workload is thus decreased.
Description
Technical field
The invention belongs to helicopter suspension design technical field, and in particular to a kind of helicopter drop in beam knot of comprehensive integration
Structure.
Background technology
Carrier suspension arrangement will generally consider the center of gravity and stability of carry thing, in prior art, particularly stability
Poor, as helicopter is moved, carry thing generally rocks more severe, and carry thing belongs to tender, it is impossible to increase thereon
Fixing device.
The content of the invention
In order to solve the above problems, the invention provides a kind of helicopter suspension beam structure of comprehensive integration, including：
Body drop in beam, for connecting body, and extends to form suspension beam to the direction away from body；
Arming unit, be fixed on it is described suspension beam on, and with hang carrier Electricity Federation；
Hitch gear, the hanging hook assembly arranged by two ends is fixed on the suspension beam, and the hitch gear at least sets
Two hanging points are equipped with, for hanging carrier；
Transmission mechanism, be fixed on it is described suspension beam on, and with the hitch gear Electricity Federation；
Centralising device, is arranged on suspension beam two ends, and is extended with crimp, the crimp to the carrier direction for treating carry
Can be flexible by control, to compress the carrier of suspension.
Preferably, the body drop in beam is set to arc, is articulated on fuselage by four joints.
In such scheme preferably, crimping locking member is provided with the hanging hook assembly, institute is fixed by crimping mode
State hitch gear.
In such scheme preferably, the centralising device includes two, is separately positioned on the two ends for hanging beam.
In such scheme preferably, arbitrary centralising device include housing, the travel mechanism being arranged in housing with
And to two compressing tablets of extension at carrier are hung, the compressing tablet is connected to one end of travel mechanism, the moving machine by rocking arm
The other end of structure stretches out the housing, and threadably controls its motion in housing.
In such scheme preferably, also including parachute-opening controlling organization, for when helicopter is thrown in and hangs carrier, opening
It is connected to the extension umbrella of the suspension carrier.
Key point of the present invention：On the basis of ensureing and housing construction original interface position is constant, re-optimization design is folded
Formula carrier drop in beam, using functional module and load drop in beam integral fusion form, designs comprehensive helicopter hanging rack system, realizes
Carrier drop in beam is lightweight, the favorably situated demand in space.
According to the characteristics of original helicopter suspension arrangement, traditional aluminum alloy framework form is eliminated, by each functional module
Directly with combine drop in beam and carry out integrated design, in helicopter suspension arrangement before and after adapter assembly is by 11 M8 bolts and goes straight up to
Machine hangs beam connection, and in front and back retainer is connected by 8 M6 bolts with the forward and backward beam for combining drop in beam.
The comprehensive helicopter hanging rack system possesses advantages below：
1. space availability ratio is high：Meet the unilateral requirement for installing jettison system to body nodal point and terrain clearance of fuselage；
2. process is simple economy：Using modularized design, the division of initial breakdown interface and the division kissing of production breakdown interface
Close, and structure design has adopted integration as far as possible, part and connector quantity is reduced, so as to reduce assembly work amount.Part
Processing using ripe manufacturing process, is easy to the connection with housing construction；
3. function is used：Overall structure and each functional module can realize fast quick-detach, simple to operate；
4. security：Strong, the rigidity Design of comprehensive hanging rack system has considered helicopter and has taken off, lands and maximum overload
The stress of each primary structure member under state and strain requirement, employ safe-life design, it is ensured that its function, dependable performance.
Description of the drawings
Fig. 1 is the structural representation 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 to hang beam connection diagram.
Fig. 3 is the suspension beam carry equipment schematic diagram of embodiment illustrated in fig. 1 of the present invention.
Wherein, 1 is body drop in beam, and 2 to hang beam, and 3 is arming unit, and 4 is hitch gear, and 5 is transmission mechanism, and 6 are letter
Number controlling organization, 7 is centralising device, and 8 is parachute-opening controlling organization；
101 is joint；
201 is front-axle beam, and 202 is the back rest, and 203 is intermediate beam, and 204 is to safeguard radome fairing
401 is hanging hook assembly, and 402 are hook, and 403 is hanging point；
701 is crimp, and 702 is housing, and 703 is rocking arm.
Specific embodiment
To make purpose, technical scheme and the advantage of present invention enforcement clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than the embodiment of whole.It is exemplary below with reference to the embodiment of Description of Drawings, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " is based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than indicate or imply the dress of indication
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The restriction of scope.
The present invention is described in further details below by embodiment.
The present invention adopts full modularization, integrated design, each separate functional unit to have independent interchangeability, cancels hanger bone
Frame, to reach drop in beam and suspension arrangement fusion type integrated design, realizes that helicopter performs task ability, mitigates overall weight,
Solve space Layout Problem.
This comprehensive hanging rack system is mainly made up of the part such as combination drop in beam, each module of suspension arrangement and electric appliance component, respectively
Part adopts comprehensive integrated design.
The helicopter suspension beam structure of comprehensive integration, as shown in Figures 1 and 2, mainly includes：
Body drop in beam 1, for connecting body, and extending to the direction away from body suspension beam 2 is formed；
Arming unit 3, is fixed on the suspension beam 2, and can be with the carrier Electricity Federation for hanging；
Hitch gear 4, the hanging hook assembly 401 arranged by two ends is fixed on the suspension beam 2, the hitch gear 4
At least provided with two hanging points, for hanging carrier；
Transmission mechanism 5, be fixed on it is described suspension beam 2 on, and with the Electricity Federation of the hitch gear 4；
Centralising device 7, is arranged on suspension beam 2 two ends, and is extended with crimp 701 to the carrier direction for treating 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 to arc, to be adapted to the arcuation body fuselage with body lower end, and passes through
At least four joints are articulated on fuselage, as shown in figure 1, four joints 101 are preferably arranged to ears chip architecture, each body is hung
Two are arranged on beam, and is symmetrically distributed in the two 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 safeguards radome fairing 204, front-axle beam
201 and the back rest 202 be main force support structure, be arranged on the two ends for hanging beam 2, in preferred embodiment, the one of itself and body drop in beam 1
Design, as the extension of body drop in beam 1, or, it adopts 7055 high-strength aluminum alloy injection moldings on body drop in beam 1.
In another embodiment of the present invention, a joint 101 of aforementioned arbitrary body drop in beam 1 and the front-axle beam 201 or the back rest that hang beam 2
202 Integral designs, with reference to Fig. 1, for forward body drop in beam 1, it only includes an ears joint in left side, the ears on right side
Joint as front-axle beam 201 a part, 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 adopted by upper type such as and designs.This design load is transferred to fuselage by front-axle beam, the back rest, effectively increases structure profit
With rate, overall weight is alleviated.
Safeguard that radome fairing 204 is hinged on the side for hanging beam 2, after the side refers to that its rectilinear direction being located is pointed to along front-axle beam
Beam, when the helicopter suspension beam structure of the comprehensive integration does not mount carrier, can be by safeguarding that beam 2 is hung in the protection of radome fairing 204
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, between two hanging hook assemblies 401 can mounting hook 402, link up with to treating carry
Carrier direction be extended with two hanging points 403, fixed by the hanging point and treat carry carrier (not shown), transmission mechanism 5 with
The Electricity Federation of hitch gear 4, it is used to control the release vehicle of hanging point 403.
It should be noted that hanging hook assembly 401 and 402 bolt connections of hook or clamping.Transmission mechanism 5 and hitch gear 4
Electricity Federation be substantially transmission mechanism 5 with hook 402 Electricity Federations, in the present embodiment hook be laminated structure, its by Electronic control, rather than
The hook structure of the bending shape of conventional meaning, it is impossible to the limiting structure because of its name.
It is understood that each communications cable of above-mentioned Electricity Federation connection is fixed on intermediate beam 203 by the form of clip
On, the communications cable is arranged in comprehensive drop in beam, is connected with electric interfaces on machine by J599/24JE26PN sockets.
In the present embodiment, with reference to Fig. 2, signal controlling machine structure 6 is additionally provided with intermediate beam 203, itself and carrier control end are electric
Connection, in release, needs apply in advance function signal to some carriers to it, for example, apply image pickup signal, so that the carrier is released
In putting descent, image information is constantly gathered, at this time, it may be necessary to pass through the camera function that signal controlling machine structure 6 opens the carrier
Switch.
Hang beam 2 and centralising device 7 is additionally provided with the outside of front-axle beam and the back rest, be arranged on suspension beam 2 two ends, and to treating 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 institutes
Show.Arbitrary centralising device 7 includes housing 702, the travel mechanism being arranged in housing and to extension at suspension carrier
Two crimps 701, such as round tablet, the compressing tablet is connected to one end of travel mechanism, the moving machine by rocking arm 703
The other end of structure stretches out the housing, and threadably controls its motion in housing.
It is understood that travel mechanism can be for example screw rod, tapped passage is provided with housing, rotates spiral shell
Bar makes it move along passage, and one end of screw rod 3 is hinged on one end of rocking arm, and the other end of rocking arm 703 fixes compressing tablet, rocking arm
703 are hinged on housing, and then, when screw rod 3 moves downward the one end for acting on rocking arm 703, the other end (the connection pressure of rocking arm
One end of piece) to contrary counter motion, even if two rocking arm enlargings in Fig. 3 become big, otherwise principle is consistent, in making Fig. 3
Two rocking arm enlargings diminish.
It is understood that when carrier carry is at hanging point 403, easily rock, and two above-mentioned compressing tablets can be compressed
The two ends of carrier, it is to avoid rocking in carry process.
In alternate embodiment, the motion of screw rod can rotate master gear by using specific purpose tool, and master gear is engagement
The screw rod, so as to the rotation for passing through master gear drives screw motion, for example, move upwards, rocking arm is lifted, clamp and carry
Body.
In the present embodiment, also including parachute-opening controlling organization 8, for when helicopter is thrown in and hangs carrier, opening to be connected to
The extension umbrella for hanging carrier.
It is last it is to be noted that：Above example only to illustrate technical scheme, rather than a limitation.To the greatest extent
Pipe has been described in detail with reference to the foregoing embodiments to the present invention, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or equivalent is carried out to which part technical characteristic and replaced
Change；And these modifications or replacement, do not make the essence of the essence disengaging various embodiments of the present invention technical scheme of appropriate technical solution
God and scope.
Claims (6)
1. the helicopter suspension beam structure of a kind of comprehensive integration, it is characterised in that include：
Body drop in beam, for connecting body, and extends to form suspension beam to the direction away from body；
Arming unit, be fixed on it is described suspension beam on, and with hang carrier Electricity Federation；
Hitch gear, by two ends arrange hanging hook assembly be fixed on it is described suspension beam on, the hitch gear at least provided with
Two hanging points, for hanging carrier；
Transmission mechanism, be fixed on it is described suspension beam on, and with the hitch gear Electricity Federation；
Centralising device, is arranged on suspension beam two ends, and is extended with crimp to the carrier direction for treating 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 claimed in claim 1, it is characterised in that the body drop in beam is arranged
For arc, it is articulated on fuselage by four joints.
3. the helicopter suspension beam structure of comprehensive integration as claimed in claim 1, it is characterised in that set on the hanging hook assembly
Crimping locking member is equipped with, the hitch gear is fixed by crimping mode.
4. the helicopter suspension beam structure of comprehensive integration as claimed in claim 1, it is characterised in that the centralising device includes
Two, it is separately positioned on the two ends for hanging beam.
5. the helicopter suspension beam structure of comprehensive integration as claimed in claim 1, it is characterised in that arbitrary centralising device
Including housing, the travel mechanism being arranged in housing and to two compressing tablets for hanging extension at carrier, the compressing tablet is by shaking
Arm is connected to one end of travel mechanism, and the other end of the travel mechanism stretches out the housing, and threadably control its
Motion in housing.
6. the helicopter suspension beam structure of comprehensive integration as claimed in claim 1, it is characterised in that also including parachute-opening control machine
Structure, for when helicopter is thrown in and hangs carrier, opening to be connected to the extension umbrella of the 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 true CN106585991A (en) | 2017-04-26 |
| CN106585991B CN106585991B (en) | 2019-05-03 |
Family
ID=58594242
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611083583.4A Active CN106585991B (en) | 2016-11-30 | 2016-11-30 | A kind of helicopter suspension beam structure of comprehensive integration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106585991B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108454878A (en) * | 2018-04-28 | 2018-08-28 | 成都致冠科技有限公司 | A kind of assembly method of Modularized 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 |
Families Citing this family (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 |
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 (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108454878A (en) * | 2018-04-28 | 2018-08-28 | 成都致冠科技有限公司 | A kind of assembly method of Modularized 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106585991B (en) | 2019-05-03 |
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