CN102381489A - Fuselage afterbody with large opening at tail part and hatchdoor - Google Patents
Fuselage afterbody with large opening at tail part and hatchdoor Download PDFInfo
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- CN102381489A CN102381489A CN2011101479274A CN201110147927A CN102381489A CN 102381489 A CN102381489 A CN 102381489A CN 2011101479274 A CN2011101479274 A CN 2011101479274A CN 201110147927 A CN201110147927 A CN 201110147927A CN 102381489 A CN102381489 A CN 102381489A
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- hatch door
- hatch
- retractable
- door
- large opening
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Abstract
本发明提供了一种缩比验证机的后机身，其特征在于包括：隔框(102)；蒙皮(101)；舱门，所述舱门为整个后机身下半部的一个大开口。
The invention provides a rear fuselage of a scaling verification machine, which is characterized in that it comprises: a bulkhead (102); a skin (101); Open your mouth.
Description
Technical field
The present invention relates to a kind of contracting, belong to the structure design field of aviation aircraft than the rear body structure design of proof machine.
Background technology
Contract than proof machine and have the flight test model of a series of similarity criterions such as geometrical similarity, kinematic similarity between a kind of and prototype (background type).Existing rear body pattern that contracts than adopts in the proof machine and prototype similarity degree are lower, generally do not have hatch door, can not simulate the dynamic performance of prototype in ground motion and flight course well.Therefore, but need the high rear body that has the folding and unfolding hatch door of a kind of and actual type similarity of research and design, guarantee to contract than proof machine test effect.
Reaching with prototype has higher similarity, promptly better meets the requirement of similarity criterion, the rear body structure of large transport airplane with and layout, the folding and unfolding of hatch door carry out and need understand.The rear door of large transport airplane is generally two sectional type, and the front forms the slope to transferring with ground for one section in handling process, and for the vehicle crew who loads goods and materials provides passage, the hatch door of back is upwards packed up in the hydraulic efficiency pressure system start, for loading and unloading provide the turnover space.
Can not carry out the simple geometric convergent-divergent according to the scheme of prototype fully but contract than the design of proof machine alighting gear; Must be to guaranteeing under the similar situation of Path of Force Transfer; Jack, lockout mechanism to the big opening local strengthening of rear body and hatch door carry out the brand new design, with the requirement of the weight, rigidity, feasibility and the reliability that satisfy miniaturization.
Summary of the invention
According to an aspect of the present invention, provide a kind of and contracted than the rear body of proof machine, it is characterized in that comprising: bulkhead, covering, hatch door, said hatch door are a big opening of whole rear body lower part.
Description of drawings
Fig. 1 is that rear body according to an embodiment of the invention adopts the longeron structure scheme drawing.
Fig. 2 is the rear body bulkhead overall diagram of embodiment shown in Figure 1.
Fig. 3 is a rear body hatch door jack scheme drawing according to an embodiment of the invention.
Fig. 4 is front and back according to an embodiment of the invention hatch door opening scheme drawings.
Fig. 5 is a pneumatic cylinders scheme drawing according to an embodiment of the invention.
Fig. 6 is pneumatic control system pipeline and the schematic diagram of control signal of the folding and unfolding control of hatch door according to an embodiment of the invention.
Fig. 7 is air operated control box according to an embodiment of the invention (containing a hatch door folding and unfolding module) outside drawing.
The specific embodiment
The design of scale model aircraft rear body is owing to will consider and the good similarity of prototype maintenance that therefore the retractable hatch door of one cover system must be arranged.The adding of this cover system has caused various problems.
At first, hatch door is by former and later two component set-ups, and this makes the rear body bottom a very considerable big opening occur, and this distribution of stress for rear body, frame deflection, distortion are to the hatch door folding and unfolding and to the stress of complete machine and creating a great impression of pneumatic distribution.For this reason, need strengthen design, the adverse effect that causes with the big opening of balance to rear body.
Next is the acting device of this cover system.What the packing up of prototype/returning device was used is hydraulic efficiency pressure system, but because hydraulic system structure is complicated, and weight is big, is not suitable for undersized contracting than proof machine, therefore must seek light more simple folding and unfolding power.For this reason, the present invention adopts pneumatics to realize draw-in and draw-off function.
The present invention realizes through the appropriate design to the local reinforcement of rear body hatch door periphery, hatch door and hatch door extension and retraction system.
The technical scheme of practical implementation of the present invention below is described.
1) rear body integral structure
As shown in Figure 1, adopt in the longeron structure at rear body according to an embodiment of the invention, whole rear body structure comprises covering (101), bulkhead (102) and hatch door (103).Whole rear body lower part is big opening, i.e. a hatch door position.Owing to the existence of big opening is arranged, therefore need around opening, carry out local structure and strengthen.
2) hatch door and draw off gear
Hatch door is divided into front door (103) and rear door (104) (Fig. 3).As shown in Figure 3, in according to one embodiment of present invention, the anterior and big open front of front door (103) is hinged (201) with hinge, and midway location and anterior pressurized strut (203) connect; Rear door (104) rear portion is hinged (211) with hinge with big open rear section, and the middle part is made tube (206) with the rear portion and linked to each other.Hatch door adopts the form framework of horizontal vertical rib to form, and guaranteeing has enough intensity and toughnesses.In the connection of hinge hinge with pressurized strut bonded assembly position local the reinforcement arranged all.
Generally contract than the acting device that does not have similar prototype on the aircraft or acting device is very simple; For example adopt steering wheel on the model of an airplane etc.; For simulating the state of true aircraft as much as possible, the present invention adopts pneumatic acting device to replace complicated heavy hydraulic efficiency pressure system.
The present invention contracts and is made up of pneumatic cylinders, tracheae, Pneumatic controller etc. than the acting device on the proof machine.Its principle of work is: the pneumatic cylinders of locating at initial time front door (103) and rear door (104) is in initial position, and the front and back hatch door combines closely.When receiving control signal, the interior air pressure of the pneumatic tube (203) that Pneumatic controller is located front door (103) increases, and makes connecting rod (208) the drive front door (103) of pressurized strut below deflect down definite angle; Simultaneously, the interior air pressure of the pneumatic tube (206) that Pneumatic controller is located rear door (104) reduces, and the connecting rod of this below is upwards shunk, and drives rear door (104) and upward deflects definite angle around its hinge, has so just realized the unlatching of hatch door, and is as shown in Figure 4.It is identical with open theory that hatch door is packed up process.
3) pneumatic control system
Design-calculated pneumatic control system principal feature has been hatch door folding and unfolding controllable function integrated among the present invention, has the function of hatch door folding and unfolding adjustable-speed simultaneously.The schematic diagram of this system pipeline and control signal is shown in 6.
The medium and small frame of broken lines of Fig. 7 is the pneumatic control switch assembly, adopts two tunnel threeway micro computer control valves and airplane model steering engine to combine, can be through the folding of steering wheel by-pass valve control, and this method is simple and reliable.In the ground hatch door folding and unfolding process, requirement can realize the adjustable of hatch door folding and unfolding speed, therefore in hatch door folding and unfolding pipeline pipeline, has added flow regulating valve, in order to the speed of control system power element on true aircraft.The main body of this pneumatic control system---air operated control box exact shape is as shown in Figure 7; Being provided with two gas source interfaces above is extension and retraction system gas source interface (402); Extension and retraction system Pressure monitoring table (405), hatch door folding and unfolding pressurized strut interface a plurality of delivery conduit interfaces such as (403) also have switch steering wheel control signal input interface (404) and folding and unfolding speed setting knob (401) simultaneously.Under the control of this pneumatic control system, can realize that hatch door packs up reliably and put down, and regulate folding and unfolding speed, its folding and unfolding process is steadily carried out, reduce to act on structural impact load, improve system reliability.
Beneficial effect
Advantage of the present invention comprises:
-rear body project organization is reasonable, and load-carrying capacity is strong, lightweight construction, and load-carrying efficient is high; The front and back hatch door is pneumatic start, and total system is simple and reliable for structure, and can simulate the hatch door folding and unfolding process of true aircraft preferably.
The module of hatch door folding and unfolding that-pneumatic control system is integrated is convenient to structure miniaturization, integrated; In hatch door folding and unfolding pilot piping, be provided with governor valve, realize the adjusting of hatch door folding and unfolding time, can reduce the suffered impact load of structure in the folding and unfolding process simultaneously.
The adjustable length of connecting rod in the-jack, but the manufacturing errors of the pneumatic on one's body tube of straightener attachment point spacing prevents to install internal stress housing construction is produced harmful effect.
Through instance embodiment of the present invention is described below:
As shown in Figure 3, for the present invention contracts than the rear body draw off gear scheme drawing of proof machine, the front and back hatch door is connected through hinge with fuselage, and acting device is connected with attachment lug (204) on the hatch door of front and back through connecting rod.Be screwed into the length of thread of joint through regulating folding and unfolding pressurized strut piston rod (302) then, make pressurized strut piston rod (302) eject fully with situation about pushing back fully under guarantee before (back) hatch door pack up (putting down) and lock and put down the position that (packing up) locks.
Then the pressure gas conduit with suitable length and caliber connects the pneumatic pilot line between air operated control box (shown in Figure 7), the front and back hatch door folding and unfolding pressurized strut.
With signal wire (SW) each control signal input interface in the corresponding signal passage of remote control receiver and the air operated control box is linked to each other then; And on telecommand equipment, adjust the stroke (telecommand equipment that the telecommand equipment of mentioning uses common model airplane to use gets final product) of each control channel here, reach and on telecommand equipment, can control the purpose that each switch opens and closes.
Connect source of the gas and adjust the pipeline gaseous tension.
So just accomplished the installation of total system, this hatch door extension and retraction system just can be applied to contract than the ground experiment of proof machine and flight test.On telecommand equipment, pull the switch of corresponding control channel when needing, the folding and unfolding of hatch door before and after can realizing.The movement relation of each parts is seen the detailed description of technical scheme part in the hatch door folding and unfolding process.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101479274A CN102381489A (en) | 2011-06-02 | 2011-06-02 | Fuselage afterbody with large opening at tail part and hatchdoor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101479274A CN102381489A (en) | 2011-06-02 | 2011-06-02 | Fuselage afterbody with large opening at tail part and hatchdoor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102381489A true CN102381489A (en) | 2012-03-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011101479274A Pending CN102381489A (en) | 2011-06-02 | 2011-06-02 | Fuselage afterbody with large opening at tail part and hatchdoor |
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| CN (1) | CN102381489A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103552695A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Test method for verifying opening and closing functions of cargo door |
| CN108284969A (en) * | 2015-10-21 | 2018-07-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft pressure measuring unit |
| CN110356541A (en) * | 2019-06-11 | 2019-10-22 | 江西昌河航空工业有限公司 | A kind of light-high-strength helicopter tail gate structure |
| CN114093211A (en) * | 2021-11-05 | 2022-02-25 | 河北汉光重工有限责任公司 | Full-section cargo hold roll-on training rack of conveyer |
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| CN101102931A (en) * | 2004-11-23 | 2008-01-09 | E·小埃洛 | Freight airplane |
| CN101374721A (en) * | 2006-01-17 | 2009-02-25 | 空中客车德国有限公司 | Structuring construction for an aircraft fuselage |
| CN201633918U (en) * | 2010-01-07 | 2010-11-17 | 哈尔滨飞机工业集团有限责任公司 | Passenger and cargo mixed aircraft cabin |
| CN101977811A (en) * | 2008-03-03 | 2011-02-16 | 空中客车运作有限责任公司 | Fuselage structure for aircraft |
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2011
- 2011-06-02 CN CN2011101479274A patent/CN102381489A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101102931A (en) * | 2004-11-23 | 2008-01-09 | E·小埃洛 | Freight airplane |
| CN101374721A (en) * | 2006-01-17 | 2009-02-25 | 空中客车德国有限公司 | Structuring construction for an aircraft fuselage |
| CN101977811A (en) * | 2008-03-03 | 2011-02-16 | 空中客车运作有限责任公司 | Fuselage structure for aircraft |
| CN201633918U (en) * | 2010-01-07 | 2010-11-17 | 哈尔滨飞机工业集团有限责任公司 | Passenger and cargo mixed aircraft cabin |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103552695A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Test method for verifying opening and closing functions of cargo door |
| CN108284969A (en) * | 2015-10-21 | 2018-07-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft pressure measuring unit |
| CN110356541A (en) * | 2019-06-11 | 2019-10-22 | 江西昌河航空工业有限公司 | A kind of light-high-strength helicopter tail gate structure |
| CN114093211A (en) * | 2021-11-05 | 2022-02-25 | 河北汉光重工有限责任公司 | Full-section cargo hold roll-on training rack of conveyer |
| CN114093211B (en) * | 2021-11-05 | 2024-04-12 | 河北汉光重工有限责任公司 | Rolling-on training bench for full-section cargo hold of conveyor |
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Application publication date: 20120321 |