CN109436370A - A kind of floatation characteristic test model - Google Patents
A kind of floatation characteristic test model Download PDFInfo
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- CN109436370A CN109436370A CN201811157480.7A CN201811157480A CN109436370A CN 109436370 A CN109436370 A CN 109436370A CN 201811157480 A CN201811157480 A CN 201811157480A CN 109436370 A CN109436370 A CN 109436370A
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- fuselage
- cabin
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- characteristic test
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to aircraft ditchings to test field, and in particular to a kind of floatation characteristic test model.For general model in the case where weight demands are stringent, intensity is not high, and easily damages.The present invention proposes a kind of floatation characteristic test model, including fuselage, wing and tail, back cabin and underbelly cabin are divided by fuselage floor in its middle fuselage, lifting adjustment system is installed above the middle part in back cabin, lifting lug can front and back adjustment position in the kidney slot of lifting adjustment system；The eminence of fuselage floor is provided with the snorkel of connection upper chamber and underbelly cabin；The underbelly cabin has weepage holes in side and bottom, and the bottom of underbelly bulkhead has the overflow hole for being connected to adjacent cabin；Chequered with black and white waterline scale is coated on the outside of fuselage skin.It can satisfy the demand of harsh experimental condition.
Description
Technical field
The invention belongs to aircraft ditchings to test field, and in particular to a kind of floatation characteristic test model.
Background technique
When civil fixed-wing aircraft certification is collected evidence at this stage, need to carry out ditching experimental study, ditching floating
Attribute testing research aircraft floating on water stability, flotation time and athletic posture, and then analysis of aircraft is in different model states
Under floatation characteristic；Simultaneously according to reasonable possible structural failure and leakage scenarios, the floating for verifying each operating condition of test of aircraft is steady
It is qualitative, determine that floating posture, the draft of aircraft change with time the floatation characteristics such as situation and flotation time.
In floatation characteristic test, test model exists according to the test speed after similarity criterion conversion
Between 10m/s-20m/s, during test, Towing strap movable model high-speed motion after reaching test speed, launches dress
Unhook is set, model is put into water, model dampening stops after sliding, and after model dampening, water flow is entered by the leak source of model
Inside model, observing and nursing constantly intake after floatation characteristic.During the whole test process, model will bear huge water ballast
Lotus has higher requirement to overall weight, the structural strength of model, at the same needed after model dampening the waterline of observation model with
The variation of flotation time entirely after the test needs that the water flow inside model is discharged completely, to carry out examination next time
It tests.
For general model in the case where weight demands are stringent, intensity is not high, and easily damages, and has seriously affected test
It is normally carried out.In order to preferably complete the test demand of ditching floatation characteristic test.Need to design a kind of reasonable examination
Test model, there is enough intensity and rigidity under conditions of as light as possible, at the same model can with fast assembling-disassembling, accurate positioning
Feature, model have the technical requirements such as leak source and waterline scale.
Summary of the invention
The purpose of the present invention is to existing aircraft ditching floatation characteristic test model designing technique backwardnesss, model
The problems such as preponderance, poor intensity, and a kind of floatation characteristic test model proposed.
A kind of floatation characteristic test model, the model include fuselage, wing and tail, are divided in middle fuselage by fuselage floor
For back cabin and underbelly cabin, lifting adjustment system, lifting lug are installed above the middle part in back cabin
Lifting adjustment system kidney slot can front and back adjust position；The eminence of fuselage floor is provided with connection upper chamber and machine
The snorkel in body lower part cabin；The underbelly cabin has weepage holes, and the bottom of underbelly bulkhead in side and bottom
Portion has the overflow hole for being connected to adjacent cabin；Chequered with black and white waterline scale is coated on the outside of fuselage skin.
Fuselage has fuselage skin, and wing has wing cover, and empennage has horizontal tail covering.
It further include that fuselage subdivision plate and several fuselage bulkheads being distributed along longitudinal direction, fuselage bearing beam are worn in the fuselage
Fuselage bulkhead and fixation are crossed, fuselage interior is divided into several seal hatch by the fuselage subdivision plate and fuselage floor.
It include Wing-Body Configurations docking beam, wing bulkhead and wing stringers beam inside wing.
It include that fuselage docks beam, horizontal tail bulkhead peace tail boom inside horizontal tail.
Lifting lug stretches out fuselage skin to outside.
The present invention solve the problems, such as universal model intensity is low, watertightness is poor, test during it is easy to damage be not easily repaired, if
A kind of light-high-strength test model of meter, can satisfy the demand of harsh experimental condition.
The utility model has the advantages that
1. modularized design is easily transported, Yi Xiufu, guarantee test fluency.Each main component of fuselage is all made of modularization
Design is directly connected by connector, easy to assemble, convenient transportation two-by-two.When model damages, broken parts are dismantled, it can be quick
It repairs, when well damage, direct replacement damage component, influence of the reduction model reparation to the test period.
2. model weight is light, intensity is good, model uses high-strength complex material covering, inside is added using lightweight grid beam structure
By force, model overall weight is light, and structural strength is good.
3. model weight is reasonably distributed, model uses combined type grid beam stressed-skin construction, and each equal light material production of component remains
Remaining inertia trim and model position of centre of gravity adjustment compared with weight for model.
4. model inner space is big, model inner space is big, can be used to place gyroscope, acceleration transducer, acquisition
The equipment such as device, battery, it is easy to operate.
Detailed description of the invention
Fig. 1 is the structure axonometric schematic diagram of floatation characteristic test model of the present invention；
Fig. 2 is floatation characteristic test model structure schematic side view of the present invention；
Fig. 3 is underbelly bulkhead structure schematic diagram of the present invention.
Specific embodiment
A parting principle of the present invention is as follows:
Modelling uses modularized design, different from real machine die joint, based on being easily assembled principle, with vertical in being parallel to
Model is split by the plane of section, and model is divided into several big components and is directly connected two-by-two by connector.
B model structure design of the present invention is as follows:
The present invention is by fuselage skin 1, fuselage subdivision plate 2, fuselage floor 3, fuselage bulkhead 4, fuselage bearing beam 5, snorkel
6, wing cover 7, wing bulkhead 8, wing stringers beam 9, Wing-Body Configurations docking beam 10, lifting adjustment system 11, horizontal tail covering 12,
Horizontal tail fuselage docks beam 13, horizontal tail bulkhead 14, horizontal tail beam 15 and forms.
Fuselage subdivision plate 2, fuselage floor 3 are located inside fuselage skin, and fuselage interior is divided into several seal hatch, fuselage
Bulkhead 4 is located inside fuselage skin 1, and outer rim is bonded with fuselage skin inner surface, and fuselage bearing beam 5 sequentially passes through fuselage bulkhead
4, snorkel 6 is fixed on the highest point of fuselage floor 3 vertically, and guaranteeing fuselage, two cabins 19,18 air can mutually circulate up and down,
Wing bulkhead 8 is located inside wing cover 7, and outer rim is bonded with wing cover inner surface, and wing bulkhead 8 passes through wing stringers beam
9 are connected and fixed, and Wing-Body Configurations docking beam 10 is fixed on central fuselage bulkhead, and Wing-Body Configurations dock beam 10 and pass through wing bulkhead 8
On location hole, to be fixedly connected with left and right wing, lifting adjustment system 11 is located at the top of the fuselage bulkhead at middle part, lifting lug stretching
The outside of fuselage skin 1, horizontal tail bulkhead 14 are located inside horizontal tail covering 12, and outer rim is bonded with horizontal tail covering inner surface, horizontal tail
Beam 15 sequentially passes through horizontal tail bulkhead 14, and horizontal tail fuselage docking beam 13 is fixed on aft fuselage bulkhead, and horizontal tail fuselage docks beam 13
Location hole on horizontal tail bulkhead 14, to be fixedly connected with left and right horizontal tail.
C model position of centre of gravity adjusts lifting method:
The working condition different for model needs front and back to adjust model position of centre of gravity.After position of centre of gravity variation, pass through
The kidney slot front and back for lifting by crane adjustment system adjusts lifting lug position, guarantees lifting lug position in model center of gravity.
Interactive construction after d model dampening is as follows:
Model flotation stage after in model investment pond, water enter model from the weepage holes 16 in model bottom and survey face
Internal lower cabin, the snorkel in model guarantee that cabin air communicates up and down, guarantee that water flow can normally enter, by covering outside
The chequered with black and white waterline scale 17 in side, the floatation characteristic of observation analysis model.
The lower edge of underbelly bulkhead 21 is equipped with several overflow holes 20, after guaranteeing that water enters underbelly cabin 18, every
Frame will not influence water flow in the indoor mutual circulation in cabin.After the completion of testing simultaneously, guarantee that water flow can quickly be discharged from model, no
Remnants can be left.
Claims (6)
1. a kind of floatation characteristic test model, it is characterised in that: the model includes fuselage, wing and tail, in middle fuselage by
Fuselage floor (3) is divided into back cabin (19) and underbelly cabin (18), on the middle part of back cabin (19)
Side is equipped with lifting adjustment system (11), and lifting lug can front and back adjustment position in the kidney slot of lifting adjustment system (11)；In machine
The eminence on body floor (3) is provided with the snorkel (6) of connection upper chamber (19) and underbelly cabin (18)；Under the fuselage
Portion cabin (18) has weepage holes (16) in side and bottom, and the bottom of underbelly bulkhead (21) has the adjacent cabin of connection
Overflow hole (20)；Chequered with black and white waterline scale (17) is coated on the outside of fuselage skin.
2. floatation characteristic test model according to claim 1, it is characterised in that: further include fuselage point in the fuselage
Deck board (2) and several fuselage bulkheads (4) being distributed along longitudinal direction, fuselage bearing beam (5) pass through fuselage bulkhead (4) and fix, by
Fuselage interior is divided into several seal hatch by the fuselage subdivision plate (2) and fuselage floor (3).
3. floatation characteristic test model according to claim 2, it is characterised in that: include that Wing-Body Configurations dock inside wing
Beam (10), wing bulkhead (8) and wing stringers beam (9).
4. floatation characteristic test model according to claim 3, it is characterised in that: include that fuselage docks beam inside horizontal tail
(13), the peaceful tail boom (15) of horizontal tail bulkhead (14).
5. floatation characteristic test model according to claim 4, it is characterised in that: lifting lug stretches out fuselage skin (1) outside
Portion.
6. floatation characteristic test model according to claim 5, it is characterised in that: fuselage has fuselage skin (1), wing
With wing cover (7), empennage has horizontal tail covering (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811157480.7A CN109436370B (en) | 2018-09-30 | 2018-09-30 | Floating characteristic test model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811157480.7A CN109436370B (en) | 2018-09-30 | 2018-09-30 | Floating characteristic test model |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109436370A true CN109436370A (en) | 2019-03-08 |
| CN109436370B CN109436370B (en) | 2022-02-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811157480.7A Active CN109436370B (en) | 2018-09-30 | 2018-09-30 | Floating characteristic test model |
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| CN (1) | CN109436370B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017257A (en) * | 2019-12-19 | 2020-04-17 | 中国特种飞行器研究所 | Equivalent simulation method and test system for seepage characteristics |
| CN112706896A (en) * | 2020-12-11 | 2021-04-27 | 中国特种飞行器研究所 | Pool towing test model of air cushion type WIG craft |
| CN112793806A (en) * | 2020-12-30 | 2021-05-14 | 中国特种飞行器研究所 | Fixed-wing aircraft draft line model test device and method |
| CN113525710A (en) * | 2021-07-30 | 2021-10-22 | 中国特种飞行器研究所 | Full-belt power model of amphibious aircraft |
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| JP2004290327A (en) * | 2003-03-26 | 2004-10-21 | Kasatani:Kk | Model helicopter, and operation training device for the same |
| CN104596729A (en) * | 2014-06-26 | 2015-05-06 | 中国特种飞行器研究所 | Test method for ditching towing tank of fixed-wing airplane model |
| CN205340144U (en) * | 2016-01-06 | 2016-06-29 | 上海交通大学 | Empty amphibious telecontrolled aircraft of water |
| CN108382583A (en) * | 2010-06-29 | 2018-08-10 | 航空环境公司 | Has the unmanned vehicle of Packed modularity compartment and fluid discharge port |
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2018
- 2018-09-30 CN CN201811157480.7A patent/CN109436370B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004290327A (en) * | 2003-03-26 | 2004-10-21 | Kasatani:Kk | Model helicopter, and operation training device for the same |
| CN108382583A (en) * | 2010-06-29 | 2018-08-10 | 航空环境公司 | Has the unmanned vehicle of Packed modularity compartment and fluid discharge port |
| CN104596729A (en) * | 2014-06-26 | 2015-05-06 | 中国特种飞行器研究所 | Test method for ditching towing tank of fixed-wing airplane model |
| CN205340144U (en) * | 2016-01-06 | 2016-06-29 | 上海交通大学 | Empty amphibious telecontrolled aircraft of water |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017257A (en) * | 2019-12-19 | 2020-04-17 | 中国特种飞行器研究所 | Equivalent simulation method and test system for seepage characteristics |
| CN112706896A (en) * | 2020-12-11 | 2021-04-27 | 中国特种飞行器研究所 | Pool towing test model of air cushion type WIG craft |
| CN112793806A (en) * | 2020-12-30 | 2021-05-14 | 中国特种飞行器研究所 | Fixed-wing aircraft draft line model test device and method |
| CN112793806B (en) * | 2020-12-30 | 2022-10-11 | 中国特种飞行器研究所 | Fixed-wing aircraft draft line model test device and method |
| CN113525710A (en) * | 2021-07-30 | 2021-10-22 | 中国特种飞行器研究所 | Full-belt power model of amphibious aircraft |
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| Publication number | Publication date |
|---|---|
| CN109436370B (en) | 2022-02-11 |
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