CN109436370B

CN109436370B - Floating characteristic test model

Info

Publication number: CN109436370B
Application number: CN201811157480.7A
Authority: CN
Inventors: 李徐; 焦俊; 江婷; 张科; 屈儒君; 李正
Original assignee: China Special Vehicle Research Institute
Current assignee: China Special Vehicle Research Institute
Priority date: 2018-09-30
Filing date: 2018-09-30
Publication date: 2022-02-11
Anticipated expiration: 2038-09-30
Also published as: CN109436370A

Abstract

The invention belongs to the field of airplane forced landing tests on water, and particularly relates to a floating characteristic test model. Under the condition of strict weight requirement, the general model has low strength and is easy to damage. The invention provides a floating characteristic test model, which comprises a machine body, wings and an empennage, wherein the interior of the machine body is divided into an upper cabin and a lower cabin by a machine body floor; a vent pipe for communicating the upper cabin and the lower cabin of the fuselage is arranged at the high position of the floor of the fuselage; the side and the bottom of the cabin at the lower part of the machine body are provided with leakage holes, and the bottom of the partition frame at the lower part of the machine body is provided with an overflow hole communicated with the adjacent cabins; and a black and white water line scale is coated on the outer side of the fuselage skin. Can meet the requirements of severe test conditions.

Description

Floating characteristic test model

Technical Field

The invention belongs to the field of airplane forced landing tests on water, and particularly relates to a floating characteristic test model.

Background

At the present stage, when the civil fixed-wing aircraft is airworthiness and evidence is obtained, a forced landing test study on water is needed, a forced landing floating characteristic test study on the water surface floating stability, floating time and motion attitude of the aircraft is carried out, and then the floating characteristics of the aircraft in different model states are analyzed; meanwhile, according to reasonable possible structural damage and leakage conditions, the floating stability of each test working condition of the airplane is verified, and the floating characteristics of the airplane, such as the floating attitude, the change condition of draft along with time, the floating time and the like, are determined.

In the floating characteristic test, the test speed of the test model after conversion according to the similarity criterion is all in

And in the test process, the trailer drives the model to move at a high speed, the throwing device is unhooked after the test speed is reached, the model is thrown into water, the model stops after the model is watered and slides, water flows into the model through a leakage source of the model after the model is watered, and the floating characteristic of the model after the model is continuously watered is observed. In whole test process, the model will bear huge water load, has higher requirement to the whole weight of model, structural strength, and the waterline that needs the observation model after the model is watered simultaneously is along with the change of showy time, after whole experiment, needs completely to discharge the inside rivers of model to carry out next experiment.

Under the condition of strict weight requirement, the general model has low strength and is easy to damage, and the normal operation of the test is seriously influenced. In order to better complete the test requirement of the overwater forced landing floating characteristic test. A reasonable test model is needed to be designed, the strength and the rigidity are enough under the condition of being as light as possible, meanwhile, the model can be quickly disassembled and assembled, the positioning is accurate, and the model has the technical requirements of a leakage source, a waterline scale and the like.

Disclosure of Invention

The invention aims to provide a floating characteristic test model aiming at the problems of laggard design technology, overweight model weight, poorer strength and the like of the existing airplane water forced landing floating characteristic test model.

A floating characteristic test model comprises a fuselage, wings and an empennage, wherein the fuselage is divided into an upper cabin and a lower cabin by a fuselage floor, a hoisting adjusting system is arranged above the middle part of the upper cabin, and lifting lugs can be adjusted in position in a waist-shaped hole of the hoisting adjusting system in a front-back manner; a vent pipe for communicating the upper cabin and the lower cabin of the fuselage is arranged at the high position of the floor of the fuselage; the side and the bottom of the cabin at the lower part of the machine body are provided with leakage holes, and the bottom of the partition frame at the lower part of the machine body is provided with an overflow hole communicated with the adjacent cabins; and a black and white water line scale is coated on the outer side of the fuselage skin.

The fuselage has a fuselage skin, the wings have wing skins, and the empennage has a horizontal tail skin.

The fuselage also comprises a fuselage bulkhead plate and a plurality of fuselage bulkheads distributed along the longitudinal direction, the fuselage bearing beam penetrates through the fuselage bulkhead and is fixed, and the fuselage is divided into a plurality of sealed cabins by the fuselage bulkhead plate and the fuselage floor.

The interior of the wing comprises a wing body butt-joint beam, a wing bulkhead and a wing truss beam.

The horizontal tail comprises a butt-joint beam, a horizontal tail spacer frame and a horizontal tail beam.

The lifting lug extends out of the fuselage skin to the outside.

The invention solves the problems of low strength, poor water tightness and easy damage and difficult repair in the test process of a common model, and the designed light high-strength test model can meet the requirements of severe test conditions.

Has the advantages that:

1. the modular design is easy to transport and repair, and the test smoothness is ensured. Each main part of the machine body adopts a modular design, and every two parts are directly connected through a connecting piece, so that the machine body is easy to assemble and disassemble and convenient to transport. When the model is damaged, the damaged part is detached and can be quickly repaired, and when the model is seriously damaged, the damaged part can be directly replaced, so that the influence of model repair on the test period is reduced.

2. The model has light weight and good strength, adopts high-strength composite material skin and is internally reinforced by adopting a light frame beam structure, and the model has light overall weight and good structural strength.

3. The weight distribution of the model is reasonable, the model is of a composite frame beam skin structure, all parts are made of light materials, and the rest weight is used for inertia balancing of the model and adjustment of the gravity center position of the model.

4. The model has large internal space, can be used for placing equipment such as a gyroscope, an acceleration sensor, a collector, a battery and the like, and is easy to operate.

Drawings

FIG. 1 is a schematic view of a structural axis of a floating characteristic test model of the present invention;

FIG. 2 is a schematic side view of a floating characteristic test model according to the present invention;

FIG. 3 is a schematic view of the structure of the bulkhead at the lower part of the fuselage according to the invention.

Detailed Description

The typing principle of the invention is as follows:

the model design adopts the modularized design, is different from the parting surface of a real machine, and is based on the principle of easy assembly to divide the model into a plurality of parts which are connected by connecting pieces directly on the plane parallel to the middle and longitudinal sections.

The model structure design of the invention is as follows:

the invention is composed of a fuselage skin 1, a fuselage subdivision plate 2, a fuselage floor 3, a fuselage bulkhead 4, a fuselage bearing beam 5, a vent pipe 6, a wing skin 7, a wing bulkhead 8, a wing truss girder 9, a wing fuselage butt joint girder 10, a hoisting adjusting system 11, a horizontal tail skin 12, a horizontal tail fuselage butt joint girder 13, a horizontal tail bulkhead 14 and a horizontal tail girder 15.

The fuselage bulkhead 2 and the fuselage floor 3 are positioned inside the fuselage skin to divide the interior of the fuselage into a plurality of sealed cabins, the fuselage bulkhead 4 is positioned inside the fuselage skin 1, the outer edge of the fuselage bulkhead is attached to the inner surface of the fuselage skin, the fuselage load-bearing beam 5 sequentially passes through the fuselage bulkhead 4, the vent pipe 6 is vertically fixed at the highest position of the fuselage floor 3 to ensure that the air in the upper and

lower cabins

19 and 18 of the fuselage can mutually circulate, the wing bulkhead 8 is positioned inside the wing skin 7, the outer edge of the wing bulkhead 8 is attached to the inner surface of the wing skin, the wing bulkhead 8 is fixedly connected through the wing truss girder 9, the wing fuselage butt girder 10 is fixed on the middle fuselage bulkhead, the wing fuselage butt girder 10 passes through a positioning hole on the wing bulkhead 8 to fixedly connect the left and right wings, the hoisting adjusting system 11 is positioned above the middle fuselage bulkhead, the lifting lug extends out of the fuselage skin 1, the horizontal tail frame 14 is positioned inside the horizontal tail skin 12, the outer edge of the horizontal tail is attached to the inner surface of a horizontal tail skin, a horizontal tail beam 15 sequentially penetrates through a horizontal tail bulkhead 14, a horizontal tail fuselage butt-joint beam 13 is fixed on a tail fuselage bulkhead, and the horizontal tail fuselage butt-joint beam 13 penetrates through a positioning hole in the horizontal tail bulkhead 14 to fixedly connect a left horizontal tail and a right horizontal tail.

c, adjusting the model gravity center position:

for different working states of the model, the gravity center position of the model needs to be adjusted forwards and backwards. After the gravity center position changes, the positions of the lifting lugs are adjusted through the waist-shaped holes of the lifting adjusting system, and the lifting lugs are guaranteed to be located at the gravity center of the model.

The action structure of the model after being watered is as follows:

in the model floating stage after the model is put into the water pool, water enters the lower cabin inside the model from the leakage holes 16 at the bottom and the measuring surface of the model, the air pipes in the model ensure that the air of the upper cabin and the air of the lower cabin are communicated, water flow can normally enter the model, and the floating characteristic of the model is observed and analyzed through the waterline scales 17 on the outer side of the skin, wherein the waterlines are black and white.

The lower edge of the lower partition frame 21 of the machine body is provided with a plurality of overflow holes 20, so that after water enters the lower cabin 18 of the machine body, the partition frame does not influence the mutual circulation of water flow in the cabin. Meanwhile, after the test is finished, the water flow can be rapidly discharged from the model, and no residue is left.

Claims

1. A floating characteristic test model is characterized in that: the model comprises a fuselage, wings and a tail wing, wherein the fuselage is provided with a fuselage skin (1), the wings are provided with wing skins (7), and the tail wing is provided with a horizontal tail skin (12); the interior of the fuselage is divided into an upper cabin (19) and a lower cabin (18) by a fuselage floor (3), a lifting adjusting system (11) is arranged above the middle part of the upper cabin (19) of the fuselage, and the lifting lugs can be adjusted in position in the front and back direction in a kidney-shaped hole of the lifting adjusting system (11); a vent pipe (6) which is communicated with the upper cabin (19) and the lower cabin (18) of the fuselage is arranged at the high position of the fuselage floor (3); the side and the bottom of the lower cabin (18) of the machine body are provided with leakage holes (16), and the bottom of the lower bulkhead (21) of the machine body is provided with overflow holes (20) communicated with the adjacent cabins; a black and white water line scale (17) is coated on the outer side of the fuselage skin; the fuselage is characterized by further comprising a fuselage bulkhead plate (2) and a plurality of fuselage bulkheads (4) distributed longitudinally, a fuselage bearing beam (5) penetrates through the fuselage bulkhead (4) and is fixed, and the fuselage is divided into a plurality of sealed cabins by the fuselage bulkhead plate (2) and the fuselage floor (3).

2. The floating property test model of claim 1, wherein: the interior of the wing comprises a wing body butt joint beam (10), a wing bulkhead (8) and a wing truss beam (9).

3. The floating property test model of claim 2, wherein: the horizontal tail comprises a butt-joint beam (13), a horizontal tail bulkhead (14) and a horizontal tail beam (15) inside.

4. The floating property test model of claim 3, wherein: the lifting lug extends out of the fuselage skin (1) to the outside.