CN113525710A - Full-belt power model of amphibious aircraft - Google Patents
Full-belt power model of amphibious aircraft Download PDFInfo
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- CN113525710A CN113525710A CN202110869610.5A CN202110869610A CN113525710A CN 113525710 A CN113525710 A CN 113525710A CN 202110869610 A CN202110869610 A CN 202110869610A CN 113525710 A CN113525710 A CN 113525710A
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Abstract
The invention belongs to the technical field of water power of amphibious aircrafts, and relates to a full-aircraft-powered model of an amphibious aircraft. The weight and rotational inertia of the model are similar to those of a real aircraft meeting the Fourier requirement; a fuselage part main body, a fuselage part tail, a wing part, a flap part, a vertical fin part and a horizontal tail part are all of a structure with carbon fiber tubes connected in series with a partition frame; the model is formed by processing carbon fiber glass fiber reinforced plastic composite materials, carbon fiber tubes, aviation laminates, Korean pine, aluminum alloy parts and other materials, the requirements of a pool towing test are met, and it is guaranteed that the model has good strength and water tightness.
Description
Technical Field
The invention belongs to the technical field of hydrodynamic force of amphibious aircraft, and relates to a full-belt power model of the amphibious aircraft.
Background
At present, only a wave resistance full-aircraft power model pool test method of a water surface aircraft and a full-aircraft unpowered model pool test method of wave resistance of the water surface aircraft are related, but the design structure of a specific test model is not explained. How to design the model structure also relates to the smooth proceeding of the experiment for the important components for completing various water experiments.
Disclosure of Invention
The purpose of the invention is as follows:
the whole-belt power model of the amphibious aircraft is provided to meet the requirement of a weight gravity center rotational inertia test based on a similar relation and can be used in the above pool test method.
The technical scheme is as follows:
in a first aspect, there is provided an all-terrain power model of an amphibious aircraft, comprising: the model comprises a fuselage part 1, a wing part 2, a flap part 3, a buoy part 4, a vertical tail part 5, a horizontal tail part 6 and a bulge part 7, wherein the weight and the rotational inertia of the model are similar to those of a real machine in a Froude-satisfaction manner; the main body and the tail part of the fuselage component 1, the wing component 2, the flap component 3, the vertical tail component 5 and the horizontal tail component 6 are all of the structures of carbon fiber tube series connection separation frames; the nose part of the fuselage component 1 is provided with 1-4 parts of Korean pine, 1-4 parts of Korean pine are provided with 1-5 parts of navigation sheets, the middle part of the fuselage component 1 is provided with 1-8 parts of straight handles, and a bulkhead in the middle part of the main body of the fuselage component 1 is connected with a bulkhead of the wing component 2; the aircraft wing partition frame 2-2 near the engine compartment is structurally combined to form an engine motor compartment 2-4, a motor is arranged in the engine motor compartment 2-4 and is connected with a propeller 2-5 and a propeller cover 2-6 to drive the propeller 2-5 to rotate, so that tension is provided for a full-engine-driven power model; a flap skin 2-6 of the flap part 3 is adhered to the flap bulkhead 3-2, and the flap part 3 is adhered to the wing part 2 by adopting a wood block; the pontoon part 4 and the wing part 2 are bonded through a wing pontoon wood block 4-4; the carbon fiber tube in the vertical tail part 5 is inserted into the carbon fiber tube at the tail part of the fuselage component 1 and is connected with the fuselage component 1; the horizontal tail part 6 is connected to the vertical tail part 5 through a bulkhead; the bulge part 7 is bonded to the fuselage part 1 through bulge skins 7-2 by silicon adhesive, the skins of the model are carbon fiber composite material skins, and the number of carbon fiber layers close to the water surface is larger than that of carbon fiber layers far away from the water surface.
Further, the main body of the fuselage component 1 comprises a fuselage transverse bulkhead 1-1, a first carbon fiber pipe 1-2, a fuselage stringer 1-3, a horizontal bulkhead 1-6 and a second carbon fiber pipe 1-7, wherein the fuselage transverse bulkhead 1-1 and the first carbon fiber pipe 1-2 are arranged in the fuselage and are fixed in a crossed mode, the fuselage transverse bulkhead 1-1 is fixed in a crossed mode with the fuselage stringer 1-3 respectively before and after a step of step, and the horizontal bulkhead 1-6 and the second carbon fiber pipe 1-7 are fixed in a vertically crossed mode at the tail portion of the fuselage component 1 and are used for installing the vertical tail component 5.
Further, the transverse partition frames 1-1 of the machine body are uniformly distributed along the length direction of the machine body, and the distance between the transverse partition frames is properly reduced near the center of gravity.
Further, the wing part 2 comprises a third carbon fiber pipe 2-1, a wing partition frame 2-2 and a wing and body connecting partition frame 2-3, wherein the wing and body connecting partition frame 2-3 is connected with the body part 1, two transversely arranged ends of the third carbon fiber pipe 2-1 are respectively connected with two ends of the wing part 2, and the wing partition frame 2-2 and the third carbon fiber pipe 2-1 of the aviation laminate are fixed in a crossed mode.
Furthermore, the buoy part 4 comprises a flap spacer frame 4-1, 2 buoy wood blocks 4-2, a fourth carbon fiber pipe 4-3 and a wing buoy wood block 4-4, wherein the flap spacer frame 4-1 and the 2 buoy wood blocks 4-2 are bonded, the buoy wood block 4-2 is connected to the wing buoy wood block 4-4 through the fourth carbon fiber pipe 4-3, and the wing buoy wood block 4-4 is bonded to the intersection position of the wing spacer frame 2-2 and the third carbon fiber pipe 2-1.
Further, the vertical fin part 5 is formed by fixing 2 fifth carbon fiber tubes 5-1 and a vertical fin bulkhead 5-2 of the aviation laminate in a crossing manner; the fifth carbon fiber tube 5-1 is connected to the fuselage component 1 by being inserted into the second carbon fiber tube 1-7.
Further, the horizontal tail part 6 is formed by fixing 2 sixth carbon fiber tubes 6-1 and vertical tail partition frames 6-2 and 6-3 of aviation laminates in a crossed mode.
Further, the upper surface of the fuselage component 1 is provided with 2 layers of upper fuselage skins 1-9 made of carbon fiber 1 layer glass fiber reinforced plastic composite materials, the lower surface of the fuselage component 1 is provided with 3 layers of lower fuselage skins 1-10 made of carbon fiber 1 layer glass fiber reinforced plastic composite materials, the surface of the wing component 2 is provided with 2 layers of wing skins 2-7 made of carbon fiber composite materials, the surface of the bulge component 7 is provided with 2 layers of bulge skins 7-2 made of carbon fiber 1 layer glass fiber reinforced plastic composite materials, and the surface of the horizontal tail component 6 is provided with 1 layer of horizontal tail skins 6-4 made of carbon fiber composite materials; the surface of the float bowl part 4 is provided with 2 layers of float bowl skins 4-5 made of carbon fiber composite materials, and the surface of the flap part 3 is provided with 2 layers of flap skins 2-6 made of carbon fiber composite materials.
Has the advantages that:
the full-belt power model of the amphibious aircraft provided by the invention is characterized in that the fuselage part 1, the wing part 2, the vertical tail part 5 and the horizontal tail part 6 all adopt carbon fiber tubes as main body structures of all the partition frames connected in series, and are processed by carbon fiber glass reinforced plastic composite materials, carbon fiber tubes, aviation laminates, pinus koraiensis, aluminum alloy pieces and other materials, so that the requirements of a pool towing test are met, and the model is ensured to have good strength and water tightness.
Drawings
FIG. 1 is a schematic structural diagram of a full-belt power model component of an amphibious aircraft.
Fig. 2 is a schematic view of the internal structure of the fuselage section 1.
Fig. 3 is a schematic view of the skin of the fuselage component 1.
FIG. 4 is a schematic view of a 1-frame fuselage transverse bulkhead 1-1.
Fig. 5 is a schematic view of the internal structure of the wing part 2.
Figure 6 is a schematic view of the skin and dynamics of the wing component 2.
Figure 7 is a schematic view of a wing bulkhead 2-2.
Fig. 8 is a schematic view of the internal structure of the wing part 3 and the flap skin 3-3.
Fig. 9 is a schematic view of the internal structure of the buoy member 4.
Fig. 10 is a schematic view of the buoy member 4 assembled.
Fig. 11 is a schematic view of the internal structure of the vertical fin member 5.
Figure 12 is a schematic view of the vertical fin bulkhead 5-2.
Fig. 13 is a schematic view of the internal structure of the horizontal tail member 6.
FIG. 14 is a schematic view of the bulkhead 6-2 with a flat tail.
FIG. 15 is a schematic view of a vertical tail skin 5-3 and a horizontal tail skin 6-4.
Figure 16 is a schematic view of the pontoon bulkhead 7-1 and the pontoon skin 7-2.
FIG. 17 is a schematic view of the pontoon bulkhead 7-1.
Wherein, the aircraft comprises an aircraft body component 1, a wing component 2, a flap component 3, a buoy component 4, a vertical tail component 5, a horizontal tail component 6, a bulge component 7, an aircraft body transverse bulkhead 1-1, a first carbon fiber pipe 1-2, an aircraft body stringer 1-3, a Korean pine 1-4, a navigation sheet 1-5, a horizontal bulkhead 1-6, a second carbon fiber pipe 1-7, a straight handle 1-8, an aircraft body upper skin 1-9, an aircraft body lower skin 1-10, an installation hole 1-1-1, a lightening hole 1-1-2, a butt joint groove 1-3, a third carbon fiber pipe 2-1, an aircraft wing bulkhead 2-2, an aircraft body connecting bulkhead 2-3, an engine compartment 2-4, a propeller 2-5, a propeller cover 2-6, a propeller cover 2-3, a propeller cover 2-8, a propeller cover 2-3, a propeller cover 2-2, a propeller cover 1, a second carbon fiber pipe, a third carbon fiber pipe, a second carbon fiber pipe, a third carbon fiber pipe, a second carbon fiber pipe, a third carbon fiber pipe, a second carbon fiber pipe, a third carbon fiber pipe, a second carbon fiber pipe, a third carbon fiber, a third, 2-7 parts of wing skin, 2-2-1 parts of mounting holes, 2-2-2 parts of lightening holes, 3-1 parts of flap bulkheads, 3-2 parts of flap stringers, 3-3 parts of flap skin, 4-1 parts of flap bulkheads, 4-2 parts of pontoon wood blocks, 4-3 parts of fourth carbon fiber tubes, 4-4 parts of wing pontoon wood blocks, 4-5 parts of pontoon skin, 5-1 parts of fifth carbon fiber tubes, 5-2 parts of vertical tail bulkheads, 5-2-1 parts of mounting holes, 5-2-2 parts of lightening holes, 5-3 parts of vertical tail skin, 6-1 parts of sixth carbon fiber tubes, 6-2 parts of vertical tail bulkheads, 6-2-1 parts of mounting holes, 6-2-2 parts of lightening holes, 6-3 parts of horizontal tail vertical tail bulkheads, 6-4 parts of horizontal tail skin, 7-1 parts of drum bag bulkheads, 7-1 parts of vertical tail bulkheads, and the like, And 7-2 of swelling skin.
Detailed Description
The technical solution of the present invention is further explained with reference to the drawings and the detailed description. According to the characteristics of a full-aircraft-belt power model of an amphibious aircraft, the shape of the amphibious aircraft is drawn out of a shell in three-dimensional modeling software, and the shape is divided into a fuselage part 1, a wing part 2, a flap part 3, a buoy part 4, a vertical tail part 5, a horizontal tail part 6 and a bulge part 7, as shown in figure 1.
Referring to figure 2, the fuselage component 1 body is formed by cross-assembling a 10-frame 3mm thick aircraft laminate fuselage transverse bulkhead 1-1 with 2 2.6 m long, 40mm diameter first carbon fibre tubes 1-2. The whole is uniformly distributed, the distance between the centers of gravity is properly reduced,
the transverse frame 1-1 of the fuselage is respectively combined with the stringers 1-3 of the fuselage with the height of 10mm and the thickness of 3mm in a crossing way before and after the step-off so as to increase the structural strength of the bottom of the fuselage component 1.
As shown in figure 4, the transverse bulkhead 1-1 of the fuselage is provided with a mounting hole 1-1-1 reserved for a first carbon fiber pipe 1-2, a lightening hole 1-1-2 and a butt joint groove 1-1-3 reserved for a stringer 1-3 of the fuselage.
The head part of the machine body component 1 is provided with 1-4 parts of Korean pine, and 1-5 parts of navigation sheet of aluminum alloy with thickness of 3mm are arranged on the 1-4 parts of Korean pine.
The tail part of the fuselage component 1 is provided with a horizontal bulkhead 1-6, and two second carbon fiber tubes 1-7 with the inner diameter of 12mm are vertically arranged on the horizontal bulkhead 1-6 and are used as installation interfaces of the vertical tail component 5.
The middle of the machine body component 1 is provided with a straight handle 1-8 which is used for being connected with a two-degree-of-freedom device in a pool test to realize pitching heave motion of the model along the gravity center.
The upper surface of the fuselage component 1 is bonded to the fuselage transverse bulkhead 1-1 by adopting 2 layers of carbon fiber and 1 layer of glass fiber reinforced plastic composite material, and the lower surface of the fuselage component 1 is bonded to the fuselage transverse bulkhead 1-1 by adopting 3 layers of carbon fiber and 1 layer of glass fiber reinforced plastic composite material, namely, the fuselage lower skin 1-10.
As shown in fig. 5, the wing part 2 is formed by the crossed combination of 3 third carbon fiber tubes 2-1 with the diameter of 20mm and 1 third carbon fiber tube with the diameter of 30mm and a wing bulkhead frame 2-2 of a 12-frame aviation laminate with the thickness of 3 mm; the wing component 2 is connected with the fuselage component 1 through a wing fuselage connection bulkhead 2-3; the wing bulkhead 2-2 near the engine compartment is combined with a plurality of aviation laminate structures to form an engine motor compartment 2-4.
As shown in figure 7, the wing bulkhead 2-2 is provided with a mounting hole 2-2-1 and a lightening hole 2-2-2 reserved for the third carbon fiber pipe 2-1.
As shown in fig. 6, a motor is arranged in a motor cabin 2-4 of the engine, and the motor is connected with a propeller 2-5 and a propeller cover 2-6; the motor drives the propellers 2-5 to rotate, so that tension is provided for the whole machine-driven power model.
The upper surface of the wing part 2 is bonded on the wing bulkhead 2-2 by adopting 2 layers of wing skins 2-7 made of carbon fiber composite materials.
As shown in fig. 8, the flap component 3 is formed by crosswise combining a flap bulkhead 3-1 of a 3-frame aviation laminate with the thickness of 3mm and a flap stringer 3-2 of a 1-frame aviation laminate with the thickness of 3mm, the left flap component 3 and the right flap component 3 are symmetrical, and the surface of the flap component 3 is adhered to the flap bulkhead 3-2 by adopting 2 layers of flap skins 3-3 made of carbon fiber composite materials; after the flap part 3 adjusts the flap angle, the flap part is adhered to the wing part 2 by adopting a balsa wood block.
As shown in figure 9, the buoy part 4 is formed by bonding a flap spacer frame 4-1 of an aviation laminate with the thickness of 2 frames and 3mm and 2 buoy wood blocks 4-2, wherein the buoy wood blocks 4-2 are connected to wing buoy wood blocks 4-4 through fourth carbon fiber pipes 4-3 with the diameter of 10mm, and the wing buoy wood blocks 4-4 are bonded to the positions where the wing spacer frame 2-2 and the third carbon fiber pipes 2-1 intersect, so that the buoy part 4 is connected to the wing part 2.
As shown in fig. 10, the pontoon components 4 are bonded to the flap formers 4-1 by 2 layers of pontoon skins 4-5 of carbon fiber composite material.
As shown in fig. 11, the vertical fin part 5 is formed by cross-combining 2 fifth carbon fiber tubes 5-1 with the diameter of 12mm and a vertical fin bulkhead 5-2 of a 4-frame aviation laminate with the thickness of 3 mm; the fifth carbon fiber tube 5-1 is connected to the fuselage component 1 by being inserted into the second carbon fiber tube 1-7.
As shown in FIG. 12, the vertical fin bulkhead 5-2 is provided with a mounting hole 5-2-1 and a lightening hole 5-2-2 reserved for the fifth carbon fiber pipe 5-1.
The vertical fin component 5 is formed by bonding 1 layer of vertical fin skin 5-3 made of carbon fiber composite materials on a vertical fin bulkhead 5-2.
As shown in fig. 13, the horizontal tail part 6 is formed by cross-combining 2 sixth carbon fiber tubes 6-1 with the diameter of 12mm and a vertical tail bulkhead 6-2 of an 8-frame aviation laminate with the thickness of 3 mm;
the horizontal tail part 6 is connected to the vertical tail part 5 through a horizontal tail vertical tail bulkhead 6-3 of a 2-frame aviation laminate with the thickness of 3 mm; the horizontal tail part 6 rotates around the sixth carbon fiber pipe 6-1, and a horizontal tail angle is integrally formed.
As shown in FIG. 14, the horizontal tail bulkhead 6-2 is provided with a mounting hole 6-2-1 and a lightening hole 6-2-2 reserved for the sixth carbon fiber pipe 6-1.
As shown in figure 15, the horizontal tail part 6 is formed by adhering 1 layer of horizontal tail skin 6-4 made of carbon fiber composite material to a horizontal tail bulkhead 6-2.
The fuselage component 1, the wing component 2, the vertical tail component 5 and the horizontal tail component 6 all adopt carbon fiber tubes as main body structures which are connected with all the bulkheads in series.
As shown in fig. 16 and 17, the bulge part 7 adopts 2 layers of carbon fiber and 1 layer of glass fiber reinforced plastic composite material to adhere the bulge skin 7-2 on the bulge bulkhead 7-1; the bulge isolation frame 7-1 is provided with lightening holes 7-1-1; the bulge element 7 is attached to the fuselage element 1 by way of a bulge skin 7-2 around its circumference by means of a silicone adhesive.
As shown in fig. 3, the upper surface of the fuselage component 1 adopts 2 layers of carbon fiber and 1 layer of glass fiber reinforced plastic composite material fuselage upper skin 1-9, and the lower surface of the fuselage component 1 adopts 3 layers of carbon fiber and 1 layer of glass fiber reinforced plastic composite material fuselage lower skin 1-10; the upper surface of the wing part 2 adopts 2 layers of wing skins 2-7 made of carbon fiber composite materials; the surface of the flap part 3 adopts 2 layers of flap skins 3-3 made of carbon fiber composite materials; the buoy part 4 adopts 2 layers of buoy skins made of carbon fiber composite materials 4-5; the vertical fin component 5 adopts 1 layer of vertical fin covering 5-3 made of carbon fiber composite material; the horizontal tail part 6 adopts 1 layer of horizontal tail skin 6-4 made of carbon fiber composite material; the bulge part 7 adopts 2 layers of carbon fiber and 1 layer of bulge skin 7-2 made of glass fiber reinforced plastic composite material; the general principle is that the number of carbon fiber layers is increased when the carbon fiber layer is close to the water surface, and the number of carbon fiber layers is reduced when the carbon fiber layer is far away from the water surface.
Claims (8)
1. An all-terrain power model of an amphibious aircraft, comprising: the model comprises a fuselage component (1), a wing component (2), a flap component (3), a buoy component (4), a vertical tail component (5), a horizontal tail component (6) and a bulge component (7), wherein the weight and the moment of inertia of the model are similar to those of a real machine in terms of satisfying Froude; the main body and the tail of the fuselage component (1), the wing component (2), the flap component (3), the vertical tail component (5) and the horizontal tail component (6) are all structures of carbon fiber tubes connected in series with bulkheads; the nose part of the fuselage component (1) is provided with a head part pinus koraiensis (1-4), the head part pinus koraiensis (1-4) is provided with a navigation sheet (1-5), the middle part of the fuselage component (1) is provided with a straight handle (1-8), and a partition frame in the middle of the main body of the fuselage component (1) is connected with a partition frame of the wing component (2); the aviation laminate structure of the wing separation frame (2-2) near the engine compartment is combined to form an engine motor compartment (2-4), a motor is arranged in the engine motor compartment (2-4), and the motor is connected with a propeller (2-5) and a propeller cover (2-6) to drive the propeller (2-5) to rotate, so that tension is provided for a full-engine-driven power model; the flap cover (2-6) of the flap part (3) is adhered to the flap frame (3-2), and the flap part (3) is adhered to the wing part (2) by adopting a wood block; the buoy part (4) is bonded with the wing part (2) through a wing buoy wood block (4-4); the carbon fiber tube in the vertical tail part (5) is inserted into the carbon fiber tube at the tail part of the machine body part (1) and is connected with the machine body part (1); the horizontal tail part (6) is connected to the vertical tail part (5) through a bulkhead; the bulge component (7) is bonded to the fuselage component (1) through bulge skins (7-2) by adopting silica gel, the skins of the model are carbon fiber composite material skins, and the number of carbon fiber layers close to the water surface is larger than that of carbon fiber layers far away from the water surface.
2. The model according to claim 1, characterized in that the fuselage component (1) body comprises a fuselage transverse bulkhead (1-1), a first carbon fiber tube (1-2), a fuselage stringer (1-3), a horizontal bulkhead (1-6), a second carbon fiber tube (1-7), wherein the fuselage transverse bulkhead (1-1) and the first carbon fiber tube (1-2) are arranged inside the fuselage and fixed crosswise, the fuselage transverse bulkhead (1-1) is fixed crosswise with the fuselage stringer (1-3) respectively before and after a step break, and the horizontal bulkhead (1-6) and the second carbon fiber tube (1-7) are fixed crosswise vertically at the tail of the fuselage component (1) for mounting the vertical tail component (5).
3. A model according to claim 1, characterized in that the fuselage transverse formers (1-1) are distributed uniformly over the length of the fuselage, with a suitably reduced spacing near the centre of gravity.
4. The model according to claim 1, characterized in that the wing part (2) comprises a third carbon fiber tube (2-1), a wing bulkhead (2-2) and a wing-body connection bulkhead (2-3), wherein the wing-body connection bulkhead (2-3) is connected with the body part (1), the third carbon fiber tube (2-1) is transversely arranged, two ends of the third carbon fiber tube are respectively connected with two ends of the wing part (2), and the wing bulkhead (2-2) of the aviation laminate is fixed with the third carbon fiber tube (2-1) in a crossing manner.
5. The model of claim 4, wherein the pontoon parts (4) comprise a flap spacer frame (4-1), 2 pontoon wooden blocks (4-2), a fourth carbon fiber pipe (4-3) and a wing pontoon wooden block (4-4), wherein the flap spacer frame (4-1) and the 2 pontoon wooden blocks (4-2) are bonded, the pontoon wooden block (4-2) is connected to the wing pontoon wooden block (4-4) through the fourth carbon fiber pipe (4-3), and the wing pontoon wooden block (4-4) is bonded to the intersection position of the wing spacer frame (2-2) and the third carbon fiber pipe (2-1).
6. A former according to claim 1, characterised in that the vertical fin member (5) is formed by the crosswise fixing of 2 fifth carbon fibre tubes (5-1) and a vertical fin box (5-2) of an aerospace laminate; the fifth carbon fiber tube (5-1) is connected to the body member (1) by being inserted into the second carbon fiber tube (1-7).
7. A former according to claim 1, characterised in that the horizontal tail member (6) is formed by 2 sixth carbon fibre tubes (6-1) secured across the aircraft laminate vertical tail former (6-2) and horizontal tail vertical tail former (6-3).
8. The model according to claim 1, wherein the upper surface of the fuselage component (1) is 2 layers of carbon fiber 1 layer glass fiber reinforced plastic composite fuselage upper skin (1-9), the lower surface of the fuselage component (1) is 3 layers of carbon fiber 1 layer glass fiber reinforced plastic composite fuselage lower skin (1-10), the surface of the wing component (2) is 2 layers of carbon fiber composite wing skin (2-7), the surface of the bulge component (7) is 2 layers of carbon fiber 1 layer glass fiber reinforced plastic composite bulge skin (7-2), and the surface of the horizontal tail component (6) is 1 layer of carbon fiber composite horizontal tail skin (6-4); the surface of the float bowl part (4) is provided with 2 layers of float bowl skins (4-5) made of carbon fiber composite materials, and the surface of the flap part (3) is provided with 2 layers of flap skins (2-6) made of carbon fiber composite materials.
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| CN202110869610.5A CN113525710B (en) | 2021-07-30 | 2021-07-30 | Full-belt power model of amphibious aircraft |
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| CN202110869610.5A CN113525710B (en) | 2021-07-30 | 2021-07-30 | Full-belt power model of amphibious aircraft |
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