CN109649633B - Fixed wing aircraft casing of easy to assemble and stable of wing frame support ware - Google Patents
Fixed wing aircraft casing of easy to assemble and stable of wing frame support ware Download PDFInfo
- Publication number
- CN109649633B CN109649633B CN201811652366.1A CN201811652366A CN109649633B CN 109649633 B CN109649633 B CN 109649633B CN 201811652366 A CN201811652366 A CN 201811652366A CN 109649633 B CN109649633 B CN 109649633B
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- aircraft
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- 238000005286 illumination Methods 0.000 claims abstract description 8
- 239000002184 metal Substances 0.000 claims description 40
- 239000003381 stabilizer Substances 0.000 claims description 33
- 238000003466 welding Methods 0.000 claims description 23
- 230000000903 blocking effect Effects 0.000 claims description 14
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- 230000008093 supporting effect Effects 0.000 abstract description 14
- 238000005728 strengthening Methods 0.000 abstract 1
- 101001017827 Mus musculus Leucine-rich repeat flightless-interacting protein 1 Proteins 0.000 description 6
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/08—Stabilising surfaces mounted on, or supported by, wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a fixed wing aircraft shell with convenient and stable assembly of a wing frame support, which comprises an aircraft propeller and an aircraft body, wherein the aircraft propeller is fixedly arranged at the middle position of the front end of the aircraft body, two sides of the aircraft propeller are provided with illumination protection covers on the aircraft body, the wing frame support formed by a side arc-shaped block, a middle lug, a top plane block, an inclined plane support column and a bottom fixer is more convenient when being connected, the wing frame support can be well inserted and connected through the middle lug on the top plane block, so that the wing frame support is more convenient when being fixed through a screw, the bottom fixer of the wing frame support is connected to the aircraft body, and the top plane block is fixed on an aircraft flank through the middle lug, so that the inclined plane support column has good tension and supporting effect, and the upper joint is stable through the strengthening of the side arc-shaped block, so that the upper joint is more stable when being used at a high speed.
Description
Technical Field
The invention belongs to the technical field of related fixed-wing aircraft, and particularly relates to a fixed-wing aircraft shell with a convenient and stable assembly of a wing frame support.
Background
The fixed wing aircraft is called an aircraft for short, and refers to an aircraft which is heavier than air and flies in the atmosphere, wherein a power device generates forward pushing force or pulling force, and a fixed wing of a fuselage generates lifting force. It is one, and most commonly one, of fixed wing aircraft, and the other fixed wing aircraft is a glider. Aircraft can be further classified into jet aircraft and propeller aircraft according to the type of engine they use. The airframe structure of an aircraft typically includes wings, a fuselage, a tail wing, and landing gear. If the aircraft engine is not in the fuselage, the nacelle is also part of the airframe structure. With the development of electronic technology, the form of the flight control device has also changed fundamentally. In large aircraft, traditional mechanical steering systems have gradually been replaced by more advanced fly-by-wire steering systems, with computer systems being fully involved in the flight steering system, and the pilot's operation no longer acting like directly steering the aircraft, but rather giving motion instructions to the aircraft.
The existing fixed wing aircraft wing frame support technology has the following problems: 1. the existing fixed wing aircraft wing frame support is not very convenient when fixed on a side wing, one hand is required to hold the wing frame support, and the other hand is required to fix, so that position deviation is easy to occur when the fixed wing aircraft wing frame support is fixed, and the fixed wing aircraft wing frame support is troublesome to install and fix. 2. The existing fixed wing aircraft wing frame support is not stable when supporting the side wing to fly at high speed, and cannot be well supported and fixed, so that the fixed wing aircraft wing frame support is not very convenient when flying at high speed, and is not very safe when being used in driving.
Disclosure of Invention
The invention aims to provide a fixed wing aircraft shell with convenient and stable assembly of a wing frame support, so as to solve the problems that the existing fixed wing aircraft wing frame support provided in the background art is not stable when supporting a side wing to fly at a high speed and the existing fixed wing aircraft wing frame support is not convenient when being fixed on the side wing.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the utility model provides a convenient and stable fixed wing aircraft shell of wing frame support equipment, includes aircraft screw and aircraft organism, the installation of aircraft screw is fixed on the front end intermediate position of aircraft organism, the both sides of aircraft screw are located and are provided with the illumination safety cover on the aircraft organism, illumination safety cover and aircraft organism pass through welded fastening, the lower extreme place ahead of aircraft organism is provided with the aircraft front wheel that takes off and land, aircraft organism and aircraft front wheel that takes off and land pass through inner member swing joint, the rear both sides of aircraft front wheel that takes off and land are located the aircraft organism outside and are provided with the aircraft rear wheel that takes off and land, aircraft rear wheel that takes off and land and aircraft organism pass through inner member swing joint, be provided with the front end observation window in the middle of the front end of aircraft organism, aircraft organism and front end observation window pass through the cross fixed screw to be fixed, the right side of front end observation window is located and is provided with right side cabin door on the aircraft organism, the right cabin door is movably connected with the aircraft body through a hinge, the left side of the front end observation window is positioned on the aircraft body and is provided with a left side observation window, the left side observation window and the aircraft body are fixed through cross fixing screws, the outer side of the upper end of the aircraft body is provided with aircraft wings, the aircraft wings and the aircraft body are fixedly connected through welding, the lower ends of the aircraft wings are provided with wing frame supporters, the lower ends of the wing frame supporters are connected on the aircraft body, the rear sides of the aircraft wings are provided with wing flaps, the aircraft wings and the wing flaps are movably connected through inner members, the inner sides of the wing flaps are positioned on the wing flaps, the aircraft wings and the wing flaps are movably connected through inner members, the outer side of the rear end of the aircraft body is provided with horizontal fixing wings, the horizontal stabilizer is fixedly connected with the aircraft body through welding, the vertical stabilizer is arranged above the rear end of the aircraft body, the vertical stabilizer is fixedly connected with the aircraft body through welding, the rear side of the vertical stabilizer is provided with a metal rudder, and the vertical stabilizer is movably connected with the metal rudder through a member.
Preferably, the aircraft screw includes rotary vane fixer, metal rotary vane, fixer lower block and screw thread dead lever, the outside a week of rotary vane fixer is provided with metal rotary vane, metal rotary vane and rotary vane fixer pass through welded fastening, the lower extreme of rotary vane fixer is provided with the fixer lower block, the lower extreme of rotary vane fixer and fixer lower block passes through welded fastening, the lower extreme of fixer lower block is provided with the screw thread dead lever, the fixer lower block passes through welded fastening with the screw thread dead lever, the screw thread dead lever is connected on the aircraft organism.
Preferably, the metal rudder comprises a fixing member, a rudder shell and an internal reinforcing net, wherein the fixing member is arranged on the inner side of the front end of the rudder shell, the internal reinforcing net is arranged in the rudder shell, and the rudder shell is connected to the vertical fixing wing through the fixing member.
Preferably, the front wheel of taking off and landing of aircraft is including connecting fixed block, metal spliced pole, bottom shell and aircraft tire, the lower extreme of connecting the fixed block is provided with the metal spliced pole, connect fixed block and metal spliced pole through welded fastening connection, the lower extreme of metal spliced pole is provided with the bottom shell, the inside of fixer lower block is provided with the aircraft tire, connect the fixed block to connect on the aircraft organism.
Preferably, the wing frame support comprises a side arc-shaped block, a middle lug, a top plane block, an inclined plane support column and a bottom fixer, wherein the bottom fixer is arranged at the lower end of the inclined plane support column, the inclined plane support column and the bottom fixer are fixedly connected through welding, the top plane block is arranged at the upper end of the inclined plane support column, the inclined plane support column and the top plane block are fixedly connected through welding, a middle lug is arranged in the middle of the upper end of the top plane block, the middle lug and the top plane block are fixedly connected through welding, the side arc-shaped block is arranged at the outer side facility of the upper end of the inclined plane support column, the side arc-shaped block, the middle lug and the top plane block are connected to the aircraft wing, and the bottom fixer is connected to the aircraft body.
Preferably, the horizontal stabilizer comprises a stabilizer shell, a blocking outer ring block and a connecting member, wherein the blocking outer ring block is arranged at the lower end of the stabilizer shell, the connecting member is arranged at the lower end of the blocking outer ring block, and the blocking outer ring block is connected to the aircraft body through the connecting member.
Preferably, the number of the horizontal stabilizer wings is two, the horizontal stabilizer wings are fixedly connected to two sides of the rear end of the aircraft body in parallel, and the horizontal stabilizer wings are horizontally and vertically arranged at the rear end of the aircraft body.
Preferably, the number of the wing frame supports is two, the wing frame supports are symmetrically fixed on two sides of the aircraft body, and the wing frame supports, the aircraft wings and the aircraft body form a triangle shape.
Preferably, the outer shape and the size of the rear end of the vertical fixing wing are equal to those of the inner shape and the size of the front end of the metal rudder, and the vertical fixing wing is vertically fixed on the aircraft body.
Preferably, the number of the side wing ailerons is two, the side wing ailerons are symmetrically fixed in the inner sides of the side wings of the two ends of the airplane body, and the outer sides of the airplane body and the side wings of the airplane are on the same straight line.
Compared with the prior art, the invention provides the fixed wing aircraft shell with convenient and stable assembly of the wing frame support, which has the following beneficial effects:
1. the wing frame support formed by the side arc blocks, the middle convex blocks, the top plane blocks, the inclined plane support columns and the bottom fixing devices is more convenient when being connected, the bottom fixing devices of the wing frame support are connected to the aircraft body and are fixed through the screws, so that the fixed installation is firmer, and when being connected and fixed with the aircraft wings, the wing frame support can be well inserted through the middle convex blocks on the top plane blocks, so that the wing frame support is more convenient when being fixed through the screws, and the assembly of an installer is more convenient.
2. The wing frame support formed by the side arc blocks, the middle convex blocks, the top plane blocks, the inclined plane support columns and the bottom fixing device has a reinforced supporting tension effect, the bottom fixing device of the wing frame support is connected to the aircraft body, and the top plane blocks are fixed on the aircraft side wings through the middle convex blocks, so that the inclined plane support columns have a good tension and supporting effect, the reinforced and stable side arc blocks are used for enabling the joints above to form a stable triangle, and the wing frame support is more stable in high-speed use and convenient for high-speed flight.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate and together with the embodiments of the invention and do not constitute a limitation to the invention, and in which:
FIG. 1 is a schematic view of a fixed wing aircraft shell with a convenient and stable assembly of a wing frame support according to the present invention;
FIG. 2 is a schematic view of an aircraft propeller structure according to the present invention;
FIG. 3 is a schematic view of a metal rudder according to the present invention;
FIG. 4 is a schematic view of the structure of a front wheel of an aircraft;
FIG. 5 is a schematic view of a wing frame support according to the present invention;
FIG. 6 is a schematic view of a horizontal fin according to the present invention;
in the figure: 1. aircraft wings; 2. a flap; 3. a wing flap; 4. a front end observation window; 5. a right cabin door; 6. a left viewing window; 7. a horizontal safety fin; 71. a stator housing; 72. blocking the outer ring block; 73. a connecting member; 8. vertical setting wings; 9. a metal rudder; 91. a fixing member; 92. a rudder housing; 93. an internal reinforcing mesh; 10. a wing frame support; 101. a side arc block; 102. a middle bump; 103. a top planar block; 104. inclined plane support column; 105. a bottom holder; 11. an aircraft propeller; 111. a rotary vane fixer; 112. a metal rotating blade; 113. a retainer lower block; 114. a threaded fixing rod; 12. an illumination shield; 13. front wheels of the aircraft; 131. connecting a fixed block; 132. a metal connection column; 133. a bottom housing; 134. aircraft tires; 14. an aircraft body; 15. the aircraft is landing a rear wheel.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1-6, the present invention provides a technical solution:
the fixed wing aircraft shell with convenient and stable assembly of the wing frame support comprises an aircraft propeller 11 and an aircraft body 14, wherein the aircraft propeller 11 is fixedly arranged at the middle position of the front end of the aircraft body 14, two sides of the aircraft propeller 11 are positioned on the aircraft body 14 and are provided with illumination protection covers 12, the illumination protection covers 12 are fixedly connected with the aircraft body 14 through welding, an aircraft landing front wheel 13 is arranged in front of the lower end of the aircraft body 14, the aircraft body 14 and the aircraft landing front wheel 13 are movably connected through internal components, two rear sides of the aircraft landing front wheel 13 are positioned at the outer side of the aircraft body 14 and are provided with aircraft landing rear wheels 15, the aircraft landing rear wheel 15 and the aircraft body 14 are movably connected through internal components, a front end observation window 4 is arranged in the middle of the front end of the aircraft body 14, the aircraft body 14 and the front end observation window 4 are fixedly arranged through cross fixing screws, the right side of the front end observation window 4 is positioned on the aircraft body 14 and is provided with a right cabin door 5, the right cabin door 5 and the aircraft body 14 are movably connected through a hinge, the left side of the front end observation window 4 is positioned on the aircraft body 14 and is provided with a left observation window 6, the left observation window 6 and the aircraft body 14 are fixed through cross fixing screws, the outer side of the upper end of the aircraft body 14 is provided with an aircraft wing flap 1, the aircraft wing flap 1 and the aircraft body 14 are fixedly connected through welding, the lower end of the aircraft wing flap 1 is provided with a wing frame support 10, the lower end of the wing frame support 10 is connected on the aircraft body 14, the rear side of the aircraft wing flap 1 is provided with a wing flap 2, the aircraft wing flap 1 and the wing flap 2 are movably connected through internal components, the inner side of the wing flap 2 is positioned on the aircraft wing flap 1 and the wing flap 3 are movably connected through internal components, the outside of the rear end of the aircraft body 14 is provided with a horizontal stabilizer 7, the horizontal stabilizer 7 is fixedly connected with the aircraft body 14 through welding, the upper part of the rear end of the aircraft body 14 is provided with a vertical mounting stabilizer 8, the vertical mounting stabilizer 8 is fixedly connected with the aircraft body 14 through welding, the rear side of the vertical mounting stabilizer 8 is provided with a metal rudder 9, and the vertical mounting stabilizer 8 is movably connected with the metal rudder 9 through a member.
Further, the aircraft screw 11 includes the vane fixer 111, the metal vane 112, the fixer lower part 113 and screw thread dead lever 114, the outside a week of vane fixer 111 is provided with the metal vane 112, metal vane 112 and vane fixer 111 pass through welded fastening, the lower extreme of vane fixer 111 is provided with fixer lower part 113, the fixer 111 and fixer lower part 113 pass through welded fastening, the lower extreme of fixer lower part 113 is provided with screw thread dead lever 114, fixer lower part 113 and screw thread dead lever 114 pass through welded fastening, screw thread dead lever 114 connects on aircraft organism 14, screw thread dead lever 114 of aircraft screw 11 connects on aircraft organism 14, so when the internal power device of aircraft organism 14 rotates, will make screw thread dead lever 114 rotate, thereby screw thread dead lever 114 will drive fixer lower part 113 and vane fixer 111 and rotate, the rotation of vane fixer 111 will make metal vane 112 rotate, will provide the air current and use like this.
Further, the metal rudder 9 includes the fixed member 91, the rudder case 92 and the internal reinforcing net 93, the fixed member 91 is provided on the front end inner side of the rudder case 92, the internal reinforcing net 93 is provided on the inside of the rudder case 92, the rudder case 92 is connected to the vertical mounting wing 8 through the fixed member 91, the rudder case 92 of the metal rudder 9 is connected to the vertical mounting wing 8 through the fixed member 91, thereby the control use can be well performed, the use is more convenient, and the internal reinforcing net 93 inside the rudder case 92 has the effect of reinforcing strength.
Further, the front wheel 13 for taking off and landing of the aircraft comprises a connecting fixing block 131, a metal connecting column 132, a bottom shell 133 and an aircraft tire 134, wherein the metal connecting column 132 is arranged at the lower end of the connecting fixing block 131, the connecting fixing block 131 and the metal connecting column 132 are fixedly connected through welding, the bottom shell 133 is arranged at the lower end of the metal connecting column 132, the aircraft tire 134 is arranged in the lower part of the lower fixer block 113, the connecting fixing block 131 is connected to the aircraft body 14, the connecting fixing block 131 of the front wheel 13 for taking off and landing of the aircraft is connected to the aircraft body 14, so that the use is more convenient, the metal connecting column 132 has a good supporting effect, and the aircraft tire 134 at the lower end of the bottom shell 133 is more convenient during sliding, so that the use is more convenient.
Further, the wing frame supporter 10 includes a side arc block 101, a middle bump 102, a top plane block 103, a bevel support column 104 and a bottom fixer 105, the bottom of the bevel support column 104 is provided with the bottom fixer 105, the bevel support column 104 and the bottom fixer 105 are fixedly connected through welding, the upper end of the bevel support column 104 is provided with the top plane block 103, the bevel support column 104 and the top plane block 103 are fixedly connected through welding, a middle bump 102 is arranged in the middle of the upper end of the top plane block 103, the middle bump 102 and the top plane block 103 are fixedly connected through welding, a side arc block 101 is arranged at the outer side facility of the upper end of the bevel support column 104, the side arc block 101, the middle bump 102 and the top plane block 103 are connected on the aircraft wing 1, the bottom fixer 105 is connected on the aircraft body 14, the bottom fixer 105 of the wing frame supporter 10 is connected on the aircraft body 14, so that the wing frame supporter is more convenient in use, and when connected, the wing frame supporter is well inserted through the middle bump 102 on the top plane block 103, so that the wing frame supporter is more convenient in fixing, and the side arc block 101 has a supporting force, so that the wing frame supporter can fly at a higher and more stable at a higher speed.
Further, the horizontal fin 7 includes a fin housing 71, a blocking outer ring block 72 and a connecting member 73, the blocking outer ring block 72 is provided at the lower end of the fin housing 71, the connecting member 73 is provided at the lower end of the blocking outer ring block 72, the blocking outer ring block 72 is connected to the aircraft body 14 through the connecting member 73, the blocking outer ring block 72 of the horizontal fin 7 is connected to the aircraft body 14 through the connecting member 73, so that the connection is more convenient, and the fin housing 71 plays a balancing role, so that the horizontal fin is more stable in use.
Further, two horizontal stabilizer wings 7 are provided, and the horizontal stabilizer wings 7 are fixedly connected to both sides of the rear end of the aircraft body 14 in parallel, and the horizontal stabilizer wings 7 are horizontally perpendicular to the rear end of the aircraft body 14, so that the use is more stable through the functions of the two horizontal stabilizer wings 7.
Further, the number of the wing frame supporters 10 is two, and the wing frame supporters 10 are symmetrically fixed on both sides of the airplane body 14, and the wing frame supporters 10, the airplane wing wings 1 and the airplane body 14 form a triangle shape, so that the wing frame supporters 10 are more stable in use and are more convenient in use.
Further, the outer shape and the inner shape of the rear end of the vertical fixing wing 8 are equal to those of the front end of the metal rudder 9, and the vertical fixing wing 8 is vertically fixed on the airplane body 14, so that the use is more convenient, and the use is convenient for users.
Further, the number of the side wing ailerons 2 is two, and the side wing ailerons 2 are symmetrically fixed in the inner sides of the side wings 1 at the two ends of the airplane body 14, the outer sides of the airplane body 14 and the side wings 1 are on the same straight line, so that the side wing ailerons are more stable in use, and are convenient for users to operate.
The working principle and the using flow of the invention are as follows: when the fixed wing aircraft of the present invention is in use, the aircraft body 14 of the fixed wing aircraft needs to be fuelled to be used on a given runway. The pilot thus opens the right cabin door 5 of the aircraft body 14 to sit in the cabin of the aircraft body 14, and then closes the right cabin door 5 to open the power plant switch of the aircraft body 14. When the power device of the aircraft body 14 is turned on, the aircraft propeller 11 at the front end of the aircraft body 14 rotates, so that reverse acting force is formed, and the aircraft body 14 can well move through the front aircraft landing wheel 13 and the rear aircraft landing wheel 15. When the rotation speed of the aircraft propeller 11 at the front end of the aircraft body 14 reaches a certain take-off speed, the front end of the fixed wing aircraft is lifted up by an operating rod in an operating cabin of the aircraft body 14, and the air flow and the ground are acted by the aircraft wings 1, the wing flap 2, the wing flap 3, the horizontal stabilizer 7, the vertical stabilizer 8 and the metal rudder 9 on the aircraft body 14, so that the aircraft propeller 11 forms an air flow and generates an action force, and the fixed wing aircraft takes off, so that the front and rear wheels are retracted. And when the fixed wing aircraft flies in the air, the outside can be well observed through the left observation window 6 and the front end observation window 4 on the aircraft body 14, so that the control and the use are convenient. While in high speed flight, the fixed wing aircraft passes through the wing frame support 10 under the aircraft wing 1, which makes the aircraft more stable in flight, and the wing frame support 10 is composed of side arc blocks 101, middle lugs 102, top plane blocks 103, inclined plane support columns 104 and bottom retainers 105. The bottom fixing device 105 of the wing frame supporting device 10 is connected to the airplane body 14, so that the wing frame supporting device is more convenient to use, and can be well plugged through the middle protruding block 102 on the top plane block 103 when connected, so that the wing frame supporting device is more convenient to fix, and the side arc blocks 101 have supporting force, so that a triangular stable state is formed above the wing frame supporting device, so that the wing frame supporting device is more stable when used at a high speed, and the wing frame supporting device is convenient for flying at a high speed.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. A fixed wing aircraft shell with a convenient and stable assembly of a wing frame support, comprising an aircraft propeller (11) and an aircraft body (14), characterized in that: the device is characterized in that the aircraft propeller (11) is fixedly arranged at the middle position of the front end of the aircraft body (14), the two sides of the aircraft propeller (11) are positioned on the aircraft body (14) and are provided with the illumination protection cover (12), the illumination protection cover (12) and the aircraft body (14) are fixedly connected through welding, the front part of the lower end of the aircraft body (14) is provided with the front aircraft landing wheel (13), the aircraft body (14) and the front aircraft landing wheel (13) are movably connected through inner components, the rear two sides of the front aircraft landing wheel (13) are positioned at the outer side of the aircraft body (14) and are provided with the rear aircraft landing wheel (15), the rear aircraft landing wheel (15) and the aircraft body (14) are movably connected through inner components, the middle of the front end of the aircraft body (14) is provided with the front end observation window (4), the aircraft body (14) and the front end observation window (4) are fixedly arranged through cross fixing screws, the right side of the front end observation window (4) is positioned on the aircraft body (14) and is movably connected through inner components, the right side aircraft landing door (5) and the left side aircraft landing door (5) are movably arranged on the aircraft body (14) and are movably connected through the left side aircraft cabin (6) and the front aircraft body (6), the aircraft comprises an aircraft body (14), wherein an aircraft wing (1) is arranged on the outer side of the upper end of the aircraft body (14), the aircraft wing (1) and the aircraft body (14) are fixedly connected through welding, a wing frame support (10) is arranged at the lower end of the aircraft wing (1), the lower end of the wing frame support (10) is connected to the aircraft body (14), a wing flap (2) is arranged on the rear side of the aircraft wing (1), the aircraft wing (1) and the wing flap (2) are movably connected through an inner member, a wing flap (3) is arranged on the aircraft wing (1) on the inner side of the wing flap (2), the aircraft wing flap (1) and the wing flap (3) are movably connected through an inner member, a horizontal stabilizer (7) is arranged on the outer side of the rear end of the aircraft body (14), a vertical stabilizer (8) is arranged above the rear end of the aircraft body (14) and is fixedly connected through welding, and the vertical stabilizer (8) and the aircraft body (14) are movably connected through a metal rudder (9) and the vertical stabilizer (8) is arranged in the vertical direction; the wing frame support (10) comprises a side arc block (101), a middle lug (102), a top plane block (103), an inclined plane support column (104) and a bottom fixer (105), wherein the bottom fixer (105) is arranged at the lower end of the inclined plane support column (104), the inclined plane support column (104) and the bottom fixer (105) are fixedly connected through welding, the top plane block (103) is arranged at the upper end of the inclined plane support column (104), the inclined plane support column (104) and the top plane block (103) are fixedly connected through welding, the middle lug (102) is arranged in the middle of the upper end of the top plane block (103), the middle lug (102) and the top plane block (103) are fixedly connected through welding, the side arc block (101), the middle lug (102) and the top plane block (103) are arranged at the outer side of the upper end of the inclined plane support column (104), and the bottom fixer (105) are connected to an airplane wing (1), and the bottom fixer (105) is connected to an airplane body (14); the wing frame supports (10) are arranged in two, the wing frame supports (10) are symmetrically fixed on two sides of the aircraft body (14), and the wing frame supports (10), the aircraft wings (1) and the aircraft body (14) form a triangle shape.
2. A fixed wing aircraft shell of claim 1, wherein the wing frame support is assembled easily and stably, and wherein: the aircraft screw (11) comprises a rotary vane fixer (111), a metal rotary vane (112), a fixer lower block (113) and a threaded fixing rod (114), wherein the metal rotary vane (112) is arranged on the outer side of the rotary vane fixer (111) in a circle, the metal rotary vane (112) and the rotary vane fixer (111) are fixedly connected through welding, the fixer lower block (113) is arranged at the lower end of the rotary vane fixer (111), the rotary vane fixer (111) and the fixer lower block (113) are fixedly connected through welding, the threaded fixing rod (114) is arranged at the lower end of the fixer lower block (113), the fixer lower block (113) is fixedly connected with the threaded fixing rod (114) through welding, and the threaded fixing rod (114) is connected to an aircraft body (14).
3. A fixed wing aircraft shell of claim 1, wherein the wing frame support is assembled easily and stably, and wherein: the metal rudder (9) comprises a fixing member (91), a rudder shell (92) and an internal reinforcing net (93), wherein the fixing member (91) is arranged on the inner side of the front end of the rudder shell (92), the internal reinforcing net (93) is arranged in the rudder shell (92), and the rudder shell (92) is connected to the vertical fixing wing (8) through the fixing member (91).
4. A fixed wing aircraft shell with easy and stable assembly of a wing frame support according to claim 2, wherein: the front wheel (13) of taking off and landing of aircraft is including connecting fixed block (131), metal spliced pole (132), bottom shell (133) and aircraft tire (134), the lower extreme of connecting fixed block (131) is provided with metal spliced pole (132), connect fixed block (131) and metal spliced pole (132) through welded fastening connection, the lower extreme of metal spliced pole (132) is provided with bottom shell (133), the inside of fixer lower block (113) is provided with aircraft tire (134), connect fixed block (131) and connect on aircraft organism (14).
5. A fixed wing aircraft shell of claim 1, wherein the wing frame support is assembled easily and stably, and wherein: the horizontal stabilizer (7) comprises a stabilizer shell (71), a blocking outer ring block (72) and a connecting member (73), wherein the blocking outer ring block (72) is arranged at the lower end of the stabilizer shell (71), the connecting member (73) is arranged at the lower end of the blocking outer ring block (72), and the blocking outer ring block (72) is connected to the aircraft body (14) through the connecting member (73).
6. A fixed wing aircraft shell of claim 1, wherein the wing frame support is assembled easily and stably, and wherein: the two horizontal stabilizer wings (7) are arranged in total, the horizontal stabilizer wings (7) are fixedly connected to two sides of the rear end of the airplane body (14) in parallel, and the horizontal stabilizer wings (7) are horizontally and vertically arranged at the rear end of the airplane body (14).
7. A fixed wing aircraft shell of claim 1, wherein the wing frame support is assembled easily and stably, and wherein: the outer shape and the size of the rear end of the vertical fixing wing (8) are equal to the inner shape and the size of the front end of the metal rudder (9), and the vertical fixing wing (8) is vertically fixed on the aircraft body (14).
8. A fixed wing aircraft shell of claim 1, wherein the wing frame support is assembled easily and stably, and wherein: the two side wing ailerons (2) are arranged in total, the side wing ailerons (2) are symmetrically fixed in the inner sides of the side wings (1) of the two ends of the airplane body (14), and the outer sides of the airplane body (14) and the side wings (1) are positioned on the same straight line.
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| CN201811652366.1A CN109649633B (en) | 2018-12-31 | 2018-12-31 | Fixed wing aircraft casing of easy to assemble and stable of wing frame support ware |
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| CN201811652366.1A CN109649633B (en) | 2018-12-31 | 2018-12-31 | Fixed wing aircraft casing of easy to assemble and stable of wing frame support ware |
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| CN109649633B true CN109649633B (en) | 2023-10-03 |
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| US4121791A (en) * | 1977-07-27 | 1978-10-24 | Taylor Bruce G | Aircraft built up from individual readily assembled and disassembled segments or components |
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| CN208102337U (en) * | 2018-05-03 | 2018-11-16 | 成都云翅科技有限公司 | A kind of telescopic unmanned plane flight support frame structure |
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|---|---|
| CN109649633A (en) | 2019-04-19 |
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