CN113060269A - Pneumatic layout of tandem tilting canal type boat wing airship - Google Patents
Pneumatic layout of tandem tilting canal type boat wing airship Download PDFInfo
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- CN113060269A CN113060269A CN202110379118.XA CN202110379118A CN113060269A CN 113060269 A CN113060269 A CN 113060269A CN 202110379118 A CN202110379118 A CN 202110379118A CN 113060269 A CN113060269 A CN 113060269A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/20—Rigid airships; Semi-rigid airships provided with wings or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
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Abstract
The utility model provides a pneumatic overall arrangement of tandem channel formula boat wing airship of verting, has a set of channel formula boat wing of verting through stationary vane installation section and hull connection respectively in the both sides of airship hull, including left front wing and left back wing, right front wing and right back wing to each boat wing is interior wing section, semi-ring wing section and outer wing section three-section. The airship is provided with four power devices, the four power devices are respectively arranged on the upper surface of each tilting canal type airship wing and are positioned in the semi-ring wing section of the airship wing. The semi-ring wing section is provided with a propeller disc which vertically flows, when the propeller rotates at a high speed, high-speed airflow is generated behind the propeller disc and flows through the upper part of the semi-ring wing section, and low-speed airflow is arranged below the semi-ring wing section. From Bernoulli's law, low-speed incompressible fluid increases pressure at an increased speed, and decreases pressure at a decreased speed. Therefore, the high-speed airflow on the upper surface of the half-ring wing section generates a low-pressure area above the boat wing, the low-speed airflow below the half-ring wing section generates a high-pressure area in the boat wing, the upper and lower pressure difference generates great lift force at the canal type boat wing, the canal type boat wing is endowed with high lift characteristic, and the defects that the lift force generated during low-speed flight of the boat wing in the prior art is smaller and the weight of the airship structure is increased are effectively overcome.
Description
Technical Field
The invention relates to the field of airship, in particular to a pneumatic layout of a serial tilting canal type airship wing airship.
Background
An airship belongs to a type of aerostat, and is an aircraft which provides lift by using a lighter-than-air gas, such as hydrogen, helium and the like. The traditional airship has the characteristics of long idle time, low operation cost, strong load-carrying capacity and the like. Traditional airships use propeller thrust for direct force control, but generally use a flat plate connected propeller motor. The CN201921163202.2 patent provides a stratospheric airship, which uses flat boat wings to connect the airship and propeller ducts. CN205952280U provides a wide body variable wing's stratospheric airship, and the screw of the airship of this patent and boat wing are independent each other, and the boat wing adopts the flat-plate wing section, lays solar cell panel on the flat-plate wing section. CN106516074A provides a deformable lifting and floating integrated aircraft aerodynamic configuration design, the aircraft lift consists of static lift and dynamic lift, the static lift is generated by the fuselage, the dynamic lift is generated by the wings, the wings are positioned on the upper part of the fuselage, the front wing and the rear wing are designed identically, a single wing is a straight wing with a large aspect ratio, and the fuselage section is a combination of two semi-ellipses. This patent uses only a flat wing or attached propeller or as a separate lifting surface, the wing itself having some structural weight but producing little lift at low speeds. CN 201367113Y is a rise and float integrative semihard formula dirigible, characterized by have one run through the rigidity fossil fragments of hull center pin, this fossil fragments and the head and the tail awl of dirigible constitute semihard formula structure, and hull both sides have a pair of rotatable dynamic lift wing. The wing aspect ratio of the aircraft is small, and the effect of increasing the dynamic lift force is limited. CN 212022950U is a distributed power airship, including buoyancy gasbag, a plurality of vector power system and control system, the vector power system includes a plurality of vector mechanism, power device and screw, a plurality of vector mechanism locate the buoyancy gasbag both sides. CN 111846191A provides a combination power dirigible, including the gasbag skeleton, the gasbag has wrapped up in outside the gasbag skeleton, the both sides of gasbag skeleton all are connected with preceding main rotor support and back main rotor support, every side all be provided with the side rotor support between preceding main rotor support and the back main rotor support, the side rotor leg joint in on the gasbag skeleton.
Above each patent configuration all is the mode of ordinary airship additional screw, though be favorable to solving the instability problem of traditional airship, the aerodynamic configuration of airship is not good, and the airship resistance increases, and structural weight increases for the payload of airship reduces, and bearing capacity descends.
Disclosure of Invention
The invention provides a pneumatic layout of a serial tilting canal type boat wing airship, aiming at the defects that the lift force generated by the boat wing of the existing airship during low-speed flight is small and the structural weight of the airship is increased.
The invention takes the flying direction of an airship as the front, the airship is a plane-symmetric geometric body, and the two sides of the flying direction are respectively the left side and the right side; the top of the forward end of the airship hull is taken as an installation reference point of the externally hanging part and is marked as O. A right-hand coordinate system for describing geometrical parameters of the airship is established at a point O, an x axis is positioned in a symmetrical plane of the airship and points to the rear of the airship horizontally and backwards, a z axis is positioned in a symmetrical plane of the airship and vertically and upwards, a y axis is perpendicular to an x-z plane and points to the right side of the airship and meets a right-hand rule, the airship comprises a hull, airship wings, an empennage and a power device, wherein the airship wings are positioned on two sides of the hull, the displacement is positioned at a tail section of the hull, and the power device is installed on the surfaces of the airship wings. The invention is technically characterized in that the hull is in an ellipsoid shape, and the cross section and the longitudinal section of the hull are both in an ellipse shape; a group of tilting channel type boat wings are respectively arranged on two sides of the airship body, and each group of tilting channel type boat wings are respectively connected with the airship body through a fixed wing installation section; the boat wings positioned on the left side of the boat body are respectively a left front wing and a left rear wing, and the boat wings positioned on the right side of the boat body are respectively a right front wing and a right rear wing; the airship is characterized in that four power devices are arranged on the upper surface of each tilting canal type airship wing respectively, are located in the semi-ring wing section of the airship wing respectively, and enable the central line of each power device to coincide with the central line of the semi-ring wing section.
The total length of the hull is 4.8m, the height is 0.96m and the width is 1.44 m.
In the geometric shape of the boat body, the coordinate data of cross-section curves with the horizontal distances of 0.3m, 0.6m, 1.4m, 3.9m, 4.3m and 4.8m relative to the installation datum points are respectively as follows:
coordinate data table for cross section of hull
The distance between the middle part of the airship body and the installation datum point is 1.5m to 3.9m, the section is an equal section, each section curve is generated by scatter points according to a sample line rule, and the three-dimensional curved surface of the airship body is generated according to each section curve according to a multi-section curved surface rule, so that the geometric shape of the airship body is obtained.
The curve coordinate data of the longitudinal symmetry plane of the hull are respectively as follows:
longitudinal section coordinate data table of boat body
The fixed wing installation sections are horizontally fixed on two sides of the submarine body, and the front edges of the fixed wing installation sections and the installation datum points are located on the same horizontal plane. The horizontal distance from the front edge of the left front fixed wing installation section to the installation reference point is 1.3m, and the distance from the front edge of the left rear fixed wing installation section to the front edge of the left front fixed wing installation section is 1.9 m. The group of fixed wing installation sections located on the right side of the hull and the group of fixed wing installation sections on the left side of the hull are symmetrical with respect to the hull. The spanwise length of each fixed wing mounting section is 0.0951m, and the chord length is 0.3 m.
Each channel formula of verting boat wing is equallyd divide into interior wing section, semi-ring wing section and outer wing section three-section. Each inner wing section is respectively positioned at the inner end of each tilting channel type boat wing, and the end part of each inner wing section close to one side of the boat body is respectively provided with a wing root of each tilting channel type boat wing, and the wing roots are respectively and fixedly connected with the fixed wing mounting sections at the positions of the tilting channel type boat wings; and each outer wing section is respectively positioned at the outer end of each tilting canal type boat wing to form a wing tip of each tilting canal type boat wing. The semi-ring wing section is positioned between the inner wing section and the outer wing section.
The wing profiles of the inner wing section and the outer wing section are NACA4412, and the chord lengths are 0.3 m; the span length of the inner wing panel is 0.165m, and the span length of the outer wing panel is 0.26 m; the radius of the leading edge line of the half-ring wing section is 0.1205m, and the profile of the chordwise section of the half-ring wing section also adopts NACA 4412. Two sides of the annular opening of the semi-ring wing section are respectively connected with the upper wing surface of the inner wing section or the upper wing surface of the outer wing section in a smooth transition mode.
The fin has four, is installed at hull tail end in the X overall arrangement. The horizontal distance of the tail leading edge of each tail root from the installation reference point is 4.2 m. The chord length of the tail root is 0.35m, and the chord length of the tail tip is 0.2 m; the span length of the empennage is 0.6m, the sweep angle is 30 degrees, and each empennage section airfoil is NACA 0012.
The power device comprises an RS2205 motor, a RAPTOR 20A electronic speed regulator and a 5045 propeller. The propeller is arranged on the motor output shaft, and the front edge of the propeller blade and the front edge of the tilting canal type boat wing are positioned on the same vertical plane. The motor is arranged in the semi-ring wing section through a motor base, and the motor base is fixed on the inner wall surface of the semi-ring wing section through a motor mounting cross beam.
Compared with the prior art, the invention has the beneficial effects that:
the canal type boat wing is divided into an inner boat wing, a semi-ring wing section and an outer boat wing section. The semi-ring wing section is provided with a propeller disc which vertically flows, when the propeller rotates at a high speed, high-speed airflow is generated behind the propeller disc and flows through the upper part of the semi-ring wing section, and low-speed airflow is arranged below the semi-ring wing section. From Bernoulli's law, low-speed incompressible fluid increases pressure at an increased speed, and decreases pressure at a decreased speed. Therefore, the high-speed airflow on the upper surface of the semi-ring wing section generates a low-pressure area above the boat wing, the low-speed airflow below the semi-ring wing section generates a high-pressure area in the thought of the boat wing, and the upper-lower pressure difference generates great lift force on the canal type boat wing to endow the canal type boat wing with high lift characteristic.
In order to verify the beneficial effect of the aerodynamic layout provided by the invention, the aerodynamic performance of the channel type boat wing is calculated by adopting a CFD numerical simulation method. Generating a computational grid of the model by ICEM CFD software, dividing a flow field computational area into a rotating area and a static area by a propeller processing MRF method, transmitting flow field information and difference values at the boundary position of the areas, and finally obtaining a flow field computational result by solving an RANS equation. The working conditions that the rotating speed of the propeller is 6000 rpm at sea level height and the angle of attack of the boat wing AOA is 0 degree are selected for comparison in the calculation working conditions, the calculation tool is CFX commercial software, and a flow field comparison diagram calculated by CFD is shown in the attached drawing. The aerodynamic performance parameters such as lift coefficient, drag coefficient and the like obtained by configuration calculation are shown in table 1.
As can be seen from fig. 10 to 12, the canal type boat wing has the propellers arranged on the boat wing and the semi-ring wing sections are used to wrap the propellers, and compared with the prior art boat wing without propellers, the high-speed slipstreaming area 17 behind the propeller disc of the canal type boat wing is larger than the high-speed slipstreaming area 16 behind the propeller disc of the prior art boat wing. According to Bernoulli's principle, the high-speed airflow generated by the channel-type boat wing helix forms a channel-type boat wing slip flow low-pressure area 19 with a larger area than the prior art boat wing low-pressure area 18 on the upper surface of the semi-ring wing section. The larger area of the canal type boat wing low-pressure area 19 increases the pressure difference between the upper surface and the lower surface of the canal type boat wing, so that the lift coefficient of the canal type boat wing is increased. As can be seen from the data in table 1, the canal-type boat wing slip-flow low-pressure area 19 increases the lift coefficient of the canal-type boat wing from 0.1778 to 0.4642 of the boat wing in the prior art, increases the lift-drag ratio from 8.7 to 113, and obtains a good power lift-increasing effect compared with the prior art boat wing adopted in the prior art patents such as CN201921163202.2, CN205952280U, CN 201367113Y, CN 111846191A, CN 212022950U, etc., thereby effectively solving the defects of small lift force and increased weight of the structure of the airship generated during the low-speed flight of the boat wing in the prior art.
TABLE 1 comparison of aerodynamic performance parameters of the conventional boat wing and the canal-type boat wing of the present invention
| Configuration name | Coefficient of lift | Coefficient of resistance | Lift to drag ratio | Coefficient of thrust |
| Boat wing in prior art | 0.1778 | 0.0205 | 8.7 | 0 |
| Canal type boat wing | 0.4642 | 0.0041 | 113 | 0.0882 |
Drawings
Fig. 1 is a schematic diagram of a tandem tilt canal airship with wings according to an embodiment of the present invention;
fig. 2 is a top view of a tandem tilt canal airship wing airship employed in an embodiment of the present invention;
fig. 3 is a side view of a tandem tilt canal airship used in an embodiment of the invention;
fig. 4 is a front view of a tandem tilt canal airship wing airship employed in an embodiment of the present invention;
FIG. 5 is a schematic illustration of an airship platform employed in embodiments of the invention;
FIG. 6 is a schematic diagram of a tilting canal boat wing used in an embodiment of the present invention;
FIG. 7 is a schematic cross-sectional view of a hull of an airship according to an embodiment of the invention;
FIG. 8 is a schematic diagram of a CFD computational grid of a tilting canal boat wing used in an embodiment of the present invention;
FIG. 9 is a schematic diagram of a method for processing a slip grid in a propeller rotation domain according to an embodiment of the present invention; wherein 9a is a stationary domain grid and 9b is a rotating domain grid; 9c is a mosaic grid;
FIG. 10 is a comparative CFD flow field diagram for a tilt-canal boat wing used in an embodiment of the present invention; wherein 10a is the space velocity cloud plot of a prior art boat wing; 10b is a space velocity cloud plot of the canal boat wing of the present invention;
FIG. 11 is a comparative CFD flow field diagram for a tilt-canal boat wing used in an embodiment of the present invention; wherein 11a is a surface pressure coefficient cloud picture of the boat wing in the prior art, and 11b is a surface pressure coefficient cloud picture of the canal type boat wing in the invention;
FIG. 12 is a comparative CFD flow field diagram for a tilt-canal boat wing used in an embodiment of the present invention; wherein 12a is a cloud picture of the plane pressure coefficient of the propeller of the boat wing in the prior art, and 10b is a cloud picture of the plane pressure coefficient of the propeller of the canal type boat wing in the invention;
in the figure: 1. an airship platform; 2. a tilting canal boat wing; 3. a power system; 4. a left front fixed wing mounting section; 5. a right front fixed wing mounting section; 6. a left rear fixed wing mounting section; 7. a right rear fixed wing mounting section; 8. a tail wing; 9. a hull; 10. an inner wing section; 11. a semi-ring wing section; 12. an outer wing section; 13. a motor is provided with a beam; 14. a propeller; 15. a motor; 16. the prior art slipstream area of the boat wing; 17. a channel type boat wing and boat wing slipstream area; 18. the prior art boat wing low pressure area; 19. the canal type boat wing and boat wing low-pressure area.
Detailed Description
The embodiment is a pneumatic layout of a tandem tilting canal type airship wing airship.
In the embodiment, the flight direction of the airship is taken as the front, the airship is a plane-symmetric geometric body, and the two sides of the flight direction are respectively the left side and the right side; the top of the forward end of the airship hull is taken as an installation reference point of the externally hanging part and is marked as O. And establishing a right-hand coordinate system for describing geometrical parameters of the airship at the point O, wherein the x axis is positioned in the symmetrical plane of the airship and points to the rear of the airship horizontally backwards, the z axis is positioned in the symmetrical plane of the airship and points to the right side of the airship vertically upwards, and the y axis is vertical to the x-z plane and meets the right-hand rule.
The airship comprises a hull, a wing, a tail and a power device. The hull 9 is shaped like an ellipsoid in the prior art, and has a total length of 4.8m, a height of 0.96m and a width of 1.44 m. The cross section and the longitudinal section of the airship body are both oval, and in order to establish the geometric appearance of the airship body, curve coordinate data of the cross section with the horizontal distance of 0.3m, 0.6m, 1.4m, 3.9m, 4.3m and 4.8m relative to an installation datum point and curve coordinate data of a longitudinal symmetry plane are given, as shown in the table. The distance between the relative installation datum points in the airship body is 1.5m to 3.9m, the sections are equal, each section curve is generated by scattered points according to a sample line rule, the three-dimensional curved surface of the airship body is generated according to each section curve according to a multi-section curved surface rule, and the geometric shape of the airship body is finally obtained.
Table 2 hull cross-section coordinate data table
Table 4 boat hull longitudinal section coordinate data table
The airship outer skin is made of laminated composite material and is compounded with several layers of material, including outer surface coating, weather resisting layer, helium resisting layer, bearing layer, adhesive layer and inner surface coating. Helium is filled in the device, and the density difference between the helium and the air is utilized to obtain the floating lift force. A group of tilting canal type boat wings are arranged on two sides of the airship body respectively and are a left front wing, a left rear wing, a right front wing and a right rear wing of the airship respectively. The tail section of the airship body is provided with a tail wing. The airship is provided with four power devices which are respectively arranged on the upper surface of each tilting canal type airship wing. The power device is arranged on the upper surface of each tilting canal type boat wing through a cross beam 13, is positioned in the semi-ring wing section 11, and enables the central line of the power device to coincide with the central line of the semi-ring wing section.
The two sides of the airship hull are respectively provided with a group of fixed wing installation sections used for being connected with the tilting canal type airship wings, and the groups of fixed wing installation sections are distributed in series along the front and the back of the airship hull. In the two groups of fixed wing installation sections, one group of fixed wing installation sections positioned on the left side of the hull comprises a left front fixed wing installation section 4 and a left rear fixed wing installation section 6; and the group of fixed wing installation sections positioned on the right side of the boat body comprises a right front fixed wing installation section 5 and a right rear fixed wing installation section 7.
Each fixed wing installation section is horizontally fixed on two sides of the submarine body, and the front edge of each fixed wing installation section and the installation datum point are located on the same horizontal plane. The horizontal distance from the front edge of the left front fixed wing installation section to the installation reference point is 1.3m, and the distance from the front edge of the left rear fixed wing installation section to the front edge of the left front fixed wing installation section is 1.9 m. The group of fixed wing installation sections located on the right side of the hull and the group of fixed wing installation sections on the left side of the hull are symmetrical with respect to the hull. The spanwise length of each fixed wing mounting section is 0.0951m, and the chord length is 0.3 m.
The two sides of the hull are respectively provided with the tilting canal type boat wings through the fixed wing installation sections, and the tilting canal type boat wings are divided into an inner wing section 10, a semi-ring wing section 11 and an outer wing section 12. Each inner wing section is respectively positioned at the inner end of each tilting channel type boat wing, and the end part of each inner wing section close to one side of the boat body is respectively provided with a wing root of each tilting channel type boat wing, and the wing roots are respectively and fixedly connected with the fixed wing mounting sections at the positions of the tilting channel type boat wings; and each outer wing section is respectively positioned at the outer end of each tilting canal type boat wing to form a wing tip of each tilting canal type boat wing. The half-ring wing sections are located between the inner wing section 10 and the outer wing section 12.
The wing profiles of the inner wing section 10 and the outer wing section 12 are both NACA4412, the chord lengths are both 0.3m, and the wing profiles are both made of aluminum plates. The span length of the inner wing panel 10 is 0.165m, and the span length of the outer wing panel is 0.26 m; the radius of the leading edge line of the half-ring wing section 11 is 0.1205m, and the profile of the chordwise section of the half-ring wing section also adopts NACA 4412. Two sides of the annular opening of the semi-ring wing section are respectively connected with the upper wing surface of the inner wing section or the upper wing surface of the outer wing section in a smooth transition mode.
The fin has four, is installed at hull tail end in the X overall arrangement. The horizontal distance of the tail leading edge of each tail root from the installation reference point is 4.2 m. The chord length of the tail root is 0.35m, and the chord length of the tail tip is 0.2 m; the span length of the empennage is 0.6m, the sweep angle is 30 degrees, and each empennage section airfoil is NACA 0012.
The power device is arranged on the upper surface of each tilting canal type boat wing through a cross beam 13, is positioned in the semi-ring wing section 11, and enables the central line of the power device to coincide with the central line of the semi-ring wing section. The power plant of the embodiment comprises an RS2205 motor, a RAPTOR 20A electronic speed regulator and a 5045 propeller. The propeller is arranged on the motor output shaft, and the front edge of the propeller blade and the front edge of the tilting canal type boat wing are positioned on the same vertical plane. The motor is installed in the semi-ring wing section through a motor base, and the motor base is fixed on the inner wall surface of the semi-ring wing section through a motor installation beam 13. The motor is connected with an electronic speed regulator according to a conventional method, and the electronic speed regulator is connected with a flight control computer and a storage battery which are arranged in the airship. The storage battery provides energy for the rotation of the motor, and the flight control computer adjusts the rotating speed of the motor through the electronic speed regulator to control the movement of the airship.
In comparison with the prior art hydrofoil without a propeller, the high-speed slipstream area 17 behind the propeller disc of the canal-type hydrofoil propeller is larger than the high-speed slipstream area 16 behind the propeller disc of the prior art hydrofoil propeller. According to Bernoulli's principle, the high-speed airflow generated by the channel-type boat wing helix forms a channel-type boat wing slip flow low-pressure area 19 with a larger area than the prior art boat wing low-pressure area 18 on the upper surface of the semi-ring wing section. The larger area of the canal type boat wing low-pressure area 19 increases the pressure difference between the upper surface and the lower surface of the canal type boat wing, so that the lift coefficient of the canal type boat wing is increased. As can be seen from the data in table 1, the canal-type boat wing slip-flow low-pressure area 19 increases the lift coefficient of the canal-type boat wing from 0.1778 to 0.4642 of the boat wing in the prior art, increases the lift-drag ratio from 8.7 to 113, and obtains a good power lift-increasing effect compared with the prior art boat wing adopted in the prior art patents such as CN201921163202.2, CN205952280U, CN 201367113Y, CN 111846191A, CN 212022950U, etc., thereby effectively solving the defects of small lift force and increased weight of the structure of the airship generated during the low-speed flight of the boat wing in the prior art.
Claims (9)
1. A pneumatic layout of a tandem tilting canal type boat wing airship takes the flight direction of the airship as the front, the airship is a plane-symmetric geometrical body, and the two sides of the flight direction are respectively the left side and the right side; taking the vertex of the front end of the airship body as an installation reference point of the externally hung part, and marking as O; establishing a right-hand coordinate system for describing geometrical parameters of the airship at a point O, wherein an x axis is positioned in a symmetrical plane of the airship and points to the rear of the airship horizontally and backwards, a z axis is positioned in the symmetrical plane of the airship and points to the right side of the airship vertically and upwards, a y axis is perpendicular to an x-z plane and meets a right-hand rule, the airship comprises a hull, airship wings, an empennage and a power device, the airship wings are positioned on two sides of the hull, the displacement is positioned at a tail section of the hull, and the power device is installed on the surfaces of the airship wings; the submarine is characterized in that the submarine body is in an ellipsoid shape, and the cross section and the longitudinal section of the submarine body are both in an oval shape; a group of tilting channel type boat wings are respectively arranged on two sides of the airship body, and each group of tilting channel type boat wings are respectively connected with the airship body through a fixed wing installation section; the boat wings positioned on the left side of the boat body are respectively a left front wing and a left rear wing, and the boat wings positioned on the right side of the boat body are respectively a right front wing and a right rear wing; the airship is characterized in that four power devices are arranged on the upper surface of each tilting canal type airship wing respectively, are located in the semi-ring wing section of the airship wing respectively, and enable the central line of each power device to coincide with the central line of the semi-ring wing section.
2. The aerodynamic layout of a tandem tilt canal airship according to claim 1, wherein the hull has a total length of 4.8m, a height of 0.96m and a width of 1.44 m.
3. The aerodynamic layout of a tandem tilt canal airship according to claim 1, wherein the hull geometry has cross-sectional curve coordinate data with horizontal distances of 0.3m, 0.6m, 1.4m, 3.9m, 4.3m and 4.8m from installation datum points:
coordinate data table for cross section of hull
The distance between the middle part of the airship body and the installation datum point is 1.5m to 3.9m, the section is an equal section, each section curve is generated by scatter points according to a sample line rule, and the three-dimensional curved surface of the airship body is generated according to each section curve according to a multi-section curved surface rule, so that the geometric shape of the airship body is obtained.
4. The aerodynamic layout of the tandem tilt canal airship wing airship of claim 1, wherein the longitudinal symmetry plane curve coordinate data of the hull are respectively:
longitudinal section coordinate data table of boat body
5. The aerodynamic layout of a tandem tilt canal airship according to claim 1, wherein each fixed wing installation section is horizontally fixed on both sides of the hull, and the front edge of each fixed wing installation section and the installation datum point are located on the same horizontal plane; the horizontal distance from the front edge of the left front fixed wing installation section to the installation reference point is 1.3m, and the distance from the front edge of the left rear fixed wing installation section to the front edge of the left front fixed wing installation section is 1.9 m; the group of fixed wing installation sections positioned on the right side of the hull and the group of fixed wing installation sections positioned on the left side of the hull are symmetrical around the hull; the spanwise length of each fixed wing mounting section is 0.0951m, and the chord length is 0.3 m.
6. The aerodynamic layout of a tandem tilt canal airship of claim 1, wherein each of the tilt canal airship wings is divided into three sections, an inner wing section, a semi-ring wing section and an outer wing section; each inner wing section is respectively positioned at the inner end of each tilting channel type boat wing, and the end part of each inner wing section close to one side of the boat body is respectively provided with a wing root of each tilting channel type boat wing, and the wing roots are respectively and fixedly connected with the fixed wing mounting sections at the positions of the tilting channel type boat wings; each outer wing section is respectively positioned at the outer end of each tilting canal type boat wing to form a wing tip of each tilting canal type boat wing; the semi-ring wing section is positioned between the inner wing section and the outer wing section.
7. The aerodynamic layout of the tandem tilt canal airship wing airship according to claim 6, wherein the wing profiles of the inner wing section and the outer wing section are both NACA4412 and have chord lengths of 0.3 m; the span length of the inner wing panel is 0.165m, and the span length of the outer wing panel is 0.26 m; the radius of the front edge line of the half-ring wing section is 0.1205m, and the profile of the chordwise section of the half-ring wing section also adopts NACA 4412; two sides of the annular opening of the semi-ring wing section are respectively connected with the upper wing surface of the inner wing section or the upper wing surface of the outer wing section in a smooth transition mode.
8. The aerodynamic configuration of a tandem tilt canal airship of claim 1, wherein four of the empennages are mounted at the aft end of the hull in an X configuration; the horizontal distance from the tail leading edge of each tail root to the installation datum point is 4.2 m; the chord length of the tail root is 0.35m, and the chord length of the tail tip is 0.2 m; the span length of the empennage is 0.6m, the sweep angle is 30 degrees, and each empennage section airfoil is NACA 0012.
9. The aerodynamic configuration of a tandem tilt canal airship wing airship of claim 1, wherein the power plant comprises an RS2205 motor, a RAPTOR 20A electronic governor, and a 5045 propeller; the propeller is arranged on the motor output shaft, and the front edge of the propeller blade and the front edge of the tilting canal type boat wing are positioned on the same vertical plane; the motor is arranged in the semi-ring wing section through a motor base, and the motor base is fixed on the inner wall surface of the semi-ring wing section through a motor mounting cross beam.
Priority Applications (1)
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| CN113911311A (en) * | 2021-10-19 | 2022-01-11 | 北京空天高科技有限公司 | Propeller-linked driving device shafting and stratospheric airship |
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