CN116674780A - Unmanned aerial vehicle with stealth flying wing layout and design method thereof - Google Patents
Unmanned aerial vehicle with stealth flying wing layout and design method thereof Download PDFInfo
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Abstract
The invention belongs to the technical field of aircrafts, and discloses a stealth flying wing layout unmanned aircraft and a design method thereof.A fuselage adopts a flying wing type pneumatic layout design, wings are arranged on two sides of the fuselage, landing gears are arranged on the lower side of the fuselage, and an engine is arranged on the middle and upper side and is consistent with an air inlet channel and a tail nozzle arranged on the back of the fuselage; the high lift device comprises a flap and ailerons, wherein 4 flaps are arranged in the middle axis of the machine body and the inner part of the outer wing, the ailerons are arranged at the positions of the outer sides of the wings, box-type missile cabins are respectively arranged at two sides of the machine body, spaces for mounting radars, sensors and various avionics equipment are reserved at the front part of the machine body, storage spaces for storing landing gears are reserved at the front part of the machine body and the two sides of the machine body, an air inlet is formed in the back of the machine body, the air inlet is communicated with an engine through an air inlet channel, and smooth transition is realized by adopting round corner design at four corners of the air inlet. The air inlet is an S-shaped air inlet.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a stealth flying wing layout unmanned aircraft and a design method thereof.
Background
At present, compared with other weaponry, the unmanned aerial vehicle has more obvious application advantages: firstly, the unmanned plane is flexible in maneuvering, has lower requirement on taking off and landing, and can adapt to various taking off and landing environments; secondly, the unmanned aerial vehicle has high attendance efficiency, strong cruising ability, lower use cost and no damage to personnel; finally, the device has small volume and strong compatibility.
Modern air defense radar technology is developed, and a fighter plane needs to utilize stealth technology to reduce the possibility of being discovered by enemy radar; in terms of the loading capacity, the engineering performance is larger than that of a prototype, and the factors such as the oil quantity and the like are comprehensively considered, so that the loading capacity can be equal to or slightly smaller than that of the prototype X-47B. Under the condition that the performance parameters of all-wing type stealth unmanned aerial vehicle with stealth performance are disclosed very little in various countries at present, an all-wing type attack unmanned aerial vehicle with stealth performance is designed.
Through the above analysis, the problems and defects existing in the prior art are as follows:
(1) The whole layout and design scheme of the existing flying wing layout unmanned aerial vehicle are not more;
(2) The aerodynamic efficiency, stability, range and loading capacity of the existing flying-wing layout unmanned plane are required to be further improved.
Disclosure of Invention
Aiming at the problems existing in the prior art, the invention provides a stealth flying wing layout unmanned aerial vehicle and a design method thereof.
The invention is realized in that a stealth flying wing layout unmanned aerial vehicle comprises:
fuselage, wings and lift-increasing devices;
the aircraft body is designed in an aerofoil type pneumatic layout, the wings are arranged on two sides of the aircraft body, the landing gear is arranged on the lower side of the aircraft body, and the engine is arranged on the middle and is consistent with the air inlet channel and the tail nozzle arranged on the back of the aircraft body;
the high lift device comprises an inner flap and an outer flap, 4 flaps are arranged on the central axis of the machine body and the inner part of the outer wing, and ailerons are arranged on the outer side of the wing.
Furthermore, a box-type bomb cabin is respectively arranged on two sides of the machine body, and the front part of the machine body is reserved with a space for installing radars, sensors and various avionics equipment.
Further, the storage space for storing the landing gear is formed in the front part of the machine body and on two sides of the machine body.
Furthermore, the landing gear adopts a front three-point landing gear, the front landing gear adopts double wheels, and the main landing gear adopts double wheels.
Further, the air inlet is formed in the back of the machine body, the air inlet is communicated with the engine through an air inlet channel, and round corner designs are adopted at four corners of the air inlet to realize smooth transition.
Further, the wing area is taken as s=57m 2 The installation angle and the upper and lower reverse angles are all 0 degrees, and MH-60 wing sections in the S-bend wing sections are selected.
Another object of the present invention is to provide a design method of a stealth flying wing layout unmanned aerial vehicle, the design method of the stealth flying wing layout unmanned aerial vehicle comprising:
step one, carrying out three-dimensional simulation modeling by using Solidworks software;
step two, according to the weight of the aircraft and a reference standard aircraft, selecting a front three-point landing gear, wherein the front landing gear adopts double wheels, and the main landing gear adopts double wheels;
selecting an engine type according to the flying height and the speed, arranging an air inlet at the back of the machine body according to stealth requirements, and bending the air inlet backwards and downwards from the inlet and then bending the air inlet upwards to the engine;
and step four, the missile pod adopts a box-type structure, a rotary hanging frame is not adopted, and the condition of the missile loading of the missile pod is verified by utilizing three-dimensional modeling.
Further, the stop angle of the landing gear in the second step is taken as 0 degrees, and the ground wiping angle, the inverted-proof angle and the front main track parameter are coupled with the average pneumatic chord length and the pneumatic center.
Further, the gravity center of the undercarriage is taken at the pneumatic center, the front wheel bears 18% -15% of load, the front wheel track and the rear wheel track are taken as 2.5m, the floor wiping angle gamma is 10 degrees to 15 degrees, the inverted angle is larger than the floor wiping angle and not smaller than 15 degrees, the main wheel track takes 30% of wingspan 5.7m, and the rollover angle is 38.7 degrees.
Further, in the third step, the thrust-weight ratio T/w=0.273 in the engine type is selected according to the flying height and speed, and the required takeoff thrust value is 4825.8kg and 47293N is obtained by the design index and the maximum takeoff weight of 17677 kg.
In combination with the technical scheme and the technical problems to be solved, the technical scheme to be protected has the following advantages and positive effects:
first, according to the aerodynamic polar curve, the machine weakens the shock resistance effect under subsonic and transonic conditions. The rising limit calculated value reaches 12000m, and the predicted time for climbing to 8000m is 13min; a certain engine was used and the total range was estimated to be 6026.93km by AAA software.
An overall design and design method of a wing-body fusion flying wing layout with stealth effect.
The method can be used as a source for acquiring enemy information, or the box-type magazine structure can be converted into a warehouse, so that technical and design method support is provided for the express unmanned aerial vehicle, and certain social and economic benefits are achieved.
Secondly, the stealth flying wing layout unmanned aerial vehicle provided by the invention has a plurality of positive effects and advantages in design and performance:
1) The stealth performance is excellent: the aircraft is designed in an aerodynamics layout mode, and the aircraft body and the wings are highly fused, so that the radar reflection sectional area of the whole aircraft is reduced, and the aircraft has good stealth performance. This helps unmanned vehicles to avoid being detected by enemy radar in investigation, monitoring etc. tasks to improve task success rate.
2) Pneumatic performance optimization: the flying wing layout meets the aerodynamic requirements, and simultaneously can make the resistance of the whole aircraft as small as possible, reduce the flight resistance and improve the flight efficiency. This helps unmanned aerial vehicle to perform tasks for long periods of time, long distances, and extends endurance.
3) Rational in infrastructure, bearing capacity is strong: in the design of the flying wing layout, the force transmission path is shortest and the stress is most reasonable through reasonable coordination of various stress components, so that the structural strength and the bearing capacity of the whole aircraft are improved. This enables unmanned aerial vehicles to fly stably in complex flight environments, bearing various weather and loads generated during flight.
4) The lift-increasing device has reasonable design: the reasonable arrangement of the flap and the aileron ensures that the aircraft can meet the required maximum lift coefficient during cruising, taking off and landing and ensures the lifting performance of the aircraft. Meanwhile, the control stability of the whole aircraft is ensured by coordinating the coordination of the length of the front wing span and the length of the auxiliary wing span.
5) The adaptability is wide: the unmanned aircraft with the stealth flying wing layout fully considers loading requirements, so that various payloads, fuel oil, equipment, engines and the like can be arranged in the aircraft body, and meanwhile, the utilization rate of the internal space is maximum. This allows the aircraft to take on a variety of tasks, accommodating a variety of combat environments.
In summary, the stealth flying wing layout unmanned aerial vehicle provided by the embodiment of the invention has great superiority in design and performance, and is beneficial to improving the success rate and adaptability of the unmanned aerial vehicle in task execution.
Drawings
FIG. 1 is a schematic structural view of an unmanned aerial vehicle with a stealth flying wing layout provided by an embodiment of the present invention;
FIG. 2 is a general layout of an unmanned aerial vehicle with a stealth flying wing layout provided by an embodiment of the present invention;
FIG. 3 is a flow chart of a design method for a stealth flying wing layout unmanned aerial vehicle provided by an embodiment of the present invention;
FIG. 4 is a graph showing the effect of the modeling result of Solidworks software provided by the embodiment of the invention;
FIG. 5 is a schematic diagram of an inlet nozzle according to an embodiment of the present invention;
FIG. 6 is a three-dimensional modeling effect diagram of an aircraft interior flow channel provided by an embodiment of the invention;
FIG. 7 is a graph of AAA computed polar curve results (0.8M) provided by an embodiment of the invention;
FIG. 8 is a graphical illustration of the variation of a given cruising altitude (8000 m) with Mach number provided by an embodiment of the present invention;
in the figure: 1. ailerons (bilateral symmetry); 2. outboard flaps (bilateral symmetry); 3. inboard flaps (bilateral symmetry).
Detailed Description
The present invention will be described in further detail with reference to the following examples in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific examples described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The stealth flying wing layout unmanned aerial vehicle provided by the embodiment of the invention comprises a fuselage, wings and a lift-increasing device;
fuselage wings are an important part of an aircraft, in general, early fuselage designs were hand painted mainly through control surfaces and points, mathematical methods such as conic circuits were applied later, and CAD software such as CATIA was mainly used recently.
The design of the fuselage needs to consider a plurality of factors, firstly, the loading requirement is considered, various payloads, fuel oil, equipment, engines and the like are arranged in the fuselage, and meanwhile, the utilization rate of the internal space is maximum; secondly, the aerodynamic requirements are met, the shape and the size of the section of the machine body are distributed along the axis of the machine body to accord with the aerodynamic principle, and the resistance is as small as possible; thirdly, the structural requirement is met, and various stress components are coordinated, so that the force transmission path is shortest and the stress is most reasonable.
The unmanned aircraft with the flying wing layout has the advantages that the design of the aircraft body is not obvious, the wing body heights are fused, and the distinction is not obvious.
The wing design needs to include effects on the relative position, wing design parameters, and aerodynamic structural properties. The method comprises the steps of confirming the relative position relationship between the wing and the fuselage by geometrical parameters such as aspect ratio, sweepback angle, tip ratio, relative thickness of the root and the tip of the wing, dihedral angle and the like.
The aircraft adopts an aerofoil type pneumatic layout design, the wings are arranged on two sides of the aircraft body, the landing gear is arranged on the lower side of the aircraft body, and the engine is arranged on the middle and is consistent with the air inlet channel and the tail nozzle arranged on the back of the aircraft body;
the high lift device comprises a flap and an aileron, wherein 4 flaps are arranged on the central axis of the fuselage and on the inner part of the outer wing, and the aileron is arranged on the outer side of the wing. The type and the parameters of the high lift device are selected, the maximum lift coefficient required by the aircraft during cruising, taking off and landing is considered, the increment required by the lift coefficient is determined, the type and the size of the flap are selected according to statistical data, and the coordination of the length of the front wing span and the length of the auxiliary wing span is well coordinated.
As shown in FIG. 1, the stealth flying wing layout unmanned aerial vehicle provided by the embodiment of the invention adopts a flying wing type pneumatic layout design and is unmanned. The engine is generally arranged on the middle part of the engine, and is consistent with the air inlet passage and the tail nozzle arranged on the back of the engine body. The two sides are respectively provided with a box-type bullet cabin, enough space is reserved at the same time, radar, sensors and various avionics equipment can be installed at the front part of the machine body, and enough space is reserved at the front part and the two sides of the machine body for stowing the landing gear.
The reference area of the unmanned aerial vehicle wing is taken as s=57m 2 The following geometric parameters were obtained from the geometry. For the flying wing type airplane, the definition of the sweepback angle and the tip ratio of a quarter chord line is not obvious, the installation angle and the upper and lower dihedral angles are all 0 degrees, and MH-60 wing sections in the S-bend wing sections are selected.
Table 1 geometrical parameters of the wing
| Sequence number | Shape parameters | Design value | Sequence number | Shape parameters | Design value |
| 1 | Wing area | 57.5m 2 | 5 | Root length | 7.38m |
| 2 | Wingspan | 19m | 6 | Geometric mean chord length | 3m |
| 3 | Aspect ratio | 6.28 | 7 | Average aerodynamic chord length | 4.04m |
| 4 | Sweep angle of front edge | 37° |
The high lift device is characterized in that 4 pieces of simple flaps are arranged in the part close to the central axis of the machine body and the inner part of the outer wing, and the machine body part is close to the nozzle of the engine to actively increase the lift; the ailerons are arranged at the outer part of the wing, the area distribution and the chord length and the span ratio coefficient are shown in Table 2:
table 2 geometrical parameters of the wing
| Device and method for controlling the same | Area of | Expansion coefficient | Chord length coefficient | Deflection angle |
| Rise-increasing device (inner) | 10.7m 2 *2 | 0.24 | 0.203 | 23° |
| Rise-increasing device (outer) | 10.6m 2 *2 | 0.20 | 0.233 | 23° |
| Aileron | 10.6m 2 *2 | 0.20 | 0.233 | ±25° |
The positions and parameters of the high lift device and aileron on the wing are shown in figure 2.
The main body structure of the stealth flying wing layout unmanned aerial vehicle provided by the embodiment of the invention comprises a fuselage, wings and a landing gear, wherein the wings comprise flaps and ailerons. The flap comprises a bilateral symmetry inner flap and a bilateral symmetry outer flap, and the aileron comprises a bilateral symmetry aileron.
The specific connection relation or position relation of the stealth flying wing layout unmanned aerial vehicle provided by the embodiment of the invention is as follows:
the fuselage is the main body part of the whole aircraft, the wings are connected to the fuselage, and the high lift device is arranged on the wings;
wings are the lift-generating part of an aircraft. The flap is connected to the trailing edge part of the wing and is used for helping to provide lift and controlling the attitude of the aircraft, and is mainly used for controlling the lifting and rolling of the aircraft; the method comprises the steps of carrying out a first treatment on the surface of the Ailerons are attached to the trailing edge portions of the wings for controlling the attitude of the aircraft, primarily for controlling yaw and roll of the aircraft.
As shown in fig. 3, the design method of the stealth flying wing layout unmanned aerial vehicle provided by the embodiment of the invention comprises the following steps:
s101, carrying out three-dimensional simulation modeling by using Solidworks software;
s102, selecting a front three-point landing gear according to the weight of the aircraft and a reference standard aircraft, wherein the front landing gear is a double wheel, and the main landing gear is a double wheel;
s103, selecting an engine type according to the flying height and speed, and setting an air inlet at the back of the machine body according to stealth requirements, wherein the air inlet is bent backwards and downwards from the inlet and then bent upwards to the engine;
s104, the missile pod adopts a box-type structure, a rotary hanging frame is not adopted, and the condition of loading the missile pod is verified by utilizing three-dimensional modeling.
And (one) carrying out three-dimensional simulation modeling by using Solidworks software to obtain an image shown in FIG. 4.
(II) landing gear overall parameters
According to the weight of the aircraft and a reference standard aircraft, a front three-point landing gear is selected, and a front landing gear is two-wheel and a main landing gear is two-wheel.
1. The stop angle-the machine is taken as 0 deg..
2. The parameters of the floor wiping angle, the inverted angle prevention and the front main wheel track are coupled with the average pneumatic chord length and the pneumatic center. The gravity center is approximately taken as the pneumatic center, the front wheel bears 15% of load (the range is 8% -15%), the front and rear main wheel track is taken as 2.5m, the floor wiping angle gamma=15° (the range is 10 ° -15 °), and the anti-inversion angle is verified to be 16 ° (larger than the floor wiping angle and not smaller than 15 °)
3. The main wheel track, namely the anti-rollover angle, is calculated to be 38.7 degrees, wherein the main wheel track takes 30 percent of span 5.7m, and meets the requirements.
TABLE 3 landing gear geometry parameters
(III) Engine selection
The engine type is selected, taking mainly into account the altitude and speed of the flight. The design limit of the unmanned aerial vehicle is 12000m, and the cruising speed is 900km/h. Because it does not have the requirement for supersonic flight, but has a relatively large range. Therefore, compared with a turbojet engine with good high-speed performance and high fuel consumption, a turbofan engine with lower cruising fuel consumption is selected, and an afterburner is not needed. The turbofan engine for the public service machine with a large bypass ratio is adopted by comprehensively considering the built-in size, the oil consumption, the thrust and the like.
The calculated thrust weight ratio T/w=0.273, and the maximum takeoff weight 17677kg, based on the design index, can obtain the required takeoff thrust value about 4825.8kg, about 47293N. After the large bypass ratio turbofan engine is studied, a certain engine is selected, and the parameters are as follows:
TABLE 4 engine part parameters
| Length of | Diameter of | Weight of (E) | Maximum thrust |
| 1900mm | 1020mm (maximum diameter) | 1040 kg (net weight) | 50900N |
Fourth, air inlet and tail nozzle
As shown in fig. 5 and 6, the air intake is designed on the back of the aircraft in view of stealth requirements. The maximum air flow rate required by the machine is estimated to be 155.2kg/s, the air inlet port adopts a rectangle similar to B-2, the width is 1.02m, the height is 0.955m, and the round corners at four corners are designed to realize smooth transition.
And obtaining the radius of the air inlet lip, wherein the coefficient is 0.05 by an empirical formula, and the radius of the air inlet lip is about 49mm. The air inlet is an S-shaped air inlet, and the air inlet is bent backwards and downwards from the inlet and then bent upwards to the engine. The length of the air inlet is estimated to be about 2m by the central axis of the air inlet.
(V) spring chamber parameters
In the overall arrangement, the design of all the components is basically consistent with that of the previous components, the important point is to coordinate the positions of a missile pod, a loading capacity and a flap, and the portable weapon is researched by combining the actual background requirement, so that a loading scheme is provided.
TABLE 5 weapon basic geometry parameters
| Spring seed | Air-to-air missile 1 | Air-to-air missile 2 | Some small radius precision guided bomb |
| Length (mm) | 3690 | 3800 | 1800 |
| Spring path (mm) | 203 | 210 | 190 |
| Weight (kg) | 220 | 200 | 129 |
The bullet cabin adopts box structure, does not adopt rotatory stores pylon, and basic loading constitution is: and the single-side 2 air-to-air missiles and 4 small-radius precision guided bombs have single-side loading capacity of about 900 kg.
And the three-dimensional modeling is utilized to verify the loading condition of the missile cabin, and the result is feasible.
The embodiment of the invention provides a design method, design and verification thought and an appearance design sample for military and civil flying-wing unmanned aerial vehicles. The unmanned aerial vehicle realizes the optimization of the ascending resistance characteristic and the endurance performance under the design of the box-type magazine, and has certain social benefit and economic benefit.
The embodiment of the invention has a great advantage in the research and development or use process, and has the following description in combination with data, charts and the like of the test process.
Resistance to rise performance
The pneumatic analysis-resistance-type I-clean configuration in AAA software is selected and input into various parameters shown in the following graph, wherein delta C D0clean Different values are taken according to different mach numbers. This process was repeated and the data was exported as excel, generating a polar curve as shown in fig. 7.
The polar curve with Mach number changes is translated on the horizontal axis, but the image translation generated by AAA software is not obvious, and according to the research on the algorithm, the influence of shock wave change on the resistance of the whole machine under the condition of sub-transonic speed is presumed to be weakened.
(II) stable flying performance
Taking the cruising speed of 250m/S, and taking S as the wing reference area of 57m 2 ，ΔC D0 For the zero-liter drag coefficient of the basic configuration with the reference height, the 0.8M of the figure is about 0.018, and the drag coefficient is taken to be 0.02 when cruising at the height of 8 km. A is an ascending resistance factor, 0.12 is taken, and delta C is taken D0,Re And DeltaC D,C All are taken as 0, and substituted data are obtained: t=d= 22582.4N. The power required by the plane flight is P x ＝49777.1N。
Will V y Taken as 0.5m/s, v taken as200m/s, assumed to be 12000m, the lookup temperature T= 216.65K, the density ρ=0.312 kg/m 3 Substituting to obtain ρ H The table look-up gave a 12000m pressure of 19399Pa and a 11000m pressure of 22700Pa, which were found to be slightly different from 12000m by the iterative ceiling.
In the given climbing stage after taking off, the weight is 17000kg, the thrust is 65% of the maximum thrust, in the resistance calculation, the density is 4000m high density, the speed is 200m/s, the climbing speed is 10.75m/s, the climbing is similar to constant-speed climbing, and the estimated time required for reaching the cruising altitude is about 13 min.
(III) maximum voyage and duration
The course comprises three parts, wherein the climbing section is calculated by the geometric relationship of V, and the horizontal course of the climbing stage is 155.13km.
The engine fuel consumption rate is increased by 15% by 0.08kg/N/h of the engine of a certain company, and the thrust effective coefficient is 0.95.
The available fuel quantity of the cruising section is 5118.5kg of fuel consumption in the cruising stage calculated by the previous fuel coefficient method, and the fuel consumption is substituted into the cruising section to calculate the range of the cruising section to be 2981.4km. The duration is 3.3 hours.
The oil consumption is continuously reduced under the constant thrust of the descent segment, the range is estimated to be 200km, and the descent segment basically accords with the climbing segment and occupies 10% of the total range of the aircraft.
The total range is approximately 3340km. The range and the design index have larger difference, and the analysis reason is that the calculation error is caused by directly dividing the thrust and the oil consumption continuously changes. Therefore, AAA software is adopted to perform fitting calculation, the cruising range of the airplane is about 5672km, and the total range is 6026.93km through comprehensive calculation.
(IV) Takeoff landing Performance
The machine uses AAA software to calculate the land-based take-off and running distance to be 1044m and the landing distance to be 1209m. The actual carrier-based process is considered to be realized by catapult-assisted take-off and barrier rope landing.
Example 1:
1) The unmanned aerial vehicle is made of carbon fiber composite materials, so that the weight is reduced, and the structural strength is improved;
2) The high-integration avionics system is adopted, so that the volume is reduced, the weight is reduced, and the power consumption is reduced;
3) The turbofan engine with high thrust-weight ratio is selected, so that the power performance of the aircraft is improved;
4) The wing adopts a self-adaptive flexible design, so that the flight stability is improved;
5) The radar system adopts an active phased array radar, so that the performance of searching for the ground and the air is improved;
6) Artificial intelligence technology is introduced to realize autonomous flight and task execution.
Example 2:
1) The double-engine layout is adopted, so that the reliability of the aircraft is improved;
2) A stealth coating technology is introduced, so that the radar sectional area is reduced;
3) The electronic warfare system is arranged in the aircraft and has interference and anti-interference capability;
4) The airborne photoelectric reconnaissance system is added, so that the searching and tracking capacity of the ground target is improved;
5) The long-endurance flight is realized by adopting a high-energy battery and a solar panel;
6) And a modularized design is introduced, so that the later-stage upgrading and maintenance are convenient.
Example 3:
1) The design of the variable geometry wing is adopted, so that the flight performance is improved;
2) Introducing an autonomous air refueling function of the aircraft, and expanding the combat radius;
3) Installing a high-resolution optical camera, and improving the target recognition precision;
4) Real-time communication is carried out with the ground command system through an airborne data link;
5) A highly autonomous task planning and execution system is adopted;
6) And the multi-machine cooperative combat capability is introduced, so that the task success rate is improved.
Example 4:
1) An internal weapon mounting mode is adopted, so that the radar sectional area is reduced;
2) The ground moving target indicator is added, so that the ground attack capability is improved;
3) Advanced pneumatic guidance and guided weapons are adopted, so that the striking precision is improved;
4) High-performance communication interference equipment is equipped to realize interference to hostile communication;
5) Through multi-source information fusion, the target searching and tracking performance is improved;
6) The electromagnetic pulse resistance and the infrared radiation resistance are increased, and the survivability is improved.
Example 5:
1) The high-integration avionics system is adopted, so that the volume is reduced, the weight is reduced, and the power consumption is reduced;
2) A wireless charging technology is introduced to realize rapid charging of the unmanned aerial vehicle on the ground or in the air;
3) Installing a remote sensing sensor to realize detection of physical and chemical parameters of the ground;
4) Real-time communication with other aerial platforms through an airborne data link;
5) A highly autonomous task planning and execution system is adopted;
6) The electromagnetic pulse resistance and the infrared radiation resistance are increased, and the survivability is improved.
Example 6:
1) The detachable design is adopted, so that the transportation and the rapid deployment are convenient;
2) The multiband radar is installed, so that the performance of searching for the ground and the air is improved;
3) The electronic warfare system is arranged in the aircraft and has interference and anti-interference capability;
4) The airborne photoelectric reconnaissance system is added, so that the searching and tracking capacity of the ground target is improved;
5) The long-endurance flight is realized by adopting a high-energy battery and a solar panel;
6) Artificial intelligence technology is introduced to realize autonomous flight and task execution.
In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front," "rear," "head," "tail," and the like are used as an orientation or positional relationship based on that shown in the drawings, merely to facilitate description of the invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The foregoing is merely illustrative of specific embodiments of the present invention, and the scope of the invention is not limited thereto, but any modifications, equivalents, improvements and alternatives falling within the spirit and principles of the present invention will be apparent to those skilled in the art within the scope of the present invention.
Claims (10)
1. A stealth flying wing layout unmanned aerial vehicle, comprising:
fuselage, wings and lift-increasing devices;
the aircraft body is designed in an aerofoil type pneumatic layout, the wings are arranged on two sides of the aircraft body, the landing gear is arranged on the lower side of the aircraft body, and the engine is arranged on the middle and is consistent with the air inlet channel and the tail nozzle arranged on the back of the aircraft body;
the high lift device comprises a flap and an aileron, wherein 4 flaps are arranged on the central axis of the fuselage and on the inner part of the outer wing, and the aileron is arranged on the outer side of the wing.
2. The stealth flying wing layout unmanned aerial vehicle of claim 1, wherein two sides of the fuselage are respectively provided with a box-type missile cabin, and the front part of the fuselage is reserved with a space for installing radar, sensors and various avionics equipment; the unmanned aerial vehicle with the stealth flying wing layout selects a box-type missile pod with larger capacity, verifies the missile hanging quantity of the missile pod from three-dimensional modeling, and simultaneously reserves a front reserved space.
3. The stealth flying wing layout unmanned aerial vehicle of claim 1, wherein the fuselage front and fuselage sides provide a receiving space for stowing landing gear.
4. The stealth flying wing layout unmanned aerial vehicle of claim 1, wherein the landing gear is a front three-point landing gear, the front landing gear is a double wheel, and the main landing gear is a double wheel; the configuration selection of the landing gear is derived from the investigation of the prototype and the iterative calculation of the maximum takeoff weight, and is selected according to the general conclusion of the statistical data.
5. The unmanned aircraft with the stealth flying wing layout according to claim 1, wherein the back of the aircraft body is provided with an air inlet, the air inlet is communicated with an engine through an air inlet channel, and four corners of the air inlet are designed to realize smooth transition by adopting a round angle; the design of the fillet transition can reduce shock resistance and improve the aerodynamic performance of the unmanned aerial vehicle.
6. The stealth flying wing layout unmanned aerial vehicle of claim 1, wherein the wing area is taken as S = 57m 2 The installation angle and the upper and lower reverse angles are all 0 degrees, and MH-60 wing sections in the S-bend wing sections are selected; the wing area is based on the estimation of the area size of a prototype and the measurement of plane drawing, the design thinking of the wing profile is that the flying wing type layout lacks a horizontal tail wing, the low head moment is easy to be large, the low head moment characteristic of the wing profile is related to the camber, and the wing profile with smaller camber, symmetry and even negative camber is selected based on the low head moment characteristic; meanwhile, the relative thickness of the wing profile influences the resistance, the structural weight, the stall characteristic and the like of the aircraft; under subsonic conditions, the relative thickness is increased, the slope of the lifting line is increased, the resistance is correspondingly increased, and the unmanned aerial vehicle adopts about 10% of the relative thickness; in the design, the curve relation of lift-drag ratio, moment coefficient and attack angle is obtained by carrying out grid computational fluid dynamics calculation on the wing profile, and the MH-60 wing profile in the S-bend wing profile is finally selected from the design requirement.
7. A stealth flying wing layout unmanned aerial vehicle, comprising:
the fuselage is the main body part of the whole aircraft, the wings are connected to the fuselage, and the high lift device is arranged on the wings;
wings are the lift-generating part of an aircraft; the flap is connected to the trailing edge part of the wing and is used for helping to provide lift and controlling the attitude of the aircraft, and is mainly used for controlling the lifting and rolling of the aircraft; ailerons are attached to the trailing edge portions of the wings for controlling the attitude of the aircraft, primarily for controlling yaw and roll of the aircraft.
8. A design method for designing the stealth flying wing layout unmanned aerial vehicle according to any one of claims 1 to 7, characterized in that the design method for the stealth flying wing layout unmanned aerial vehicle comprises:
step one, carrying out three-dimensional simulation modeling by using Solidworks software;
step two, according to the weight of the aircraft and a reference standard aircraft, selecting a front three-point landing gear, wherein the front landing gear adopts double wheels, and the main landing gear adopts double wheels;
selecting an engine type according to the flying height and the speed, arranging an air inlet at the back of the machine body according to stealth requirements, and bending the air inlet backwards and downwards from the inlet and then bending the air inlet upwards to the engine;
and step four, the missile pod adopts a box-type structure, a rotary hanging frame is not adopted, and the condition of the missile loading of the missile pod is verified by utilizing three-dimensional modeling.
9. The method for designing the unmanned aircraft with the stealth flying wing layout according to claim 8, wherein the stop angle of the landing gear in the second step is taken as 0 degrees, and the ground wiping angle, the anti-reverse angle and the front main track parameter are coupled with the average aerodynamic chord length and the aerodynamic center;
the gravity center of the undercarriage is taken at the pneumatic center, the front wheel bears 18% -15% of load, the front and rear main wheel tracks are taken as 2.5m, the floor wiping angle gamma is 10 degrees to 15 degrees, the inverted angle is larger than the floor wiping angle and not smaller than 15 degrees, the main wheel track takes 30% of wingspan 5.7m, and the rollover angle is 38.7 degrees; the basic requirements of the landing gear include damping requirements, braking requirements, requirements and the like, the relative positions of the center of gravity of the airplane wheel and the airplane and the height of the landing gear are required to be controlled, the final ground wiping angle is 15 degrees, the stop angle is 0 degree, and the rollover prevention angle is 38.7 degrees.
10. The method for designing an unmanned aircraft with a stealth flying wing layout according to claim 7, wherein the third step is to select the thrust-weight ratio T/w=0.273 in the engine type according to the flying height and speed, and the maximum takeoff weight 17677kg is calculated by the design index, so as to obtain a desired takeoff thrust value of 4825.8kg and 47293N; the appropriate engine can thus be selected while taking into account the space inside the aircraft, by studying the engine dimensions and simulating the actual installation by three-dimensional modeling.
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| CN202310786195.6A CN116674780A (en) | 2023-06-29 | 2023-06-29 | Unmanned aerial vehicle with stealth flying wing layout and design method thereof |
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