CN113232853B - Short-distance take-off and landing aircraft - Google Patents
Short-distance take-off and landing aircraft Download PDFInfo
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- CN113232853B CN113232853B CN202110361585.XA CN202110361585A CN113232853B CN 113232853 B CN113232853 B CN 113232853B CN 202110361585 A CN202110361585 A CN 202110361585A CN 113232853 B CN113232853 B CN 113232853B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/28—Collapsible or foldable blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/64—Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
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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
- B64C3/385—Variable incidence wings
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Abstract
The invention relates to the technical field of airplanes, and particularly discloses a short-distance take-off and landing airplane; the aircraft comprises an aircraft body, two main wings and two tail wings, wherein the two main wings and the two tail wings are rotationally connected with the aircraft body; engines are arranged on the lower surfaces of the main wing and the tail wing, and telescopic propellers are connected to output shafts of the main wing engines; the short-distance take-off and landing aircraft disclosed by the invention can change the angle between the wings and the aircraft body according to different flight states of the aircraft through the self-locking hydraulic motor, and can realize the acceleration and take-off and landing processes by combining the rotation angle of the wings and only using one set of power system device on the whole wing, so that the power system of the whole aircraft occupies small space of the aircraft, and the problems of great weight, poor flexibility, less oil carrying, small operation radius and the like of the existing short-distance take-off and landing aircraft are effectively solved.
Description
Technical Field
The invention relates to the technical field of airplanes, and particularly discloses a short-distance take-off and landing airplane.
Background
The short-distance takeoff and landing airplane refers to an airplane with a fixed wing which takes off and lands in a vertical or short distance. So far, the types of the existing short-distance take-off and landing aircrafts in the world are more, for example, the short-distance take-off and landing aircraft-Jack-141 fighter has the defects of poor flexibility, poor stability, supersonic speed and small operational radius, and only a plurality of prototype machines are produced without mass production. The second is a jet aircraft of the uk type, which achieves a volume production of 1200, but the operational radius of the aircraft does not exceed 200 kilometers. And secondly, american F35-B is an invisible short-distance take-off and landing aircraft and also has the problems of large weight, complex structure, poor flexibility, unstable performance and the like.
The reason why the most typical three types of short-distance take-off and landing aircraft developed at present do not realize large-scale production is that the three types of short-distance take-off and landing aircraft are complex in structure, enough power is generated to lift the aircraft in the vertical direction during the flight process of the aircraft, enough power is provided in the horizontal direction to ensure that the aircraft can run at high speed, and one set of power system device is difficult to complete the two tasks, two sets of systems are required to complete the two tasks of take-off and landing in the vertical direction and acceleration in the horizontal direction, so that extra weight of the aircraft and the precious space occupied by the aircraft are increased invisibly, and the problems of great weight of the short-distance take-off and landing aircraft, poor flexibility, less oil carrying, small combat radius and the like are caused. In addition, the length of the blades of the propeller of the existing short-distance takeoff and landing aircraft cannot be adjusted, so that the power of the engine can be increased only when larger power is needed, the power of the engine is increased, and higher technical requirements are imposed on the service life of the engine. Therefore, aiming at some defects of the existing short-distance take-off and landing aircraft, the design of the short-distance take-off and landing aircraft which can simultaneously complete the take-off and landing in the vertical direction and the acceleration task in the horizontal direction by only one set of power system is a technical problem to be solved.
Disclosure of Invention
The invention aims to design a short-distance take-off and landing aircraft which can simultaneously complete take-off and landing in the vertical direction and acceleration tasks in the horizontal direction only by one set of power system aiming at some defects of the existing short-distance take-off and landing aircraft.
The invention is realized by the following technical scheme:
a short take-off and landing aircraft comprises an aircraft body, two main wings and two tail wings, wherein the two main wings are connected to the left side and the right side of the front end of the aircraft body in a mirror image opposite side mode, and the two tail wings are connected to the left side and the right side of the rear end of the aircraft body in a mirror image opposite side mode;
the lower surface of the main wing is provided with a main wing engine, the upper surface of the empennage is provided with an empennage engine, an output shaft of the empennage engine is in transmission connection with a balance propeller, and an output shaft of the main wing engine is in transmission connection with a telescopic propeller;
the telescopic propeller comprises a rotating shaft, a driven gear ring is arranged on the outer circular surface of the rotating shaft, a power gear meshed with the driven gear ring is arranged on an output shaft of the main wing engine, the outer end of the rotating shaft is connected with a blade fastening disc, a plurality of large blades which are arranged in a hollow mode are fixedly connected to the blade fastening disc in an annular array mode, each large blade is movably embedded with a small blade, a hydraulic cylinder is fixedly connected to the inner end of an inner cavity of each large blade, the end portion of a piston rod of each hydraulic cylinder is fixedly connected with the corresponding small blade, and a hydraulic control system independent of the aircraft body is arranged in the rotating shaft.
As a further arrangement of the above scheme, the first rotary driving system and the second rotary driving system each include a self-locking hydraulic motor disposed inside the machine body, transmission shafts are respectively connected to synchronous output shafts at two ends of the self-locking hydraulic motor, and a gear is disposed at an outer end of each of the transmission shafts;
the left side and the right side of the front end of the engine body are both connected with main wing connecting sleeves, the inner ends of the two main wings are both connected with main wing connecting shafts, the main wing connecting shafts are rotatably connected with the main wing connecting sleeves, the outer circular surfaces of the inner ends of the main wing connecting shafts are fixedly connected with first outer gear rings, gears in a first rotary driving system are meshed with the corresponding first outer gear rings, the left side and the right side of the rear end of the engine body are both connected with tail wing connecting sleeves, the inner ends of the two tail wings are both connected with tail wing connecting shafts, the tail wing connecting shafts are rotatably connected with the tail wing connecting sleeves, the outer circular surfaces of the inner ends of the tail wing connecting shafts are fixedly connected with second outer gear rings, and the gears in the second rotary driving system are meshed with the corresponding second outer gear rings; the angle of the two main wings and the two tail wings and the machine body can be accurately adjusted by driving of the self-locking hydraulic motor and then by the meshing action between the outer gear ring and the gear.
As a further arrangement of the above scheme, a hollow inner cavity is formed in the rotating shaft, hydraulic oil is filled in the hollow inner cavity, and two oil pipes on the hydraulic cylinder penetrate through the blade fastening disc and extend into the hollow inner cavity;
the hydraulic control system comprises a bearing arranged at the circle center of the inner wall of the blade fastening disc, a crankshaft is connected to the bearing, a sealing piston is movably connected to each section of bent rod of the crankshaft, a piston cylinder matched with each sealing piston is fixedly arranged on the inner wall of the hollow inner cavity, an oil inlet pipe is connected to each piston cylinder, a one-way valve is arranged on each oil inlet pipe, and an oil guide pipe is connected to the outer end of each piston cylinder;
the end part of the crankshaft is connected with a power shaft extending out of the hollow inner cavity, the outer end of the power shaft is connected with a brake disc, a brake device acting on the brake disc is arranged on the main wing, a poking block is also arranged at the outer end of the power shaft, a poking groove is formed in the poking block, a poking device acting on the poking block is arranged on the main wing, a shaft sleeve covering the periphery of the power shaft is connected onto the poking block, a diversion valve assembly is fixedly arranged on the inner wall of the hollow inner cavity and comprises an annular partition plate, the shaft sleeve extends into the hollow inner cavity and is fixedly connected with the annular partition plate, and the power shaft penetrates through the diversion valve assembly and the shaft sleeve;
the utility model discloses a hydraulic cylinder, including the inlet and outlet oil position, two oil discharge holes have been seted up to the annular baffle of both ends about the slot, lead oil pipe's tip and stretch into and set up in the slot that corresponds, two oil pipes on the pneumatic cylinder set up respectively between the slot that corresponds in the inlet and outlet oil position and the oil discharge hole, just oil pipe's mouth of pipe and the sealed laminating of annular baffle.
The hydraulic control system is directly arranged in the hollow inner cavity of the rotating shaft, and can realize the control of the extension or the shortening of the blades on the telescopic propeller in the process of high-speed rotation of the telescopic propeller, so that the problem of oil inlet and outlet when the hydraulic cylinder is extended or shortened in a high-speed rotation state is effectively solved.
As a further arrangement of the above scheme, sliding blocks are arranged on the outer circular surfaces of the inner ends of the main wing connecting shaft and the empennage connecting shaft, arc-shaped limiting grooves are arranged on the inner walls of the main wing connecting sleeve and the empennage connecting sleeve which are positioned at the sliding blocks, and the sector angle of each arc-shaped limiting groove is 100 degrees; the rotation angle range of the main wing and the empennage can be ensured to be 0 to 100 degrees through the mutual matching action between the sliding blocks and the arc-shaped limiting grooves, so that the airplane can safely take off or accurately land to a specified place when facing the wind or downwind without accidents.
As a further arrangement of the scheme, the number of the large blades connected with the outer end of the rotating shaft is 4 to 8; the number of the specific telescopic propellers is selected according to actual conditions.
Compared with the prior art, the invention has the beneficial effects that:
1) The short-distance take-off and landing aircraft disclosed by the invention can change the angle between the wings and the aircraft body according to different flight states of the aircraft through the self-locking hydraulic motor, and can realize the acceleration of the aircraft in high altitude and the take-off and landing process of the aircraft by combining the rotation angle of the wings and only one set of power system device on the wings, so that the whole power system of the aircraft occupies small space of the aircraft, and the problems of great weight, poor flexibility, less oil carrying, small operation radius and the like of the existing short-distance take-off and landing aircraft body are effectively solved.
2) The invention discloses a short-distance take-off and landing aircraft which is specially designed for a propeller on a main wing, wherein the traditional blades are provided with a telescopic large blade and a telescopic small blade, the small blade is extended and contracted in the large blade through a hydraulic cylinder, different power can be provided for the whole aircraft through the change of the rotating diameter of the telescopic propeller on the main wing, and the short plate of the existing aircraft which can only improve the rotating speed of an engine when power is increased is effectively solved; the whole airplane combines the change of the rotating diameter of the telescopic propeller and the balance propeller on the empennage to achieve the balance effect of the airplane in the taking-off and landing process in the process of the airplane wing state change, so that the whole airplane is more stable in the flying taking-off and landing process.
3) According to the invention, the hydraulic control system is arranged in the hollow inner cavity of the rotating shaft, the relative motion is generated between the curved rod and the rotating shaft by braking the internal power shaft, then the hydraulic oil in the hollow inner cavity can be injected into the hydraulic cylinder from two directions by the action of the piston and the piston cylinder and the action of changing the flow direction of the hydraulic oil by the diversion valve assembly, so that the extension or the shortening of the piston rod of the hydraulic cylinder is realized, the adjustment of the length of the propeller blade on the main wing is realized, the whole hydraulic control system is independent relative to the machine body, the problem that the hydraulic cylinder cannot adjust the length of the blade by conveying the hydraulic oil when the propeller of the airplane rotates at high speed is effectively solved, and the hydraulic control system is novel in structure and ingenious in design.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a top plan view of the present invention;
FIG. 2 is a front view internal plan view of the present invention;
FIG. 3 is a side plan view of the aircraft of the present invention as it accelerates;
FIG. 4 is a side view of the aircraft in the form of a structure according to the invention;
FIG. 5 is a schematic plan view of the retractable propeller of the present invention;
FIG. 6 is a schematic view of the front view of the main wing engine driven by the retractable propeller of the present invention;
FIG. 7 is a schematic plan view of a hydraulic control system in the interior cavity of the rotating shaft according to the present invention;
FIG. 8 is a schematic plan view of a first embodiment of the oil inlet/outlet portion at A in FIG. 7;
FIG. 9 is a schematic plan view of the second state of the oil inlet/outlet portion at A in FIG. 7 according to the present invention
Fig. 10 is a schematic view of the internal structure of the hydraulic cylinder of the present invention.
Detailed Description
In order to make the technical solutions of the present application better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only some embodiments of the present application, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In the present application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings. These terms are used primarily to better describe the invention and its embodiments and are not intended to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used in other meanings besides orientation or positional relationship, for example, the term "upper" may also be used in some cases to indicate a certain attaching or connecting relationship. The specific meanings of these terms in the present invention can be understood by those skilled in the art as appropriate.
Furthermore, the terms "mounted," "disposed," "provided," "connected," and "sleeved" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. The specific meanings of the above terms in the present invention can be understood by those of ordinary skill in the art according to specific situations.
It should be noted that, in the present application, the embodiments and features of the embodiments may be combined with each other without conflict. The present application will be described in detail with reference to the following examples with reference to the accompanying drawings 1 to 10.
The invention discloses a short take-off and landing aircraft, which mainly comprises an aircraft body 1, two main wings 2 and two tail wings 3, wherein the two main wings 2 are connected to the left side and the right side of the front end of the aircraft body 1 in a mirror image opposite side manner, and the two tail wings 3 are also connected to the left side and the right side of the rear end of the aircraft body 1 in a mirror image opposite side manner. The two main wings 2 and the two tail wings 3 are rotatably connected with the machine body 1.
When the aircraft is specifically arranged, a first rotary driving system 4 is arranged between the two main wings 2 and the aircraft body 1, and a second rotary driving system 5 is arranged between the tail wing 3 and the aircraft body 1. Wherein, first rotary driving system 4 and second rotary driving system 5 all include a setting at the inside auto-lock hydraulic motor 6 of organism 1, can set up auto-lock hydraulic motor 6 in the upper end of organism 1 inner chamber when the short distance aircraft of taking off and landing as the bomber, the lower extreme of its inner chamber generally stores the storehouse for the ammunition, and can set up auto-lock hydraulic motor 6 at the lower extreme of organism 1 inner chamber when the short distance aircraft of taking off and landing as the cargo airplane, and the organism 1 inner space that is located auto-lock hydraulic motor 6 top is the machine storehouse space. The synchronous output shafts at the two ends of the self-locking hydraulic motor 6 are respectively connected with a transmission shaft 9, and the outer end of each transmission shaft 9 is provided with a gear 10.
The left side and the right side of the front end of the machine body 1 are both connected with main wing connecting sleeves 11, the inner ends of the two main wings 2 are both connected with main wing connecting shafts 12, the main wing connecting shafts 12 are rotatably connected with the main wing connecting sleeves 11, first outer gear rings 13 are welded on the outer circular surfaces of the inner ends of the main wing connecting shafts 12, and gears 10 in a first rotary driving system 4 of the first rotary driving system are meshed with the corresponding first outer gear rings 13. Similarly, the left side and the right side of the rear end of the machine body 1 are both connected with tail wing connecting sleeves 14, the inner ends of the two tail wings 3 are both connected with tail wing connecting shafts 15, and the tail wing connecting shafts 15 are rotatably connected with the tail wing connecting sleeves 14. Similarly, a second external gear ring (not shown in the figure) is welded on the outer circular surface of the inner end of the empennage connecting shaft 15, and the gear 10 in the second rotary driving system 5 is meshed with the corresponding second external gear ring.
In addition, it should be noted that sliding blocks 17 are welded on the outer circular surfaces of the inner ends of the main wing connecting shaft 12 and the empennage connecting shaft 15, arc-shaped limiting grooves 18 are arranged on the inner walls of the main wing connecting sleeve 11 and the empennage connecting sleeve 14 which are positioned at the sliding blocks 17, the size of a sector angle of each arc-shaped limiting groove 18 is set to be 100 degrees, and the main wing 2 can rotate in the horizontal direction by 0 to 100 degrees due to the action between the sliding blocks 17 and the arc-shaped limiting grooves 18 when the main wing 2 rotates on the machine body 1; similarly, the tail wing 3 can also rotate in the horizontal direction by 0-100 degrees.
A main wing engine 19 is provided on the lower surface of the main wing 2 as a power source, a tail wing engine 21 is provided on the upper surface of the tail wing 3 as a power source, and the main wing engine 19 and the tail wing engine 21 are spatially offset from each other. The tail engine 21 is provided with a balance propeller 22 facing the nose, the balance propeller 22 is a conventional airplane propeller, which is not specifically described here, and has two main functions: firstly, the airplane has a balance effect when taking off and landing, and the head and the tail of the airplane are kept to rise horizontally; and secondly, the airplane plays a role in accelerating and propelling when flying forwards.
Further, a telescopic propeller 20 is drivingly connected to an output shaft of the main wing engine 19. When the telescopic propeller 20 is specifically arranged, the telescopic propeller comprises a rotating shaft 201, a driven gear ring 205 is arranged on the outer circumferential surface of the rotating shaft 201, a power gear 206 meshed with the driven gear ring 205 is arranged on the output shaft of the main wing engine 19, and the rotating shaft 201 is not on the same axis with the output shaft of the main wing engine 19 when rotating through the transmission relationship between the driven gear ring 205 and the power gear 206. The outer end of the rotating shaft 201 is connected with a blade fastening disc 101, a plurality of large blades 202 which are arranged in a hollow mode are fixedly connected to the blade fastening disc 101 in an annular array mode, the number of the large blades 202 can be set to be 4-8, small blades 203 are movably embedded in each large blade 202, a hydraulic cylinder 204 is fixedly connected to the inner end of an inner cavity of each large blade 202, the end portion of a piston rod of the hydraulic cylinder 204 is fixedly connected with the corresponding small blade 203, the small blades 203 can stretch out and draw back in the large blades 202 under the driving action of the hydraulic cylinder 204, and therefore the rotating radius of the propeller can be adjusted.
In order to solve the problem of hydraulic oil delivery of the hydraulic cylinder 204 of the telescopic propeller 20 when rotating at high speed, the invention also provides a hydraulic control system in the rotating shaft 201, which is independent of the aircraft body 1.
The specific arrangement mode is as follows, referring to fig. 5, fig. 6 and fig. 7, a hollow inner cavity 100 is formed in the rotating shaft 201, hydraulic oil is filled in the hollow inner cavity 100, and the volume of the hydraulic oil is slightly smaller than the inner volume of the hollow inner cavity 100, so that the influence caused by thermal expansion and cold contraction of the hydraulic oil is avoided. Two oil pipes 2041 provided on hydraulic cylinders 204 in large blades 202 on blade fastening disk 101 are extended into hollow inner cavity 100 through blade fastening disk 101. The structure of the fuel engine is characterized in that a bearing 102 is arranged at the center of the circle of the inner wall of a blade slurry fastening disc 101, a crankshaft 103 is connected to the bearing 102, a sealing piston 104 is movably connected to each section of bent rod of each crankshaft 103, a piston cylinder 105 is arranged on the periphery of each piston 104, the piston cylinder 105 is fixedly connected with a hollow inner cavity 100 (at the moment, the connection mode between the sealing piston 104 and the piston cylinder 105 is similar to that of a piston and a cylinder barrel in a fuel engine), an oil inlet pipe 1051 is connected to the piston cylinder 105, a one-way valve (not shown in the figure) is arranged on the oil inlet pipe 1051, and an oil guide pipe 106 is connected to the outer end of each piston cylinder 105. When a rotation speed difference is generated between the crankshaft 103 and the rotating shaft 201, the sealing piston 103 reciprocates in the piston cylinder 105, then the hydraulic oil in the hollow inner cavity 100 is pumped in through the oil inlet pipe 1051 and then is pressed into the oil guide pipe 106, and the arranged check valve can prevent the hydraulic oil from being discharged back and forth from the oil inlet pipe 105 when being pressed out.
A power shaft 107 extending out of the hollow cavity 100 is fixedly connected to an inner end of the crankshaft 103, a brake disk 108 is connected to an outer end of the power shaft 107, and a brake device 109 for activating a braking action on the brake disk 108 is provided on the main wing 2 on the side of the brake disk 108. The outer end of the power shaft 107 is further provided with a toggle block 110, a toggle groove is formed in the toggle block 110, and a toggle device (not shown in the figure) acting on the toggle block 110 is also arranged on the main wing 2, so that the toggle block 110 can move along the axis direction of the power shaft 107 through the toggle device. A shaft sleeve 111 covering the periphery of the power shaft 107 is connected to the toggle block 110, and the shaft sleeve 111 is arranged to extend into the hollow inner cavity 100. A diversion valve assembly 112 is fixedly arranged on the inner wall of the hollow inner cavity, the diversion valve assembly 112 comprises a valve body fixedly connected with the inner wall of the hollow inner cavity 100 and an annular partition 113, the shaft sleeve 111 extends into the hollow inner cavity and is fixedly connected with the annular partition 113, and the power shaft 107 penetrates through the diversion valve assembly 112 and the shaft sleeve 111. Here, the annular partition 113 can move up and down on the diverter valve assembly 112 by shifting the shifting block 110 back and forth, so that the up-and-down position of the annular partition 113 can be adjusted.
An oil inlet and outlet portion corresponding to each hydraulic cylinder 204 is disposed on the diverter valve assembly 112, referring to fig. 7 and 8, the oil inlet and outlet portion includes a groove 1131 disposed in the middle of the partition 113, two oil discharge holes 1132 and 1133 symmetrically disposed at two ends of the groove 113, and the oil discharge holes 1132 and 1133 are communicated with the hollow inner cavity 100. Two oil pipes 2041 and 2042 in the corresponding hydraulic cylinder 204 on the blade pulp fastening disc 101 are respectively arranged between the groove 1131 and the oil drainage holes 1132 and 1133, and the mouths of the oil pipes 2041 are in sealing fit with the annular partition 113. The end of the oil conduit 106 connected to one of the piston cylinders 105 is then set extending into the groove 1131.
The working process and the principle of the automatic hydraulic system are as follows:
when the telescopic propeller 20 is in a static state (i.e., a piston rod of the hydraulic cylinder is not extended or shortened), the state of the oil inlet and outlet portion on the diversion valve assembly 112 is as shown in fig. 8, at this time, the end portions of the two oil pipes 2041 and 2042 on the hydraulic cylinder 204 are attached to the annular partition 113 and are both in a sealed state, hydraulic oil in the hollow inner cavity cannot enter the hydraulic cylinder 204 through the two oil pipes 2041 and 2042, i.e., the two oil pipes 2041 and 2042 on the hydraulic cylinder 204 are both locked, and a piston rod of the hydraulic cylinder is also locked, so that the radius of a blade on the telescopic propeller 20 is ensured to be unchanged.
When the rotation radius of the telescopic propeller 20 needs to be lengthened, when the annular partition 113 is pulled down to the bottom end by the dial block 110, referring to fig. 9 and fig. 10, at this time, the oil tube 2041 of the hydraulic cylinder 204 is communicated with the oil discharge hole 1132, the other oil tube 2042 is communicated with the groove 1131, then the brake disc 108 is braked, and at this time, the rotating shaft 201 is still in a rotating state, so that the relative rotation between the crankshaft 103 and the hollow inner cavity 100 occurs, and then the hydraulic oil can be injected into the groove 1131 through the oil guide tube 106 by the action of the sealing piston 104 and the piston cylinder 105, because at this time, one oil tube 2042 of the hydraulic cylinder 204 is communicated with the groove 1131, so that the injected hydraulic oil is injected into the hydraulic cylinder 204 from the groove 1131 through the oil tube 2042, and the other oil tube 2041 of the hydraulic cylinder 204 is communicated with the oil discharge hole 1132, and the inside of the oil is discharged from the oil discharge hole 1132, so that the piston rod 1132 of the hydraulic cylinder 204 is pushed to extend outwards, and the extension of the blades on the telescopic propeller 20 is realized.
On the contrary, to reduce the rotation radius of the telescopic propeller 20, the annular partition 113 is pushed upward to the top by the toggle block 110, at this time, the two oil pipes 2041 on the hydraulic cylinder 204 are opposite to the oil inlet and outlet positions, and then the crankshaft 103 and the hollow inner cavity 100 rotate relatively by the braking action of the brake disc, so that the hydraulic oil is reversely input, and the blades on the telescopic propeller 20 are shortened.
The whole process is the hydraulic control system which is independent from the aircraft body, and the hydraulic control system can be used for adjusting the length of the blades through the hydraulic cylinder in the process of conveying hydraulic oil in the process of high-speed rotation of the aircraft propeller.
The main wing 2 and the tail wing 3 of the short take-off and landing aircraft disclosed by the invention are in a horizontal state in the acceleration process, namely the rotation angle of the main wing 2 is 0 degree (refer to the attached figure 3), and the aircraft can be driven to accelerate by the power provided by the main wing engine 19 and the tail wing engine 21.
In the taking-off and landing process of the airplane, the gears 10 at the two ends of the transmission shaft 9, the first outer gear ring 13 and the second outer gear ring are meshed through the transmission function of the self-locking hydraulic motor 6, so that the two main wings 2 synchronously and slowly rotate at the same time, the main wings 2 slowly rotate from 0 degrees to 90 degrees, and at the moment, the main wing engine 19, the telescopic propeller 20, the empennage engine 21 and the propeller 22 are all in a vertically upward state (refer to the attached figure 4), and the vertical taking-off and landing of the airplane are realized.
In addition, the power required by the airplane during takeoff is large, the airplane needs to have a propeller radius long enough to ascend to a safe high altitude of about 100 meters, and at the moment, the small blades 203 can be pushed outwards through the hydraulic cylinders 204, so that the length of the whole blades is increased. When the power is not used, the hydraulic 204 cylinder can be controlled to be shortened, the length of the whole blade is reduced, the rotating speed of the propeller is increased, and the flying speed is improved. It should be noted that the length of the blades is changed, the rotating speed of the propeller is adjusted, and the rotation of the wing angle of the airplane is a slow gradual change process, and the safe and stable takeoff or landing of the airplane can be ensured through the three steps.
In addition, when the short take-off and landing aircraft disclosed by the invention is used as a carrier-based aircraft on a large ship, the main wing except the main wing engine 19 can also be arranged into a folding type.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalents and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A short take-off and landing aircraft comprises an aircraft body, two main wings and two tail wings, wherein the two main wings are connected to the left side and the right side of the front end of the aircraft body in a mirror image opposite side mode, and the two tail wings are connected to the left side and the right side of the rear end of the aircraft body in a mirror image opposite side mode;
the lower surface of the main wing is provided with a main wing engine, the upper surface of the empennage is provided with an empennage engine, an output shaft of the empennage engine is connected with a balance propeller, and an output shaft of the main wing engine is in transmission connection with a telescopic propeller;
the telescopic propeller comprises a rotating shaft, a driven gear ring is arranged on the outer circular surface of the rotating shaft, a power gear meshed with the driven gear ring is arranged on an output shaft of the main wing engine, the outer end of the rotating shaft is connected with a blade fastening disc, a plurality of large blades which are arranged in a hollow manner are fixedly connected to the blade fastening disc in an annular array manner, a small blade is movably embedded in each large blade, a hydraulic cylinder is fixedly connected to the inner end of an inner cavity of each large blade, the end part of a piston rod of each hydraulic cylinder is fixedly connected with each small blade, and a hydraulic control system independent of the aircraft body is arranged in the rotating shaft;
a hollow inner cavity is formed in the rotating shaft, hydraulic oil is filled in the hollow inner cavity, and two oil pipes on the hydraulic cylinder penetrate through the blade fastening disc and extend into the hollow inner cavity;
the hydraulic control system comprises a bearing arranged at the circle center of the inner wall of the blade fastening disc, a crankshaft is connected to the bearing, a sealing piston is movably connected to each section of bent rod of the crankshaft, a piston cylinder matched with each sealing piston is fixedly arranged on the inner wall of the hollow inner cavity, an oil inlet pipe is connected to each piston cylinder, a one-way valve is arranged on each oil inlet pipe, and an oil guide pipe is connected to the outer end of each piston cylinder;
the end part of the crankshaft is connected with a power shaft extending out of the hollow cavity, the outer end of the power shaft is connected with a brake disc, a brake device acting on the brake disc is arranged on the main wing, a poking block is also arranged at the outer end of the power shaft, a poking groove is formed in the poking block, a poking device acting on the poking block is arranged on the main wing, a shaft sleeve wrapping the periphery of the power shaft is connected onto the poking block, a diversion valve assembly is fixedly arranged on the inner wall of the hollow cavity, the diversion valve assembly comprises an annular partition plate, the shaft sleeve extends into the hollow cavity and is fixedly connected with the annular partition plate, and the power shaft penetrates through the diversion valve assembly and the shaft sleeve;
be provided with the business turn over oil position that corresponds with every pneumatic cylinder on the diverter valve assembly, business turn over oil position is including seting up the slot in the middle of the annular baffle, is located two oil drain holes have been seted up to the symmetry on the annular baffle at both ends about the slot, lead oil pipe's tip and stretch into and set up in the slot that corresponds, two oil pipes on the pneumatic cylinder set up respectively between the slot that corresponds in business turn over oil position and oil drain hole, just oil pipe's mouth of pipe and the sealed laminating of annular baffle.
2. The short take-off and landing aircraft as claimed in claim 1, wherein the first rotary driving system and the second rotary driving system each include a self-locking hydraulic motor disposed inside the aircraft body, transmission shafts are respectively connected to synchronous output shafts at two ends of the self-locking hydraulic motor, and a gear is disposed at an outer end of each of the transmission shafts;
the front end left and right sides of organism all is connected with main wing connecting sleeve, two the inner of main wing all is connected with the main wing connecting axle, rotate between main wing connecting axle and the main wing connecting sleeve and be connected, the first outer ring gear of fixedly connected with on the outer disc of the inner of main wing connecting axle, gear and the first outer ring gear that corresponds in the first rotary driving system mesh mutually, the rear end left and right sides of organism all is connected with fin connecting sleeve, two the inner of fin all is connected with the fin connecting axle, rotate between fin connecting axle and the fin connecting sleeve and be connected, the outer ring gear of fixedly connected with second on the outer disc of the inner of fin connecting axle, gear and the outer ring gear mesh of second that corresponds in the second rotary driving system.
3. The short take-off and landing aircraft as claimed in claim 2, wherein sliding blocks are disposed on outer circumferential surfaces of inner ends of the main wing connecting shaft and the tail wing connecting shaft, arc-shaped limiting grooves are disposed on inner walls of the main wing connecting sleeve and the tail wing connecting sleeve at the sliding blocks, and a sector angle of each arc-shaped limiting groove is 100 °.
4. The short take-off and landing aircraft as claimed in any one of claims 1 to 3, wherein the number of the large blades connected to the outer end of the rotating shaft is 4 to 8.
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| CN113525678B (en) * | 2021-09-17 | 2022-05-10 | 北京航空航天大学 | Traction-propulsion type manned aircraft with tilting wings for vertical take-off and landing |
| CN114802710A (en) * | 2022-04-21 | 2022-07-29 | 中国航空工业集团公司沈阳飞机设计研究所 | V-shaped tail structure of airplane |
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| CA1017729A (en) * | 1968-09-12 | 1977-09-20 | Evan A. Fradenburgh | Mechanism for synchronously varying diameter of a plurality of rotors and for limiting the diameters thereof |
| CN1907806A (en) * | 2005-08-02 | 2007-02-07 | 韩培洲 | helicopter with tilted front rotary wing |
| CN200995782Y (en) * | 2007-01-17 | 2007-12-26 | 赵文志 | Airplane |
| US8459948B2 (en) * | 2008-10-24 | 2013-06-11 | Esteban A. Caraballoso | Retractable composite rotor blade assembly |
| US9079659B2 (en) * | 2010-09-09 | 2015-07-14 | General Aeronautics Corporation, Inc. | Rotor hub and blade root fairing apparatus and method |
| US8784057B2 (en) * | 2011-02-28 | 2014-07-22 | The Boeing Company | Disc rotor retraction system |
| CN104773291A (en) * | 2015-04-08 | 2015-07-15 | 南昌航空大学 | Disc-shaped rotor wing unmanned helicopter |
| KR101726652B1 (en) * | 2015-07-31 | 2017-04-13 | 한국항공우주연구원 | Blade for unmanned aerial vehicle |
| ITUA20161595A1 (en) * | 2016-03-15 | 2017-09-15 | Navis S R L | Vertical take-off aircraft with revolving wings and electric motors |
| US10252797B2 (en) * | 2016-09-08 | 2019-04-09 | General Electric Company | Tiltrotor propulsion system for an aircraft |
| US10814959B2 (en) * | 2016-09-30 | 2020-10-27 | General Electric Company | Translating fan blades for an aircraft tail mounted fan assembly |
| CN106986015A (en) * | 2017-03-29 | 2017-07-28 | 北京华信智航科技有限公司 | A kind of wing VUAV that verts of use modular power |
| CN207773496U (en) * | 2018-01-05 | 2018-08-28 | 江西冠一通用飞机有限公司 | A kind of turbo-propeller for general-purpose aircraft |
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