CN109484655A - A kind of engine vibration-damping structure of the dynamic unmanned plane of oil - Google Patents
A kind of engine vibration-damping structure of the dynamic unmanned plane of oil Download PDFInfo
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- CN109484655A CN109484655A CN201811580648.5A CN201811580648A CN109484655A CN 109484655 A CN109484655 A CN 109484655A CN 201811580648 A CN201811580648 A CN 201811580648A CN 109484655 A CN109484655 A CN 109484655A
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- 239000003921 oil Substances 0.000 description 31
- 238000009434 installation Methods 0.000 description 10
- 230000000694 effects Effects 0.000 description 8
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 239000013585 weight reducing agent Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
A kind of engine vibration-damping structure of the dynamic unmanned plane of oil, four foot props including supporting engine, four foot props pass through damping shock absorber respectively and are supported on four erecting beds, and four foot props are connected as one by connecting rod between each other.The present invention is reduced to the greatest extent the contact point of engine and fuselage support, by being installed four foot props by four erecting beds to reduce the quantity of support construction.And four foot props are connected into rigid entirety, to improve lifting capacity, unnecessary structural strengthening is avoided, increased weight can be reduced to greatest extent while vibration damping.In four erecting beds and four foot prop positions, damping shock absorber is set; the vibration that engine operates is separated with fuselage support as far as possible; to completely cut off engine on an independent frame; the vibration of engine is avoided to adversely affect other components, it is particularly possible to protect the fuel tank, electronic equipment of compact layout under small space inside unmanned plane from the influence of engine luggine.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an oil-driven unmanned aerial vehicle with multiple rotors, and particularly relates to an engine vibration damping structure of the oil-driven unmanned aerial vehicle.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles are divided into reconnaissance aircraft and target drone. The civil unmanned aerial vehicle is widely applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, quick-delivery transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, electric power inspection tour, disaster relief, movie and television shooting and the like.
Current many rotor unmanned aerial vehicle is electronic unmanned aerial vehicle usually. Many rotor electric unmanned aerial vehicle's simple structure easily makes, and motor light in weight, rotation are steady, and driving system is easily standardized, thus the complete machine is easily controlled relatively, and the flight noise is low, and is comparatively active in the civilian field development of short voyage. However, because the energy density of the battery is far lower than that of fuel oil, the electric unmanned aerial vehicle is limited by the battery, the range is short, the load level is low, and the electric unmanned aerial vehicle cannot be applied to the field of military large-load reconnaissance and attack. The existing long-range fuel oil unmanned aerial vehicle usually adopts a fixed wing structure, is limited by an airport in taking off and landing, cannot hover, is high in manufacturing cost, is complex to operate and control, and is not flexible and flexible to use.
CN 106697278A discloses many rotor unmanned aerial vehicle of direct-driven formula oil moves fixed speed variable pitch, including fuselage, driving system, undercarriage and avionics system, the fuselage for the integrated fuselage of full compound material, driving system constitute by engine system, variable pitch system, oil feeding system and rotor system. Above-mentioned prior art's oil moves unmanned aerial vehicle's six rotors equiangular interval and around the organism setting, the application load that leads to carrying on the organism can only set up under the organism, and because each direction all receives blockking of rotor, the operation can only be carried out downwards to the load of carrying on, can't launch the weapon to oblique top or observe, there is the load level low, structural layout is unreasonable, be difficult to exert unmanned aerial vehicle's control and the defect of security advantage, the development of rotor unmanned aerial vehicle in military affairs and monitoring field is used has been restricted.
CN 205998123U discloses a vertical overall arrangement fuel power four rotor flight platform, and its constitution includes frame, driving system, navigation and control system, electrical system and task platform. Four identical machine arms are butted in pairs on a hard shell type machine body connected with an undercarriage to form a rack; the power system is arranged at the tail end of each horn and provides power and energy for the flying platform; the navigation and control system senses and controls the attitude, the height and the position of the flying platform; the electric system has the functions of charging, power supply and indication; the task platform is used for installing different task devices. This prior art's oil moves unmanned aerial vehicle has set up four independent engines, and the air current interference between adjacent rotor each other is difficult to arrange and is solved, and the interval that increases the engine can further increase volume and weight.
Above-mentioned prior art's oil moves unmanned aerial vehicle all disposes an oil and moves the engine on every cantilever, and naked engine adds the noise of rotor, leads to unmanned aerial vehicle hardly can use in urban airspace, uses under the military environment not there is not any disguise yet. In addition, the existing oil-driven unmanned aerial vehicle basically does not consider the heat dissipation problem under the condition that an engine is built in, and can only passively dissipate heat by increasing the opening of the body, so that the noise of the oil-driven unmanned aerial vehicle is very loud, and meanwhile, the whole body is easily heated to form a huge and striking infrared target due to the fact that no effective heat dissipation design exists, so that the whole body is extremely easy to find and knock down.
In order to solve the defects of the prior art, the applicant of the present application discloses a heat dissipation structure for an oil-driven unmanned aerial vehicle in a previously applied chinese patent application 201711089236.7, which comprises a heat radiator arranged above the tail of a vehicle body, wherein a heat dissipation cavity of the heat radiator is connected with a cooling water tank of an engine installed inside the vehicle body through an upper water pipe and a lower water pipe respectively, and the cooling water tank is provided with a circulating water pump. This prior art utilizes the recirculated cooling water to distribute away the heat that sets up the engine in the inside of fuselage with the water-cooling mode of forcing through setting up the radiator in the outside of fuselage, therefore need not set up large-scale thermovent on unmanned aerial vehicle's the fuselage, and the noise of engine can be got up by the fine shielding of fuselage, has improved unmanned machine's disguised performance, has reduced unmanned aerial vehicle's detectability.
This prior art effectively overcomes the deficiencies of the prior art, but there is still room for improvement. This prior art only provides and has carried out radiating structure to the engine, but does not consider the huge vibration of engine also can be to unmanned aerial vehicle's structural strength and the influence problem of other structures inside, especially to fuel tank, the electronic equipment of compact layout under the inside narrow and small space of unmanned aerial vehicle, need provide the technical solution who reduces the engine vibration influence to need furthest to reduce the weight gain of solving this problem and bringing.
Disclosure of Invention
The invention aims to provide an engine vibration reduction structure of an oil-driven unmanned aerial vehicle, so as to reduce or avoid the problems.
In order to solve the technical problem, the invention provides an engine vibration reduction structure of an oil-driven unmanned aerial vehicle, wherein the oil-driven unmanned aerial vehicle comprises a body, an undercarriage and an engine arranged in the body of the oil-driven unmanned aerial vehicle, the body is provided with a longitudinal symmetrical axis, the head and the tail of the oil-driven unmanned aerial vehicle are respectively provided with two cantilevers which are arranged symmetrically to the longitudinal symmetrical axis, each cantilever supports a rotor wing, and the engine vibration reduction structure comprises: the engine vibration reduction structure comprises four foot frames for supporting the engine, the four foot frames are supported on four mounting platforms through damping vibration absorbers respectively, and the four foot frames are connected into a whole through connecting rods.
Preferably, the oil-driven unmanned aerial vehicle comprises a fuselage support with a full-symmetrical structure; the fuselage cradle having a transverse axis of symmetry perpendicular to the longitudinal axis of symmetry; the machine body support comprises two carbon fiber main beams symmetrically arranged on the longitudinal symmetry axis and two engine bearing rib plates symmetrically arranged on the transverse symmetry axis; the four foot rests are respectively arranged at four point positions where the two engine bearing rib plates are connected with the two carbon fiber main beams.
Preferably, the four mounting platforms are fixedly mounted at the four point positions.
Preferably, the damping vibration absorber comprises a first rubber pad and a second rubber pad; the first rubber pad is arranged between the mounting table and the mounting cylinder at the lower end of the foot rest; the second rubber pad is arranged inside the mounting cylinder; the second rubber pad, the mounting cylinder, the first rubber pad and the mounting platform are connected together through bolts.
Preferably, a gasket is arranged on the upper end face of the second rubber pad; and a gasket is arranged on the lower end face of the first rubber gasket.
Preferably, the mounting tube is welded at the lower end of the foot rest, and a side of the mounting tube, which faces away from the engine, is provided with a truncated cut facilitating mounting of the second rubber pad.
Preferably, the top of the first rubber pad is provided with a boss penetrating into the mounting cylinder, and the boss isolates the mounting cylinder from a bolt.
According to the invention, the four foot rests are installed through the four installation platforms, so that the contact points of the engine and the body support are reduced as much as possible, and the number of the support structures is reduced. And the four foot stands are connected into a rigid whole to improve the load-carrying capacity, avoid unnecessary structural reinforcement and reduce the increased weight to the maximum extent while reducing the vibration. Damping shock absorbers are arranged at the positions of the four mounting tables and the four foot stands to isolate the running vibration of the engine from a machine body support as much as possible, so that the engine is isolated on an independent frame, the adverse effect of the vibration of the engine on other parts is avoided, and particularly, a fuel tank and electronic equipment which are compactly distributed in a narrow space inside the unmanned aerial vehicle can be protected from the influence of the vibration of the engine.
Drawings
The following drawings are only intended to illustrate and explain the present invention and do not limit the scope of the present invention. Wherein,
fig. 1 shows a perspective view of a gasoline-powered drone according to a particular embodiment of the invention;
fig. 2 shows a schematic structural view of the oil-driven unmanned aerial vehicle shown in fig. 1 with a part of the structure removed;
fig. 3 is a schematic view showing the internal structure of the body of the oil-powered unmanned aerial vehicle according to another embodiment of the present application;
fig. 4 is a schematic structural diagram of an oil-powered unmanned aerial vehicle according to an embodiment of the present application;
fig. 5 is a schematic diagram showing an engine vibration reduction structure of an oil-powered unmanned aerial vehicle according to another embodiment of the invention.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
As described in the background art, the invention provides an engine vibration reduction structure for an oil-driven unmanned aerial vehicle, aiming at the defects of a heat dissipation structure for the oil-driven unmanned aerial vehicle disclosed in the prior chinese patent application 201711089236.7, so as to elastically support an engine above a body support and isolate the engine from other structures inside the body, so as to reduce the vibration influence of the engine vibration on a fuel tank and electronic equipment which are compactly arranged in a narrow space inside the unmanned aerial vehicle, and simultaneously increase the structural weight as little as possible.
Specifically, the engine damping structure of the present invention is a further improvement proposed on the basis of the heat dissipation structure of 201711089236.7, which is incorporated in the present application, and those skilled in the art can understand other structures related to the oil-driven unmanned aerial vehicle based on the disclosure of the prior art. As shown in fig. 1-2, fig. 1 is a schematic three-dimensional structure diagram of an oil-driven unmanned aerial vehicle according to an embodiment of the present invention; fig. 2 shows a schematic diagram of the oil-powered drone shown in fig. 1 with part of the structure removed.
Referring to fig. 1-2, like the prior art, the oil-driven unmanned aerial vehicle of this application also includes fuselage 1, frame 2, four cantilevers 3 and four rotors 5 that rise and fall, and four cantilevers 3 are connected to fuselage 1, and every cantilever 3 all supports a rotor 5 of the same diameter. The machine body 1 is in a strip shape with a bilateral symmetry structure, the machine body 1 is provided with a longitudinal symmetry axis 6, and the machine body 1 is in a strip shape on the whole and is parallel to the symmetry axis 6. The aircraft nose and the tail of unmanned aerial vehicle respectively are provided with two symmetries in rotor 5 that symmetry axis 6 arranged. Loads such as a photoelectric pod 7 and a weapon barrel 8 are arranged below the body 1. The fuselage 1 is a generally elongated shuttle-shaped structure with narrow nose and tail widths and a maximum mid-width for the engine 99. A pod mounting structure capable of mounting the photoelectric pod 7 is arranged at the front end of the machine body 1, and a mounting frame capable of mounting the weapon launching tube 8 is arranged below the machine body 1. Each rotor 5 is surrounded by a dome 4 having the same circular shape.
Specific features of the fuselage bearing structure of the present application are described in further detail below with reference to fig. 3-4, where fig. 3 shows a schematic view of the internal structure of the fuselage of an oil-driven unmanned aerial vehicle according to another specific embodiment of the present application; fig. 4 shows a schematic structural diagram of a body of an oil-powered unmanned aerial vehicle according to an embodiment of the present application.
As shown in the drawings, as mentioned before, the oil-driven unmanned aerial vehicle of the present application includes a body 1, an undercarriage 2 and an engine 99 installed inside the body 1 of the oil-driven unmanned aerial vehicle, the body 1 has a longitudinal symmetry axis 6, the head and the tail of the oil-driven unmanned aerial vehicle are respectively provided with two cantilevers 3 arranged symmetrically to the symmetry axis 6, and each cantilever 3 supports a rotor 5.
In the illustrated embodiment, the fuselage bearing structure of the unmanned aerial vehicle powered by oil of the present application includes a fuselage support 20 of a fully symmetrical structure, the fuselage support 20 having a transverse axis of symmetry 10 perpendicular to the longitudinal axis of symmetry 6. That is, the fuselage airframe 20 of the present application is bilaterally symmetric about the longitudinal axis of symmetry 6, and is also symmetric about the transverse axis of symmetry 10. The advantage of such a structural arrangement is obvious, that is, the assembled body support 20 can be used without being divided into the front and rear directions, so that the installation pressure can be greatly reduced, and the installation efficiency can be improved.
Further, the fuselage airframe 20 includes two carbon fiber main beams 201 disposed symmetrically to the longitudinal axis of symmetry 6, two engine load bearing ribs 202 disposed symmetrically to the transverse axis of symmetry 10, two landing gear load bearing ribs 203 disposed symmetrically to the transverse axis of symmetry 10, two cantilever load bearing ribs 204 disposed symmetrically to the transverse axis of symmetry 10, and two tip load bearing ribs 205 disposed symmetrically to the transverse axis of symmetry 10; the engine load bearing rib 202, the landing gear load bearing rib 203, the cantilever load bearing rib 204, and the tip load bearing rib 205 are arranged in this order from the center of symmetry of the airframe support 20 along both sides of the longitudinal axis of symmetry 6. In this embodiment, the fuselage support 20 is an all-carbon structural component with an all-symmetric structure, and compared with the prior art, the carbon fiber main beam 201 and the ribs 202, 203, 204, and 205 are made of carbon fiber composite materials, so that the structure is light in weight, and the weight reduction effect is obvious. In the prior art, only rod-shaped structural components are made of carbon fiber composite materials, and each frame structure has to be made of metal due to the anti-torsion requirement, so that the structural weight is large. In a specific embodiment, in order to improve the torsion resistance, the cross section of the carbon fiber main beam 201 is i-shaped, and each rib plate 202, 203, 204 and 205 also adopts a box-shaped structure, so that the inertia moment of the fuselage support 20 can be greatly enhanced, the torsion resistance of the structure is improved, and meanwhile, the all-carbon thin-wall structure is lighter in weight and higher in strength.
In a preferred embodiment, the cross section of the carbon fiber main beam 201 is gradually reduced from the symmetrical center of the fuselage support 20 along both sides of the longitudinal symmetrical axis 6, so that a more balanced equal-strength structure can be obtained, a more excellent weight reduction effect can be further obtained, and the design strength can be maintained.
The above-mentioned fuselage bearing structure of this application can obtain sufficient torsional property and intensity through the web structure of lower height through the full carbon fuselage support of holosymmetry structure, can reject current metal component simultaneously, alleviates structure weight greatly. The lower height of the fuselage can be obtained by the lower height web structure, the wind resistance is reduced, the skin area is reduced, and the excellent weight reduction effect is achieved. In addition, the lower fuselage support of height can set up various parts in the top of fuselage support, is convenient for install and overhaul.
In addition, in a specific embodiment, four foot rests 991 for supporting the engine 99 are respectively arranged at four points where the two engine bearing ribs 202 are connected to the two carbon fiber main beams 201. That is, the engine 99 is the heaviest single component for the whole fuselage structure, and it is preferable to arrange the engine 99 at the central position of the fuselage support 20 and at the position where the cross section of the carbon fiber main beam 201 is the largest, and further arrange the foot rest 991 at four points where the engine load bearing rib plate 202 is connected with the two carbon fiber main beams 201 to obtain greater support strength.
In another embodiment of the present application, a mounting rack 81 for mounting weapon shooting barrels 8 is arranged on the two carbon fiber main beams 201 below the mounting points of the four foot stands 991. Since the weight of the rocket projectile or the like mounted in the weapon barrel 8 is large, the mounting bracket 81 is disposed at the same position as the support point of the engine 99, and it is avoided that the space is wasted and the weight is increased by disposing the reinforcing structure at more positions, respectively.
In another embodiment of the present application, the cantilever 3 is fixedly connected to the cantilever 31 on the carbon fiber girder 201, and the cantilever 31 is disposed at the connection point of the carbon fiber girder 201 and the cantilever load bearing rib 204.
In a further embodiment of the application, the landing gear 2 is arranged outside the fuselage skin below the carbon fibre main beam 201, and the forces of the landing gear 2 are transmitted by the landing gear load-bearing ribs 203.
In addition, also with the reinforcing structure of the two landing gear load-bearing ribs 203, one fuel tank support frame 207 may be provided above the landing gear load-bearing ribs 203, respectively, for supporting two weight-balanced fuel tanks.
In addition, as mentioned above, because the fuselage support 20 of the present application adopts a fully symmetrical structure, the two end bearing rib plates 205 can be arbitrarily set as bearing structures at the positions of the nose and the tail, so that when the fuselage load is mounted on the fuselage support 20, the front and back directions are not separated, and the convenience of operation is improved.
Further, the upper ends of the two oil tank supporting frames 207 are connected with bearing arms 208 extending to the outside of the fuselage 1, inclined supporting arms 209 are arranged below the bearing arms 208, and the lower ends of the inclined supporting arms 209 are arranged at the connecting positions of the two terminal bearing rib plates 205 and the carbon fiber main beams 201, as shown in the figure.
Further, as shown in fig. 5, an engine damping structure is arranged inside the fuselage 1 of the oil-powered unmanned aerial vehicle, wherein fig. 5 is a schematic diagram of the engine damping structure of the oil-powered unmanned aerial vehicle according to another embodiment of the present invention.
As shown in the figure, the engine vibration damping structure of the present application includes the aforementioned four foot rests 991 supporting the engine 99, the four foot rests 991 are respectively supported on the four mounting platforms 993 through the damping vibration dampers 992, and the four foot rests 991 are connected as a whole through the connecting rod 994.
Further, as mentioned above, the oil-driven unmanned aerial vehicle of the present application includes a fuselage support 20 of a fully symmetrical structure; the fuselage cradle 20 has a transverse axis of symmetry 10 perpendicular to the longitudinal axis of symmetry 6; the fuselage support 20 comprises two carbon fiber main beams 201 arranged symmetrically to the longitudinal symmetry axis 6 and two engine bearing rib plates 202 arranged symmetrically to the transverse symmetry axis 10; the four foot rests 991 are respectively arranged at four point positions where the two engine bearing rib plates 202 are connected with the two carbon fiber main beams 201. More specifically, four mounting tables 993 are fixedly mounted at four point positions.
Namely, the heat insulation concept of the invention is to insulate the engine on an independent frame, so that the adverse effect of the vibration of the engine on other components is avoided, and particularly, a fuel tank and electronic equipment which are compactly arranged in a narrow space inside the unmanned aerial vehicle can be protected from the influence of the vibration of the engine. Because all the structures of the unmanned aerial vehicle are supported by the fully symmetrical body support, the vibration of the engine needs to be isolated from the body support particularly. Firstly, four foot rests are installed through four installation platforms, and contact points of an engine and a machine body support are reduced as much as possible, so that the number of supporting structures is reduced. And because the fuselage support is the all-carbon structure, easy fracture under the heavy load condition sets up the mount table that the metal made and also can be convenient for carry out structure protection to the fuselage support. Secondly, the four foot rests are connected into a rigid whole, the load-carrying capacity is improved by the structural framework of the integral titanium alloy, unnecessary structural reinforcement is avoided, and the increased weight can be reduced to the maximum extent while vibration is reduced. And damping shock absorbers are arranged at the positions of the four mounting tables and the four foot frames to isolate the running vibration of the engine from the body support as much as possible.
Further, as shown, damping vibration absorber 992 of the present application includes a first rubber pad 995 and a second rubber pad 996; a first rubber pad 995 is provided between the mount table 993 and the mount cylinder 997 at the lower end of the foot stand 991; the second rubber pad 996 is arranged inside the mounting cylinder 997; the second rubber pad 996, the mounting cylinder 997, the first rubber pad 995, and the mounting table 993 are coupled together by bolts (not shown). In this embodiment, the two rubber pads constituting the damping vibration absorber clamp the mounting tube of the foot rest, so that there is no hard contact between the foot rest and the mounting table, and the vibration of the engine can be absorbed by the elastic deformation of the two rubber pads.
In a preferred embodiment, the top of the first rubber pad 995 has a boss 998 that penetrates the interior of the mounting cylinder 997, and the boss 998 isolates the mounting cylinder 997 from the bolt. That is, because second rubber pad 996, installation section of thick bamboo 997, first rubber pad 995 and mount table 993 pass wherein through the bolt and link together, the inboard of installation section of thick bamboo forms hard contact with the bolt and transmits the vibration for the fuselage support through the bolt when avoiding vibrating, in this embodiment, set up the first rubber pad that has the boss very much, penetrate installation section of thick bamboo through the boss inside, when the bolt passes first rubber pad, the outside at the bolt is just covered to the boss, only can contact with the boss when the foot rest rocks, and can not touch the bolt, therefore can avoid hard contact, the damping effect has been improved.
In a preferred embodiment, the upper end surface of the second rubber pad 996 may be provided with a spacer for increasing friction when coupled with a bolt. In addition, a gasket may be disposed on the lower end surface of the first rubber pad 995 to increase the friction between the first rubber pad and the mounting table.
In another embodiment, as shown, a mounting tube 997 is welded to the lower end of the foot bracket 991, and the side thereof facing away from the engine 99 is formed with a truncated cutout for facilitating the mounting of a second rubber pad 996. The oblique cut-off can remove a part of the structural weight of the mounting cylinder on the one hand, and the cylindrical structure of the residual part of the oblique cut-off can ensure that the second rubber gasket cannot move in the mounting cylinder on the other hand. In addition, the side of an installation barrel can be exposed through the oblique cut, the second rubber pad is convenient to install, meanwhile, when a bolt is conveniently installed on one side of the oblique cut departing from the engine, tools such as a wrench can be stretched into the installation barrel to screw the bolt head, and observation and maintenance can be facilitated.
In summary, the four foot rests are installed through the four installation tables, so that contact points between the engine and the body support are reduced as much as possible, and the number of the support structures is reduced. And the four foot stands are connected into a rigid whole, so that the load-carrying capacity is improved, unnecessary structural reinforcement is avoided, and the increased weight can be reduced to the maximum extent while vibration is reduced. Set up the damping bumper shock absorber in four mount tables and four foot rest positions, separate engine operation's vibration as far as possible with the fuselage support to with the engine isolation on an independent frame, avoid the vibration of engine to cause adverse effect to other parts, especially can protect fuel tank, the electronic equipment of compact overall arrangement under the inside narrow and small space of unmanned aerial vehicle to avoid the influence of engine vibration.
It should be appreciated by those skilled in the art that while the present invention has been described in terms of several embodiments, each embodiment does not necessarily encompass a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (7)
1. The utility model provides an oil moves unmanned aerial vehicle's engine damping structure, oil moves unmanned aerial vehicle includes fuselage (1), undercarriage (2) and installs oil moves inside engine (99) of unmanned aerial vehicle's fuselage (1), fuselage (1) has a longitudinal symmetry axis (6), oil moves unmanned aerial vehicle's aircraft nose and tail respectively be provided with two symmetries in cantilever (3) that longitudinal symmetry axis (6) were arranged, every cantilever (3) all support there is a rotor (5), its characterized in that: the engine vibration reduction structure comprises four foot stands (991) supporting the engine (99), wherein the four foot stands (991) are supported on four mounting platforms (993) through damping vibration absorbers (992), and the four foot stands (991) are connected into a whole through connecting rods (994).
2. The engine dampening structure of claim 1, characterized in that the oil-powered drone comprises a fuselage cradle (20) of a fully symmetrical structure; the fuselage cradle (20) having a transverse axis of symmetry (10) perpendicular to the longitudinal axis of symmetry (6); the fuselage support (20) comprises two carbon fiber main beams (201) which are arranged symmetrically to the longitudinal symmetry axis (6) and two engine bearing rib plates (202) which are arranged symmetrically to the transverse symmetry axis (10); the four foot stands (991) are respectively arranged at four point positions where the two engine bearing rib plates (202) are connected with the two carbon fiber main beams (201).
3. The engine vibration damping structure according to claim 2, characterized in that the four mount tables (993) are fixedly mounted at the four point positions.
4. The engine vibration damping structure according to claim 1, characterized in that the damping vibration damper (992) includes a first rubber pad (995) and a second rubber pad (996); the first rubber pad (995) is arranged between the mounting table (993) and a mounting cylinder (997) at the lower end of the foot rest (991); the second rubber pad (996) is arranged inside the mounting cylinder (997); the second rubber pad (996), the mounting cylinder (997), the first rubber pad (995) and the mounting table (993) are connected together through bolts.
5. The engine vibration damping structure according to claim 4, characterized in that an upper end face of the second rubber pad (996) is provided with a gasket; the lower end surface of the first rubber pad (995) is provided with a gasket.
6. The engine vibration damping structure according to claim 4, characterized in that the mounting cylinder (997) is welded to a lower end of the foot rest (991), and a side thereof facing away from the engine (99) is formed with a truncated cutout for facilitating mounting of the second rubber pad (996).
7. The vibration damping structure for engine according to claim 4, wherein the top of the first rubber pad (995) has a boss (998) penetrating into the inside of the mounting cylinder (997), and the boss (998) isolates the mounting cylinder (997) from the bolt.
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Cited By (1)
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|---|---|---|---|---|
| CN112829954A (en) * | 2021-01-11 | 2021-05-25 | 林春 | Oil moves unmanned aerial vehicle engine protection device |
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| CN203512061U (en) * | 2013-09-12 | 2014-04-02 | 中国运载火箭技术研究院 | Impact reducing structure suitable for small spacecraft |
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| CN203512061U (en) * | 2013-09-12 | 2014-04-02 | 中国运载火箭技术研究院 | Impact reducing structure suitable for small spacecraft |
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| CN109484655B (en) | 2020-08-28 |
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