CN115610693B - Rocket launching unmanned aerial vehicle is with thrust cone subassembly - Google Patents
Rocket launching unmanned aerial vehicle is with thrust cone subassembly Download PDFInfo
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- CN115610693B CN115610693B CN202211190944.0A CN202211190944A CN115610693B CN 115610693 B CN115610693 B CN 115610693B CN 202211190944 A CN202211190944 A CN 202211190944A CN 115610693 B CN115610693 B CN 115610693B
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- 238000004880 explosion Methods 0.000 claims abstract description 58
- 210000001015 abdomen Anatomy 0.000 claims abstract description 7
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims abstract description 3
- 239000002760 rocket fuel Substances 0.000 claims abstract description 3
- 239000002360 explosive Substances 0.000 claims description 13
- 230000013011 mating Effects 0.000 claims description 4
- 238000000926 separation method Methods 0.000 abstract description 12
- 238000009434 installation Methods 0.000 abstract description 9
- 230000009471 action Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 230000001133 acceleration Effects 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000037237 body shape Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
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- 230000003313 weakening effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The application discloses a thrust cone assembly for a rocket launching unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicle launching, and comprises a thrust cone support, an explosion bolt assembly and a thrust cone, wherein: the thrust cone support is in a triangular prism shape, the first side surface of the thrust cone support is provided with an explosion bolt assembly, and the explosion bolt assembly is used for connecting the thrust cone support and a thrust cone beam of the belly of the unmanned aerial vehicle and exploding when rocket fuel is exhausted so as to separate the thrust cone support from the unmanned aerial vehicle; the thrust cone is arranged on the second side surface of the thrust cone support, the large-diameter end of the thrust cone is connected with the thrust cone support, and the conical surface of the thrust cone is used for being matched with the cone cylinder of the rocket head. According to the application, the installation angle of the thrust cone and the rocket is fixed through the thrust cone support, the rocket is automatically separated in a conical surface matching mode, the explosion separation of the thrust cone support is realized under the action of the explosion bolt, and the large bulge affecting the aerodynamic performance is not left on the unmanned aerial vehicle body, so that the rapid and stable emission of the supersonic unmanned aerial vehicle is realized.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicle launching, in particular to a thrust cone assembly for a rocket launching unmanned aerial vehicle.
Background
Under the large background that the sixth generation of fighter plane is unmanned or unmanned, various countries have deeply ploughed for many years in the technical field of unmanned aerial vehicles, unmanned aerial vehicle system technology has been greatly developed, and supersonic unmanned aerial vehicles are also generated, and therefore, the supersonic unmanned aerial vehicle has the characteristics of small aspect ratio, high maneuverability, good stealth performance and the like, and a plurality of supersonic unmanned aerial vehicles are developed at home and abroad successively. One great advantage of unmanned aerial vehicles is that the unmanned aerial vehicle is not dependent on an airport, and the existing modes such as throwing, vertical emission and the like are obviously unrealizable by depending on the engine power of the unmanned aerial vehicle, so that how to realize the rapid and stable emission of the supersonic unmanned aerial vehicle becomes a great difficulty.
Disclosure of Invention
The application mainly aims to provide a thrust cone assembly for a rocket launching unmanned aerial vehicle, and aims to solve the problem that the supersonic unmanned aerial vehicle cannot be launched rapidly and stably in the prior art.
The technical scheme adopted by the application is as follows:
the utility model provides a rocket launch unmanned aerial vehicle is with thrust cone subassembly, includes thrust cone support, explosion bolt assembly and thrust cone, wherein:
the thrust cone support is in a triangular prism shape, the first side surface of the thrust cone support is provided with an explosion bolt assembly, and the explosion bolt assembly is used for connecting the thrust cone support and a thrust cone beam of the belly of the unmanned aerial vehicle and exploding when rocket fuel is exhausted so as to separate the thrust cone support from the unmanned aerial vehicle;
The thrust cone is arranged on a second side face of the thrust cone support, the second side face is a side face, close to the tail of the unmanned aerial vehicle, of the thrust cone support, the large-diameter end of the thrust cone is connected with the thrust cone support, and the conical face of the thrust cone is used for being matched with a cone cylinder of the rocket head.
Optionally, the thrust cone assembly further comprises a thrust cone mounting seat, the large diameter end of the thrust cone is connected with the thrust cone mounting seat, a plurality of kidney-shaped holes are formed in the second side face of the thrust cone support, the extending direction of the kidney-shaped holes is parallel to the vertical extending direction of the second side face, the centers of the two side faces of the plurality of kidney-shaped holes Kong Raodi are uniformly distributed, and the thrust cone mounting seat is connected with the thrust cone support through the kidney-shaped holes.
Optionally, the explosion bolt assembly includes explosion bolt, flange subassembly and self-locking nut, and explosion bolt passes through flange subassembly and thrust cone beam connection, and explosion bolt's one end is cooperateed with self-locking nut after penetrating thrust cone support's first side.
Optionally, the explosion bolt assembly further comprises an igniter, wherein the igniter is arranged at one end of the explosion bolt, which is close to the unmanned aerial vehicle, and the igniter is used for triggering the explosion of the explosion bolt and is electrically connected with the control system of the unmanned aerial vehicle.
Optionally, the thrust cone assembly further comprises a supporting assembly, the supporting assembly comprises a first circular tube, a second circular tube and a connecting tube, one end of the first circular tube is in threaded connection with one end of the connecting tube, one end of the second circular tube is in threaded connection with the other end of the connecting tube, two ends of the supporting assembly penetrate through the top surface and the bottom surface of the thrust cone support respectively and form through holes, and the connecting tube is located in an inner cavity of the thrust cone support.
Optionally, a clamping plane is disposed on an outer wall of one end, far away from each other, of the first circular tube and the second circular tube, and the first circular tube and the second circular tube are in clearance fit with the through hole.
Optionally, the outer diameter of the connecting tube is larger than the diameter of the through hole.
Optionally, the thrust cone support is a hollow structure, a through hole extending along the axial direction of the thrust cone is formed in the thrust cone, and a connecting hole is formed in the second side surface of the thrust cone support, so that the inner cavity of the thrust cone support is communicated with the through hole of the thrust cone.
Optionally, a plurality of lugs are arranged around the first side surface of the thrust cone support, and a plurality of matching holes matched with the lugs are arranged on the thrust cone beam.
Optionally, the bump is clearance fit with the mating hole.
Compared with the prior art, the application has the beneficial effects that:
According to the rocket launching unmanned aerial vehicle thrust cone assembly, the rapid launching of the unmanned aerial vehicle is achieved through a rocket launching mode, the triangular prism-shaped thrust cone support is used for being matched with the pushing of a rocket, the installation angle of the thrust cone and the rocket is fixed, the thrust cone support is connected with the thrust cone beam of the belly of the unmanned aerial vehicle through the explosion bolt assembly, the thrust cone is installed on the inclined side face of the thrust cone support and matched with the propelling direction of the rocket, the large-diameter end of the thrust cone is connected with the thrust cone support, the conical surface of the thrust cone is always stably matched with the cone barrel of the rocket head through the matching of the conical surface under the propelling of the rocket, after the fuel consumption of the rocket is achieved, the rocket naturally slides down through the cone barrel of the head of the rocket, the acceleration of the unmanned aerial vehicle is reduced after the separation is achieved, the explosion bolt assembly explodes and separates the thrust cone support and the unmanned aerial vehicle, and the body can keep good air property due to the fact that the protruding parts such as the thrust cone support are separated with the body, the body shape can keep good air property, the requirement of supersonic flight is met, and rapid and stable launching of the unmanned aerial vehicle is achieved.
Drawings
Fig. 1 is a schematic structural diagram of a thrust cone assembly for a rocket launching unmanned aerial vehicle according to an embodiment of the present application;
fig. 2 is a schematic structural diagram of a thrust cone support in a thrust cone assembly for a rocket launching unmanned aerial vehicle according to an embodiment of the present application;
Fig. 3 is a schematic structural view of a support assembly in a thrust cone assembly for a rocket launch unmanned aerial vehicle according to an embodiment of the present application;
Fig. 4 is a schematic structural diagram of an explosive bolt assembly in a thrust cone assembly for a rocket launching unmanned aerial vehicle according to an embodiment of the present application;
fig. 5 is an assembly schematic diagram of a rocket launching unmanned aerial vehicle according to an embodiment of the present application when the rocket launching unmanned aerial vehicle participates in launching;
FIG. 6 is a schematic view of a partial enlarged structure at A in FIG. 5;
Fig. 7 is a schematic diagram of separation of a thrust cone support in a thrust cone assembly for a rocket launch unmanned aerial vehicle according to an embodiment of the present application;
The reference numerals in the drawings indicate:
The device comprises a 1-unmanned aerial vehicle, a 2-rocket, a 3-thrust cone, a 4-thrust cone support, a 5-thrust cone beam, a 6-flange, a 7-igniter, an 8-explosion bolt, a 9-first gasket, a 10-self-locking nut, an 11-bolt component, a 12-second gasket, a 13-matching hole, a 14-countersunk bolt, a 15-supporting plate nut, a 16-countersunk rivet, a 17-first round tube, a 18-hexagonal bolt, a 19-through hole, a 20-second round tube, a 21-clamping plane, a 22-through hole, a 23-waist-shaped hole, a 24-connecting hole, a 25-through hole, a 26-bump, a 27-connecting tube and a 28-explosion bolt fracture surface.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present application are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
In the present application, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, if there is a description of "first", "second", etc. in the embodiments of the present application, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" as it appears throughout includes three parallel schemes, for example "A and/or B", including the A scheme, or the B scheme, or the scheme where A and B are satisfied simultaneously. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present application.
Unmanned aerial vehicles play an important role in modern warfare, and unmanned aerial vehicle system technology has been greatly developed under the large background that people begin to explore sixth generation warfare, namely unmanned or unmanned aerial vehicles, as five generation warfare becomes the main air defense force of all countries of the world. The supersonic unmanned aerial vehicle has the characteristics of small aspect ratio, high maneuverability, good stealth performance and the like, and a plurality of supersonic unmanned aerial vehicles are developed at home and abroad.
In order to ensure that the supersonic unmanned aerial vehicle is rapidly put into operation, the rocket launching unmanned aerial vehicle is adopted to become a new unmanned aerial vehicle launching thought, and the supersonic unmanned aerial vehicle has the advantages of being independent of airports, rapid in response and the like. The launching mode needs to set a thrust cone on the unmanned aerial vehicle to transfer the thrust of the rocket and realize the automatic falling of the aircraft. The thrust cone of the subsonic unmanned aerial vehicle is often fixedly arranged on a bulkhead or a beam at the tail part of the aircraft, so that the appearance of the aircraft is larger concave and convex, the aerodynamic performance of the aircraft is often poor, and the scheme of the thrust cone cannot be adopted when the supersonic unmanned aerial vehicle adopts rocket for launching.
Therefore, a rocket launching thrust cone scheme for the supersonic unmanned aerial vehicle is designed, so that the supersonic unmanned aerial vehicle can be launched rapidly and stably, and the method has important significance for the development of unmanned aerial vehicle launching technology.
The embodiment of the application provides a thrust cone assembly for a rocket launching unmanned aerial vehicle, which comprises a thrust cone support 4, an explosion bolt assembly and a thrust cone 3, wherein the thrust cone support 4 is in a triangular prism shape, the explosion bolt assembly is arranged on a first side surface of the thrust cone support 4 and is used for connecting the thrust cone support 4 with a thrust cone beam 5 on the belly of the unmanned aerial vehicle, and the explosion bolt assembly explodes when fuel of a rocket 2 is exhausted so as to separate the thrust cone support 4 from the unmanned aerial vehicle 1; the thrust cone 3 is arranged on a second side surface of the thrust cone support 4, the second side surface is a side surface of the thrust cone support 4, which is close to the tail of the unmanned aerial vehicle, the large-diameter end of the thrust cone 3 is connected with the thrust cone support 4, and the conical surface of the thrust cone 3 is used for being matched with a cone cylinder at the head of the rocket 2.
In this embodiment, the rocket propulsion mode is adopted, the unmanned aerial vehicle can quickly reach the condition of supersonic flight, in order to make the propulsion emission better and stable, the conical surface matching mode is adopted, the conical cylinder at the head of the rocket 2 is matched with the conical surface of the thrust cone 3, the thrust cone 3 is connected with the thrust cone beam 5 at the abdomen of the unmanned aerial vehicle 1 through the thrust cone support 4, the installation angle of the rocket 2 and the thrust cone 3 is fixed, and the power transmission is realized, and under the propulsion of the rocket 2, the rocket 2 always keeps stable and tight butt with the thrust cone 3 due to the adoption of the conical surface matching mode, after the fuel of the rocket 2 is exhausted, the acceleration of the unmanned aerial vehicle which loses the boosting of the rocket 2 is reduced, the rocket 2 cannot keep butt with the thrust cone 3, the separation with the unmanned aerial vehicle 1 is realized along the conical surface, the rocket 2 can be started to explode the explosion bolt assembly to separate the thrust cone support 4 from the thrust cone beam 5 at the same time, and the appearance of the unmanned aerial vehicle 1 can keep good aerodynamic performance due to the explosion separation of the protruding parts such as the thrust cone support 4, especially the appearance of the abdomen can not influence the supersonic flight, and the supersonic emission is realized, and the supersonic emission is fast and stable.
In the embodiment of the present application, the thrust cone support 4 is configured as a triangular prism, as shown in fig. 2, referring to the structure of the triangular prism, two surfaces with the same shape are the top surface and the bottom surface of the triangular prism respectively, the other surfaces are side surfaces, that is, the horizontal surface in the drawing is the first side surface of the thrust cone support 4, the second side surface of the thrust cone support is provided with the kidney-shaped hole 23, the second side surface is required to face the tail of the unmanned aerial vehicle 1 during installation, the surface forming the through hole 22 is the top surface and the bottom surface of the thrust cone support 4 respectively, in order to reduce the weight of the thrust cone support 4 and improve the strength of the structure, the thrust cone support 4 can be configured as a hollowed structure, and the hollowed structure can be arranged on the first side surface, the bottom surface and the top surface.
In one embodiment, as shown in fig. 1 and 2, the thrust cone assembly further includes a thrust cone mounting seat, the large diameter end of the thrust cone 3 is connected with the thrust cone mounting seat, the second side surface of the thrust cone support 4 is provided with a plurality of kidney-shaped holes 23, the extending direction of the kidney-shaped holes 23 is parallel to the vertical extending direction of the second side surface, the plurality of kidney-shaped holes 23 are uniformly distributed around the center of the second side surface, the thrust cone mounting seat is connected with the thrust cone support 4 through the kidney-shaped holes 23 by bolts, and as shown in fig. 6, the thrust cone mounting seat is connected with the thrust cone support 4 by bolts 11, and the bolts 11 include self-locking nuts, second gaskets 12 and hexagonal bolts 18.
In this embodiment, since the launch angle is calculated in advance during launching, that is, the inclination angle of the second side surface is fixed with the assembly angle of the rocket 2, there is no deviation in angle, but during actual launching, there is a certain deviation between the rocket 2 and the position of the thrust cone 3 in the vertical direction due to factors such as the launch pad, the rocket 2 size, the unmanned aerial vehicle 1 size, etc., and the launch pad, the rocket 2, etc. are fixed large components, which is inconvenient to adjust, and at this time, the installation position of the thrust cone 3 can be adjusted up and down through the kidney-shaped hole 23, so as to realize accurate butt-joint assembly with the rocket 2.
In one embodiment, as shown in fig. 1, 4 and 6, an implementation of an explosion bolt assembly is provided, specifically, the explosion bolt assembly includes an explosion bolt 8, a flange assembly and a self-locking nut 10, the explosion bolt 8 is connected with a thrust cone beam 5 through the flange assembly, and one end of the explosion bolt 8 penetrates through a first side surface of a thrust cone support 4 and then is matched with the self-locking nut 10. The flange assembly is characterized in that a flange connection mode is adopted, tight assembly can be achieved, quick assembly and disassembly can be achieved, a flange assembly can be composed of a flange 6, a countersunk bolt 14, a supporting plate nut 15 and a countersunk rivet 16 as shown in the attached drawing 1, an explosion bolt 8 is connected with the flange 6 through threads, the flange 6 is connected with a thrust cone beam 5 through the countersunk bolt 14, the supporting plate nut 15 and the countersunk rivet 16 after a mounting hole is formed, one end of the explosion bolt 8 penetrates through the thrust cone support 4, a through hole 25 is formed in the first side face of the thrust cone support 4, and the explosion bolt 8 is mounted in a threaded fit with the self-locking nut 10. In other embodiments, the assembly and installation of the explosive bolt assembly may be realized by adopting a hexagon bolt, welding, etc., and in order to ensure the tight assembly of the self-locking nut 10, a gasket, that is, the first gasket 9, is added at the matching position of the self-locking nut 10 and the explosive bolt 8.
In this embodiment, the explosive bolt 8 is also called a fragment-free explosive bolt, and is used for multipoint connection of the separating surfaces. The explosion bolt 8 is similar to a common bolt, is internally provided with an explosive and an igniter, and is detonated when separated, so that the shear lock is sheared or broken along a bolt weakening groove to realize two-separation unlocking, and the explosion bolt has various varieties and mainly comprises a slotted type, a shear pin type, a steel ball type explosion bolt, a pollution-free explosion bolt and the like. The device has the advantages of large bearing capacity, simple structure, reliable operation and convenient use, and in the embodiment of the application, the explosion bolt 8 is used as a main shaft to be connected, and a plurality of explosion points are not arranged, so that a plurality of explosion points are required to be successfully exploded in explosion separation, and only one explosion bolt 8 is required to be cracked along the explosion bolt fracture surface 28 after explosion, thereby realizing the rapid separation of the thrust cone support 4.
In an embodiment, as shown in fig. 1, an igniter 7 of an explosion bolt 8 is arranged at one end of the explosion bolt 8, which is close to the unmanned aerial vehicle 1, so that the igniter 7 is prevented from being inconvenient to control outside, the igniter 7 is used for triggering the explosion of the explosion bolt 8, the igniter 7 is electrically connected with a control system of the unmanned aerial vehicle 1, and after the separation condition is achieved, the control system of the unmanned aerial vehicle 1 controls the explosion bolt 8 to conduct electrifying and igniting, so that the rapid automatic control of the separation is realized.
In one embodiment, as shown in fig. 1 and 3, in order to provide a supporting point for the unmanned aerial vehicle 1 when the launching cradle launches the unmanned aerial vehicle 1, a supporting component is added for the thrust cone component, specifically, the supporting component comprises a first circular tube 17, a second circular tube 20 and a connecting tube 27, one end of the first circular tube 17 is in threaded connection with one end of the connecting tube 27, one end of the second circular tube 20 is in threaded connection with the other end of the connecting tube 27, two ends of the supporting component respectively penetrate through the top surface and the bottom surface of the thrust cone support 4 and form a through hole 22, and the connecting tube 27 is located in an inner cavity of the thrust cone support 4.
In this embodiment, through setting up the level to with unmanned aerial vehicle 1 launch starting direction vertically supporting component, make unmanned aerial vehicle 1 can seek balanced supporting position on the launching frame, can all realize flexible regulation through the mode of screw thread first pipe 17 and second pipe 20 and lift the emitter realization, first pipe 17 and second pipe 20 and thrust cone support 4 on the through-hole 22 adopt clearance fit, in order to guarantee quick adjustment installation, the external diameter of connecting pipe 27 is greater than the diameter of through-hole 22, in order to restrict the axial displacement of first pipe 17 and second pipe 20.
In one embodiment, as shown in fig. 1 and 3, a clamping plane 21 is provided on the outer wall of the end, away from each other, of the first round tube 17 and the second round tube 20, and the smooth tube wall can be clamped stably and adjusted quickly by using tools such as a wrench through the clamping plane 21.
In one embodiment, as shown in fig. 1, in order to facilitate separation of the rocket 2 on the basis that the thrust cone support 4 is configured as a hollow structure, a through hole 19 extending in the axial direction of the thrust cone 3 is formed, and a connection hole 24 is formed on a second side surface of the thrust cone support 4, so that an inner cavity of the thrust cone support 4 is communicated with the through hole of the thrust cone 3. The arrangement avoids that the rocket 2 cannot be naturally separated due to the fact that the rocket 2 is in tight contact with the thrust cone 3 and air pressure difference is formed between the rocket 2 and the outside, after the rocket 2 is communicated with the outside, the matched part is communicated with the outside, consistent air pressure is maintained, and after the fuel of the rocket 2 is exhausted, the rocket can be naturally separated along the matched conical surface due to gravity.
In one embodiment, as shown in fig. 1 and 2, in order to facilitate positioning and installation, a plurality of protruding blocks 26 are disposed around the first side surface of the thrust cone support 4, a plurality of matching holes 13 matched with the protruding blocks 26 are disposed on the thrust cone beam 5, when the thrust cone support 4 is installed, quick installation is realized through positioning of the protruding blocks 26 and the matching holes 13, and the protruding blocks 26 and the matching holes 13 adopt a clearance fit mode so as to facilitate quick falling off of the thrust cone support 4 after explosion separation.
The working principle of the thrust cone assembly for the rocket launching unmanned aerial vehicle provided by the embodiment of the application is as follows: as shown in fig. 5, the assembly of the thrust cone assembly is completed, the rocket 2 transmits thrust through the thrust cone 3 box unmanned aerial vehicle 1 when waiting for launching, because the rocket 2 and the thrust cone 3 transmit force through conical surface contact, when the rocket 2 is exhausted, the rocket 2 automatically drops off from the thrust cone 3 along the conical surface, the engine of the unmanned aerial vehicle 1 can be synchronously started during launching, the unmanned aerial vehicle 1 receives the common thrust of the rocket 1 and the engine, after the rocket 2 is separated, the acceleration of the unmanned aerial vehicle 1 is reduced, the acceleration of the aircraft control system can be reduced to be the basis for separating the rocket 2, the explosion bolt 8 is controlled to be electrified and ignited, the explosion bolt 8 is disconnected along the explosion bolt fracture surface 28, the thrust cone support 4 falls off from the unmanned aerial vehicle 1 under the action of gravity, the first circular tube 17, the second circular tube 20, the connecting tube 27, the thrust cone 3 and a plurality of connecting pieces also fall off along with the thrust cone support 4, and the flange 6, most of the explosion bolt 8 and the supporting plate 15 and the connecting pieces thereof remain on the unmanned aerial vehicle 1 at the moment, as shown in fig. 7, the engine body has no large bulge, and has good aerodynamic performance.
In summary, according to the thrust cone assembly for the rocket launching unmanned aerial vehicle, provided by the embodiment of the application, the launching conditions of the supersonic unmanned aerial vehicle are met through rocket boosting, the launching component can be quickly dropped off after boosting is completed, a large bulge which influences aerodynamic performance is not left on a machine body, and the rapid and stable launching of the supersonic unmanned aerial vehicle is realized.
The foregoing description of the preferred embodiments of the application is not intended to limit the application to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the application are intended to be included within the scope of the application.
Claims (10)
1. The utility model provides a rocket launch unmanned aerial vehicle is with thrust cone subassembly which characterized in that, includes thrust cone support, explosion bolt assembly and thrust cone, wherein:
The thrust cone support is in a triangular prism shape, the explosion bolt assembly is arranged on the first side face of the thrust cone support and is used for connecting the thrust cone support with a thrust cone beam on the belly of the unmanned aerial vehicle, and the explosion bolt assembly explodes when rocket fuel is exhausted so as to separate the thrust cone support from the unmanned aerial vehicle;
The thrust cone is arranged on a second side face of the thrust cone support, the second side face is a side face, close to the tail of the unmanned aerial vehicle, of the thrust cone support, the large-diameter end of the thrust cone is connected with the thrust cone support, and the conical face of the thrust cone is used for being matched with a cone cylinder of the rocket head.
2. A rocket launch vehicle according to claim 1 wherein said thrust cone assembly further comprises a thrust cone mount, said thrust cone large diameter end being connected to said thrust cone mount, said thrust cone mount having a second side provided with a plurality of kidney-shaped apertures, said kidney-shaped apertures extending parallel to a vertical direction of extension of said second side, said plurality of kidney-shaped apertures being uniformly distributed about a center of said second side, said thrust cone mount being bolted to said thrust cone mount through said kidney-shaped apertures.
3. A rocket launch vehicle thrust cone assembly according to claim 1 wherein said explosive bolt assembly comprises an explosive bolt, a flange assembly and a self-locking nut, said explosive bolt being connected to said thrust cone beam by said flange assembly, one end of said explosive bolt passing through said first side of said thrust cone support and then engaging said self-locking nut.
4. A rocket launch vehicle thrust cone assembly according to claim 3 wherein said explosive bolt assembly further comprises an igniter disposed at an end of said explosive bolt adjacent said vehicle, said igniter being adapted to trigger an explosion of said explosive bolt, said igniter being electrically connected to said vehicle control system.
5. A rocket launch vehicle according to claim 1 wherein said thrust cone assembly further comprises a support assembly comprising a first tubular, a second tubular and a connecting tube, one end of said first tubular being threadably connected to one end of said connecting tube, one end of said second tubular being threadably connected to the other end of said connecting tube, both ends of said support assembly extending through the top and bottom surfaces of said thrust cone support respectively and forming a through hole, said connecting tube being located in the interior cavity of said thrust cone support.
6. A rocket launch vehicle thrust cone assembly according to claim 5 wherein said first and second tubular tubes are provided with a gripping surface on an outer wall of said end thereof remote from each other, said first and second tubular tubes being in clearance fit with said through-hole.
7. A rocket launch unmanned aerial vehicle thrust cone assembly according to claim 5 wherein the outer diameter of said connecting tube is greater than the diameter of said through-hole.
8. The rocket launch vehicle thrust cone assembly of claim 1 wherein the thrust cone support is hollow, the thrust cone is provided with a through hole extending in the axial direction thereof, and the second side of the thrust cone support is provided with a connecting hole, so that the inner cavity of the thrust cone support is communicated with the through hole of the thrust cone.
9. A rocket launch vehicle according to claim 1 wherein a plurality of projections are provided around the first side of the thrust cone support, and a plurality of mating holes are provided in the thrust cone beam for mating with the projections.
10. A rocket launch vehicle thrust cone assembly according to claim 9 wherein said lugs are clearance fit with said mating holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211190944.0A CN115610693B (en) | 2022-09-28 | 2022-09-28 | Rocket launching unmanned aerial vehicle is with thrust cone subassembly |
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| CN202211190944.0A CN115610693B (en) | 2022-09-28 | 2022-09-28 | Rocket launching unmanned aerial vehicle is with thrust cone subassembly |
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| CN115610693A CN115610693A (en) | 2023-01-17 |
| CN115610693B true CN115610693B (en) | 2024-05-14 |
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Citations (16)
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