CN111422370A - Unmanned aerial vehicle ejection rack single machine, parallel track ejection rack and launching method thereof - Google Patents
Unmanned aerial vehicle ejection rack single machine, parallel track ejection rack and launching method thereof Download PDFInfo
- Publication number
- CN111422370A CN111422370A CN202010198538.3A CN202010198538A CN111422370A CN 111422370 A CN111422370 A CN 111422370A CN 202010198538 A CN202010198538 A CN 202010198538A CN 111422370 A CN111422370 A CN 111422370A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- main
- wing
- main track
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
A flexible combined type unmanned aerial vehicle united track ejection rack comprises a plurality of unmanned aerial vehicle ejection rack units which are connected in parallel, and each unmanned aerial vehicle ejection rack unit comprises a main frame body, a main track pulley, an elastic part, a locking and releasing mechanism and a buffering mechanism. The flexible combined type unmanned aerial vehicle row track ejection rack is suitable for multiple unmanned aerial vehicles combined through wing tip connection structures, synchronous emission of the flexible combined type unmanned aerial vehicles is achieved through the flexible combined type unmanned aerial vehicle row track ejection rack, and the problem that wing joints are damaged due to incongruity of stress is solved. The unmanned aerial vehicle ejection rack single machine, the parallel track ejection rack and the launching method thereof have the characteristics of adjustable launching angle, adjustable launching speed, good synchronism and strong universality.
Description
Technical Field
The invention relates to the field of aircraft design, in particular to an unmanned aerial vehicle ejection rack single machine, a row track ejection rack and an ejection method thereof.
Background
The unmanned aerial vehicle does not need the characteristics of an airborne pilot, can be suitable for harsher and dangerous task environments, does not need to be provided with equipment such as a life support system, a cockpit and the like, and can carry more task loads under the same weight, so that the aim of light weight of the aircraft is fulfilled. With the development of the unmanned aerial vehicle industry, the unmanned aerial vehicle mainly used for military in the past gradually enters the civil mission, and is widely applied to the aspects of environment monitoring, line patrol, high-altitude survey, terrain mapping, aerial photography and the like. At present, the main development directions of unmanned aerial vehicles are low-altitude digitization (small unmanned aerial vehicles), high-altitude long endurance (large-aspect-ratio unmanned aerial vehicles) and cluster intelligence, and development requirements of ' developing, integrating, generalizing and intelligently communicating, navigating and controlling systems ' are clearly proposed in ' national strategic emerging industry development planning ', and developing technical systems and equipment ' which are applied to multi-class airspace fusion are developed. The combined type unmanned aerial vehicle integrated system is based on the military and civil integration application development requirements of unmanned aerial vehicles, combines the characteristics of large exhibition ratio and light and thin fuselage of the unmanned aerial vehicle during high-altitude long-endurance flight and the characteristics of low cost, flexible structure and clustering of low-altitude digital small unmanned aerial vehicles, and provides an innovative cluster formation form of a combined type unmanned aerial vehicle with large exhibition ratio formed by connecting a plurality of small unmanned aerial vehicles in parallel through flexible connection of wings, and develops the overall scheme and subsystem scheme design of the combined type unmanned aerial vehicle.
The flexible combined unmanned aerial vehicle is a basic unit of a small and medium-sized unmanned aerial vehicle which is low in cost, high in reliability and easy to group, and a plurality of single machines are connected through a flexible structure to form a large-aspect-ratio cooperative whole body, as shown in figure 1. The flexible combination is the characteristics of assembly unmanned aerial vehicle, and flexible structure adopts elastic material or the flexible mechanism that has the limited degree of freedom deformation of certain direction to realize. The flexible combined unmanned aerial vehicle mainly has the characteristics of low flying speed, large aspect ratio, flexible connection and the like.
The takeoff (launching) and landing (recovery) phases of the unmanned aerial vehicle are often considered to be the most difficult and critical phases in the operation of the unmanned aerial vehicle, and directly influence the tactical indexes and requirements of the unmanned aerial vehicle system, such as maneuverability, regional adaptability, reusability, viability and the like. Therefore, selecting and determining the appropriate combined unmanned aerial vehicle (launch) and landing (recovery) mode is an important task to be accomplished in the overall solution of the unmanned aerial vehicle system. At present, no research is specially aimed at the taking-off and landing technology of the novel unmanned aerial vehicle, and the conventional common launching technologies mainly comprise rocket boosting, track ejection, air launching, vehicle-mounted launching, hand-thrown launching and vertical take-off. In the transmission scheme that is applicable to flexible combination formula unmanned aerial vehicle, comparatively speaking: 1. the ground running depends on airport runways or better ground environment conditions, the maneuverability is poor, and the undercarriage part also needs to occupy the onboard space and the weight of the unmanned aerial vehicle part; 2. the aerial launching needs a proper carrier to provide a launching platform, depends on a guarantee system, and has high use cost and poor maneuverability; 3. hand-thrown launch is a viable solution, but takeoff weight is limited; 4. the ground ejection mode of the ejection rack has good maneuverability, good safety, good concealment and low use cost, can meet the requirements of economy and operability, but has higher requirements on synchronism and reliability for a large-exhibition ratio flexible combined unmanned aerial vehicle, and the common ejection mode cannot ensure the synchronism and universality requirements of the emission stage of the combined unmanned aerial vehicle, so that the research on the characteristics and the design scheme of the emission of the combined unmanned aerial vehicle needs to be carried out.
Disclosure of Invention
In view of the above, the present invention provides a single drone ejection rack, a tandem track ejection rack and a launching method thereof, so as to at least partially solve at least one of the above mentioned technical problems.
In order to achieve the purpose, the invention adopts the following technical scheme:
as one aspect of the present invention, there is provided an unmanned aerial vehicle ejection rack stand-alone, comprising:
the two ends of the main frame body in the extension direction are respectively a starting end and a tail end;
the main track pulley is arranged on the main frame body in a sliding mode and used for bearing and launching the unmanned aerial vehicle;
an elastic member provided at the end of the main frame body for driving the main rail block to move along the start end to the end of the main frame body by a tensile elastic force;
the locking and releasing mechanism is arranged at the initial end of the main frame body and is used for controlling the locking or releasing of the main track pulley at the initial end;
the buffer mechanism is arranged at the tail end of the main frame body and used for preventing the main track pulley from continuously moving and absorbing the kinetic energy of the main track pulley;
when the main track pulley is pulled by the elastic component to move to be in contact with the buffer mechanism, the main track pulley and the borne unmanned aerial vehicle move relatively and are separated, and catapult takeoff of the unmanned aerial vehicle is achieved.
As another aspect of the invention, the invention also provides a flexible combined unmanned aerial vehicle parallel track catapult which comprises a plurality of unmanned aerial vehicle catapult single machines which are arranged in parallel.
As a further aspect of the present invention, there is also provided a launching method using the flexible combined type unmanned aerial vehicle parallel rail ejection rack as described above, including the following steps:
step 1: the flexible combined unmanned aerial vehicle launching frame is characterized in that a plurality of flexible combined unmanned aerial vehicles are respectively and correspondingly arranged on each main track pulley of the flexible combined unmanned aerial vehicle parallel track launching frame, the elastic component applies stretching elastic force to the main track pulley at the starting end, and the locking and releasing mechanism applies locking force balanced with the stretching elastic force to the main track pulleys;
step 2: the locking and releasing mechanism releases locking force to the main track pulley, and the main track pulley drives the flexible combined unmanned aerial vehicle to move from the starting end to the tail end of the main frame body under the driving of the elastic component;
and step 3: when the main track pulley contacts the buffer mechanism, the main track pulley and the flexible combined unmanned aerial vehicle move relatively until being separated, and catapult takeoff of the flexible combined unmanned aerial vehicle is completed.
Based on the technical scheme, compared with the prior art, the invention has at least one or one part of the following beneficial effects:
the flexible combined unmanned aerial vehicle parallel rail ejection rack adopts an unmanned aerial vehicle ejection rack single-machine parallel mode, and adapts to the ejection requirements of different numbers of flexible combined unmanned aerial vehicles by connecting different numbers of unmanned aerial vehicle ejection rack single machines in parallel;
the unmanned aerial vehicle ejection rack single machine adopted by the flexible combined type unmanned aerial vehicle parallel track ejection rack utilizes the elastic part to provide driving force, utilizes the buffer mechanism to realize ejection, utilizes the locking and releasing mechanism to control operation, and has high safety and simple and energy-saving driving mode;
the flexible combined type unmanned aerial vehicle parallel track ejection rack adopts the electric magnetic type locking and releasing mechanism, so that the release instantaneity, synchronism and reliability of the single machine of each unmanned aerial vehicle ejection rack can be ensured, and the damage of the flexible combined type unmanned aerial vehicle caused by the emission difference of different unmanned aerial vehicle ejection racks is avoided;
the main frame bodies of the flexible combined type unmanned aerial vehicle parallel track ejection frame have an adjustable function, can realize selection of different emission angles and different emission speeds, and can meet emission requirements of flexible combined type unmanned aerial vehicle structures with different wingspans and different body lengths.
Drawings
Fig. 1 is a schematic view of a flexible combined drone;
fig. 2 is a perspective view of an unmanned aerial vehicle ejection rack unit according to embodiments 1-3 of the present invention;
FIG. 3 is a schematic view of the U-shaped groove of the fuselage mounting assembly and the U-shaped boss of the fuselage cradle of embodiments 1-3 of the present invention;
FIG. 4 is a schematic front view of a main rail block according to embodiments 1 to 3 of the present invention;
FIG. 5 is a schematic perspective view of a wing support according to embodiments 1-3 of the present invention;
FIG. 6 is a right-side view of the electromagnetic chuck in accordance with embodiments 1-3 of the present invention;
fig. 7 is a schematic perspective view of a tandem track ejector according to embodiments 2-3 of the present invention.
In the above figures, corresponding reference numerals have the following meanings:
1. a flexible combined unmanned aerial vehicle; 2. a support pillar; 3. an emission angle positioning hole; 4. a launch angle positioning bolt; 5. a slot; 6. an elastic member; 7. a buffer mechanism; 8. a fuselage cradle; 9. a U-shaped boss; 10. a wing support; 11. a main track block; 12. an electromagnetic chuck; 13. a ground support; 14. Positioning a rod; 15. positioning a support; 16. a hauling rope; 17. a launching speed positioning hole; 18. a pulley; 19. a main frame body; 20. a chuck power signal line; 21. a capstan power signal line; 22. an electric capstan; 23. a power signal controller; 24. a fuselage mount; 25. a U-shaped groove; 26. the unmanned aerial vehicle launches a stand single machine; 27. a stop angle positioning hole; 28. a machine halt angle positioning bolt; 29. a wing bracket vertical section; 30. a wing bracket cross section; 31. wingspan positioning holes; 32. a span positioning bolt; 33. a body length positioning hole; 34. a tab; 35. a fuselage length positioning bolt; 36. and fastening the bolt.
Detailed Description
The invention mainly aims to overcome the defects of the prior art on flexible combined unmanned aerial vehicle ejection with large display ratio, and researches and provides an unmanned aerial vehicle ejection rack single-machine, a parallel rail ejection rack and an ejection method thereof.
This flexible combination formula unmanned aerial vehicle allies oneself with arranges track launching cradle includes that a plurality of unmanned aerial vehicle launching cradles the unit and connects in parallel, and unmanned aerial vehicle launching cradle unit includes the body frame body, main track coaster, elasticity part, locking release mechanism, buffer gear. The flexible combined type unmanned aerial vehicle row track ejection rack is suitable for multiple unmanned aerial vehicles combined through wing tip connection structures, synchronous emission of the flexible combined type unmanned aerial vehicles is achieved through the flexible combined type unmanned aerial vehicle row track ejection rack, and the phenomenon that wing joints are damaged due to incongruity of stress is avoided. The unmanned aerial vehicle ejection rack single machine, the parallel track ejection rack and the launching method thereof have the characteristics of adjustable launching angle, adjustable launching speed, good synchronism and strong universality.
In order that the objects, technical solutions and advantages of the present invention will become more apparent, the present invention will be further described in detail with reference to the accompanying drawings in conjunction with the following specific embodiments.
Example 1
In a first exemplary embodiment of the present invention, as shown in fig. 2-6, there is provided a drone ejection rack stand, comprising:
the main frame body 19, the two ends of the main frame body 19 in the extending direction are respectively a starting end and a tail end;
the main track pulley 11 is arranged on the main frame body 19 in a sliding mode and used for bearing and launching the unmanned aerial vehicle;
an elastic member 6 provided at the end of the main frame 19 for driving the main rail block 11 to move along the start end to the end of the main frame 19 by a tensile elastic force;
a locking and releasing mechanism which is arranged at the initial end of the main frame body 19 and is used for controlling the locking or releasing of the main track pulley 11 at the initial end;
the buffer mechanism 7 is arranged at the tail end of the main frame body 19 and used for preventing the main track pulley 11 from continuing to move and absorbing the kinetic energy of the main track pulley 11;
when the main track pulley 11 is pulled by the elastic component 6 to move to contact with the buffer mechanism 7, the main track pulley 11 and the loaded unmanned aerial vehicle move relatively and break away from each other, and the catapult takeoff of the unmanned aerial vehicle is realized.
It should be noted that, in the embodiment of the present invention, as shown in fig. 2, the beginning is defined as a right end, and the end is defined as a left end.
In an embodiment of the present invention, as shown in fig. 2, the unmanned aerial vehicle ejection rack stand-alone further includes a power signal controller 23;
wherein, the power signal controller comprises a power module, an electric capstan control module, and an electromagnetic chuck control module (not shown); the power module supplies power to the unmanned aerial vehicle ejection rack single machine through an external power supply or an internal battery, namely supplies power to the locking and releasing mechanism and the electric carrying equipment such as the electric winch and the like; the electric winch control module is used for controlling the operation mode of the electric winch, and the electromagnetic chuck control module is used for controlling the operation of the locking and releasing mechanism;
the locking and releasing mechanism is of an electric magnetic type, and the main track pulley 11 is made of a magnetic material;
the locking and releasing mechanism comprises an electromagnetic chuck 12, and the electromagnetic chuck 12 is electrically connected with a power signal controller 23;
more specifically, the locking and releasing mechanism further includes a chuck power signal line 20; the electromagnetic chuck 12 is connected with the power signal controller 23 through a chuck power signal wire 20; the electromagnetic chuck control module of the power signal controller 23 controls the electromagnetic chuck 12 to be powered on and off instantly or to be powered off and demagnetized instantly.
As shown in fig. 2 and 6, a plurality of emission speed positioning holes 17 are formed in the main frame body 19 at intervals along the extending direction of the main frame body 19, and the electromagnetic chuck 12 is screwed and fixed to the predetermined emission speed positioning holes 17 by fastening bolts 36.
More specifically, the main track pulley 11 is made of a magnetic material, and after the electromagnetic chuck 12 of the locking and releasing mechanism is electrified and magnetized, the electromagnetic chuck can be in contact with the main track pulley 11 to generate attraction force for locking; when the electromagnetic chuck 12 is demagnetized, the suction force with the main rail block 11 disappears, and the main rail block 11 is instantaneously released under the driving of the stretching elastic force of the elastic component 6.
In addition, it is worth mentioning that the electromagnetic chuck 12 selects different launching speed positioning holes 17 for position fixing, that is, determines the stretching length of the elastic component 6, and further selects the running speed of the main track pulley 11 driven by the elastic component 6, thereby controlling the launching speed of the unmanned aerial vehicle.
In the embodiment of the invention, as shown in fig. 2 and 4, the unmanned plane catapult stand unit further comprises an electric winch 22 and a winch power signal wire 21; the electric capstan 22 is provided at the beginning of the main frame 19, i.e., at the right end in the present embodiment; the electric capstan 22 is electrically connected with the power signal controller 23; namely, the electric capstan 22 is electrically connected with the power supply signal controller 23 through the capstan power signal wire 21; the electric capstan control module of the power signal controller 23 controls the forward rotation operation or the reverse rotation operation of the electric capstan 22.
As shown in fig. 4, the main track trolley 11 is provided with a lug 34, and more specifically, the lug 34 is arranged at the bottom of the main track trolley 11; the electric winch 22 is connected to the tab 34 by the pull cord 16.
In the embodiment of the present invention, as shown in fig. 2, the elastic member 6 includes a spring, one end of which is connected to the end of the main frame body 19 and the other end of which is connected to the main rail block 11.
In the embodiment of the present invention, the buffer mechanism 7 includes a columnar buffer body and a columnar elastic body, one end of the buffer body is fixedly connected to the main frame 19, the other end of the buffer body is covered by the elastic body, and the elastic body extends outward along the axial direction of the buffer body;
wherein, the buffer body is made of metal material;
wherein, the elastomer is made of porous polyurethane material.
In the embodiment of the invention, as shown in fig. 2 and 3, the main track trolley 11 is vertically provided with the fuselage support 8, the top of the fuselage support 8 is provided with a boss, the unmanned aerial vehicle is provided with the fuselage mounting piece 24, and the fuselage mounting piece 24 is correspondingly provided with a groove which is matched and butted with the boss;
the lug boss and the groove are matched and arranged into a U shape;
it should be noted that, in the embodiment of the present invention, the main rail trolley 11 is designed into a frame shape, and includes an upper plate, a lower plate and two side plates, and the upper plate of the main rail trolley 11 is provided with the machine body support 8; 8 tops of fuselage support are equipped with a U type boss 9, correspond on the fuselage installed part 24 on the unmanned aerial vehicle and set up U type recess 25, and the connection function is realized through the butt joint of U type boss 9 and U type recess 25 to main track coaster 11 and unmanned aerial vehicle.
As shown in fig. 4, the machine body support 8 is a two-section sleeved connection, one of the sections of the machine body support 8 is correspondingly provided with a plurality of stop angle positioning holes 27, and the two sections of the machine body support 8 are screwed to the predetermined stop angle positioning holes 27 through stop angle positioning bolts 28 for adjustment and fixation. By selecting different stop angle positioning holes 27, the launch angle of attack of the unmanned aerial vehicle 1 can be finely adjusted.
In the present embodiment, as shown in fig. 4 and 5, the wing frames 10 are respectively disposed on two side walls (i.e. two side plates) of the main track trolley 11, and the wing frames 10 include L-type wing frame horizontal sections 30 and wing frame vertical sections 29;
the free end of the vertical section part 29 of the wing support is used for supporting the wing of the unmanned aerial vehicle, so that the wing supporting effect of the large aspect ratio is realized;
wherein, a plurality of fuselage length positioning holes 33 are respectively arranged on two side walls of the main track pulley 11, and the free end of the wing support cross section part 30 is screwed in the preset fuselage length positioning holes 33 through a fuselage length positioning bolt 35 for adjustment and fixation; namely, the root of the wing support 10 is connected to the positioning holes 33 with different fuselage lengths, so that the wing support 10 can support the unmanned aerial vehicles with different fuselage lengths.
As shown in fig. 5, the wing support horizontal section 30 is a two-section type, in which a plurality of span positioning holes 31 are correspondingly disposed on one section of the wing support horizontal section 30, and the wing support 10 is screwed into a predetermined span positioning hole 31 through a span positioning bolt 32 for adjustment and fixation; the length of the wing support transverse section part 30 is adjusted by adjusting and fixing the wing support transverse section part to different wingspan positioning holes 31, and then the transverse distance of the wing support vertical section part 29 relative to the main track pulley 11 is adjusted, so that the wing support device is suitable for unmanned aerial vehicles with different wingspans and supports wings of the unmanned aerial vehicles with different wingspans.
As shown in fig. 2 and 4, a plurality of pulleys 18 are provided on the main rail block 11, and the main rail block 11 slides on the main frame 19 via the pulleys 18.
More specifically, pulleys 18 are respectively installed on an upper plate, a lower plate and two side plates of the main rail block 11, and when the main rail block 11 operates, the main rail block 11 contacts with a main frame body 19 through the pulleys 18 in a rolling mode, so that friction is reduced.
In the embodiment of the present invention, as shown in fig. 2, the bottom of the initial end of the main frame body 19 is connected to the ground support 13;
wherein, the ground support 13 is provided with at least two positioning supports 15 with round holes at intervals, and the centers of the round holes are positioned on the same horizontal straight line;
more specifically, the lower end of the right side of the main frame body 19 is welded to the ground support 13. The hole centers of the round holes of the positioning support 15 are positioned on the same horizontal straight line and used for carrying out reference positioning when a plurality of unmanned aerial vehicle ejection rack single machines 26 are arranged in a row.
In the embodiment of the present invention, as shown in fig. 2, two side portions of the tail end of the main frame 19 are respectively provided with the supporting columns 2, and the supporting columns 2 are inserted into the slots 5 of the main frame 19; that is, the main frame 19 is provided with the support post 2 at the left end, and the support post 2 is inserted into the slot 5 at the side of the main frame 19.
The support column 2 is in a sleeved two-section type, a plurality of emission angle positioning holes 3 are correspondingly arranged on one section of the support column 2, and the two sections of the support column 2 are screwed in the preset emission angle positioning holes 3 through emission angle positioning bolts 4 to be adjusted and fixed. The attack angle of the unmanned aerial vehicle during launching is determined by selecting the positioning holes 3 with different launching angles.
Thus, the first exemplary embodiment of the present invention has been described.
Example 2
In a second exemplary embodiment of the invention, as shown in fig. 7, a flexible combined unmanned aerial vehicle parallel rail ejection rack is further provided, which comprises a plurality of unmanned aerial vehicle ejection rack units 26 in parallel arrangement according to embodiment 1.
The plurality of unmanned aerial vehicle ejection rack single machines 26 are connected in parallel, and are inserted into the round holes of the positioning supports 15 of the unmanned aerial vehicle ejection rack single machines 26 through the positioning rods 14 to perform the reference positioning of the row.
In addition, it is worth mentioning that the electromagnetic chucks 12 of the plurality of locking and releasing mechanisms and the plurality of electric winches 22 are controlled by the same power signal controller 23 to realize instantaneous simultaneous release, and complete simultaneous operation, launching and takeoff of the plurality of flexible combined unmanned aerial vehicles 1.
Thus, the second exemplary embodiment of the present invention has been described.
Example 3
In a third exemplary embodiment of the present invention, as shown in fig. 2 to 7, there is further provided a launching method using the flexible combined unmanned aerial vehicle parallel rail ejection rack of embodiment 2, including the following steps:
step 1: the flexible combined unmanned aerial vehicle (1) is respectively and correspondingly arranged on each main track pulley (11) of the flexible combined unmanned aerial vehicle parallel track launcher, the elastic component (6) applies stretching elastic force to the main track pulley (11) at the starting end, and the locking release mechanism applies locking force balanced with the stretching elastic force to the main track pulley (11);
more specifically, a U-shaped groove 25 on a fuselage mounting piece 24 of the unmanned aerial vehicle is buckled with a U-shaped boss 9 at the top end of a fuselage support 8; starting the electromagnetic chuck 12 and magnetizing, starting the electric winch 22, enabling the main track pulley 11 to be pulled by the traction rope 16 to move rightwards until the right end face of the main track pulley 11 is tightly combined with the left end face of the electromagnetic chuck 12, and closing the electric winch 22.
Step 2: the locking and releasing mechanism releases locking force to the main track pulley 11, and the main track pulley 11 drives the flexible combined unmanned aerial vehicle 1 to move from the starting end to the tail end of the main frame body 19 under the driving of the elastic component 6;
and step 3: when the main track pulley 11 contacts the buffer mechanism 7, the main track pulley 11 and the flexible combined unmanned aerial vehicle 1 move relatively until being separated, and catapult takeoff of the flexible combined unmanned aerial vehicle 1 is completed.
More specifically, the power signal controller 23 demagnetizes the electromagnetic chuck 12, and each main track pulley 11 drives the flexible combined unmanned aerial vehicle 1 to move to the left side simultaneously under the driving of the elastic component 6 at the moment of demagnetization; when the main track coaster 11 moves 19 left ends of the main frame body, stop motion when the main track coaster 11 contacts with buffer gear 7, flexible combination formula unmanned aerial vehicle 1 continues to move left, and U type boss 9 separates with unmanned aerial vehicle 1's fuselage installed part 24, and flexible combination formula unmanned aerial vehicle 1 leaves flexible combination formula unmanned aerial vehicle and allies oneself with row track ejection rack, accomplishes the transmission.
Of course, it is worth mentioning that before step 1, it is also necessary to determine the launching site and assemble the flexible combined unmanned aerial vehicle parallel rail launching rack, and adjust the launching status. The method specifically comprises the following steps:
determining a launching site and assembling: the method is characterized in that a flat and open region suitable for ejection is selected, the unmanned aerial vehicle ejection rack single machines 26 are assembled, a plurality of unmanned aerial vehicle ejection rack single machines 26 are connected in parallel through the connecting and positioning rod 14, and the suction disc power signal line 20 and the winch power signal line 21 of each unmanned aerial vehicle ejection rack single machine 26 are connected into the power signal controller 23.
Adjusting the emission state: the attack angle of the flexible combined unmanned aerial vehicle 1 during launching is preliminarily determined by adjusting the launching angle positioning hole 3 and the launching angle positioning bolt 4 on the supporting column 2 of the unmanned aerial vehicle launching rack single machine 26, and the launching speed of the flexible combined unmanned aerial vehicle 1 is determined by adjusting the electromagnetic chuck 12 and the launching speed positioning hole 17 on the upper surface of the main rack body 19. The final launching angle of the flexible combined unmanned aerial vehicle 1 is determined by adjusting the stop angle positioning hole 27 on the body support 8. The width of the wing support 10 suitable for the flexible combined unmanned aerial vehicle 1 is determined by selecting the wingspan positioning hole 31 on the wing support 10. The proper width between the fuselage support 8 and the wing support 10 is determined by selecting the main rail trolley 11 side wing support 10 and the fuselage length positioning hole 33.
Thus, the third exemplary embodiment of the present invention has been described.
It should be noted that, for those skilled in the art, the configuration of fig. 7 is only one specific embodiment of the present invention, and the present invention is not limited to the flexible combination connection of three drones. By the flexible combined type unmanned aerial vehicle parallel track catapult frame and the catapulting method, the catapulting, taking off and landing requirements of flexible combined type unmanned aerial vehicles with different configurations and different quantities can be met.
It should be understood by those skilled in the art that the invention of the present invention is not the development of the software or application program, and the software or application program that can perform the functions of providing power, controlling the plurality of electromagnetic chucks to simultaneously and instantaneously magnetize or demagnetize, and simultaneously and positively or negatively rotating the plurality of electric winches in the prior art is applicable to the embodiment of the present invention and will not be described herein again.
It should be noted that the above definition of each module is not limited to the specific structures or shapes mentioned in the embodiments, and those skilled in the art can easily substitute the same.
All modules of embodiments of the present invention may be hardware structures, physical implementations of which include, but are not limited to, physical devices including, but not limited to, transistors, memristors, DNA computers.
Those skilled in the art will appreciate that the modules in the device in an embodiment may be adaptively changed and disposed in one or more devices different from the embodiment. The modules or units or components of the embodiments may be combined into one module or unit or component, and furthermore they may be divided into a plurality of sub-modules or sub-units or sub-components. All of the features disclosed in this specification (including any accompanying claims, abstract and drawings), and all of the processes or elements of any method or apparatus so disclosed, may be combined in any combination, except combinations where at least some of such features and/or processes or elements are mutually exclusive. Each feature disclosed in this specification (including any accompanying claims, abstract and drawings) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. Also in the unit claims enumerating several means, several of these means may be embodied by one and the same item of hardware.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An unmanned aerial vehicle ejection rack unit, its characterized in that includes:
the two ends of the main frame body in the extension direction are respectively a starting end and a tail end;
the main track pulley is arranged on the main frame body in a sliding mode and used for bearing and launching the unmanned aerial vehicle;
an elastic member provided at the end of the main frame body for driving the main rail block to move along the start end to the end of the main frame body by a tensile elastic force;
the locking and releasing mechanism is arranged at the initial end of the main frame body and is used for controlling the locking or releasing of the main track pulley at the initial end;
the buffer mechanism is arranged at the tail end of the main frame body and used for preventing the main track pulley from continuously moving and absorbing the kinetic energy of the main track pulley;
when the main track pulley is pulled by the elastic component to move to be in contact with the buffer mechanism, the main track pulley and the borne unmanned aerial vehicle move relatively and are separated, and catapult takeoff of the unmanned aerial vehicle is achieved.
2. The unmanned aerial vehicle ejector stand unit of claim 1, further comprising a power signal controller;
the locking and releasing mechanism is of an electric magnetic type, and the main track pulley is made of a magnetic material;
the locking and releasing mechanism comprises an electromagnetic chuck, and the electromagnetic chuck is electrically connected with the power signal controller;
the electromagnetic chuck is fixedly connected with the preset emission speed positioning holes in a threaded manner through fastening bolts.
3. The unmanned aerial vehicle ejector stand unit of claim 2, further comprising an electric winch;
the electric winch is arranged at the initial end of the main frame body and is electrically connected with the power supply signal controller;
the main track pulley is provided with lugs, and the electric winch is connected with the lugs through a traction rope.
4. The unmanned aerial vehicle ejector stand unit of claim 1, wherein the resilient member comprises a spring, one end of the spring being attached to the distal end of the main frame body and the other end of the spring being attached to the main rail trolley.
5. The unmanned aerial vehicle ejection rack stand-alone of claim 1, wherein the buffer mechanism comprises a columnar buffer body and a columnar elastic body, one end of the buffer body is fixedly connected with the main frame body, the other end of the buffer body is coated with the elastic body, and the elastic body extends outwards along the axial direction of the buffer body;
the buffer body is made of a metal material;
wherein, the elastomer is made of porous polyurethane material.
6. The unmanned aerial vehicle ejection rack stand-alone unit as claimed in claim 1, wherein the main rail trolley is vertically provided with a body support, a boss is arranged at the top of the body support, the unmanned aerial vehicle is provided with a body mounting piece, and the body mounting piece is correspondingly provided with a groove matched and butted with the boss;
the lug boss and the groove are matched and arranged into a U shape;
the two sections of the machine body support are in threaded connection with a preset stop angle positioning hole through stop angle positioning bolts for adjustment and fixation.
7. The unmanned aerial vehicle ejection rack stand-alone machine as claimed in claim 1 or 6, wherein wing supports are respectively arranged on two side walls of the main track trolley, and each wing support comprises a wing support transverse section part and a wing support vertical section part of L type;
the free end of the vertical section part of the wing support is used for supporting the wing of the unmanned aerial vehicle;
the free end of the transverse section of the wing bracket is in threaded connection with a preset fuselage length positioning hole through a fuselage length positioning bolt so as to be adjusted and fixed;
the wing support comprises wing support cross sections, wing support positioning holes, wing support bolts and wing support positioning bolts, wherein the wing support cross sections are in a sleeved two-section type, a plurality of wing span positioning holes are correspondingly formed in one section of each wing support cross section, and the wing supports are screwed in preset wing span positioning holes through the wing span positioning bolts to be adjusted and fixed;
the main track pulley is provided with a plurality of pulleys, and the main track pulley slides on the main frame body through the pulleys.
8. The unmanned aerial vehicle ejector rack unit of claim 1, wherein the bottom of the primary frame body is connected to the ground support;
the ground support is provided with at least two positioning supports with round holes at intervals, and the centers of the round holes are positioned on the same horizontal straight line;
support columns are respectively arranged at two side parts of the tail end of the main frame body, and the support columns are inserted into the slots of the main frame body;
the support column is in a sleeved two-section type, a plurality of emission angle positioning holes are correspondingly formed in one section of the support column, and the two sections of the support column are in threaded connection with preset emission angle positioning holes through emission angle positioning bolts so as to be adjusted and fixed.
9. A flexible combined unmanned aerial vehicle parallel rail ejector rack, comprising a plurality of unmanned aerial vehicle ejector rack units in parallel arrangement according to any one of claims 1 to 8.
10. A launching method using the flexible combined unmanned aerial vehicle row track ejection rack of claim 9, characterized by comprising the following steps:
step 1: the flexible combined unmanned aerial vehicle launching frame is characterized in that a plurality of flexible combined unmanned aerial vehicles are respectively and correspondingly arranged on each main track pulley of the flexible combined unmanned aerial vehicle parallel track launching frame, the elastic component applies stretching elastic force to the main track pulley at the starting end, and the locking and releasing mechanism applies locking force balanced with the stretching elastic force to the main track pulleys;
step 2: the locking and releasing mechanism releases locking force to the main track pulley, and the main track pulley drives the flexible combined unmanned aerial vehicle to move from the starting end to the tail end of the main frame body under the driving of the elastic component;
and step 3: when the main track pulley contacts the buffer mechanism, the main track pulley and the flexible combined unmanned aerial vehicle move relatively until being separated, and catapult takeoff of the flexible combined unmanned aerial vehicle is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010198538.3A CN111422370A (en) | 2020-03-19 | 2020-03-19 | Unmanned aerial vehicle ejection rack single machine, parallel track ejection rack and launching method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010198538.3A CN111422370A (en) | 2020-03-19 | 2020-03-19 | Unmanned aerial vehicle ejection rack single machine, parallel track ejection rack and launching method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111422370A true CN111422370A (en) | 2020-07-17 |
Family
ID=71549666
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010198538.3A Pending CN111422370A (en) | 2020-03-19 | 2020-03-19 | Unmanned aerial vehicle ejection rack single machine, parallel track ejection rack and launching method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111422370A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111924124A (en) * | 2020-08-11 | 2020-11-13 | 西北工业大学 | Vehicle-mounted small unmanned aerial vehicle multi-frame electromagnetic emission device and method |
-
2020
- 2020-03-19 CN CN202010198538.3A patent/CN111422370A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111924124A (en) * | 2020-08-11 | 2020-11-13 | 西北工业大学 | Vehicle-mounted small unmanned aerial vehicle multi-frame electromagnetic emission device and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3621877B1 (en) | Modular aircraft with vertical takeoff and landing capability | |
| US9815563B2 (en) | Long range electric aircraft and method of operating same | |
| US5289994A (en) | Equipment carrying remote controlled aircraft | |
| US10940932B2 (en) | Modular fuselage for unmanned aerial vehicle | |
| US20160297520A1 (en) | Modular nacelles to provide vertical takeoff and landing (vtol) capabilities to fixed wing aerial vehicles, and associated systems and methods | |
| CN212243873U (en) | Unmanned aerial vehicle ejection rack unit and flexible combined unmanned aerial vehicle row-connected track ejection rack thereof | |
| CN112105555B (en) | Mechanical adapter for a frame and unmanned aerial vehicle having a fragile frame structure | |
| TWI676578B (en) | Take-off device and method for unmanned aircraft without landing gear | |
| CN103738496A (en) | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof | |
| CN102910288A (en) | Multifunctional unmanned aerial vehicle provided with flexible stamping parafoil | |
| CN111422370A (en) | Unmanned aerial vehicle ejection rack single machine, parallel track ejection rack and launching method thereof | |
| CN205293099U (en) | Use coaxial tandem twin engine's fixed wing uavs | |
| US8168929B2 (en) | Non-powered, aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles | |
| CN106915453A (en) | A kind of takeoff and landing mode and system | |
| CN107161329A (en) | A kind of restructural amphibious robot | |
| CN112550682A (en) | Negative surface landing mechanism, rotor unmanned aerial vehicle and landing and takeoff method thereof | |
| CN209382275U (en) | A kind of combined type aircraft | |
| CN206885351U (en) | A kind of takeoff and landing system | |
| CN205615699U (en) | General type fixed wing uavs | |
| CN212243865U (en) | Aircraft take-off and landing platform | |
| CN114013230A (en) | Four-rotor robot with wall surface stopping and crawling capabilities | |
| WO2019080180A1 (en) | Vertical takeoff method for fixed-wing unmanned aerial vehicle | |
| WO2019080179A1 (en) | Takeoff method for fixed-wing unmanned aerial vehicle | |
| CN111284721A (en) | Aircraft take-off and landing platform | |
| CN217374880U (en) | Quick portable fixed wing unmanned aerial vehicle of dismantlement installation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |