A device and method for adjusting the thrust line of a boost rocket of a flying device

Abstract

The application discloses a kind of flight device boost rocket thrust line adjusting device and adjusting method, adjusting device includes support frame, support shaft, thrust cone, arc block, mounting seat, laser emitter, marking plate, two installation side plates and two fasteners;Support frame is set to launch frame slope;Support shaft is fixedly connected to support frame top end and is rotatably connected with thrust cone;Arc block is fixedly connected with thrust cone;Installation side plate is fixedly connected to the side of mounting seat;Laser emitter is detachably connected to the end of thrust cone.The application realizes that unmanned aerial vehicle is placed on launch frame to adjust thrust line, avoids the influence generated by using hanging mode to actual gravity center of unmanned aerial vehicle, in the process of adjusting thrust cone, arc block of the end of thrust cone is always closely matched with arc-shaped sliding groove on mounting seat, so that the connection between thrust cone and belly after mounting and fixing is always kept closely, avoids further larger installation error of thrust cone when connecting, guarantees the accuracy of thrust line adjustment.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of flight device boosting, in particular to a flight device boosting rocket thrust line adjusting device and adjusting method. BACKGROUND

[0002] The rocket launching mode of the unmanned aerial vehicle is the most common take-off mode of the unmanned aerial vehicle, which refers to launching the unmanned aerial vehicle by the launching frame through the rocket boosting, and the boosting rocket automatically separates after the combustion, and the flight task is completed by the main engine. The axis of the launching connection interface of the boosting rocket and the unmanned aerial vehicle is the thrust line, which is the straight line of the thrust that meets a certain angle of launching, and the launching safety can be ensured only when the extension line of the thrust line passes through the actual center of gravity of the unmanned aerial vehicle, so the distance between the actual center of gravity of the unmanned aerial vehicle and the thrust line needs to be measured and adjusted before launching.

[0003] The traditional unmanned aerial vehicle thrust line measurement and adjustment usually adopts the ways of multiple abdominal hanging measurement, gasket adjustment and the like to make the thrust line coincide with the actual center of gravity of the unmanned aerial vehicle as much as possible. However, when the traditional hanging way is used to adjust the unmanned aerial vehicle thrust line, there is a large deviation between the center of gravity of the oil tank when the unmanned aerial vehicle is in the hanging state and the center of gravity of the oil tank when the unmanned aerial vehicle is on the launching frame, which leads to inaccurate actual thrust line adjustment. Moreover, when the thrust cone is connected with the belly, the gasket adjustment way is used for adjustment, which makes the connection between the thrust cone and the belly not tight, further leading to a large installation error of the thrust cone during connection, finally further affecting the accuracy of the thrust line adjustment, and the gasket adjustment way makes the overall operation complicated and the overall work efficiency low. SUMMARY

[0004] The present application provides a flight device boosting rocket thrust line adjusting device and adjusting method, which solves the technical problems that in the prior art, when the unmanned aerial vehicle thrust line is adjusted by the hanging way, there is a large deviation between the center of gravity of the oil tank when the unmanned aerial vehicle is in the hanging state and the center of gravity of the oil tank when the unmanned aerial vehicle is on the launching frame, which leads to inaccurate actual thrust line adjustment, and when the thrust cone is connected with the belly, the gasket adjustment way is used for adjustment, which makes the connection between the thrust cone and the belly not tight, further leading to a large installation error of the thrust cone during connection, finally further affecting the accuracy of the thrust line adjustment, and the gasket adjustment way makes the overall operation complicated and the overall work efficiency low, realizes the adjustment of the thrust line by placing the unmanned aerial vehicle on the launching frame, avoids the influence of the actual center of gravity of the unmanned aerial vehicle caused by the hanging way, the arc-shaped block at the end of the thrust cone is always in close cooperation with the arc-shaped sliding groove on the mounting seat during the adjustment of the thrust cone, which makes the connection between the thrust cone and the belly after installation and fixation always keep tight, avoids a large installation error of the thrust cone during connection, guarantees the accuracy of the thrust line adjustment, and improves the overall work efficiency.

[0005] In a first aspect, this application provides a thrust line adjustment device for a flight booster rocket, comprising a support frame, a support shaft, a thrust cone, an arc-shaped block, a mounting base, a laser emitter, a marking plate, two mounting side plates, and two fasteners; the support frame is disposed on the inclined surface of the launch pad and is slidable along the width direction of the inclined surface of the launch pad; the support shaft is fixedly connected to the top end of the support frame and passes through or at least partially inserts into the thrust cone along the radial direction of the thrust cone, and is rotatably connected to the thrust cone; the mounting base is fixedly connected to the belly of the UAV, and an arc-shaped groove is formed on the side of the mounting base near the thrust cone; the arc-shaped block is fixedly connected to the thrust cone... The cone has a large opening end, and the arc-shaped surface of the arc-shaped block is adapted to the arc-shaped groove, allowing it to rotate around the axis of the support shaft in the arc-shaped groove; the two mounting side plates are respectively fixedly connected to both sides of the mounting base and contact both ends of the arc-shaped block; the fastener is detachably connected between the mounting side plates and the ends of the arc-shaped block, and can be fixed after the arc-shaped block is adjusted into place; the laser emitter is detachably connected to the small opening end of the thrust cone, and can emit laser along the axis of the thrust cone; the marking plate is fixedly connected to the inclined surface of the transmitter, and can receive the laser emitted by the laser emitter, and the marking plate is provided with at least one marking point.

[0006] In conjunction with the first aspect, in one possible implementation, the thrust cone has a through hole in the radial direction, and the support shaft passes through the through hole and is rotatably connected to the through hole.

[0007] In conjunction with the first aspect, in one possible implementation, the mounting side plate has an arc-shaped through groove, the center of which is located on the axis of the support shaft; the end of the arc-shaped block has a mounting hole located in the arc-shaped through groove; and the fastener is detachably connected to the arc-shaped through groove and the mounting hole.

[0008] In conjunction with the first aspect, in one possible implementation, the support frame includes two support columns, and the support shaft includes two short support shafts; a slide rail is fixedly connected to the inclined surface of the launcher along its width direction; the bottom ends of the two support columns are slidably connected to the slide rails; the two short support shafts are respectively fixedly connected to the inner sides of the adjacent top ends of the two support columns, and the adjacent ends of the two short support shafts extend into the interior of the thrust cone and are rotatably connected to the thrust cone.

[0009] With reference to the first aspect, in a possible implementation manner, the flight device boost rocket thrust line adjusting device provided in the application further includes a driving assembly, the driving assembly includes a lead screw and two fixing plates; the two fixing plates are respectively located outside the two support columns and are fixedly connected to the slope of the launching frame; reverse threads are respectively formed in the center of the lead screw to the rod bodies at the two ends of the lead screw; the lead screw penetrates through the two support columns and the two fixing plates, and is threadedly connected between the two support columns and rotationally connected between the two fixing plates.

[0010] With reference to the first aspect, in a possible implementation manner, end portions of the arc-shaped blocks are provided with a plurality of mounting holes, and the center points of the arc surfaces where the plurality of mounting holes are located are located on the axis of the support shaft.

[0011] With reference to the first aspect, in a possible implementation manner, the marker plate is provided with a plurality of marker points, which respectively correspond to different working time periods of the unmanned aerial vehicle engine.

[0012] Secondly, the application provides a flight device boost rocket thrust line adjusting method, which includes the following steps:

[0013] The unmanned aerial vehicle is installed and placed on the launching frame, so that the unmanned aerial vehicle is in a state of waiting for flight;

[0014] The mounting seat and the mounting side plate are fixedly connected to the belly of the unmanned aerial vehicle in advance;

[0015] The thrust cone is rotationally connected to the outside of the support shaft, and the support frame is slid along the width direction of the slope of the launching frame, so that the arc-shaped block connected to the large end of the thrust cone can enter the arc-shaped sliding groove by rotation;

[0016] A horizontal and vertical coordinate system is drawn on the marker plate;

[0017] The center of gravity G point of the unmanned aerial vehicle and the midpoint O point of the axis of the support shaft are obtained, and then the line connecting the G point and the O point is extended to the marker plate, so that a standard point B point can be marked in the horizontal and vertical coordinate system on the marker plate;

[0018] One end of the thrust cone is rotated by being turned, so that the thrust cone rotates around the support shaft, and the arc-shaped block synchronously slides in the arc-shaped sliding groove; the laser emitter mounted at the small end of the thrust cone marks a marker point M point on the marker plate; the M point is moved to coincide with the B point; at this time, the axis of the thrust cone coincides with the actual center of gravity G point of the unmanned aerial vehicle; at this time, the thrust cone is stopped at this position; finally, the arc-shaped block and the mounting seat are fixedly connected together by the fastener, so that the adjustment of the thrust line is completed.

[0019] After the thrust cone and the arc-shaped block are fixedly installed, the support frame is moved along the width direction of the launching frame slope, and finally the support shaft is separated from the thrust cone.

[0020] In combination with the second aspect, in a possible implementation manner, the gravity center G points corresponding to different working periods of the unmanned aerial vehicle engine are acquired, and the lines connecting the gravity center G points and the O point are respectively extended to the marking plate to obtain the standard points B points corresponding to the different working periods.

[0021] Based on the working periods of the unmanned aerial vehicle engine, the corresponding standard points B points are determined for adjustment of the thrust cone.

[0022] The one or more technical solutions provided in the present application have at least the following technical effects or advantages:

[0023] In the present application, the support frame, the support shaft and the thrust cone are adopted, and the support shaft is penetrated through or at least partially inserted into the thrust cone in the radial direction of the thrust cone and is rotationally connected with the thrust cone, so that the thrust cone can rotate around the support shaft, thereby the axis (i.e., the thrust line) of the thrust cone can be adjusted. Further, the actual gravity center of the unmanned aerial vehicle and the center of the axis of the support shaft are acquired, so that the line connecting the actual gravity center of the unmanned aerial vehicle and the center of the axis of the support shaft is extended to the marking plate, thereby the standard points can be made on the marking plate.

[0024] The mounting seat, the mounting side plate and the arc-shaped block are provided, and the arc-shaped sliding groove is formed on the mounting seat, the center point of the arc-shaped sliding groove and the center point of the arc-shaped block coincide and are located on the axis of the support shaft. By turning one end of the thrust cone, the thrust cone and the arc-shaped block can rotate around the support shaft as a whole, and the arc-shaped block can rotate synchronously in the arc-shaped sliding groove. The laser emitter provided at the small opening end of the thrust cone can make the marking point on the marking plate irradiated by the laser emitter gradually move to coincide with the standard point during the rotation and adjustment of the thrust cone, so that the axis of the thrust cone can pass through the gravity center of the unmanned aerial vehicle. At this time, the arc-shaped block and the mounting side plate are fixedly connected together by the fastener, so that the installation of the thrust cone is completed, and the adjustment of the thrust line is completed.

[0025] The effective solution is that the present application places the unmanned aerial vehicle on the launching rack to adjust the thrust line, avoids the influence of the actual center of gravity of the unmanned aerial vehicle caused by the hanging mode, the arc-shaped block of the end of the thrust cone is always in close cooperation with the arc-shaped sliding groove on the mounting seat during the adjustment of the thrust cone, the connection between the thrust cone and the belly after the mounting and fixing is always kept close, the mounting error of the thrust cone during the connection is avoided, the accuracy of the thrust line adjustment is ensured, the operation steps are simplified, and the overall work efficiency is improved. BRIEF DESCRIPTION OF DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the description of the embodiments of the present application or the prior art. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort on the basis of these drawings.

[0027] Figure 1 A shaft drawing of a flight device boost rocket thrust line adjustment device provided by an embodiment of the present application;

[0028] Figure 2 For Figure 1 A local enlarged view of region A in the middle;

[0029] Figure 3 An assembly structure schematic view of a thrust cone, an arc-shaped block, a mounting seat, a mounting side plate and a fastener provided by the present application;

[0030] Figure 4 A shaft drawing when two support short shafts are separated from the thrust cone after the thrust cone is adjusted to the position and fixed on the mounting seat provided by the present application;

[0031] Figure 5 A structure schematic view of the actual center of gravity G point of the unmanned aerial vehicle, the center point O point of the shaft center line of the support shaft, the standard point B point and the mark point M point marked by the laser emitter in the embodiment of the present application.

[0032] Reference: 1 - support frame; 2 - support shaft; 21 - support stub shaft; 3 - thrust cone; 31 - through hole; 4 - arc block; 41 - mounting hole; 5 - mounting seat; 51 - arc-shaped sliding groove; 6 - laser emitter; 7 - marking plate; 8 - mounting side plate; 81 - arc-shaped through slot; 9 - fastener; 10 - launching frame; 101 - slide rail; 11 - unmanned aerial vehicle; 12 - support column; 13 - drive assembly; 131 - lead screw; 132 - fixed plate. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0034] In the description of the embodiments of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application. The terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance. In addition, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication between two elements inside. For those skilled in the art, the specific meaning of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0035] Reference Figures 1-4The application provides a flight device boosting rocket thrust line adjusting device, which comprises a support frame 1, a support shaft 2, a thrust cone 3, an arc block 4, a mounting seat 5, a laser emitter 6, a marking plate 7, two mounting side plates 8 and two fasteners 9. The support frame 1 is arranged on the inclined surface of a launching frame 10 and can slide along the width direction of the inclined surface of the launching frame 10. The support shaft 2 is fixedly connected to the top end of the support frame 1 and penetrates or is at least partially inserted into the thrust cone 3 along the radial direction of the thrust cone 3 and is rotationally connected with the thrust cone 3. The mounting seat 5 is fixedly connected to the belly of a drone 11, and an arc-shaped sliding groove 51 is formed in the side of the mounting seat 5 close to the thrust cone 3. The arc block 4 is fixedly connected to the large end of the thrust cone 3, and the arc surface of the arc block 4 is matched with the arc-shaped sliding groove 51 and can rotate around the axis of the support shaft 2 in the arc-shaped sliding groove 51. The two mounting side plates 8 are respectively fixedly connected to the two sides of the mounting seat 5 and are in contact with the two ends of the arc block 4. The fastener 9 is detachably connected between the end of the arc block 4 and the mounting side plate 8 and can be fixed after the arc block 4 is adjusted in place. The laser emitter 6 is detachably connected to the small end of the thrust cone 3 and can emit laser light along the axis of the thrust cone 3. The marking plate 7 is fixedly connected to the inclined surface of the launching frame 10 and can receive the laser light emitted by the laser emitter 6. At least one marking point is arranged on the marking plate 7. In the application, the launching frame 10 is a conventional launching frame 10 for the drone 11, the weight of the drone 11 is effectively supported by the launching frame 10, the mounting seat 5 needs to be fixedly connected to the belly of the drone 11 in advance and can be integrally formed with the belly of the drone 11 or fixedly connected to the belly of the drone 11 through bolts, the mounting side plate 8 is integrally formed with the mounting seat 5, the arc block 4 is welded to the large end of the thrust cone 3, the center point of the arc-shaped sliding groove 51 and the center point of the arc block 4 coincide and are located on the axis of the support shaft 2, the arc block 4 can rotate in the arc-shaped sliding groove 51 and always tightly matches with the arc-shaped sliding groove 51, the fastener 9 is selected from a fastening bolt, the fastener 9 can pass through the mounting side plate 8 and be threadedly connected with the end of the arc block 4, when the thrust cone 3 is adjusted in place by rotating the arc block 4, the fastener 9 is threadedly connected with the end of the arc block 4, the mounting side plate 8 is fixedly connected with the arc block 4 as a whole through the fastener 9, and the mounting and fixing of the thrust cone 3 are realized.

[0036] Referring to Figures 2-4 The thrust cone 3 is provided with a through hole 31 in the radial direction, and the support shaft 2 penetrates the through hole 31 and is rotationally connected with the through hole 31. In the application, the through hole 31 is specifically formed in the thrust cone 3 in the radial direction, so that the support shaft 2 can penetrate the through hole 31 and be rotationally connected with the through hole 31, so that the thrust cone 3 can rotate around the outside of the support shaft 2, and the rotational adjustment of the axis of the thrust cone 3 is facilitated.

[0037] Referring to Figure 3The arc-shaped through slot 81 is provided on the mounting side plate 8, and the center point of the arc-shaped through slot 81 is on the axis line of the support shaft 2. The mounting hole 41 is provided at the end of the arc-shaped block 4 and is in the arc-shaped through slot 81. The fastener 9 is detachably connected to the arc-shaped through slot 81 and the mounting hole 41. In the embodiment, the center point of the arc-shaped through slot 81, the center point of the arc-shaped sliding slot 51 and the center point of the arc-shaped block 4 all coincide at one point, and are on the axis line of the support shaft 2. In the embodiment, the number of the mounting hole 41 is two, and the two mounting holes 41 are arranged in an annular array in the arc-shaped through slot 81. The fastener 9 is a fastening bolt, which passes through the arc-shaped through slot 81 and is screwed in the mounting hole 41. When the thrust cone 3 is adjusted, the fastening bolt is in a loose state in the mounting hole 41, and the nut of the fastening bolt does not generate extrusion force on the mounting side plate 8. During the rotation of the thrust cone 3, the arc-shaped block 4 rotates in the arc-shaped sliding slot 51 and drives the fastening bolt to move synchronously in the arc-shaped through slot 81. After the thrust cone 3 is adjusted to the position, the fastening bolt is tightened, and the nut of the fastening bolt is tightened on the mounting side plate 8, so as to fixedly connect the arc-shaped block 4 and the mounting side plate 8, and realize the fixing and mounting of the thrust cone 3 after the adjustment.

[0038] With reference to Figure 2 , 4 The support frame 1 includes two support columns 12, and the support shaft 2 includes two support short shafts 21. The slope of the launching frame 10 is fixedly connected with a sliding rail 101 along the width direction of the slope. The bottom ends of the two support columns 12 are slidingly connected with the sliding rail 101. The two support short shafts 21 are fixedly connected to the inner sides of the top ends of the two support columns 12 close to each other, and the end portions close to each other of the two support short shafts 21 extend into the interior of the thrust cone 3 and are rotationally connected with the thrust cone 3. In the embodiment, the support frame 1 includes two support columns 12, and the support shaft 2 includes two support short shafts 21. Before the thrust cone 3 is adjusted, the two support columns 12 move towards each other, and the two support short shafts 21 are inserted into the through hole 31 provided in the radial direction of the thrust cone 3, so as to rotationally support the thrust cone 3, facilitate the subsequent rotation adjustment of the thrust cone 3, and after the thrust cone 3 is adjusted to the position and is fixed on the mounting seat 5 by the fastener 9, the two support columns 12 move away from each other, so that the two support short shafts 21 are gradually separated from the through hole 31 of the thrust cone 3, without affecting the subsequent installation between the rocket barrel and the thrust cone 3.

[0039] With reference to Figure 1The flight device boosting rocket thrust line adjusting device provided by the embodiment of the application further comprises a driving assembly 13, the driving assembly 13 comprises a lead screw 131 and two fixed plates 132; the two fixed plates 132 are respectively located at the outer sides of the two support columns 12 and are fixedly connected to the inclined surface of the launching rack 10; reverse threads are respectively formed on the rod bodies at the two ends of the lead screw 131; the lead screw 131 penetrates through the two support columns 12 and the two fixed plates 132, and is threadedly connected between the two support columns 12 and rotationally connected between the two fixed plates 132. In the embodiment of the application, the driving assembly 13 is specifically arranged, that is, by arranging the reverse threads on the lead screw 131, the two support columns 12 can be driven to move towards each other or away from each other by rotating the lead screw 131, so that the rotating support of the thrust cone 3 before adjustment is conveniently realized, and the support short shaft 21 can be quickly separated from the thrust cone 3 after adjustment.

[0040] With reference to Figure 5 The embodiment of the application provides a flight device boosting rocket thrust line adjusting method, which comprises the following steps:

[0041] The unmanned aerial vehicle 11 is installed and placed on the launching rack 10, so that the unmanned aerial vehicle 11 is in a state of waiting to fly; by directly placing the unmanned aerial vehicle 11 on the launching rack 10, the actual center of gravity of the unmanned aerial vehicle 11 before launching can be accurately simulated, the problem that the center of gravity is inconsistent between the center of gravity when being hung and the center of gravity when actually launching in the prior art is avoided, and the accuracy of thrust line adjustment can be improved.

[0042] The mounting seat 5 and the mounting side plate 8 are fixedly connected to the belly of the unmanned aerial vehicle 11 in advance; the thrust cone 3 is rotationally connected to the outer side of the support shaft 2, and the support frame 1 is slid along the width direction of the inclined surface of the launching rack 10, so that the arc-shaped block 4 connected to the large end of the thrust cone 3 can enter the arc-shaped sliding groove 51 by rotating;

[0043] A horizontal and vertical coordinate system is drawn on the marking plate 7; the center of gravity G point of the unmanned aerial vehicle 11 and the midpoint O point of the axis line of the support shaft 2 are obtained, the center of gravity G point can be obtained by a corresponding detection means, and the intersection of the extension line of the line connecting the center of gravity G point and the midpoint O point of the axis line of the support shaft 2 and the marking plate 7 can be obtained by a prior art method such as computer simulation, so that a standard point B point can be marked in the horizontal and vertical coordinate system on the marking plate 7; the line connecting the G point and the O point can be accurately simulated by computer simulation, the line can be extended to the corresponding horizontal and vertical coordinate system on the simulated marking plate 7, and the actual coordinate value on the simulated marking plate 7 can be obtained, so that the standard point B point can be marked on the actual marking plate 7 by using the actual coordinate value;

[0044] By rotating the end of the thrust cone 3 around the support shaft 2, the arc block 4 is synchronously slid in the arc-shaped sliding groove 51, and the laser emitter 6 installed at the small end of the thrust cone 3 marks a mark point M on the mark plate 7. When the M point is moved to coincide with the B point, the axis of the thrust cone 3 coincides with the actual center of gravity G of the UAV 11. At this time, the thrust cone 3 is kept at this position, and finally the arc block 4 and the mounting seat 5 are fixedly connected together through the fastener 9, so that the adjustment of the thrust line is completed.

[0045] After the thrust cone 3 and the arc block 4 are installed and fixed, the support frame 1 is moved along the width direction of the inclined surface of the launching frame 10, and finally the support shaft 2 is separated from the thrust cone 3, without affecting the subsequent installation work between the rocket barrel and the thrust cone 3.

[0046] The center of gravity G corresponding to different working periods of the engine of the UAV 11 is obtained, and the line connecting the center of gravity G and the O point is extended to the mark plate 7 to obtain the standard point B corresponding to different working periods. Based on the working period of the engine of the UAV 11, the corresponding standard point B is determined for the adjustment of the thrust cone 3. In the embodiment of the application, the engine of the UAV 11 is started before launching, and needs to pass through two working periods of the slow vehicle stage and the large vehicle stage. After the engine is adjusted to the large vehicle stage, the UAV 11 is ignited and launched. However, the fuel tank is always being consumed in the slow vehicle stage and the large vehicle stage, so that before launching in the large vehicle stage, the actual center of gravity of the UAV 11 deviates from the center of gravity in the full fuel state. Therefore, in order to ensure the accuracy of the thrust line adjustment during launching, the actual center of gravity of the UAV 11 is obtained by using existing technical means such as a computer before launching in the large vehicle stage, and the accurate standard point on the mark plate 7 is quickly judged, so that the thrust cone 3 is conveniently and quickly fine-tuned (the thrust cone 3 in the full fuel state is fine-tuned), and the accuracy of the thrust line adjustment is further ensured. In the embodiment of the application, the actual center of gravity of the UAV 11 in the large vehicle stage can also be dynamically simulated by a computer, so that the actual center of gravity of the UAV 11 before launching in the large vehicle stage can be predicted, the predicted standard point on the mark plate 7 can be inferred according to the predicted actual center of gravity, and the thrust cone 3 is conveniently and quickly fine-tuned to improve the coincidence between the thrust line after adjustment and the actual center of gravity of the UAV 11 during launching.

[0047] The various embodiments in the specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referred to each other. Each embodiment mainly describes the difference from other embodiments.

[0048] The above examples are only used to illustrate the technical solutions of the present application, and are not intended to limit the present application; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that the technical solutions recorded in the foregoing examples can still be modified, or some or all of the technical features thereof can be replaced by equivalents; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. A flight device boost rocket thrust line adjusting device, characterized by, Including support frame (1), support shaft (2), thrust cone (3), arc block (4), mounting seat (5), laser emitter (6), marking plate (7), two installation side plates (8) and two fasteners (9); The support frame (1) is arranged on the inclined surface of the launching frame (10) and can slide along the width direction of the inclined surface of the launching frame (10); The support shaft (2) is fixedly connected to the top end of the support frame (1), penetrates or at least partially inserts the thrust cone (3) along the radial direction of the thrust cone (3), and is rotatably connected with the thrust cone (3); The mounting seat (5) is fixedly connected to the belly of the unmanned aerial vehicle (11), and an arc-shaped sliding groove (51) is formed in the side of the mounting seat (5) close to the thrust cone (3); The arc block (4) is fixedly connected to the large end of the thrust cone (3), and the arc surface of the arc block (4) is matched with the arc-shaped sliding groove (51) and can rotate around the axis of the support shaft (2) in the arc-shaped sliding groove (51); Two installation side plates (8) are respectively fixedly connected to the two sides of the mounting seat (5) and are in contact with the two ends of the arc block (4); The fastener (9) is detachably connected between the installation side plate (8) and the end of the arc block (4), and can be fixed after the arc block (4) is adjusted in place; The laser emitter (6) is detachably connected to the small end of the thrust cone (3) and can emit laser light along the axis of the thrust cone (3); The marking plate (7) is fixedly connected to the inclined surface of the launching frame (10) and can receive the laser light emitted by the laser emitter (6), and at least one marking point is arranged on the marking plate (7).

2. The flight apparatus boost rocket thrust line adjustment apparatus according to claim 1, characterized by, The thrust cone (3) is provided with a through hole (31) in the radial direction, and the support shaft (2) penetrates the through hole (31) and is rotatably connected with the through hole (31).

3. The flight device boost rocket thrust line adjusting apparatus according to claim 1, characterized by, An arc-shaped through groove (81) is formed in the installation side plate (8), and the center point of the arc-shaped through groove (81) is on the axis of the support shaft (2); An installation hole (41) is formed in the end of the arc block (4), and the installation hole (41) is in the arc-shaped through groove (81); The fastener (9) is detachably connected in the arc-shaped through groove (81) and the installation hole (41).

4. The flight device boost rocket thrust line adjusting apparatus according to claim 1, wherein The support frame (1) includes two support columns (12), and the support shaft (2) includes two support short shafts (21); The inclined surface of the launching frame (10) is fixedly connected with a sliding rail (101) along the width direction of the inclined surface; The bottom ends of the two support columns (12) are slidably connected with the sliding rail (101); The two support short shafts (21) are respectively fixedly connected to the inner sides of the top ends of the two support columns (12) close to each other, and the end portions of the two support short shafts (21) close to each other extend into the interior of the thrust cone (3) and are rotatably connected with the thrust cone (3).

5. The flight device boost rocket thrust line adjustment apparatus according to claim 4, characterized by, Further comprising a driving assembly (13), the driving assembly (13) comprising a lead screw (131) and two fixed plates (132); Two fixing plates (132) are respectively arranged outside the two support columns (12) and are fixedly connected to the inclined surface of the launching rack (10); The center of the lead screw (131) is provided with reverse threads on the rod bodies at the two ends of the lead screw (131); The lead screw (131) penetrates through the two support columns (12) and the two fixing plates (132), and is threadedly connected between the lead screw (131) and the two support columns (12) and is rotationally connected between the lead screw (131) and the two fixing plates (132).

6. The flight device boost rocket thrust line adjusting apparatus according to claim 2, wherein The end of the arc-shaped block (4) is provided with a plurality of mounting holes (41), and the centers of the arcs where the plurality of mounting holes (41) are located are on the axis of the support shaft (2).

7. The flight device boost rocket thrust line adjustment apparatus according to claim 1, characterized by, The marker plate (7) is provided with a plurality of marker points, which correspond to different working periods of the engine of the unmanned aerial vehicle (11).

8. A method of adjusting the thrust line of a boost rocket of a flying device, based on the flying device boost rocket thrust line adjustment device according to any one of claims 1 to 7, characterized in that, The method comprises the steps of: Placing the unmanned aerial vehicle (11) on the launching rack (10) so that the unmanned aerial vehicle (11) is in a state of waiting for flight; Fixing the mounting seat (5) and the mounting side plate (8) to the belly of the unmanned aerial vehicle (11) in advance; Rotating the thrust cone (3) to the outside of the support shaft (2), sliding the support frame (1) along the width direction of the inclined surface of the launching rack (10), so that the arc-shaped block (4) connected to the large end of the thrust cone (3) can enter the arc-shaped sliding groove (51) by rotating; Drawing a horizontal and vertical coordinate system on the marker plate (7); Obtaining the center of gravity G point of the unmanned aerial vehicle (11) and the midpoint O point of the axis of the support shaft (2), and then extending the line connecting the G point and the O point to the marker plate (7), so that a standard point B point can be marked on the horizontal and vertical coordinate system on the marker plate (7); Rotating the thrust cone (3) around the support shaft (2) by turning one end of the thrust cone (3), and synchronously sliding the arc-shaped block (4) in the arc-shaped sliding groove (51), the laser emitter (6) mounted at the small end of the thrust cone (3) will mark a marker point M point on the marker plate (7), and the M point is moved to coincide with the B point, at this time the axis of the thrust cone (3) coincides with the actual center of gravity G point of the unmanned aerial vehicle (11), at this time the thrust cone (3) is stopped, and finally the arc-shaped block (4) and the mounting seat (5) are fixedly connected together by the fastener (9), so that the adjustment of the thrust line is completed; After the thrust cone (3) and the arc-shaped block (4) are installed and fixed, the support frame (1) is moved along the width direction of the inclined surface of the launching rack (10), and finally the support shaft (2) is separated from the thrust cone (3).

9. The method of adjusting the thrust line of a boost rocket of a flight device according to claim 8, characterized in that, Obtaining the center of gravity G point corresponding to different working periods of the engine of the unmanned aerial vehicle (11), and extending the line connecting the center of gravity G point and the O point to the marker plate (7) to obtain the standard point B point corresponding to different working periods; Based on the working period of the engine of the unmanned aerial vehicle (11), the corresponding standard point B point is determined for the adjustment of the thrust cone (3).

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