Adjustable launcher for rocket boosting type unmanned aerial vehicle

Abstract

The invention provides an adjustable launcher for a rocket-boosted unmanned aerial vehicle. The adjustable launcher is mainly used for solving the technical problems that the pitching angle of an existing launcher for the rocket-boosted unmanned aerial vehicle cannot be adjusted, the launching direction cannot be changed by 360 degrees according to the wind direction, the requirement for ground flatness is high, and flexibility is poor. The platform comprises a pitching platform, an azimuth platform and a fixed platform. The fixed platform is arranged on the ground through ground nails, and the gradient of the ground can be horizontally adjusted; a slewing bearing is arranged between the azimuth platform and the fixed platform, the azimuth platform is driven by the slewing bearing to rotate, rotation adjustment of the azimuth platform is facilitated, and the unmanned aerial vehicle takes off along the wind; a second screw elevator is arranged between the pitching platform and the azimuth platform and used for adjusting the pitching angle when the unmanned aerial vehicle is launched, and the take-off effect of the unmanned aerial vehicle is guaranteed. The take-off device is only composed of a mechanical structure, the structure is simple, and a guarantee is provided for take-off of the rocket-assisted unmanned aerial vehicle.

Description

Technical Field

[0001] The invention relates to an adjustable launching frame for an unmanned aerial vehicle, and in particular to an adjustable launching frame for a rocket-propelled unmanned aerial vehicle. Background Art

[0003] In the prior art, drone launch is generally achieved through different forms such as rocket-assisted launch, rubber rope elastic launch, gas-hydraulic ejection, gas launch, and electromagnetic launch. The launch weight covers micro to large drones, and the launch type covers a wide range. In rocket-assisted launch, the kinetic energy of the drone takeoff comes from the energy generated by the combustion of fuel in the rocket booster. It has low cost, mature technology, is less affected by the outside world, and can be deployed at a faster speed. Therefore, it is widely used in countries around the world. Therefore, the research on rocket-assisted drone launch equipment is of great significance.

[0004] However, its disadvantage is that the launch pitch angle of the launch pad for rocket-propelled UAVs cannot be adjusted, and the launch direction cannot be changed 360° according to the wind direction. Therefore, it has high requirements on the flatness of the ground and poor flexibility. It cannot be adjusted in time according to the situation on the battlefield, thus affecting the take-off of the UAV and even missing the opportunity to fight. Summary of the invention

[0005] The purpose of the present invention is to solve the technical problems that the pitch angle of the existing launch rack for rocket-boosted UAVs cannot be adjusted, the launch direction cannot be changed 360° according to the wind direction, the ground flatness requirement is high, and the flexibility is poor, and an adjustable launch rack for rocket-boosted UAVs is proposed.

[0006] To solve the above technical problems, the technical solutions provided by the present invention are as follows:

[0007] An adjustable launcher for a rocket-propelled UAV, which is special in that it comprises a pitch platform, an azimuth platform, and a fixed platform; the fixed platform is fixedly connected to the ground, the azimuth platform is rotatably connected to the fixed platform, and the rear end of the pitch platform is hinged to the rear end of the azimuth platform;

[0008] The pitching platform includes an upper frame, a front lodging component, a first wing supporting component, a second wing supporting component, a fuselage supporting component, and a launching tube supporting component;

[0009] The bottom of the front lodging component is hinged to the front end of the upper frame, and a groove is provided on the top of the front lodging component for supporting the head of the UAV; the first wing supporting component and the second wing supporting component are respectively arranged on both sides of the upper frame for supporting the two wings of the UAV; the fuselage supporting component is foldably arranged on the upper frame for supporting the fuselage of the UAV; the launching tube supporting component is foldably arranged at the rear end of the upper frame for supporting the launching tube of the UAV;

[0010] The azimuth platform includes a second screw lift, a push rod shaft, a guide ring and a lower frame; the rear end of the lower frame is hinged with the rear end of the upper frame, a turntable is arranged in the middle, and a guide rail is arranged between the turntable and the front end of the lower frame;

[0011] The second screw lift is mounted on the lower frame, and its input end is connected to an external power source; the guide ring is sleeved on the driving end of the second screw lift and placed on the guide rail; one end of the push rod shaft is hinged to the guide ring, and the other end is hinged to the upper frame, so as to adjust the pitch angle of the upper frame compared to the lower frame;

[0012] The fixed platform comprises a fixed frame and a slewing bearing; the slewing bearing is arranged in the middle of the fixed frame, the inner ring of the slewing bearing is fixedly connected to the fixed frame, and the outer ring is fixedly connected to the slewing table on the lower frame.

[0013] Furthermore, two inverted mounting seats are vertically arranged at the front end of the upper frame;

[0014] The front lodging component includes a front lodging frame, and two frame mounting seats symmetrically mounted on both sides of the front lodging frame, a shear pin, a front quick release pin, a torsion spring mounting seat, and a first pin shaft front lodging torsion spring;

[0015] The frame mounting seat comprises a first bottom plate and a connecting plate which are perpendicular to each other, the first bottom plate is fixedly connected to the upper part of the lodging mounting seat, the shear pin and the front quick release pin pass through the connecting plate and are connected to the front lodging frame, and the front quick release pin is used to remove and release the front lodging frame before launching;

[0016] The torsion spring mounting base includes a second bottom plate and three side plates perpendicular to the second bottom plate; the second bottom plate is fixedly connected to the upper frame, the first pin shaft passes through a side plate, a side frame of the front inverted frame and the remaining two side plates in sequence, the front inverted torsion spring is sleeved on the first pin shaft and is located between the remaining two side plates; one end of the front inverted torsion spring is connected to the second bottom plate, and the other end is connected to the front inverted frame, which is used to drive the front inverted frame to rotate and tilt forward around the first pin shaft after the front inverted frame is released, and separate from the head of the drone.

[0017] Further, the first wing support component includes a first lower support arm, a first upper support arm, a first top screw, a first quick release pin, a screw pair and a transverse and longitudinal adjustment structure;

[0018] The first lower arm is connected to one side of the upper frame, the lower end of the first upper arm is inserted into the first lower arm, the first top screw and the first quick-release pin are installed at the upper end of the first lower arm, and are used to fix and disassemble the first upper arm; the screw pair is installed at the upper end of the first upper arm, and is used to vertically adjust the position of the abutment against the wing of the drone; the transverse and longitudinal adjustment structure is installed at the top end of the screw pair, and is used to horizontally and longitudinally adjust the position of the abutment against the wing of the drone;

[0019] The second wing support component includes a second lower support arm, a second upper support arm, a second top screw, a second quick release pin and a transverse and longitudinal adjustment structure;

[0020] The second lower support arm is connected to the other side of the upper frame, and the lower ends of the second upper support arms are respectively inserted into the second lower support arms. The second top screw and the second quick-release pin are installed at the upper end of the second lower support arm for fixing and disassembling the second upper support arm; the transverse and longitudinal adjustment structure is installed at the upper end of the second upper support arm for transversely and longitudinally adjusting the position of the abutment against the drone wing.

[0021] Further, the fuselage support component includes a fixing plate, a rotation pin plate, a second pin shaft, a first screw lifter, a hand wheel, a support block, and a support column;

[0022] The fixed plate is fixedly connected to the upper frame, and the rotation pin plate and the fixed plate are hinged via a second pin shaft;

[0023] One end of the support column is connected to the turn pin plate, and the other end is connected to the first screw lift;

[0024] The hand wheel is connected to the input end of the first screw elevator, the driving end of the first screw elevator is connected to one side of the support block, and the other side of the support block is used to support the fuselage of the drone when the swing pin plate and the fixing plate are folded.

[0025] Furthermore, the launch tube support component includes a launch tube support frame, a mounting plate, a rotating shaft, a launch tube torsion spring, a launch tube support ring, a horizontal lead screw nut pair, and a vertical lead screw nut pair;

[0026] The mounting plate is fixedly mounted on the upper frame, and the bottom of the launch tube support frame is connected to the mounting plate through a rotating shaft; the launch tube torsion spring is sleeved on the rotating shaft to realize the folding of the launch tube support frame after the UAV is launched;

[0027] The horizontal lead screw nut pair is arranged inside the launch tube support frame and is parallel to the rotating shaft; a connecting block is provided on the nut of the horizontal lead screw nut pair, and the nut of the vertical lead screw nut pair is connected to the connecting block and is perpendicular to the horizontal lead screw nut pair;

[0028] The launch tube support ring is installed at the upper end of the vertical screw nut pair and is used to contact the UAV booster rocket.

[0029] Further, the pitch platform also includes an upper bearing mounting seat and two latch clamps;

[0030] The azimuth platform also includes a lower rotating shaft seat;

[0031] The upper bearing mounting seat is arranged on both sides of the rear end of the upper frame, and the lower shaft seat is arranged at the end of the lower frame and is connected to the upper bearing mounting seat through the pitch shaft;

[0032] The two latch clamps are respectively arranged at the front end of the upper frame and are detachably connected to the lower frame, and are used to lock and connect the upper frame with the front end of the lower frame when the drone is not installed.

[0033] Furthermore, the pitch platform also includes two triangular positioning seats, which are arranged on the upper frame and are respectively located on both sides of the supporting column, and are connected to the supporting column when the drone is not installed.

[0034] Furthermore, the azimuth platform also includes two transmission shafts and bearing seats; the two bearing seats are respectively installed on the two side edges of the lower frame, and the two transmission shafts are respectively installed in the two bearing seats; one end of the transmission shaft is connected to the external power source, and the other end is connected to the input end of the second screw elevator through a coupling for transmitting power.

[0035] Furthermore, the orientation platform also includes four adjustment feet, which are respectively arranged at both ends of the two sides of the lower frame, and are used to adjust the lower frame horizontally;

[0036] The fixed platform also includes a ground nail and a third quick-release pin;

[0037] The number of the ground nails is four, which are respectively arranged at the four top corners of the fixed frame and are used to fix the fixed frame on the ground; the third quick-release pin passes through the turntable on the lower frame and the slewing support installation and is used to position the turntable.

[0038] Compared with the prior art, the present invention has the following beneficial effects:

[0039] 1. The present invention provides an adjustable launcher for rocket-assisted UAVs, which includes a pitch platform, an azimuth platform and a fixed platform. The fixed platform is set on the ground through ground nails, and the ground slope can be adjusted horizontally by adjusting the feet on the azimuth platform; a slewing bearing is set between the azimuth platform and the fixed platform, and the slewing bearing is used to drive the azimuth platform to rotate, which is convenient for rotating the azimuth platform and allowing the UAV to take off with the wind; a second screw elevator is set between the pitch platform and the azimuth platform, which is used to adjust the pitch angle of the UAV when launching, so as to ensure the take-off effect of the UAV. The present invention is only composed of mechanical structures, with simple structure, low cost, and high degree of mechanization, which provides guarantee for the take-off of rocket-assisted UAVs.

[0040] 2. The front lodging component in the present invention is hinged to the front end of the frame on the pitching platform. After the drone is installed, the front lodging frame is perpendicular to the upper frame through the shear pin and the front quick-release pin to support the head of the drone; the front quick-release pin is removed before the drone is launched, and after the launch, the shear pin is disconnected by the shear force, and the front lodging frame is driven by the front lodging torsion spring to rotate and tilt forward around the first pin shaft, and separate from the head of the drone to avoid obstruction to the launch of the drone.

[0041] 3. In the present invention, the first wing support component and the second wing support component are plug-in structures. After the UAV is installed on the launcher, the first upper arm and the second upper arm are respectively plugged into the first lower arm and the second lower arm to provide support for the two wings respectively. The plug-in structure does not require electronic control equipment, is simple to operate, low cost, and easy to assemble and maintain. The screw pair is installed at the upper end of the first upper arm, and the position of the UAV wing can be adjusted vertically; the transverse and longitudinal adjustment structure is installed at the upper end of the second upper arm, and the position of the UAV wing can be adjusted laterally and longitudinally. When the UAV takes off, the wing can slide along the transverse and longitudinal adjustment structure, which has the function of assisting takeoff.

[0042] 4. The fuselage support component of the present invention can be foldably arranged on the upper frame. When the launcher is not equipped with a UAV, the turn pin plate is perpendicular to the fixing plate and the support column is parallel to the upper frame. After the UAV is installed, the turn pin plate is folded and the support column is perpendicular to the upper frame, so that the support block supports the fuselage of the UAV. The height of the support block can be adjusted by the first screw lift.

[0043] 5. The launch tube support component of the present invention can be foldably installed on the upper frame. When the launcher is not equipped with a UAV, the launch tube support frame is folded on the upper frame through the launch tube torsion spring. After the UAV is installed, the launch tube support frame is perpendicular to the upper frame. The launch tube support ring supports the UAV booster rocket. The horizontal screw nut pair and the vertical screw nut pair can adjust the support position of the launch tube support ring in the horizontal and vertical directions respectively.

[0044] 6. The present invention is provided with a plurality of adjustable structures, which helps to eliminate processing errors and assembly errors, ensures that the UAV is in firm contact with the supporting surfaces of the launch frame when taking off, and takes off stably, further improving the take-off effect of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a structural schematic diagram of an embodiment of an adjustable launcher for a rocket-propelled UAV of the present invention;

[0046] Figure 2 It is a structural schematic diagram of a pitch platform in an embodiment of an adjustable launcher for a rocket-propelled UAV of the present invention;

[0047] Figure 3 It is a structural schematic diagram of a front lodging support component in an embodiment of an adjustable launcher for a rocket-propelled UAV of the present invention;

[0048] Figure 4 It is a structural schematic diagram of a wing support component in an embodiment of an adjustable launcher for a rocket-boosted UAV of the present invention;

[0049] Figure 5 It is a structural schematic diagram of a fuselage support component in an embodiment of an adjustable launcher for a rocket-boosted UAV of the present invention;

[0050] Figure 6 It is a structural schematic diagram of a launch tube support component in an embodiment of an adjustable launch rack for rocket-propelled UAV of the present invention;

[0051] Figure 7 It is a structural schematic diagram of an azimuth platform in an embodiment of an adjustable launcher for a rocket-boosted UAV of the present invention;

[0052] Figure 8 It is a structural schematic diagram of a fixed platform in an embodiment of an adjustable launcher for a rocket-propelled UAV of the present invention;

[0053] Fig. 9 This is a structural schematic diagram of an adjustable launcher for a rocket-propelled UAV in an embodiment of the present invention when no UAV is installed;

[0054] Fig.10 This is a schematic structural diagram of an adjustable launch rack for a rocket-propelled UAV according to an embodiment of the present invention, in a state where the UAV is installed.

[0055] Description of reference numerals:

[0056] 1-pitch platform, 11-front lodging component, 111-front lodging frame, 112-frame mounting seat, 113-shear pin, 114-torsion spring mounting seat, 115-first pin shaft, 116-front quick release pin, 117-front lodging torsion spring;

[0057] 12-first wing supporting member, 121-first lower arm, 122-first upper arm, 123-second upper arm, 124-first top screw, 125-first quick release pin, 126-screw pair, 127-lateral and longitudinal adjustment structure;

[0058] 13-fuselage support component, 131-fixed plate, 132-turn pin plate, 133-second pin shaft, 134-first screw lifter, 135-hand wheel, 136-support block, 137-support column;

[0059] 14-launch tube support component, 141-launch tube support frame, 142-mounting plate, 143-rotating shaft, 144-launch tube torsion spring, 145-launch tube support ring, 146-horizontal lead screw nut pair, 147-vertical lead screw nut pair;

[0060] 15-upper frame; 16-latch clamp; 17-triangular positioning seat; 18-upper shaft mounting seat;

[0061] 2-azimuth platform, 21-second screw lift, 22-coupling, 23-transmission shaft, 24-push rod shaft, 25-guide ring, 26-lower shaft seat, 27-adjusting foot, 28-bearing seat, 29-lower frame;

[0062] 3-fixed platform, 31-fixed frame, 32-slewing bearing, 33-ground nail, 34-third quick release pin. DETAILED DESCRIPTION

[0063] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0064] The present invention provides an adjustable launcher for a rocket-propelled UAV, such as Figure 1 As shown, it is composed only of a mechanical structure, including a pitch platform 1, an azimuth platform 2 and a fixed platform 3.

[0065] The pitching platform 1 can achieve pitching on the azimuth platform 2 to provide a pitch angle for the UAV launch. Figure 2 As shown, the pitching platform 1 includes a front falling component 11, a first wing support component 12 and a second wing support component, a fuselage support component 13, a launch tube support component 14, an upper frame 15, a latch clamp 16, a triangular positioning seat 17 and an upper shaft mounting seat 18. Two falling mounting seats are also vertically arranged at the front end of the upper frame 15, and the front falling component 11 is installed in the falling mounting seats. There are two latch clamps 16, which are respectively arranged at the front end of the upper frame 15, and the pitching platform 1 is locked and connected with the azimuth platform 2 in the transportation and storage state. The fuselage support component 13 is arranged at the rear half of the upper frame 15, and the first wing support component 12 and the second wing support component are respectively arranged on both sides of the upper frame 15 and close to the fuselage support component 13. The launch tube support component 14 is connected to the end of the upper frame 15. There are two upper shaft mounting seats 18, which are respectively arranged on both sides of the end of the upper frame 15.

[0066] like Figure 3As shown, the main body of the front lodging component 11 includes a front lodging frame 111, and frame mounting seats 112, shear pins 113, torsion spring mounting seats 114, first pin shafts 115, front quick-release pins 116 and front lodging torsion springs 117 symmetrically arranged on both sides of the front lodging frame 111. A groove is formed at the top of the front lodging frame 111 for supporting the head of the drone. The two frame mounting seats 112 include a first bottom plate and a connecting plate perpendicular to each other. The first bottom plate is fixedly connected to the upper part of the lodging mounting seat. The shear pin 113 and the front quick-release pin 116 are connected to the front lodging frame 111 through the connecting plate. The front quick-release pin 116 is used to remove and release the front lodging frame 111 before launching.

[0067] The two torsion spring mounting seats 114 include a second bottom plate and three side plates perpendicular to the second bottom plate; the second bottom plate is fixedly connected to the front end of the upper frame 15, and the first pin shaft 115 passes through a side plate, the side frame of the front fall frame 111 and the remaining two side plates in sequence. The front fall torsion spring 117 is sleeved on the first pin shaft 115 and is located between the remaining two side plates; one end of the front fall torsion spring 117 is also connected to the second bottom plate, and the other end is connected to the waist-shaped hole at the bottom end of the front fall frame 111. After the drone is launched, the shear pin 113 is disconnected by shear force, releasing the front fall frame 111; the front fall torsion spring 117 drives the front fall frame 111 to rotate around the first pin shaft 115 to achieve forward tilting, thereby achieving the safe release of the drone.

[0068] like Figure 4 As shown, the first wing support component 12 and the second wing support component are plug-in structures, and the first wing support component 12 includes a first lower arm 121, a first upper arm 122, a first top screw 124, a first quick release pin 125, a screw pair 126 and a transverse and longitudinal adjustment structure 127. The second wing support component includes a second lower arm, a second upper arm 123, a second top screw, a second quick release pin and a transverse and longitudinal adjustment structure 127. The first lower arm 121 and the second lower arm are connected to both sides of the upper frame 15 respectively. After the UAV is installed on the launcher, the lower ends of the first upper arm 122 and the second upper arm 123 are respectively plugged into the square steel of the two first lower arms 121 and the second lower arm, and the first top screw 124 and the first quick release pin 125 are installed at the upper end of the first lower arm 121 to fix the first upper arm 122; the second top screw and the second quick release pin are installed at the upper end of the second lower arm to fix the second upper arm 123. The upper end of the first upper arm 122 is connected to a small screw pair 126, which can adjust the position of the abutment against the wing vertically. The transverse and longitudinal adjustment structure 127 is installed at the top of the screw pair 126. The upper end of the second upper arm 123 is connected to the transverse and longitudinal adjustment structure 127, which can adjust the position of the abutment against the wing in the transverse and longitudinal directions. A slideway is provided at the top end of the transverse and longitudinal adjustment structure 127. When the UAV takes off, the wing can slide along the slideway on the transverse and longitudinal adjustment structure 127 to assist in taking off.

[0069] like Figure 5 As shown, the fuselage support component 13 includes a fixed plate 131, a rotating pin plate 132, a second pin shaft 133, a first screw elevator 134, a hand wheel 135, a support block 136 and a support column 137. The fixed plate 131 is fixedly connected to the upper frame 15, and the rotating pin plate 132 and the fixed plate 131 are hinged by the second pin shaft 133. When the launcher is not equipped with a UAV, the rotating pin plate 132 and the fixed plate 131 remain in a vertical state. One end of the support column 137 is connected to the rotating pin plate 132, and the other end is connected to the first screw elevator 134. The hand wheel 135 is arranged on one side of the first screw elevator 134 and connected to the input end of the first screw elevator 134. The driving end of the first screw elevator 134 is connected to one side of the support block 136. There are two triangular positioning seats 17, which are arranged on the upper frame 15 and are respectively located on both sides of the support column 137. When the UAV is not installed, they are connected to the support column 137 by screws. After the drone is installed on the launcher, the rotating pin plate 132 rotates 90 degrees and folds with the fixing plate 131, parallel to the upper frame 15. The supporting column 137 is separated from the triangular positioning seat 17, and the rotating pin plate 132 drives the supporting column 137, the first screw elevator 134 and the supporting block 136 to be perpendicular to the upper frame 15. The first screw elevator 134 is rotated by the hand wheel 135, and the first screw elevator 134 pushes the supporting block 136 to rise, and the other side of the supporting block 136 supports the fuselage.

[0070] like Figure 6 As shown, the launch tube support component 14 includes a launch tube support frame 141, a mounting plate 142, a rotating shaft 143, a launch tube torsion spring 144, a launch tube support ring 145, a horizontal lead screw nut pair 146, and a vertical lead screw nut pair 147. The mounting plate 142 is fixedly mounted on the upper frame 15, the bottom of the launch tube support frame 141 is connected to the mounting plate 142 through the rotating shaft 143, and the launch tube torsion spring 144 is sleeved on the rotating shaft 143, which is used to realize the forward tilt of the launch tube support frame 141 after the UAV is launched, and at the same time, it can provide preload support for the booster rocket. The horizontal lead screw nut pair 146 is arranged inside the launch tube support frame 141 and is parallel to the rotating shaft 143. A connecting block is arranged on the nut of the horizontal lead screw nut pair 146, and the nut of the vertical lead screw nut pair 147 is connected to the connecting block and is perpendicular to the horizontal lead screw nut pair 146. The launch tube support ring 145 is installed at the upper end of the vertical lead screw nut pair 147 and contacts the UAV booster rocket. The horizontal lead screw nut pair 146 and the vertical lead screw nut pair 147 are used to achieve all-round adjustment of the contact position of the booster rocket.

[0071] like Figure 7As shown, the azimuth platform 2 includes a second screw lift 21, a transmission shaft 23, a push rod shaft 24, a guide ring 25, a lower rotating shaft seat 26, an adjustment foot 27, a bearing seat 28 and a lower frame 29. The lower frame 29 is a rectangular frame, and its width is greater than the width of the upper frame 15. A turntable is provided in the middle of the lower frame 29. A guide rail is provided between the turntable and the front end of the lower frame 29. The second screw lift 21 is mounted on the lower frame 29 and is located above the guide rail. There are two bearing seats 28, which are respectively mounted on both sides of the lower frame 29. There are two transmission shafts 23, which are respectively mounted in two bearing seats 28. One end of the transmission shaft 23 is connected to an external power source, and the other end is connected to the input end of the second screw lift 21 through a coupling 22 for transmitting power. The guide ring 25 is connected to the driving end of the second screw lift 21 and is driven by an external power source. The power is transmitted to the driving end of the second screw lift 21 through the transmission shaft 23 and the coupling 22, thereby pushing the guide ring 25 to move along the guide rail. One end of the push rod shaft 24 is hinged to the guide ring 25, and the other end is hinged to the upper frame 15. The lower shaft seat 26 is arranged at the end of the lower frame 29 and is connected to the upper shaft mounting seat 18 through the pitch shaft. Driven by the guide ring 25, the push rod shaft 24 can make the upper frame 15 rotate around the pitch shaft in the lower shaft seat 26, thereby adjusting the pitch angle. There are four adjusting feet 27, which are respectively arranged at the two ends of the two sides of the lower frame 29, and are used to adjust the lower frame 29 horizontally.

[0072] like Figure 8 As shown, the fixed platform 3 includes a fixed frame 31, a slewing bearing 32, a ground nail 33, and a third quick-release pin 34. The slewing bearing 32 is arranged in the middle of the fixed frame 31, the inner ring of the slewing bearing 32 is fixedly connected to the fixed frame 31, and the outer ring is fixedly connected to the turntable on the lower frame 29. The horizontal angle of the azimuth platform 2 can be adjusted by the slewing bearing 32 to provide a 360° launch direction for the UAV. There are four ground nails 33, which are respectively arranged at the four top corners of the fixed frame 31 to fix the fixed frame 31 on the ground. The third quick-release pin 34 is connected to the turntable on the lower frame 29 and the slewing bearing 32, and is used to position the slewing bearing 32.

[0073] like Fig. 9 As shown, when no UAV is placed on the launcher, the second screw lift 21 does not push the push rod shaft 24, and the upper frame 15 is parallel to the lower frame 29; the latch clamp 16 connects the upper frame 15 with the front end of the lower frame 29; the front fall frame 111 is in a forward tilted state under the action of the front fall torsion spring 117; the first upper support arm 122 and the second upper support arm 123 are not inserted in the first lower support arm 121 and the second lower support arm; the turn pin plate 132 is perpendicular to the upper frame 15, and the support column 137 is connected to the triangular positioning seat 17 by screws; the launch tube support frame 141 is in a forward tilted state under the action of the launch tube torsion spring 144.

[0074] like Fig.10 As shown, when the launcher is to install the UAV, first unlock the latch clamp 16, add the shear pin 113 and the front quick release pin 116 to the frame mounting seat 112, so that the front falling frame 111 is perpendicular to the upper frame 15 and remains fixed; the first upper arm 122 and the second upper arm 123 are inserted into the first lower arm 121 and the second lower arm. The UAV fuselage is hoisted on the launcher, and then the turn pin plate 132 is folded, and the support column 137 is separated from the triangular positioning seat 17. The turn pin plate 132 drives the support column 137, the first screw elevator 134 and the support block 136 to be perpendicular to the upper frame 15. The first screw elevator 134 is rotated by the hand wheel 135, and the first screw elevator 134 pushes the support block 136 to rise, and the support block 136 supports the fuselage. After ensuring reliable support, install the wings of the rear UAV, adjust the screw pair 126 and the transverse and longitudinal adjustment structure 127, so that the wings of the UAV are in stable contact with the first wing support component 12 and the second wing support component respectively, and then open the pin plate 132 to flip the support column 137 back to a state parallel to the upper frame 15.

[0075] The UAV is equipped with a rocket booster launch tube, the launch tube support frame 141 is turned over to keep it in a vertical posture with the upper frame 15, and the horizontal screw nut pair 146 and the vertical screw nut pair 147 are adjusted to make the launch tube support ring 145 contact with the UAV booster launch tube and have a certain pre-tightening force;

[0076] Finally, the second screw lifter 21 is driven by an external power source to make the upper frame 15 meet the pitch angle required for launching, and then the azimuth platform 2 is rotated to the launch direction with the wind according to the wind direction, and the UAV is ready to launch after the front quick release pin 116 is removed. After the UAV is launched, the UAV flies out at a certain angle on the launch rack, and the shear pin 113 in the front fall component 11 of the launch rack is disconnected by the shear force, and the front fall torsion spring 117 is used to tilt forward, effectively avoiding the collision between the UAV fuselage and the front fall component 11 during launch. After the launch is completed, the launch tube support frame 141 tilts forward under the action of the launch tube torsion spring 144.

Claims

1. An adjustable launcher for a rocket-propelled UAV, characterized in that: It comprises a pitching platform (1), an azimuth platform (2), and a fixed platform (3); the fixed platform (3) is fixedly connected to the ground, the azimuth platform (2) is rotatably connected to the fixed platform (3), and the rear end of the pitching platform (1) is hinged to the rear end of the azimuth platform (2); The pitching platform (1) comprises an upper frame (15), a front lodging component (11), a first wing supporting component (12), a second wing supporting component, a fuselage supporting component (13), and a launching tube supporting component (14); The bottom of the front lodging component (11) is hinged to the front end of the upper frame (15); the top of the front lodging component (11) is provided with a groove for supporting the head of the UAV; the first wing supporting component (12) and the second wing supporting component are respectively arranged on both sides of the upper frame (15) for supporting the two wings of the UAV; the fuselage supporting component (13) is foldably arranged on the upper frame (15) for supporting the fuselage of the UAV; The launch tube support component (14) is foldably arranged at the rear end of the upper frame (15) and is used to support the launch tube of the drone; The azimuth platform (2) comprises a second screw lift (21), a push rod shaft (24), a guide ring (25) and a lower frame (29); the rear end of the lower frame (29) is hinged to the rear end of the upper frame (15), a turntable is arranged in the middle thereof, and a guide rail is arranged between the turntable and the front end of the lower frame (29); The second screw lift (21) is mounted on the lower frame (29), and its input end is connected to an external power source; the guide ring (25) is sleeved on the driving end of the second screw lift (21) and placed on the guide rail; one end of the push rod shaft (24) is hinged to the guide ring (25), and the other end is hinged to the upper frame (15), so as to adjust the pitch angle of the upper frame (15) relative to the lower frame (29); The fixed platform (3) comprises a fixed frame (31) and a slewing bearing (32); the slewing bearing (32) is arranged in the middle of the fixed frame (31), the inner ring of the slewing bearing (32) is fixedly connected to the fixed frame (31), and the outer ring is fixedly connected to the slewing table on the lower frame (29).

2. The adjustable launcher for a rocket-propelled UAV according to claim 1, characterized in that: The front end of the upper frame (15) is also vertically provided with two inverted mounting seats; The front lodging component (11) comprises a front lodging frame (111), and two frame mounting seats (112) symmetrically mounted on both sides of the front lodging frame (111), a shear pin (113), a front quick-release pin (116), a torsion spring mounting seat (114), a first pin shaft (115), and a front lodging torsion spring (117); The frame mounting seat (112) comprises a first bottom plate and a connecting plate which are perpendicular to each other, the first bottom plate is fixedly connected to the upper part of the inverted mounting seat, the shear pin (113) and the front quick release pin (116) pass through the connecting plate and are connected to the front inverted frame (111), and the front quick release pin (116) is used to remove and release the front inverted frame (111) before launching; The torsion spring mounting seat (114) comprises a second bottom plate and three side plates perpendicular to the second bottom plate; the second bottom plate is fixedly connected to the upper frame (15); the first pin shaft (115) passes through a side plate, a side frame of the front inverted frame (111) and the remaining two side plates in sequence; the front inverted torsion spring (117) is sleeved on the first pin shaft (115) and is located between the remaining two side plates; one end of the front inverted torsion spring (117) is connected to the second bottom plate, and the other end is connected to the front inverted frame (111), so as to drive the front inverted frame (111) to rotate and tilt forward around the first pin shaft (115) after the front inverted frame (111) is released, so as to separate from the head of the drone.

3. An adjustable launcher for a rocket-propelled UAV according to claim 1 or 2, characterized in that: The first wing support component (12) comprises a first lower support arm (121), a first upper support arm (122), a first top screw (124), a first quick-release pin (125), a screw pair (126) and a transverse and longitudinal adjustment structure (127); The first lower arm (121) is connected to one side of the upper frame (15); the lower end of the first upper arm (122) is inserted into the first lower arm (121); a first top screw (124) and a first quick-release pin (125) are installed at the upper end of the first lower arm (121) for fixing and disassembling the first upper arm (122); a screw pair (126) is installed at the upper end of the first upper arm (122) for vertically adjusting the position of the abutment against the wing of the UAV; the transverse and longitudinal adjustment structure (127) is installed at the top end of the screw pair (126) for transversely and longitudinally adjusting the position of the abutment against the wing of the UAV; The second wing support component comprises a second lower support arm, a second upper support arm (123), a second top screw, a second quick release pin and a transverse and longitudinal adjustment structure (127); The second lower support arm is connected to the other side of the upper frame (15); the lower end of the second upper support arm (123) is respectively inserted into the second lower support arm; the second top screw and the second quick-release pin are installed at the upper end of the second lower support arm for fixing and disassembling the second upper support arm (123); the transverse and longitudinal adjustment structure (127) is installed at the upper end of the second upper support arm (123) for transversely and longitudinally adjusting the position of the abutment against the wing of the drone.

4. The adjustable launcher for a rocket-propelled UAV according to claim 3, characterized in that: The fuselage support component (13) comprises a fixing plate (131), a rotating pin plate (132), a second pin shaft (133), a first screw lifter (134), a hand wheel (135), a support block (136), and a support column (137); The fixed plate (131) is fixedly connected to the upper frame (15), and the rotating pin plate (132) and the fixed plate (131) are hinged via a second pin shaft (133); One end of the support column (137) is connected to the turn pin plate (132), and the other end is connected to the first screw elevator (134); The hand wheel (135) is connected to the input end of the first screw elevator (134), the driving end of the first screw elevator (134) is connected to one side of the support block (136), and the other side of the support block (136) is used to support the fuselage of the drone when the rotating pin plate (132) and the fixing plate (131) are folded.

5. The adjustable launcher for a rocket-propelled UAV according to claim 4, characterized in that: The launch tube support component (14) comprises a launch tube support frame (141), a mounting plate (142), a rotating shaft (143), a launch tube torsion spring (144), a launch tube support ring (145), a horizontal lead screw nut pair (146), and a vertical lead screw nut pair (147); The mounting plate (142) is fixedly mounted on the upper frame (15); the bottom of the launch tube support frame (141) is connected to the mounting plate (142) via a rotating shaft (143); a launch tube torsion spring (144) is sleeved on the rotating shaft (143) and is used to realize the folding of the launch tube support frame (141) after the UAV is launched; The horizontal lead screw nut pair (146) is arranged inside the launch tube support frame (141) and is parallel to the rotating shaft (143); a connecting block is provided on the nut of the horizontal lead screw nut pair (146), and the nut of the vertical lead screw nut pair (147) is connected to the connecting block and is perpendicular to the horizontal lead screw nut pair (146); The launch tube support ring (145) is mounted on the upper end of the vertical screw nut pair (147) and is used to contact the UAV booster rocket.

6. The adjustable launcher for a rocket-propelled UAV according to claim 1, characterized in that: The pitch platform (1) also includes an upper bearing mounting seat (18) and two latch clamps (16); The azimuth platform (2) further comprises a lower rotating shaft seat (26); The upper bearing mounting seat (18) is arranged on both sides of the rear end of the upper frame (15), and the lower shaft seat (26) is arranged at the end of the lower frame (29) and is connected to the upper bearing mounting seat (18) through a pitch shaft; The two latch clamps (16) are respectively arranged at the front end of the upper frame (15) and are detachably connected to the lower frame (29) so as to lock and connect the front ends of the upper frame (15) and the lower frame (29) when the drone is not installed.

7. The adjustable launcher for a rocket-propelled UAV according to claim 5, characterized in that: The pitching platform (1) further comprises two triangular positioning seats (17), which are arranged on the upper frame (15) and are respectively located on both sides of the supporting column (137), and are connected to the supporting column (137) when the drone is not installed.

8. The adjustable launcher for a rocket-propelled UAV according to claim 7, characterized in that: The azimuth platform (2) further comprises two transmission shafts (23) and bearing seats (28); the two bearing seats (28) are respectively mounted on the two side edges of the lower frame (29), and the two transmission shafts (23) are respectively mounted in the two bearing seats (28); one end of the transmission shaft (23) is connected to an external power source, and the other end is connected to the input end of the second screw elevator (21) through a coupling (22) for transmitting power.

9. The adjustable launcher for a rocket-propelled UAV according to claim 8, characterized in that: The orientation platform (2) further comprises four adjustment feet (27), which are respectively arranged at both ends of the two sides of the lower frame (29) and are used to adjust the level of the lower frame (29); The fixed platform (3) further comprises a ground nail (33) and a third quick-release pin (34); The number of the ground nails (33) is four, which are respectively arranged at the four top corners of the fixed frame (31) and are used to fix the fixed frame (31) on the ground; the third quick-release pin (34) passes through the turntable on the lower frame (29) and the slewing bearing (32) and is installed to position the turntable.

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