Rocket boosting type zero-length take-off high-speed target drone launcher and launching method

Abstract

The invention discloses a rocket boosting type zero-length take-off high-speed target drone launcher and a launching method.The launcher comprises a lodging mechanism, a booster rocket supporting seat, a booster rocket bracket mechanism, a high-speed target drone steel cable fixing mechanism and a transfer wheel mechanism. The space trajectory of the booster rocket is effectively avoided; the positions of the booster rocket bracket mechanism, the long lead screw, the threaded ejector rod and the short lead screw can be adjusted through nuts, adjustment and installation of the booster rocket in three directions can be achieved, a high-speed target drone steel cable fixing mechanism is provided, a safe and firm fixing structure is provided for a high-speed target drone, it is ensured that the thrust of the rocket reaches a preset value, and the service life of the high-speed target drone is prolonged. The booster rocket is launched; the launcher is of a pure mechanical structure, is simple in structure, high in safety and reliability, high in practicability and convenient to transfer, and can meet the rocket boosting launching requirements under different conditions of land, cement land, ship-borne decks and the like.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle ground launch devices, and in particular to a rocket-assisted zero-length takeoff high-speed target drone launcher and a launch method. Background Art

[0002] At present, the ground launch and take-off methods of UAVs can be roughly divided into rocket-assisted launch, vertical take-off, jettison take-off, taxiing take-off and catapult take-off; among them, zero-length take-off does not require a runway and has little dependence on the site, and is widely used in the take-off of small and medium-sized UAVs. High-speed target drones are widely used in rocket-assisted launch due to their high minimum take-off speed. Rocket-assisted launch is currently widely used in the field of UAV launch and take-off. This take-off method has the advantages of low cost, small footprint and low requirements for launch sites. The launch rack used in current rocket-assisted launch technology generally uses various electrical, hydraulic control and other devices, and the installation posture of the booster rocket is difficult to achieve rapid adjustment, which greatly reduces the application of UAV rocket-assisted launch technology in harsh environments, and also increases the deviation of UAV boosted launch. Summary of the invention

[0003] In order to overcome the deficiencies of the prior art, the purpose of the present invention is to provide a rocket-assisted zero-length take-off high-speed target drone launcher and a launching method to solve the technical problems mentioned in the background technology.

[0004] In order to solve the technical problem, the present invention adopts the following technical solution:

[0005] A rocket-assisted zero-length takeoff high-speed target drone launcher, comprising a launcher body, wherein the launcher body comprises a front launch bracket, a rear launch bracket and a connecting bracket, wherein the front end of the connecting bracket is connected to the front launch bracket, and the rear end is connected to the rear launch bracket; further comprising a falling mechanism, a booster rocket support seat, a booster rocket bracket mechanism, a high-speed target drone steel cable fixing mechanism and a transfer wheel mechanism, wherein the falling mechanism comprises a flip support frame and a pull rod assembly, wherein the upper end of the flip support frame is provided with a front launch pin support seat, and the lower end is elastically rotatably connected to the upper end of the front launch bracket through a torsion spring, a vertical bearing seat and a pin shaft, and one end of the pull rod assembly is hinged with the connecting bracket The rear launch bracket is connected to the rear launch support frame by a quick-pull pin, and the other end is connected to the flip support frame by a quick-pull pin. The upper end of the rear launch bracket is provided with a rear launch pin fixing mechanism, and the lower end is fixedly installed with a booster rocket support seat. The booster rocket bracket mechanism includes a bracket base, a screw assembly and an adjusting nut. The bracket base is adjustably mounted on the booster rocket support seat through the screw assembly and the adjusting nut. One end of the high-speed target drone steel cable fixing mechanism is fixedly mounted on the bracket base, and the other end extends outward and can be hung on the bottom of the target drone when the high-speed target drone is launched to prevent the booster rocket from being launched when the predetermined thrust is not reached. The transfer wheel mechanism is arranged at the lower ends of the front launch bracket and the rear launch bracket.

[0006] Specifically, a double-fork rotating rod is provided at the lower end of the flip support frame, and an extension limit rod is provided at the upper end of the front launching bracket. The upper end of the extension limit rod protrudes from the upper end of the connecting bracket, and the vertical bearing seat is arranged on one side of the extension limit rod. The pin shaft passes through the vertical bearing seat and the two ends of the pin shaft are respectively rotatably connected to the double-fork rotating rods on both sides. One output end of the torsion spring abuts on the extension limit rod, and the other output end can abut on one side of the double-fork rotating rod. The unfolded state of the flip support frame is realized by compressing the torsion spring through the pull rod assembly, and the flip support frame is automatically flipped downward by releasing the pull rod assembly with the help of the torsion spring.

[0007] Specifically, the booster rocket support seat includes a front plate, a side plate, a bottom plate and a rear seat plate, wherein the front plate is fixedly connected to the rear launch bracket, the bracket base includes a top frame and side frames extending downward from both sides of the top frame, the screw assembly includes a long screw and a short screw, the long screw passes through the side plates and side frames in a threaded fit, a threading position is formed between the two side frames, one end of the short screw is fixedly connected to a side of the bracket base close to the rear seat plate, and the other end can abut against the rear seat plate, the rear seat plate and the bottom plate form an obtuse angle to adapt to the launch angle of the booster rocket, a plurality of adjusting nuts are respectively installed on the long screw and the side plates or the long screw and the side frames or the short screw and the top frame, a rocket bracket is provided at the upper end of the top frame, a threaded push rod is provided between the rocket bracket and the top frame, and the rocket bracket achieves fine adjustment of the installation angle through the threaded push rod.

[0008] Specifically, the high-speed target drone cable fixing mechanism includes an outer mounting plate, an inner mounting plate, a lifting eye screw, a steel cable and a shear seat, wherein the upper end of the lifting eye screw is connected to the steel cable, the end of the steel cable is connected to the shear seat, and the shear seat is provided with a rod hole for the shear rod to pass through, a hollow groove is provided in the middle of the rear seat plate, and lateral adjustment grooves are provided on the left and right sides, the inner mounting plate is arranged on the outer side of the rear seat plate and covers the hollow groove, the inner mounting plate is adjustably locked with the rear seat plate through the lateral adjustment grooves on both sides by adjusting nuts, a screw groove for the lifting eye screw to pass through is opened in the middle of the inner mounting plate, and longitudinal adjustment grooves are symmetrically provided on the left and right sides, the outer mounting plate is arranged on the outer side of the inner mounting plate and adjustably locked with the longitudinal adjustment grooves on both sides by adjusting nuts, the lifting eye screw is fixedly connected to the outer mounting plate through the screw groove, and a support groove is also provided at the position of the rear seat plate corresponding to the segment screw, the support groove has an arc-shaped concave surface, and an arc-shaped stop block is provided at the position of the short screw corresponding to the arc-shaped concave surface.

[0009] Specifically, the front launch pin support seat is installed at the left and right ends of the top of the flip support frame to support the two circular pin shafts set on the front fuselage of the high-speed target aircraft; the rear launch pin fixing mechanism includes an upper pressure block, a spring hinge, a rear launch pin support seat and a buckle. The upper pressure block is connected to the rear launch pin support seat through a spring hinge. The buckle is opened before the high-speed target aircraft is launched, and the upper pressure block can automatically flip backwards under the action of the spring hinge to cancel the limit fixation of the drone.

[0010] Specifically, a reinforcement frame is provided on one side of the rear launch bracket, the reinforcement frame is composed of a plurality of triangular support frames, and at least one side is parallel to the connecting bracket to form a stepping fulcrum for test flight personnel to step on when performing maintenance at a high altitude;

[0011] Specifically, one side of the flip support frame is also provided with a front storage and launch area for target drone transportation and launch embedding, and the upper end of the rear launch support is provided with a rear storage and launch area for target drone transportation and launch embedding;

[0012] Specifically, the bottom of the front launching bracket and the rear launching bracket are each provided with a launching support foot, and the launching support foot is provided with a nail hole. The transfer wheel mechanism comprises a transfer wheel, a support rod, a connecting rod, a connecting rod pin, an L-shaped pull rod and a handle, and the L-shaped pull rod is provided with a fixing hole and a supporting hole. One side of the front launching bracket and the rear launching bracket is provided with a fixing ear, and the L-shaped pull rod is connected to the fixing ear through a fixing bolt, the front end of the support rod is passed through by a rotating shaft, and the other end passes through the supporting hole, the inner end of the rotating shaft is hinged to the connecting rod, and the other end is connected to the transfer wheel, the other end of the connecting rod is connected to the connecting rod pin, and the connecting rod pin is rotatably connected to one side of the front launching bracket or the rear launching bracket, one end of the support rod is provided with a connecting hole, and the handle is detachably connected to the connecting hole, and the supporting connecting rod and the transfer wheel can be quickly removed by pulling out the handle.

[0013] A rocket-assisted zero-length takeoff high-speed target drone launching method includes using the aforementioned launcher, and the launching method is as follows:

[0014] S1: The rocket booster launcher is transported to the launch site through the transfer wheel mechanism, and then the four sets of transfer wheel mechanisms are disassembled, and the launch support feet of the launcher are fixed to the ground through eight ground nails;

[0015] S2: The flip support frame in the launcher's falling mechanism is unfolded and fixed at the launcher installation point through the pull rod assembly, and the buckle of the rear launch pin fixing mechanism is opened to pop open the upper pressure block;

[0016] S3: Place the two circular pins on the front and rear fuselages of the high-speed target drone on the corresponding positions of the front launch pin support seat and the rear launch pin fixing mechanism of the launcher, and then lock the upper pressure block on the rear launch pin fixing mechanism by means of a buckle;

[0017] S4: docking the booster rocket with the high-speed target drone and placing it on the bracket base of the booster rocket bracket mechanism, adjusting the booster rocket to a predetermined launch angle by adjusting the long lead screw, the short lead screw and the adjusting nut on the threaded push rod, and locking the booster rocket and the rocket bracket;

[0018] S5: The shear seat at the end of the high-speed target drone cable fixing mechanism is fixedly connected to the shear pin on the high-speed target drone, and the other end is fixed to the outer mounting plate through a lifting eye screw, and the upper, lower, left and right position is adjusted through the inner mounting plate and the outer mounting plate, and the high-speed target drone cable fixing mechanism is adjusted to a predetermined shear angle position;

[0019] S6: Finally, the fixing bolts connecting the flip support frame and the pull rod assembly on the launcher are disengaged, and the buckle on the rear launch pin fixing mechanism is disengaged, so that the high-speed target aircraft reaches the boost launch state. When the boost rocket is launched, the flip support frame automatically flips and folds downward under the action of the forward thrust of the high-speed target aircraft and the torsion spring, thereby realizing the safe boost ejection of the high-speed target aircraft.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] The present invention provides a lodging mechanism, which not only plays a supporting role in the installation of the high-speed target drone, but also effectively avoids the risk of collision between the wing and tail of the high-speed target drone when launching. The triangular reinforcement frames on the left and right sides of the launcher not only improve the overall strength of the launcher, but also provide a stepping fulcrum for the test pilot before launching the high-speed target drone, thereby improving the convenience of repairing the drone.

[0022] By providing a booster rocket bracket mechanism, the long lead screw, threaded push rod and short lead screw are all movable mechanisms, and the position of each can be adjusted by a nut, so that the booster rocket can be installed in three directions with higher accuracy and reliability;

[0023] By providing a high-speed target drone steel cable fixing mechanism, a safe and firm fixing structure is provided for the high-speed target drone, ensuring that the rocket thrust reaches the predetermined value, and the shear rod will cut off the shear pin on the UAV fuselage to launch the high-speed target drone;

[0024] The launcher of the present invention adopts a launcher of a purely mechanical structure, which has a simple structure, high safety and reliability, high practicality, and convenient transportation, and can meet the needs of rocket booster launch under different conditions such as land, concrete ground and shipboard deck. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 : One of the three-dimensional angle schematic diagrams of the assembly state of the overall structure of the launcher of the present invention;

[0026] Figure 2 : A schematic diagram of the launcher overall structure assembly state from a side view of the present invention;

[0027] Figure 3 : The second three-dimensional angle diagram of the assembly state of the launcher overall structure of the present invention;

[0028] Figure 4 : Schematic diagram of the structure decomposition of the lodging mechanism in the launcher of the present invention;

[0029] Figure 5 : The third three-dimensional angle diagram of the assembly state of the launcher overall structure of the present invention;

[0030] Figure 6 : Figure 5 Enlarged view of part A in the middle;

[0031] Figure 7 : Figure 5 Enlarged view of middle part B;

[0032] Figure 8 : Schematic diagram of the exploded rear launch pin fixing mechanism in the launcher of the present invention;

[0033] Fig. 9 : Schematic diagram of the booster rocket bracket mechanism and the high-speed target drone steel lock fixing mechanism in the launcher of the present invention;

[0034] Fig.10 : Exploded view of the booster rocket bracket mechanism and the high-speed target drone steel lock fixing mechanism in the launcher of the present invention;

[0035] Fig.11 : Assembly diagram (left) and exploded diagram (right) of the transfer wheel mechanism;

[0036] Fig.12 : Schematic diagram of booster rocket bracket mechanism and high-speed target drone steel lock fixing mechanism in the launcher of the present invention;

[0037] Fig.13 : Schematic diagram of the arc-shaped stopper in the short lead screw and the arc-shaped concave surface structure on the support groove;

[0038] In the figure: a launcher body 1, a front launch bracket 11, a rear launch bracket 12, a connecting bracket 13, a falling mechanism 2, a booster rocket bracket mechanism 5, a high-speed target drone cable fixing mechanism 6, a transfer wheel mechanism 7, a flip support frame 21, a pull rod assembly 22, a front launch pin support seat 211, a torsion spring 201, a vertical bearing seat 202, a pin 203, a quick-pull pin 204, a double-fork rotating rod 212, and an extension limit rod 205;

[0039] Rear launch pin fixing mechanism 3, booster rocket support seat 4, bracket base 51, screw assembly 52, adjusting nut 53, front plate 41, side plate 42, bottom plate 43, rear seat plate 44, top frame 511, side frame 512, long screw 521, short screw 522, cable insertion position 501, rocket bracket 54, threaded top rod 55, outer mounting plate 61, inner mounting plate 62, eye screw 63, steel cable 64, shear seat 65, rod hole 651, hollow groove 441, lateral adjustment groove 442, screw groove 621, longitudinal adjustment groove 622, support groove 443, arc concave surface 443a, arc-shaped stop block 522a;

[0040] Upper pressure block 31, spring hinge 32, rear launch pin support seat 33, buckle 34, reinforced frame 14, pedal fulcrum 141, front storage and transportation launch area 111, rear storage and transportation launch area 121, launch support foot 15, nail hole 151, transfer wheel 71, support rod 72, connecting rod 73, connecting rod pin 74, L-shaped pull rod 75, handle 76, fixing hole 751, supporting hole 752, fixing ear 721, connecting hole 721. DETAILED DESCRIPTION

[0041] The present invention is further described below in conjunction with the accompanying drawings and specific implementation methods. It should be noted that, under the premise of no conflict, the various embodiments or technical features described below can be arbitrarily combined to form a new embodiment.

[0042] refer to Figures 1 to 13 :

[0043] The present invention discloses a rocket-assisted zero-length takeoff high-speed target drone launcher, comprising a launcher body 1, wherein the launcher body 1 comprises a front launch bracket 11, a rear launch bracket 12 and a connecting bracket 13, wherein the front end of the connecting bracket 13 is connected to the front launch bracket 11, and the rear end is connected to the rear launch bracket 12; and the height of the front launch bracket 11 is higher than the height of the rear launch bracket 12, so as to provide an upward angle when the rocket is launched, and further comprises a falling mechanism 2, a booster rocket support seat 4, a booster rocket bracket mechanism 5, a high-speed target drone steel cable fixing mechanism 6 and a transfer wheel mechanism 7, wherein the launcher body 1 is used for ground support, and the falling mechanism 2 comprises a flipping support frame 21 and a pull rod assembly 22, wherein the upper end of the flipping support frame 21 is provided with a front launch pin support seat 211, and the lower end is provided with a pull rod assembly 22. The torsion spring 201, the vertical bearing seat 202 and the pin shaft 203 are elastically rotatably connected to the upper end of the front launch bracket 11. One end of the pull rod assembly 22 is hinged to the connecting bracket 13, and the other end is connected to the flip support frame 21 through the quick-pull pin 204. Here, when the high-speed target drone (unmanned aerial vehicle) is in a non-launching state, the falling mechanism 2 is in an unfolded state with the help of the pull rod assembly 22, thereby providing a support and embedding effect for the transportation of the high-speed target drone, or when the high-speed target drone is in a launching state, by releasing the pull rod assembly 22, the high-speed target drone can be helped to provide an initial support effect before the booster rocket reaches a predetermined thrust, and when the high-speed target drone is launched, it automatically flips downward to avoid the space trajectory of the booster rocket by relying on the forward thrust of the high-speed target drone and the action of the torsion spring 201, thereby realizing a safe booster launch of the high-speed target drone;

[0044] Specifically, a rear launch pin fixing mechanism 3 is provided at the upper end of the rear launch bracket 12, and a booster rocket support seat 4 is fixedly installed at the lower end. The booster rocket bracket mechanism 5 includes a bracket base 51, a screw assembly 52 and an adjusting nut 53. The bracket base 51 is adjustably mounted on the booster rocket support seat 4 through the screw assembly 52 and the adjusting nut 53. One end of the high-speed target drone steel cable fixing mechanism 6 is fixedly mounted on the bracket base 51, and the other end extends outward and can be hung on the bottom of the target drone when the high-speed target drone is launched. At the same time, the shear rod is locked to prevent the booster rocket from being launched when the predetermined thrust is not reached. Only when the booster rocket reaches the predetermined thrust, the shear rod is sheared off by the corresponding thrust. At this time, the booster rocket is launched with the high-speed target drone. The transfer wheel mechanism 7 is arranged at the lower ends of the front launch bracket 11 and the rear launch bracket 12 to facilitate the transfer of this launch bracket.

[0045] Specifically, a double-forked rotating rod 212 is provided at the lower end of the flip support frame 21, an extended limiting rod 205 is provided at the upper end of the front launching bracket 11, and the upper end of the extended limiting rod 205 protrudes from the upper end of the connecting bracket 13. The vertical bearing seat 202 is arranged on one side of the extended limiting rod 205, and the pin shaft 203 passes through the vertical bearing seat 202. At the same time, the two ends of the pin shaft 203 are respectively rotatably connected with the double-forked rotating rod 212 on both sides. One output end of the torsion spring 201 abuts on the extended limiting rod 205, and the other output end can abut on one side of the double-forked rotating rod 212. The flipping support frame is realized by compressing the torsion spring 201 through the pull rod assembly 22. The unfolded state of 21 is realized by releasing the pull rod assembly 22 and realizing the automatic downward flipping of the flip support frame 21 with the help of the torsion spring 201. It should be noted here that the automatic downward flipping of the flip support frame 21 requires the help of a certain thrust, such as a forward thrust given when a high-speed target drone is fired forward. Because the front launch bracket 11 itself has a backward tilting angle, the flip support frame 21 will also tilt backward, and the force of the torsion spring 201 itself is not enough to directly flip the flip support frame 21 backward, or when the launch frame is not needed, a person can give the flip support frame 21 a forward bending force to make it flip downward with the help of gravity and the force of the torsion spring 201.

[0046] Specifically, the booster rocket support seat 4 includes a front plate 41, a side plate 42, a bottom plate 43 and a rear seat plate 44, wherein the front plate 41 is fixedly connected to the rear launch bracket 12, the bracket base 51 includes a top frame 511 and side frames 512 extending downward from both sides of the top frame 511, the screw assembly 52 includes a long screw 521 and a short screw 522, the long screw 521 simultaneously passes through the side plate 42 and the side frame 512 in a thread-matching manner, and a cable insertion position 501 for the steel cable 64 to pass through is formed between the two side frames 512, as shown in FIG. Therefore, the slight swing of the booster rocket between ignition and reaching the predetermined thrust will not hit other parts. One end of the short screw 522 is fixedly connected to the side of the bracket base 51 close to the rear seat plate 44, and the other end can abut on the rear seat plate 44. In this way, the rear end of the bracket base 51 has the short screw 522 abutting on the rear seat plate 44 as a supporting force, and the lower end of the bracket base 51 is connected to the side plate 42 through the long screw 521. Specifically, the rear seat plate 44 forms an obtuse angle with the bottom plate 43 to adapt to the booster rocket. The multiple adjusting nuts 53 are respectively installed on the long lead screw 521 and the side plate 42 or the long lead screw 521 and the side frame 512 or the short lead screw 522 and the top frame 511 to realize the left and right position adjustment and the front and rear swing angle adjustment of the bracket base 51 between the two side plates 42. For example, if the length of the lead screw 522 is shortened, the angle between the corresponding bracket base 51 and the rear seat plate 44 will become smaller, and vice versa, it will become larger, thereby realizing the fine adjustment of the launch angle of the booster rocket. The upper end of the top frame 511 is provided with a rocket bracket 54 A threaded push rod 55 is provided between the rocket bracket 54 and the top frame 511. The rocket bracket 54 can achieve fine adjustment of the installation angle through the threaded push rod 55. The installation angle here is based on the angle of rotation of the axis of the screw push rod. When in use, the booster rocket is docked with the high-speed target aircraft and placed on the rocket bracket 54 of the booster rocket bracket mechanism 5. The booster rocket is adjusted to a predetermined launch angle by adjusting the long lead screw 521, the short lead screw 522 and the locking nut on the threaded push rod 55, and the booster rocket and the rocket bracket 54 are locked and matched.

[0047] Specifically, the steel cable 64 fixing mechanism includes an outer mounting plate 61, an inner mounting plate 62, a lifting eye screw 63, a steel cable 64 and a shear seat 65, wherein the upper end of the lifting eye screw 63 is connected to the steel cable 64, and the end of the steel cable 64 is connected to the shear seat 65. The shear seat 65 is provided with a rod hole 651 for the shear rod to pass through. The shear rod can simultaneously pass through the locking pin hole and the rod hole 651 at the bottom of the high-speed target drone. When the booster rocket reaches a predetermined thrust, the shear rod will be sheared by the forward thrust of the rocket. Here, the shear rod is preferably an aluminum rod. The predetermined thrust value of the booster rocket is adapted by simulating and measuring the shear force of shear rods of different diameters, densities or materials, thereby eliminating the cumbersome thrust sensor and calculation structure, and the launch of the high-speed target drone can be completed quickly. The launch work is carried out while reducing the production cost and the single launch cost of the launch rack. Specifically, a hollow groove 441 is provided in the middle of the rear seat plate 44, and transverse adjustment grooves 442 are provided on the left and right sides. The inner mounting plate 62 is arranged on the outer side of the rear seat plate 44 and covers the hollow groove 441. The inner mounting plate 62 is adjustably locked with the rear seat plate 44 through the transverse adjustment grooves 442 on both sides by adjusting nuts 53. A screw groove 621 for the eye screw 63 to pass through is opened in the middle of the inner mounting plate 62, and longitudinal adjustment grooves 622 are symmetrically provided on the left and right sides. The outer mounting plate 61 is arranged on the outer side of the inner mounting plate 62 and is adjustably locked with the adjusting nuts 53 through the longitudinal adjustment grooves 622 on both sides. The eye screw 63 passes through the screw groove 621 and is fixedly connected to the outer mounting plate 61. Here, the inner mounting plate 62 can be adjusted laterally relative to the rear seat plate 44, and the outer mounting plate 61 can be adjusted longitudinally relative to the inner mounting plate 62, that is, the inner eye screw 63 can achieve transverse and longitudinal adjustment positions, so as to adapt to the requirements of different booster rockets or high-speed target drone mounting positions. Specifically, in adjusting the longitudinal flip angle of the bracket base 51, the length of the short lead screw 522 is adjusted here. However, when the short lead screw 522 directly abuts against the rear seat plate 44, hard contact is often formed. When fine-tuning is required, the adjusting nut 53 on the long lead screw 521 needs to be loosened, and the bracket base 5 needs to be quickly rotated. 1 is used to drive the short lead screw 522 to rotate, which is relatively difficult to achieve. Here, a solution is provided. A support groove 443 is further provided at the position of the rear seat plate 44 corresponding to the lead screw. The support groove 443 has an arc-shaped concave surface 443a. The short lead screw 522 is provided with an arc-shaped stopper 522a at the position corresponding to the arc-shaped concave surface 443a. Through this arrangement, when it is necessary to fine-tune the bracket base 51, the bracket base 51 can be directly rotated. When the bracket base 51 rotates, the arc-shaped stopper 522a at the outer end of the short lead screw 522 cooperates with the arc-shaped concave surface 443a, thereby overcoming the problem of being unable to fine-tune due to hard contact. Of course, as another optional embodiment, the arc-shaped stopper 522a here can be a sphere.

[0048] Specifically, the front launch pin support seat 211 is installed at the left and right ends of the top of the flip support frame 21 to support the two circular pin shafts 203 set on the front fuselage of the high-speed target aircraft; the rear launch pin fixing mechanism 3 includes an upper pressure block 31, a spring hinge 32, a rear launch pin support seat 33 and a buckle 34. The upper pressure block 31 is connected to the rear launch pin support seat 33 through the spring hinge 32. The buckle 34 is opened before the high-speed target aircraft is launched, and the upper pressure block 31 can automatically flip backwards under the action of the spring hinge 32, thereby canceling the limit fixation of the drone.

[0049] Specifically, a reinforcing frame 14 is provided on one side of the rear launch bracket 12. The reinforcing frame 14 is composed of a plurality of triangular support frames and has at least one side parallel to the connecting bracket 13 to form a stepping fulcrum 141 for test flight personnel to step on when performing maintenance at a high altitude.

[0050] Specifically, one side of the flip support frame 21 is also provided with a front storage and launch area 111 for the transfer and launch of the target drone, and the upper end of the rear launch bracket 12 is provided with a rear storage and launch area 121 for the transfer and launch of the target drone. With this arrangement, the launcher can also serve as a transport vehicle for high-speed target drones. When multiple high-speed target drone launch operations are required in succession, one of the high-speed target drones can be pre-installed in the hangar and transported to the destination by the launcher for launch. After the launch, other high-speed target drones can be replaced for launch.

[0051] Specifically, the bottom of the front launching bracket 11 and the rear launching bracket 12 are both provided with a launching support foot 15, and the launching support foot 15 is provided with a nail hole 151, and the nail hole 151 is for steel nails to be inserted, so as to fix the launching bracket during launching. The transfer wheel mechanism 7 includes a transfer wheel 71, a support rod 72, a connecting rod 73, a connecting rod latch 74, an L-shaped pull rod 75 and a handle 76, and the L-shaped pull rod 75 is provided with a fixing hole 751 and a supporting hole 752. One side of the front launching bracket 11 and the rear launching bracket 12 is provided with a fixing ear 721, and the L-shaped pull rod 75 is connected to the fixing ear 721 by a fixing bolt. Here, the fixing ear 721 has a screw hole, and the fixing bolt can pass through the screw hole and be fixedly connected to the fixing hole 751 on the L-shaped pull rod 75, and the front end of the support rod 72 is penetrated by the rotating shaft. The other end passes through the supporting hole 752, the inner end of the rotating shaft is hinged to the connecting rod 73, and the other end is connected to the transfer wheel 71, the other end of the connecting rod 73 is connected to the connecting rod pin 74, and the connecting rod pin 74 is rotatably connected to one side of the front launching bracket 11 or the rear launching bracket 12, one end of the support rod 72 is provided with a connecting hole 721, and the handle 76 is detachably connected to the connecting hole 721, and the support connecting rod 73 and the transfer wheel 71 can be quickly removed by pulling out the handle 76. Here, the insertion direction of the connecting rod pin 74 can be inserted from the side away from the connecting rod 73 to the side of the connecting rod 73 and locked with the connecting rod 73 through a nut, so that when quick release is achieved, the nut can be directly contacted, the connecting rod pin 74 can be pulled out, and then the support rod 72 can be pulled out from the supporting hole 752, and the quick release of the transfer wheel mechanism 7 can be completed.

[0052] Based on the aforementioned launcher technical solution, the present invention also discloses a rocket-assisted zero-length takeoff high-speed target drone launching method, the launching method is as follows:

[0053] S1: The rocket-boosted launcher is transported to the launch site by the transfer wheel mechanism 7. In order to make full use of the installation position and save preparation time after arriving at the destination, the high-speed target drone can be fixed in advance in the hangar to the front storage and transportation launch area 111 and the rear storage and transportation launch area 121 on the front launch bracket 11 and the rear launch bracket 12. At this time, the quick-pull pin 204 of the pull rod assembly 22 is plugged in, the support frame 21 is flipped over, and then the four groups of transfer wheel mechanisms 7 are disassembled, and the launch support feet 15 of the launcher are fixed to the ground by 8 ground nails;

[0054] S2: The flip support frame 21 in the launcher falling mechanism 2 is unfolded and fixed at the launcher installation point through the pull rod assembly 22, and the buckle 34 of the rear launch pin fixing mechanism 3 is opened to pop open the upper pressing block 31;

[0055] S3: Place the two circular pins 203 on the front and rear fuselages of the high-speed target drone on the corresponding positions of the front launch pin support seat 211 and the rear launch pin fixing mechanism 3 of the launcher, and then lock the upper pressing block 31 on the rear launch pin fixing mechanism 3 by means of the buckle 34;

[0056] S4: docking the booster rocket with the high-speed target drone and placing it on the bracket base 51 of the booster rocket bracket mechanism 5, adjusting the booster rocket to a predetermined launch angle by adjusting the long lead screw 521, the short lead screw 522 and the adjusting nut 53 on the threaded push rod 55, and locking the booster rocket and the rocket bracket 54;

[0057] S5: The shear seat 65 at the end of the steel cable 64 fixing mechanism is fixedly connected to the shear pin on the high-speed target machine, and the other end is fixed to the outer mounting plate 61 through the eye screw 63. The upper, lower, left and right positions are adjusted through the inner mounting plate 62 and the outer mounting plate 61, and the steel lock fixing mechanism is adjusted to a predetermined shear angle position;

[0058] S6: Finally, the fixing bolts connecting the flip support frame 21 and the pull rod assembly 22 on the launcher are disengaged, and the buckle 34 on the rear launch pin fixing mechanism 3 is disengaged, so that the high-speed target aircraft reaches the boost launch state. When the booster rocket reaches the predetermined thrust, the forward impulse of the booster rocket cuts off the shear rod, and the booster rocket is launched with the high-speed target aircraft or UAV. At the moment of the booster rocket launch, the flip support frame 21 automatically flips and folds downward under the action of inertia force and torsion spring 201, avoiding the space trajectory of the booster rocket, and realizing the safe boost ejection of the high-speed target aircraft.

[0059] The above-mentioned embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. A rocket-assisted zero-length takeoff high-speed target drone launcher, comprising a launcher body, wherein the launcher body comprises a front launch bracket, a rear launch bracket and a connecting bracket, wherein the front end of the connecting bracket is connected to the front launch bracket, and the rear end is connected to the rear launch bracket; characterized in that: The invention also includes a falling mechanism, a booster rocket support seat, a booster rocket bracket mechanism, a high-speed target drone steel cable fixing mechanism and a transfer wheel mechanism. The falling mechanism includes a flip support frame and a pull rod assembly. The upper end of the flip support frame is provided with a front launch pin support seat, and the lower end is elastically rotatably connected to the upper end of the front launch bracket through a torsion spring, a vertical bearing seat and a pin shaft. One end of the pull rod assembly is hinged to the connecting bracket, and the other end is connected to the flip support frame through a quick-pull pin. The upper end of the rear launch bracket is provided with a rear launch pin fixing mechanism, and the lower end is fixedly installed with a booster rocket support seat. The booster rocket bracket mechanism includes a bracket base, a screw assembly and an adjusting nut. The bracket base is adjustably mounted on the booster rocket support seat through the screw assembly and the adjusting nut. One end of the high-speed target drone steel cable fixing mechanism is fixedly mounted on the bracket base, and the other end extends outward and can be hung on the bottom of the target drone when the high-speed target drone is launched to prevent the booster rocket from being launched when the predetermined thrust is not reached. The transfer wheel mechanism is arranged at the lower end of the front launch bracket and the rear launch bracket.

2. A rocket-assisted zero-length takeoff high-speed target drone launcher as claimed in claim 1, characterized in that: A double-fork rotating rod is provided at the lower end of the flip support frame, and an extension limit rod is provided at the upper end of the front launching bracket. The upper end of the extension limit rod protrudes from the upper end of the connecting bracket, and the vertical bearing seat is arranged on one side of the extension limit rod. The pin shaft passes through the vertical bearing seat and the two ends of the pin shaft are respectively rotatably connected with the double-fork rotating rods on both sides. One output end of the torsion spring abuts on the extension limit rod, and the other output end can abut on one side of the double-fork rotating rod. The unfolded state of the flip support frame is realized by compressing the torsion spring through the pull rod assembly, and the flip support frame is automatically flipped downward by releasing the pull rod assembly with the help of the torsion spring.

3. A rocket-assisted zero-length takeoff high-speed target drone launcher as claimed in claim 1, characterized in that: The booster rocket support seat includes a front plate, a side plate, a bottom plate and a rear seat plate, wherein the front plate is fixedly connected to the rear launch bracket, the bracket base includes a top frame and side frames extending downward from both sides of the top frame, the screw assembly includes a long screw and a short screw, the long screw simultaneously passes through the side plates and the side frames in a threaded fit, a threading position is formed between the two side frames, one end of the short screw is fixedly connected to a side of the bracket base close to the rear seat plate, and the other end can abut against the rear seat plate, the rear seat plate and the bottom plate form an obtuse angle to adapt to the launch angle of the booster rocket, a plurality of adjusting nuts are respectively installed on the long screw and the side plates or the long screw and the side frames or the short screw and the top frame, a rocket bracket is provided at the upper end of the top frame, a threaded push rod is provided between the rocket bracket and the top frame, and the rocket bracket achieves fine adjustment of the installation angle through the threaded push rod.

4. A rocket-assisted zero-length takeoff high-speed target drone launcher as claimed in claim 3, characterized in that: The high-speed target drone cable fixing mechanism comprises an outer mounting plate, an inner mounting plate, a lifting eye screw, a steel cable and a shear seat, wherein the upper end of the lifting eye screw is connected to the steel cable, the end of the steel cable is connected to the shear seat, and the shear seat is provided with a rod hole for the shear rod to pass through, a hollow groove is provided in the middle of the rear seat plate, and lateral adjustment grooves are provided on the left and right sides, the inner mounting plate is arranged on the outer side of the rear seat plate and covers the hollow groove, the inner mounting plate is adjustably locked with the rear seat plate through the lateral adjustment grooves on both sides by adjusting nuts, a screw groove for the lifting eye screw to pass through is opened in the middle of the inner mounting plate, and longitudinal adjustment grooves are symmetrically provided on the left and right sides, the outer mounting plate is arranged on the outer side of the inner mounting plate and adjustably locked with the longitudinal adjustment grooves on both sides by adjusting nuts, the lifting eye screw is fixedly connected to the outer mounting plate through the screw groove, and a support groove is also provided at the position of the rear seat plate corresponding to the segment screw, the support groove has an arc-shaped concave surface, and an arc-shaped stop block is provided at the position of the short screw corresponding to the arc-shaped concave surface.

5. A rocket-assisted zero-length takeoff high-speed target drone launcher as claimed in claim 1, characterized in that: The front launch pin support seat is installed at the left and right ends of the top of the flip support frame to support the two circular pin shafts set on the front fuselage of the high-speed target aircraft; the rear launch pin fixing mechanism includes an upper pressure block, a spring hinge, a rear launch pin support seat and a buckle. The upper pressure block is connected to the rear launch pin support seat through a spring hinge. The buckle is opened before the high-speed target aircraft is launched, and the upper pressure block can automatically flip backwards under the action of the spring hinge to cancel the limit fixation of the drone.

6. A rocket-assisted zero-length takeoff high-speed target drone launcher as claimed in claim 1, characterized in that: A reinforcing frame is provided on one side of the rear launch bracket. The reinforcing frame is composed of a plurality of triangular support frames and has at least one side parallel to the connecting bracket to form a stepping fulcrum for test pilots to step on when performing maintenance at high altitudes.

7. A rocket-assisted zero-length takeoff high-speed target drone launcher as claimed in claim 1, characterized in that: A front storage and launch area for target drone transportation and launch embedding is also provided on one side of the flip support frame, and a rear storage and launch area for target drone transportation and launch embedding is provided on the upper end of the rear launch bracket.

8. A rocket-assisted zero-length takeoff high-speed target drone launcher as claimed in claim 1, characterized in that: The bottom of the front launching bracket and the rear launching bracket are both provided with launching support feet, and the launching support feet are provided with nail holes. The transfer wheel mechanism comprises a transfer wheel, a support rod, a connecting rod, a connecting rod latch, an L-shaped pull rod and a handle, and the L-shaped pull rod is provided with a fixing hole and a supporting hole. One side of the front launching bracket and the rear launching bracket is provided with a fixing ear, and the L-shaped pull rod is connected to the fixing ear through a fixing bolt, the front end of the support rod is passed through by the rotating shaft, and the other end passes through the supporting hole, the inner end of the rotating shaft is hinged to the connecting rod, and the other end is connected to the transfer wheel, the other end of the connecting rod is connected to the connecting rod latch, and the connecting rod latch is rotatably connected to one side of the front launching bracket or the rear launching bracket, one end of the support rod is provided with a connecting hole, and the handle is detachably connected to the connecting hole, and the supporting connecting rod and the transfer wheel can be quickly removed by pulling out the handle.

9. A method for launching a rocket-assisted zero-length takeoff high-speed target drone, comprising using a launcher as described in any one of claims 1 to 8, wherein the launching method is as follows: S1: The rocket booster launcher is transported to the launch site through the transfer wheel mechanism, and then the four sets of transfer wheel mechanisms are disassembled, and the launch support feet of the launcher are fixed to the ground through eight ground nails; S2: The flip support frame in the launcher's falling mechanism is unfolded and fixed at the launcher installation point through the pull rod assembly, and the buckle of the rear launch pin fixing mechanism is opened to pop open the upper pressure block; S3: Place the two circular pins on the front and rear fuselages of the high-speed target drone on the corresponding positions of the front launch pin support seat and the rear launch pin fixing mechanism of the launcher, and then lock the upper pressure block on the rear launch pin fixing mechanism by means of a buckle; S4: docking the booster rocket with the high-speed target drone and placing it on the bracket base of the booster rocket bracket mechanism, adjusting the booster rocket to a predetermined launch angle by adjusting the long lead screw, the short lead screw and the adjusting nut on the threaded push rod, and locking the booster rocket and the rocket bracket; S5: The shear seat at the end of the high-speed target drone cable fixing mechanism is fixedly connected to the shear pin on the high-speed target drone, and the other end is fixed to the outer mounting plate through a lifting eye screw, and the upper, lower, left and right position is adjusted through the inner mounting plate and the outer mounting plate, and the high-speed target drone cable fixing mechanism is adjusted to a predetermined shear angle position; S6: Finally, the fixing bolts connecting the flip support frame and the pull rod assembly on the launcher are disengaged, and the buckle on the rear launch pin fixing mechanism is disengaged, so that the high-speed target aircraft reaches the boost launch state. When the boost rocket is launched, the flip support frame automatically flips and folds downward under the action of the forward thrust of the high-speed target aircraft and the torsion spring, thereby realizing the safe boost ejection of the high-speed target aircraft.

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