CN117232325A - Vertical platform, double-rocket aircraft launching installation method and launching system - Google Patents

Abstract

The invention discloses a launching installation method and a launching system of a standing platform and a double-rocket aircraft, wherein the launching installation method comprises the following steps: a chassis; for connection to a transmitting ground; a vertical frame is erected; one end of the device is hinged with the underframe, and a vertical driving piece is arranged between the underframe and the vertical frame and used for driving the vertical frame to switch between a horizontal state and a vertical state; the front supporting device is arranged on the vertical frame and used for supporting and fixing the front end of the rocket booster; the rear supporting device is arranged on the vertical frame and is used for supporting the rear end of the rocket booster; the two locking bullet baffle assemblies are arranged on the vertical frame and used for fixing the rear end of the rocket booster; the wing body supporting component is arranged on the erection frame and used for supporting the wing body section. The invention can solve the problems caused by large volume, heavy weight and lack of special launching equipment in the launching flight test of the double-rocket aircraft.

Description

Vertical platform, double-rocket aircraft launching installation method and launching system

Technical Field

The invention belongs to the technical field of rocket launching, and particularly relates to a launching installation method and a launching system of a standing platform and a double-rocket aircraft.

Background

The utility model provides a certain two rocket body unmanned aerial vehicle boost rocket is a novel two style parallel rocket, is including being located the wing body section in the middle and being located two rocket boosters of wing body section both sides, wherein the wing body section is as the supporting part who bears unmanned aerial vehicle. The total length of the double-rocket aircraft is more than 10m, the width of the double-rocket aircraft is more than 8m, the diameters of rocket boosters on two sides are more than 1m, the axial distance between the rocket boosters is about 5m, and the full load weight of the whole aircraft is more than 20 tons.

In general, the rocket is erected on a launching system by using a mobile platform for launching the rocket, but is limited by shooting range launching conditions, so that enough factory space is often not available for accommodating the aircraft at the height, and great difficulty is brought to the installation of the aircraft before launching. In summary, aiming at the novel double-rocket aircraft, the novel double-rocket aircraft has large volume and large weight, and no special launching equipment at present, which brings great difficulty to the launching flight test of the double-rocket aircraft.

Disclosure of Invention

The invention aims to provide a lifting platform, a double-rocket aircraft launching installation method and a launching system, which are used for solving the problems caused by large volume, heavy weight and lack of special launching equipment in a launching flight test of the double-rocket aircraft.

The invention is realized by the following technical scheme:

an erection platform comprising:

a chassis; the underframe is used for being connected with the ground of the launching site;

a vertical frame is erected; the lifting frame is used for bearing the double-rocket aircraft, one end of the lifting frame is hinged with the underframe, and a lifting driving piece is arranged between the underframe and the lifting frame and used for driving the lifting frame to switch between a horizontal state and a lifting state;

the front supporting device is arranged on the vertical frame and used for supporting and fixing the front end of the rocket booster;

the rear supporting device is arranged on the vertical frame and is used for supporting the rear end of the rocket booster;

the two locking bullet blocking device assemblies are arranged on the vertical frame and used for fixing the rear end of the rocket booster;

the wing body supporting component is arranged on the erection frame and used for supporting the wing body section.

In some embodiments, the front supporting device comprises a front supporting frame and enclasping assemblies oppositely arranged at two ends of the front supporting frame, the lifting frame and the front supporting frame are respectively provided with corresponding front supporting installation interfaces, the front supporting frame is connected to the lifting frame through the front supporting installation interfaces, and the enclasping assemblies are used for enclasping the front end of the rocket booster.

In some embodiments, the clasping assembly includes a bottom frame, a middle frame, an upper frame, and a clasping assembly disposed on the upper frame;

the chassis is fixedly arranged on the front supporting frame, a transverse guide rail is arranged on the chassis along the transverse direction of the vertical frame, a middle frame is arranged on the transverse guide rail, a transverse moving driving assembly is arranged between the chassis and the middle frame, and the transverse moving driving assembly can drive the middle frame to move on the transverse guide rail;

the middle frame is provided with a lifting mechanism and a lifting driving assembly, the upper frame is arranged on the lifting mechanism, and the lifting of the lifting mechanism is controlled by the lifting driving assembly to adjust the height of the upper frame in the vertical direction;

the holding clamp assembly comprises two holding clamps hinged with the upper frame respectively, the two holding clamps are oppositely arranged to form an openable hoop structure, an openable driving assembly is arranged on the upper frame, and the opening driving assembly is used for controlling the rotation of the holding clamps and adjusting the clamping and loosening actions of the holding clamp assembly.

In some embodiments, the rear supporting device comprises a rear supporting frame and rear supporting assemblies oppositely arranged at two ends of the rear supporting frame, the upright frame and the rear supporting frame are respectively provided with corresponding rear supporting installation interfaces, the rear supporting frame is connected to the upright frame through the rear supporting installation interfaces, and the rear supporting assemblies are used for supporting the rear end of the rocket booster.

In some embodiments, the rear support assembly comprises a base frame, a top frame and a support piece arranged on the top frame, wherein the base frame is arranged on the rear support frame, a transverse adjusting mechanism is arranged between the rear support frame and the base frame, the top frame is arranged on the transverse adjusting mechanism, and the transverse adjusting mechanism is used for adjusting the position of the top frame along the transverse direction of the vertical frame; and a height adjusting mechanism is arranged between the top frame and the supporting piece and is used for adjusting the height of the supporting piece along the vertical direction.

In some embodiments, the wing body support assembly includes a first support disposed on the erection frame and a second support disposed on the rear support frame.

In some embodiments, the device further comprises a mounting fixture capable of being arranged on one side of the erection frame, wherein the mounting fixture is used for positioning the position of the double rocket aircraft on the erection frame.

In some embodiments, the lockout cartridge holder assembly includes a lockout cartridge holder including a cartridge holder and two sets of lockout assemblies disposed on the cartridge holder, the two sets of lockout assemblies being disposed crosswise on the cartridge holder;

the locking assembly comprises a tensioning piece, a first supporting seat and a second supporting seat, wherein the first supporting seat and the second supporting seat are oppositely arranged on the bullet blocking disc, a mounting claw used for being connected with the rocket booster is arranged on the second supporting seat, the mounting claw is rotationally connected with the second supporting seat, two ends of the tensioning piece are fixedly connected with the first supporting seat and the mounting claw respectively, rotation of the mounting claw is limited, and rotation limitation on the mounting claw is relieved when the tensioning piece is fused.

In some embodiments, the latch bullet blocking assembly comprises a latch bullet blocking assembly, the latch bullet blocking assembly comprises an inclined support frame, a large bracket and a small bracket, the inclined support frame is fixedly arranged on one side of the vertical support frame, the large bracket is fixedly arranged on the inclined support frame, the small bracket is fixedly arranged on the vertical support frame, the large bracket and the small bracket are oppositely arranged at intervals, and two ends of the latch bullet blocking assembly are respectively fixedly arranged on the large bracket and the small bracket.

In another aspect, the present invention further provides a method for installing a double rocket vehicle in a launching manner, including:

hoisting the wing body section of the double-rocket aircraft to a wing body supporting component on the lifting frame, and supporting the wing body section through the wing body supporting component;

positioning and mounting the mounting tool on the left side of the erection frame, adjusting the position of the wing body section, enabling the wing body section to be matched between the side mounting surface and the side surface of the mounting tool, detecting the mounting position of the wing body section through a positioning pin hole arranged on the mounting tool, and adjusting the position of the wing body section on the erection frame according to the detection condition;

the transverse position and the height of the enclasping assembly in the front supporting device are adjusted to enable the enclasping assembly to be located at the lowest position and enable the enclasping clamp assembly to be in a loosening state, and the transverse position and the height of the supporting piece in the rear supporting device are adjusted to enable the supporting center of the supporting piece and the enclasping center of the enclasping clamp assembly on the front supporting device to be located on the same horizontal axis;

a rocket booster is arranged on the wing body section; firstly, installing a right rocket booster, hoisting the rocket booster to a lifting platform, adjusting the rocket booster to a position matched with a connecting interface on a wing body section, completing adjustment and butt joint of the position of the rocket booster, and then fixedly connecting the right rocket booster with the wing body section through bolts; after the installation of the right rocket booster is completed, removing an installation tool arranged on the left side of the erection frame, and then adopting the same installation method as that for installing the right rocket booster to fixedly install the left rocket booster on the wing body section;

after the installation of the rocket booster is completed, the two holding clamp assemblies are loosened, the whole double-rocket aircraft is dragged towards the locking bullet blocking device assembly, the rear end of the rocket booster is attached to the end face of the locking bullet blocking device, and the locking bullet blocking device is fixedly connected with the rocket booster through the installation claw;

and adjusting the holding clamp assembly again to hold the rocket booster tightly, and finishing the assembly and the fixed installation of the double-rocket aircraft on the erection platform.

On the other hand, the invention also provides a launching system which comprises the erection platform.

Compared with the prior art, the invention has the following advantages:

1) The erection platform is formed by constructing all parts of a frame structure, so that the problems of large size, large weight, large butt joint installation difficulty and inconvenient installation of the aircraft on a launching site are solved, the erection platform can be used as an assembly platform of the double-rocket aircraft while being used as the launching erection platform, the installation of the double-rocket aircraft is more convenient and rapid, the installation precision is easy to be ensured, the quick installation and the withdrawal of a launching system on the launching site are convenient in the launching process, and the requirement of quick response of a launching flight task can be met.

2) The launching system can realize the installation support of the aircraft, the whole erection and the connection between the launching platform after the erection, thereby well solving the problems existing in the installation, transportation and launching links of the double-rocket aircraft in the launching flight test, well meeting the rapid launching and the anytime withdrawing operation under various launching site conditions and providing a brand new solution for the design of the novel double-rocket aircraft launching system.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following description will briefly describe the drawings in the embodiments, it being understood that the following drawings only illustrate some embodiments of the present invention and should not be considered as limiting the scope, and that other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of the structure of the launching system and the erection platform of the present invention in a horizontal state.

FIG. 2 is a schematic diagram of the structure of the launching system and the erection platform of the present invention in an erect state.

FIG. 3 is a schematic view of another view of the launching system of the present invention with the erection platform in an erect position.

FIG. 4 is a schematic view of the structure of the chassis of the erecting platform according to the present invention.

FIG. 5 is a schematic view of the structure of the erection frame in the erection platform of the invention.

FIG. 6 is a schematic view of the front support structure of the erection platform of the invention.

FIG. 7 is a schematic view of the structure of the hugging assembly in the vertical platform system of the present invention.

FIG. 8 is a schematic view of an alternative view of the hug assembly in the vertical platform of the present invention.

Fig. 9 is a partial schematic view of fig. 8 at a.

FIG. 10 is a schematic view of the rear support structure of the erection platform of the invention.

FIG. 11 is a schematic view of the rear support assembly in the erection platform of the invention.

FIG. 12 is a schematic view of the installation tool structure in the erection platform of the invention.

FIG. 13 is a schematic view of a latch spring retainer assembly in an erection platform of the present invention.

FIG. 14 is a schematic view of a latch spring retainer in a vertical platform according to the present invention.

Fig. 15 is a schematic view of a structure of a launching platform in the launching system of the present invention.

FIG. 16 is a schematic view of the structure of the launching system of the present invention with the latch stopper mounted to the launching platform in an erect condition.

Wherein:

10. a vertical platform is arranged;

11. the device comprises a chassis, 111, a down force fixer, 112, a lower pitching support, 113, a lifting frame connecting support, 114, anchor bolt installation seats, 115 and a transmitting platform connecting seat;

12. the device comprises a vertical frame, 121, a front supporting device installation interface, 122, a rear supporting device installation interface, 123, a locking bullet blocking device assembly installation interface, 124, a vertical frame installation shaft, 125, an upper pitching support, 126, an ascending force fixer, 127, lifting lugs, 128 and an installation tool installation interface;

13. front supporting device, 131, front supporting frame, 132, underframe, 133, middle frame, 134, upper frame, 135, holding clamp assembly, 1351, holding clamp, 1352, shifting fork chute, 1353, limiting piece, 136, transverse driving assembly, 137, lifting mechanism, 138, lifting driving assembly, 139, opening and closing driving assembly, 1391, double-end screw, 1392, transmission piece, 1393 and transmission rod;

14. rear supporting device 141, rear supporting frame 142, base frame 143, top frame 144, supporting piece 145, transverse adjusting mechanism 146 and height adjusting mechanism;

151. a first support 152, a second support;

16. a vertical driving member;

17. mounting a tool, namely a 171 and a positioning pin hole;

20. a latch spring retainer assembly;

21. a locking bullet blocking device 211, a bullet blocking disc 212, a tensioning piece 213, a first supporting seat 214, a second supporting seat 215 and a mounting claw;

221. the inclined support frame, 222, the big bracket, 223 and the small bracket;

30. the device comprises a launching platform 31, a launching frame 311, a launching platform 312, a supporting and adjusting piece 313, a drainage through hole 314, a fluid director 32, a connecting frame 321 and a chassis mounting seat;

401. front support mounting interface, 403, launch fixing hole.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention.

Compared with the prior launching operation of a small-sized aircraft, the double-rocket aircraft has the characteristics of large volume and large weight, and the double-rocket aircraft adopts a combined structure formed by a wing body and two rocket boosters, so that the problem of double-rocket aircraft assembly is also required to be considered during launching, and great difficulty is brought to the launching operation of the double-rocket aircraft.

Meanwhile, based on the specificity of the launching flight task, the influence of various factors such as weather needs to be considered, so that the launching system is required to meet the requirements of quick installation and retraction at any time, and obviously, the launching system of the existing small-sized aircraft is difficult to meet the requirements.

Based on the problems and the requirements, the double-rocket aircraft launching system provided by the invention integrally adopts a frame type, combined type and modularized design thought so as to realize the installation and assembly platform of the double-rocket aircraft and the use of the double-rocket aircraft launching platform, thereby realizing the quick response to launching tasks.

Referring to fig. 1, 2 and 3, in one embodiment, a launch system for dual rocket vehicle launch consists essentially of an erection platform 10 and a launch platform 30; wherein:

the erection platform 10 comprises a bottom frame 11 and a erection frame 12, wherein the bottom frame 11 is used for being connected with the ground of a launching site; the erection frame 12 is used for carrying a double rocket vehicle (not shown in the figure, and comprises a wing body section and two rocket boosters arranged on two sides of the wing body section), the erection frame 12 is hinged between one end and the underframe 11, an erection driving piece 16 is arranged between the underframe 11 and the erection frame 12, and the erection driving piece 16 is used for driving the erection frame to switch between a horizontal state and an erection state so as to realize the functions of quick erection and retraction of a launching system in the launching process.

The erection platform is used as a main functional part of the launching system, and in order to meet the requirements of providing the functions of installing and assembling the platform for the double-rocket aircraft and supporting the erection platform for the double-rocket aircraft, the erection platform needs to have a size matched with that of the double-rocket aircraft. In the embodiment, the length of the erection frame in the erection platform is more than 10m, the width is about 2.5m, the height is about 2m, the erection and the withdrawal of a load of 20 tons can be met, and the control of the shooting precision of the aircraft can be realized through the connection between the erection frame and the underframe and the arrangement of the erection driving piece, wherein the shooting precision is not lower than 20'.

Referring to fig. 4, the base frame 11 is constructed in a frame type structure, and a down force fixer 111, a lower elevation support 112, an elevation support 113, an anchor bolt mounting base 114, and a launching platform connecting base 115 are provided on the base frame 11 of the frame structure.

Wherein, the down force fixer 111 is used for fixing the free end of the erection frame in the marching process, so as to ensure the stability of the erection frame on the bottom frame; the lower pitching support 112 is used for connecting the erection driving element 16, the erection driving element 16 can adopt a hydraulic cylinder, and the erection driving element 16 is hinged with the lower pitching support 112; the upright frame connecting support 113 is used for connecting the upright frame 12, and the upright frame 12 is hinged with the upright frame connecting seat 113; the anchor mounts 114 are used to fixedly connect the chassis to the launch floor; the launching platform coupling mount 115 is used for positioning connection between the chassis and the launching platform.

Referring to fig. 5, an erection frame 12 is used as a main body structure of an erection double rocket vehicle, and is constructed in a frame type structure to have sufficient strength and rigidity; the riser 12 is provided with a front support mounting interface 121, a rear support mounting interface 122, a latch assembly mounting interface 123, a riser mounting shaft 124, an upper pitch support 125, an up-take anchor 126, a lifting lug 127, and a mounting fixture mounting interface 128.

Wherein the front support device mounting interface 121 is used for the fixed mounting of the front support device on the upright frame; the rear support mounting interface 122 is used for the fixed mounting of the rear support on the riser; the locking bullet blocking assembly mounting interface 123 is used for fixedly mounting the locking bullet blocking assembly on the vertical frame; the erection frame installation shaft 124 is used for being connected with an erection frame connection support on the underframe to realize hinge connection between the erection frame and the underframe; the upper pitching support 125 is used for connecting the other end of the erection driving element, so that the erection driving element is hinged with the erection frame; the ascending and descending arming retainers 126 are matched with the descending arming retainers 111 on the underframe 11 to fixedly connect the erection frame on the underframe; lifting lugs 127 are used for lifting the vertical frame 12; the mounting fixture mounting interface 128 is used for positioning and mounting the mounting fixture on one side of the front support frame.

The erection frame 12 is provided with a front support device 13 for installing a rocket booster, a rear support device 14 and a first support 151 for supporting wing segments, provides an installation platform for the assembly of the double rocket vehicle, and simultaneously fixes the double rocket vehicle on the erection frame.

Referring to fig. 6, 7, 8 and 9, the front supporting device 13 includes a front supporting frame 131 and enclasping assemblies oppositely disposed at two ends of the front supporting frame, and a front supporting mounting interface 401 is disposed on the front supporting frame 131 for positioning and matching mounting of the front supporting frame on the erection frame. Referring to fig. 4, inclined support structures are disposed on two sides of the front support 131 and are connected with two sides of the erection frame in a matched manner, so that the front support and the erection frame are matched on three surfaces, and stable assembly of the front support on the erection frame is ensured.

The enclasping assembly is used for enclasping and fixing the rocket booster and comprises a bottom frame 132, a middle frame 133, an upper frame 134 and an enclasping clamp assembly 135 arranged on the upper frame, wherein the bottom frame 132 is fixedly arranged on a front supporting frame 131, a transverse guide rail is arranged on the middle frame 133 along the transverse direction of the vertical frame, the middle frame is arranged on the transverse guide rail, a transverse moving driving assembly 136 is arranged between the bottom frame and the middle frame, and the transverse moving driving assembly 136 can drive the middle frame to move on the transverse guide rail; the middle frame 133 is provided with a lifting mechanism 137 and a lifting driving assembly 138, the upper frame 134 is arranged on the lifting mechanism 137, and the lifting of the lifting mechanism is controlled by the lifting driving assembly to adjust the height of the upper frame in the vertical direction; the holding clamp assembly 135 comprises two holding clamps 1351 hinged with the upper frame respectively, the two holding clamps 1351 are oppositely arranged to form an openable hoop structure, an opening and closing driving assembly is arranged on the upper frame 134, and the opening and closing driving assembly is used for controlling the rotation of the holding clamps to adjust the clamping and loosening actions of the holding clamp assembly.

The transverse driving assembly 136 comprises a hand wheel, an adjusting screw connected to the hand wheel and a sliding block connected with the middle frame, the sliding block is in sliding fit with the transverse guide rail, the sliding block is in threaded connection with the adjusting screw, and the hand wheel is used for controlling the rotation of the adjusting screw to control the adjustment of the position of the middle frame in the transverse direction.

The lifting mechanism 137 adopts four column type lifting pieces, the lifting driving assembly can adopt a hand wheel and a gear transmission assembly, the lifting driving assembly is simultaneously connected with the four column type lifting pieces through the gear transmission assembly, and the simultaneous lifting adjustment of the four column type lifting pieces can be realized through the gear transmission assembly when the hand wheel is rotated, so that the adjustment of the lifting height of an upper frame is realized; the column lifter and the gear assembly are commercially available products, and the construction thereof will not be described in detail.

The opening and closing driving assembly 139 comprises a hydraulic motor and a double-end screw rod 1391 connected to the hydraulic motor, threads at two ends of the double-end screw rod are opposite in rotation direction, transmission blocks 1392 are respectively arranged at two ends of the double-end screw rod, and the two transmission blocks 1392 are respectively connected with the double-end screw rod 1391 in a threaded manner; the transmission block 1392 is provided with a transmission rod 1393, one end of the holding clamp 1351 is provided with a shifting fork sliding chute 1352, the transmission rod 1393 is matched and arranged in the shifting fork sliding chute 5352, sliding fit is formed between the transmission rod 1393 and the shifting fork sliding chute, and therefore when the double-head screw is driven to rotate through the hydraulic motor, synchronous inward or synchronous outward movement of the transmission block can be achieved, and at the moment, opening and clamping actions of the two holding clamps can be achieved through the matching between the transmission rod and the shifting fork sliding chute.

In order to control the clamping force of the holding clamp assembly, limiting pieces 1353 are respectively arranged on the outer sides of the two holding clamps on the upper frame 134, the rotating positions of the holding clamps are limited through the limiting pieces 1353, the clamping force of the holding clamp assembly is controlled through controlling the opening degree of the holding clamps, and the transmission rod can be prevented from falling out of the shifting fork sliding groove.

Referring to fig. 10 and 11, the rear supporting device 14 includes a rear supporting frame 141 and rear supporting assemblies disposed at both ends of the rear supporting frame, the rear supporting frame 141 has a structure substantially identical to that of the front supporting frame, and a corresponding rear supporting mounting interface is disposed on the rear supporting frame 141 for positioning and mounting the rear supporting frame on the erection frame.

The rear support assembly is used for supporting the rear end of the rocket booster and comprises a base frame 142, a top frame 143 and a support piece 144 arranged on the top frame, wherein the base frame 142 is arranged on the rear support frame 141, a transverse adjusting mechanism 145 is arranged between the rear support frame 141 and the base frame 142, the top frame 143 is arranged on the transverse adjusting mechanism 145, and the position of the top frame can be adjusted along the transverse direction of the vertical frame through the transverse adjusting mechanism; the transverse adjusting mechanism can adopt a transverse guide rail and a transverse moving driving assembly or similar structure adopted in the enclasping assembly, and the structure is not described in detail here; a height adjusting mechanism 146 is provided between the top frame 143 and the supporting member 144, and the height of the supporting member can be adjusted in the vertical direction by the height adjusting mechanism 146, wherein the height adjusting mechanism can adopt a lifting mechanism and a lifting driving assembly or the like which are adopted in the hugging assembly, and the detailed description of the structure thereof is omitted.

A wing body supporting assembly is provided on the erection frame, and includes a first supporting member 151 provided on the erection frame and a second supporting member 152 provided on the rear supporting frame. A second support 152 on the rear support frame cooperates with the first support 151 to provide auxiliary support for the wing segments of the double rocket vehicle.

Based on the above description of the structure and function of the front and rear supporting devices, it can be seen that the erection frame at this time can be used as a mounting assembly platform for a double rocket vehicle.

The inclinometer and the indication mark line are arranged on the erection frame to assist in adjusting the position and angle of the erection frame in the installation and emission states.

Referring to fig. 12, which is a schematic structural diagram of an installation tool, when the double-rocket vehicle is installed on the launching system, the installation tool 17 is installed at a corresponding position on the left side of the erection frame, and a positioning pin hole 171 is arranged on the installation tool 17 and used for positioning the installation position of the double-rocket vehicle on the erection platform, so that the accuracy of the installation position of the double-rocket vehicle is ensured.

Referring to fig. 13 and 14, two latch stopper assemblies 20 are provided on the erection platform 10, and the two latch stopper assemblies 20 are provided on the erection frame at positions corresponding to the two rocket boosters, respectively.

The latch stopper assembly 20 includes a latch stopper 21 for fixing the rocket booster and a latch stopper mounting assembly for mounting the latch stopper; wherein:

the latch spring stopper installation assembly comprises an inclined supporting frame 221, a large bracket 222 and a small bracket 223, wherein the inclined supporting frame 221 is fixedly arranged on one side of the vertical lifting frame 12, the large bracket 222 is fixedly arranged on the inclined supporting frame 221, the small bracket 223 is fixedly arranged on the vertical lifting frame 12, and corresponding installation interfaces are arranged on the inclined supporting frame, the large bracket, the vertical lifting frame and the small bracket to ensure the latch spring stopper installation assembly and the matching installation precision thereof on the vertical lifting frame.

The locking bullet blocking device 21 comprises a bullet blocking disc 211 and two groups of locking components arranged on the bullet blocking disc, and two ends of the bullet blocking disc 211 are respectively fixedly connected to a large bracket 222 and a small bracket 223, so that the locking bullet blocking device is fixedly installed on the vertical frame. The bullet blocking disc 211 is provided with a through hole for the flame of the rocket booster to pass through, and the two groups of locking components are arranged above the through hole in a crossing way.

The locking assembly comprises a tensioning piece 212, a first supporting seat 213 and a second supporting seat 214 which are oppositely arranged on the bullet blocking disc, a mounting claw 215 which is used for being connected with the rocket booster is arranged on the second supporting seat 214, the mounting claw 215 is rotationally connected with the second supporting seat 214, two ends of the tensioning piece 212 are respectively fixedly connected with the first supporting seat 213 and the mounting claw 215 so as to limit the rotation of the mounting claw, and when the tensioning piece is fused by flame sprayed out of the rocket booster, the rotation limitation of the mounting claw is relieved.

The tensioning member 212 may be a magnesium strap made of magnesium, so that it can be quickly fused under the action of the flame of the rocket booster. Before launching, the rocket booster is connected with the bolt at the bottom of the rocket booster through the mounting claw, and due to the tensioning effect of the magnesium belt, stable connection can be formed between the rocket booster and the bottom of the rocket booster through the two groups of locking assemblies, so that the rocket booster is fixed on the locking bullet blocking assembly; when the aircraft is launched, the rocket booster is ignited, the magnesium belt is ablated and disconnected by flame airflow in millisecond-level time under the action of high-temperature flame, so that the locking component loses locking acting force, the mounting claw rotates under the action of the rocket booster, and the rocket booster is separated from the locking device.

The tensioning member 212 further comprises pull blocks arranged at two ends of the magnesium belt, wherein one end of each pull block is fixedly connected with the magnesium belt, and the other end of each pull block is fixedly connected with the first supporting seat and the mounting claw through a bolt, so that the tensioning member can be conveniently mounted on the locking bullet blocking device.

Referring to fig. 15 and 16, a launching platform 30 is used for stabilizing and supporting a double rocket vehicle before launching, the launching platform 30 is disposed at one end of the erection platform 10, and includes two launching frames 31 disposed side by side, and the launching platform is configured to support two rocket boosters right after being erected by the erection platform.

The launching cradle 31 adopts a frame structure, a launching platform 311 is arranged on the launching cradle 31, and a launching fixing structure is arranged on the launching platform 311 and is configured to fixedly connect the locking bullet blocking device in the standing state to the launching platform. Specifically, the launching fixing structure includes a plurality of launching fixing holes 403 disposed on the launching platform 311, and a plurality of corresponding launching fixing holes 403 are correspondingly disposed on the bullet blocking disc 211 of the locking bullet blocking device, so that the locking bullet blocking device can be quickly and fixedly connected to the launching frame through the launching fixing holes and bolts.

A support adjustment mechanism is provided on the launch pad 311, and is configured to enable the launch pad to support the end surface of the latch projectile stopper in the upright state at a plurality of positions, so as to ensure the stability and reliability of the installation of the double rocket vehicle on the launch pad.

Specifically, in one embodiment, the support adjustment mechanism includes a plurality of support adjustment members 312 disposed on the launching cradle in the direction of arrangement, and the support adjustment members 312 are screwed with the launching pad 311. When the vertical platform is in a vertical state, the locking bullet blocking device is arranged above the launching platform, at the moment, the plurality of supporting adjusting pieces are tightly matched with the end faces of the bullet blocking disc by adjusting the height positions of the plurality of supporting adjusting pieces, and at the moment, the launching platform can stably support the double-rocket aircraft.

A discharge hole 313 is arranged on the launching platform 311, and the discharge hole 313 corresponds to the through hole on the bullet stop plate 211 and is also used for passing the flame of the rocket booster; a deflector 314 is disposed on the launching cradle 31 below the drain hole, the deflector 314 is a hollow cavity structure having an inlet and an outlet, and the inlet is disposed toward the drain hole 313. The deflector 314 is configured to deflect the high temperature flame airflow generated during ignition of the rocket booster, thereby reducing damage and impact to the launching system.

Here the outlets of the deflectors 314 on the two racks 31 are arranged opposite each other along the length of the platform towards the outside. Through the arrangement of the outlet direction, high-temperature flame airflow is guided to the two sides of the emission platform, so that the direct action on the emission system is reduced; meanwhile, the directions of the outlets at the two sides are symmetrically distributed, so that the acting force of the launching platform during launching is more balanced.

The launching platform 30 further comprises a connecting frame 32 for connecting the two launching frames 31, an underframe mounting seat 321 is arranged on the connecting frame 32, a matching is formed between the underframe mounting seat 321 and a launching platform connecting seat 115 arranged on the underframe, and the positioning matching installation between the launching platform and the launching platform is used for enabling the two locking bullet blocking devices to be just in the centering arrangement with the two launching frames respectively when the launching frames are erected to the erecting state, and the bullet blocking disc and the launching fixing holes arranged on the launching platform can just in time form one-to-one correspondence so as to facilitate the operation and the launching efficiency in the whole launching process.

The launching system adopts a modularized and spliced structure, and the launching operation of the double-rocket aircraft by adopting the launching system comprises the assembly and transportation of the launching system, the assembly of the double-rocket aircraft on a erection platform and the erection launching process.

Firstly, assembling a erection platform in a factory building, installing an erection frame on a bottom frame, and installing an erection driving piece on the bottom frame and the erection frame respectively;

mounting the front support device, the first support piece and the rear support device on the upright frame respectively;

and respectively installing the two groups of locking device installation assemblies on the erection frame, and then respectively installing the locking device bullet blocking devices on the locking device installation assemblies, thereby completing the assembly of the erection platform.

After the assembly of the erection platform is completed, the double rocket aircraft is assembled on the erection platform, and the method comprises the following steps of:

hoisting the wing body section of the double rocket aircraft to a first supporting piece and a second supporting piece on the erection frame, and supporting the wing body section through the first supporting piece and the second supporting piece; the supporting surfaces of the first supporting piece and the second supporting piece are set to be profile surfaces matched with the profile of the wing body section, so that good fit between the wing body section and the wing body section can be formed; the position of the wing body section is adjusted to enable the shooting line on the wing body section to coincide with the shooting line marked on the erection frame;

positioning and mounting the mounting tool on the left side of the erection frame, adjusting the position of the wing body section, enabling the wing body section to be matched between the side mounting surface and the side surface of the mounting tool, detecting the mounting position of the wing body section through a positioning pin hole arranged on the mounting tool, and adjusting the position of the wing body section on the erection frame according to the detection condition;

the transverse position and the height of the enclasping assembly in the front supporting device are adjusted to enable the enclasping assembly to be located at the lowest position and enable the enclasping clamp assembly to be in a loosening state, and the transverse position and the height of the supporting piece in the rear supporting device are adjusted to enable the supporting center of the supporting piece and the enclasping center of the enclasping clamp assembly on the front supporting device to be located on the same horizontal axis;

a rocket booster is arranged on the wing body section;

firstly installing a right side rocket booster, hoisting the rocket booster onto a lifting platform, adjusting the rolling gesture and the front and back positions of the rocket booster, adjusting a holding clamp assembly to clamp the rocket booster, simultaneously adjusting the transverse positions of a holding assembly and a supporting piece at the moment, slowly adjusting the rocket booster to the corresponding installation position of a wing body section, simultaneously adjusting the heights of the holding assembly and the supporting piece, adjusting the rocket booster to the position matched with a connecting interface on the wing body section, completing the adjustment and butt joint of the position of the rocket booster, and then fixedly connecting the right side rocket booster with the wing body section through bolts;

after the installation of the right rocket booster is completed, the right rocket booster is stably connected and installed on the erection frame through the front supporting device and the rear supporting device, the installation positions and the states of the right rocket booster and the wing body section on the erection frame are stable, at the moment, an installation tool arranged on the left side of the erection frame can be removed, and then the left rocket booster is fixedly installed on the wing body section by adopting the same installation method as that for installing the right rocket booster;

after the installation of the rocket booster is completed, the two holding clamp assemblies are loosened, the whole double-rocket aircraft is dragged towards the locking bullet blocking device assembly, the rear end of the rocket booster is attached to the end face of the locking bullet blocking device, and the locking bullet blocking device is fixedly connected with the rocket booster through the installation claw;

and adjusting the holding clamp assembly again to hold the rocket booster tightly, and finishing the assembly and the fixed installation of the double-rocket aircraft on the erection platform.

After the assembly and installation of the double rocket aircraft are completed, the operation of the subsequent erection and launching stage can be performed, and the method comprises the following steps:

lifting the erection platform and the double-rocket aircraft on a flat car integrally, and conveying the flat car to a launching field; after an operator determines the direction of the shooting, marking a scribing line on the ground of the shooting field, hoisting the erection platform to the ground through a crane, and adjusting the position of the erection platform to enable the erection platform to coincide with the scribing line marked on the ground, so that the accuracy of the shooting is ensured; the levelness of the erecting platform is adjusted through the inclinometer, and the underframe is fixed on the ground after leveling;

the transmitting platform is fixedly connected with the underframe in a positioning way, and then the transmitting platform is fixedly connected to the ground;

the vertical lifting frame is lifted to a vertical lifting state (90 degrees with the horizontal plane) through the vertical lifting driving piece, a support adjusting mechanism on the launching platform is adjusted to stably support the end face of the locking bullet blocking device, then the locking bullet blocking device is connected with the launching platform through a bolt and a launching fixing hole, and the locking bullet blocking device is fixedly connected to the launching platform;

the connection between the locking bullet blocking device and the locking bullet blocking device assembly is released, at the moment, the double-rocket aircraft is fixedly connected to the launching platform, then the holding clamp assembly is loosened, and the connection between the double-rocket aircraft and the rocket booster is released;

and (5) withdrawing the vertical platform to a horizontal state, and completing the preparation of the double-rocket aircraft before launching.

And after receiving the launching instruction, carrying out an ignition launching test of the double-rocket aircraft.

In the description of the present invention, it should be noted that, as the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are used to indicate orientations or positional relationships based on those shown in the drawings, or those that are conventionally put in use in the product of the present invention, they are merely used to facilitate description of the present invention and simplify description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.

Furthermore, the terms "horizontal," "vertical," and the like in the description of the present invention, if any, do not denote absolute levels or overhangs, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present invention, it should also be noted that, unless explicitly stated and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.

The foregoing description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and any simple modification, equivalent variation, etc. of the above embodiment according to the technical matter of the present invention fall within the scope of the present invention.

Claims (10)

1. Erect the platform, its characterized in that includes:

a chassis; the underframe is used for being connected with the ground of the launching site;

a vertical frame is erected; the lifting frame is used for bearing the double-rocket aircraft, one end of the lifting frame is hinged with the underframe, and a lifting driving piece is arranged between the underframe and the lifting frame and used for driving the lifting frame to switch between a horizontal state and a lifting state;

the front supporting device is arranged on the vertical frame and used for supporting and fixing the front end of the rocket booster;

the rear supporting device is arranged on the vertical frame and is used for supporting the rear end of the rocket booster;

the two locking bullet blocking device assemblies are arranged on the vertical frame and used for fixing the rear end of the rocket booster;

the wing body supporting component is arranged on the erection frame and used for supporting the wing body section.

2. The erection platform of claim 1, wherein the front supporting device comprises a front supporting frame and enclasping assemblies oppositely arranged at two ends of the front supporting frame, the front supporting frame and the front supporting frame are respectively provided with corresponding front supporting installation interfaces, the front supporting frame is connected to the erection frame through the front supporting installation interfaces, and the enclasping assemblies are used for enclasping the front end of the rocket booster.

3. The erection platform of claim 2, wherein the clasping assembly comprises a bottom frame, a middle frame, an upper frame, and a clasping assembly disposed on the upper frame;

the chassis is fixedly arranged on the front supporting frame, a transverse guide rail is arranged on the chassis along the transverse direction of the vertical frame, a middle frame is arranged on the transverse guide rail, a transverse moving driving assembly is arranged between the chassis and the middle frame, and the transverse moving driving assembly can drive the middle frame to move on the transverse guide rail;

the middle frame is provided with a lifting mechanism and a lifting driving assembly, the upper frame is arranged on the lifting mechanism, and the lifting of the lifting mechanism is controlled by the lifting driving assembly to adjust the height of the upper frame in the vertical direction;

the holding clamp assembly comprises two holding clamps hinged with the upper frame respectively, the two holding clamps are oppositely arranged to form an openable hoop structure, an openable driving assembly is arranged on the upper frame, and the opening driving assembly is used for controlling the rotation of the holding clamps and adjusting the clamping and loosening actions of the holding clamp assembly.

4. The erection platform of claim 1, wherein the rear supporting device comprises a rear supporting frame and rear supporting assemblies oppositely arranged at two ends of the rear supporting frame, the rear supporting frame and the rear supporting frame are respectively provided with corresponding rear supporting installation interfaces, the rear supporting frame is connected to the erection frame through the rear supporting installation interfaces, and the rear supporting assemblies are used for supporting the rear end of the rocket booster.

5. The erection platform of claim 4, wherein the rear support assembly comprises a base frame, a top frame and a support member arranged on the top frame, the base frame is arranged on the rear support frame, a transverse adjusting mechanism is arranged between the rear support frame and the base frame, the top frame is arranged on the transverse adjusting mechanism, and the transverse adjusting mechanism is used for adjusting the position of the top frame along the transverse direction of the erection frame; and a height adjusting mechanism is arranged between the top frame and the supporting piece and is used for adjusting the height of the supporting piece along the vertical direction.

6. An erection platform according to claim 1, further comprising a mounting fixture which can be provided to one side of the erection frame, the mounting fixture being for locating the position of the double rocket aerial vehicle on the erection frame.

7. The lift platform of claim 1, wherein the lockout cartridge holder assembly comprises a lockout cartridge holder comprising a cartridge holder and two sets of lockout assemblies disposed on the cartridge holder, the two sets of lockout assemblies being disposed crosswise on the cartridge holder;

the locking assembly comprises a tensioning piece, a first supporting seat and a second supporting seat, wherein the first supporting seat and the second supporting seat are oppositely arranged on the bullet blocking disc, a mounting claw used for being connected with the rocket booster is arranged on the second supporting seat, the mounting claw is rotationally connected with the second supporting seat, two ends of the tensioning piece are fixedly connected with the first supporting seat and the mounting claw respectively, rotation of the mounting claw is limited, and rotation limitation on the mounting claw is relieved when the tensioning piece is fused.

8. The erection platform of claim 7, wherein the latch stop assembly comprises a latch stop mounting assembly comprising an inclined support frame, a large bracket and a small bracket, wherein the inclined support frame is fixedly arranged on one side of the erection frame, the large bracket is fixedly arranged on the inclined support frame, the small bracket is fixedly arranged on the erection frame, the large bracket and the small bracket are oppositely arranged at intervals, and two ends of the latch stop are respectively fixedly arranged on the large bracket and the small bracket.

9. The method for launching and installing the double-rocket aircraft is characterized by comprising the following steps of:

hoisting the wing body section of the double-rocket aircraft to a wing body supporting component on the lifting frame, and supporting the wing body section through the wing body supporting component;

positioning and mounting the mounting tool on the left side of the erection frame, adjusting the position of the wing body section, enabling the wing body section to be matched between the side mounting surface and the side surface of the mounting tool, detecting the mounting position of the wing body section through a positioning pin hole arranged on the mounting tool, and adjusting the position of the wing body section on the erection frame according to the detection condition;

the transverse position and the height of the enclasping assembly in the front supporting device are adjusted to enable the enclasping assembly to be located at the lowest position and enable the enclasping clamp assembly to be in a loosening state, and the transverse position and the height of the supporting piece in the rear supporting device are adjusted to enable the supporting center of the supporting piece and the enclasping center of the enclasping clamp assembly on the front supporting device to be located on the same horizontal axis;

a rocket booster is arranged on the wing body section; firstly, installing a right rocket booster, hoisting the rocket booster to a lifting platform, adjusting the rocket booster to a position matched with a connecting interface on a wing body section, completing adjustment and butt joint of the position of the rocket booster, and then fixedly connecting the right rocket booster with the wing body section through bolts; after the installation of the right rocket booster is completed, removing an installation tool arranged on the left side of the erection frame, and then adopting the same installation method as that for installing the right rocket booster to fixedly install the left rocket booster on the wing body section;

after the installation of the rocket booster is completed, the two holding clamp assemblies are loosened, the whole double-rocket aircraft is dragged towards the locking bullet blocking device assembly, the rear end of the rocket booster is attached to the end face of the locking bullet blocking device, and the locking bullet blocking device is fixedly connected with the rocket booster through the installation claw;

and adjusting the holding clamp assembly again to hold the rocket booster tightly, and finishing the assembly and the fixed installation of the double-rocket aircraft on the erection platform.

10. A launch system comprising an erection platform according to any one of claims 1 to 8.