A launch platform

Abstract

The present invention discloses a launching platform, which comprises a first main body, a second main body, a clamping ring assembly and a limiting assembly. During the erection and launching process of an aircraft, the erection beam is horizontally placed on the first main body, and the opening and closing buckles on the clamping ring assembly are in a separated state. The aircraft is moved onto the erection beam, and the two opening and closing buckles are driven to approach each other by a second pushing portion until the opening and closing buckles rotate and embrace the aircraft, and at the same time, the bottom of the aircraft is fixed to the limiting plate by a locking member, and then the erection beam is driven to rotate by the first pushing portion until the aircraft is in a vertical state. At this time, the support plate is supported under the limiting plate. Before launching the aircraft, the locking member is removed, and the two opening and closing buckles are driven to separate by the second pushing portion until the opening and closing buckles loosen the aircraft to a certain extent, and the distance between the opening and closing buckles is not enough for the aircraft to move out radially. At this time, the aircraft maintains a vertical state and can be ignited and launched at any time.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft erection and launch, and in particular to a launch platform. Background Art

[0002] Existing erection and launch technologies are mostly vehicle-mounted launch. The launch vehicle has automatic leveling, erection, and launch functions, and the system integration is high. The launch vehicle development cycle is long and the cost is high, which does not meet the requirements of short development project cycle and low cost.

[0003] At present, simple erection and launch devices in the private aerospace field are all built with the cooperation of two cranes to realize the erection and launch of the aircraft. This method has great safety hazards, and because the levels of the crane operators are inconsistent, it directly affects the safety of erection. In addition, the cooperation of two manually operated cranes at the same time is difficult and has low operating accuracy. It is also difficult to adjust the direction of the aircraft, which can easily affect the safe, timely and controllable progress of the aircraft launch process. Summary of the invention

[0004] In view of the defects existing in the prior art, the present application provides a launching platform to solve the problems in the prior art that it is difficult, unsafe and difficult to adjust when two cranes cooperate to complete the erection and launch of an aircraft.

[0005] The above-mentioned purpose of the present invention is mainly achieved through the following technical solutions:

[0006] A launching platform, comprising:

[0007] A first main body, on which a vertical beam is movably provided, a first end of the vertical beam is rotatably connected to the first main body, and a first pushing portion for driving the vertical beam to rotate to a vertical state is provided between the first main body and the middle portion of the vertical beam;

[0008] A second body, fixedly connected to the first body, a support plate is provided on the second body, and when the erecting beam is rotated to a vertical state, the support plate is used to be supported on the lower part of the aircraft;

[0009] The clamping ring assembly comprises a base, two opening and closing buckles and two second pushing parts, wherein the base is fixedly connected to the vertical beam, the opening and closing buckle is rotatably arranged on the base, and the second pushing part is arranged between the base and the opening and closing buckle and drives the two opening and closing buckles to move closer or farther away, so that the clamping ring assembly embraces or releases the aircraft;

[0010] The limiting assembly comprises a limiting plate connected to the first end of the vertical beam, and the limiting plate is detachably provided with a locking member, and the locking member is used to fix the aircraft on the limiting plate.

[0011] Furthermore, the locking member includes a positioning sleeve and a locking rod, the positioning sleeve is fixed on the limit plate, and the positioning sleeve is parallel to the center line of the limit plate, the positioning sleeve has a first space for accommodating the locking rod, and the first space has a tightening surface for blocking the locking rod, one end of the locking rod can pass through the positioning sleeve and be used to be threadedly connected to the aircraft.

[0012] Furthermore, the locking member also includes a pressure cover, a first positioning nut and a second positioning nut. The limiting plate is provided with a fine-tuning hole whose inner diameter is larger than the outer diameter of the positioning sleeve. The positioning sleeve is arranged in the fine-tuning hole. The first positioning nut and the second positioning nut are threadedly connected to the positioning sleeve and are respectively pressed on both sides of the limiting plate. The pressure cover is detachably connected to the limiting plate. The pressure cover has a first through hole for the positioning sleeve to pass through. The inner diameter of the first through hole is smaller than the outer diameter of the positioning nut, so that the pressure cover is pressed on the first positioning nut.

[0013] Furthermore, the second main body is also provided with a shooting direction adjustment component, which includes a turntable and a slewing support. The turntable and the slewing support are connected to a gear box via a reducer so that the turntable drives the slewing support to rotate, and the slewing support is fixedly connected to the support plate.

[0014] Furthermore, the support plate is provided with a plurality of adjustment pairs, and the adjustment pairs include a support block and an adjustment screw connected by threads. The adjustment screw is rotatably provided on the support plate, and the adjustment screw rotates to drive the support block to rise or fall.

[0015] Furthermore, a plurality of adjusting legs are respectively threadedly connected to the bottom of the first main body and the bottom of the second main body.

[0016] Furthermore, a plurality of mounting blocks are provided on the erecting beam, each mounting block is provided with a clamping ring assembly, and a plurality of concave cross beams matching with the outer side wall of the aircraft are provided in the middle of the erecting beam.

[0017] Furthermore, two ends of the first pushing portion and two ends of the second pushing portion are rotatably connected with a rotating pair respectively.

[0018] Furthermore, the first pushing part and the second pushing part adopt hydraulic cylinders, the launching platform also includes a hydraulic system, the hydraulic system includes an oil tank, a power pump, a filter and an electric heater, the oil tank is provided with hydraulic oil, the power pump is arranged between the oil tank and the first pushing part and the second pushing part, and is used to drive the hydraulic oil to flow to the first pushing part and the second pushing part, the filter is arranged at the oil outlet end and the oil return end of the oil tank, and the electric heater is arranged in the oil tank and is used to heat the hydraulic oil.

[0019] Furthermore, a second through hole is respectively provided on the limit plate and the support plate, and the second through hole is used to provide a channel for the tail flame of the aircraft to pass through. A guide plate is also provided on the second body, and the guide plate is located at the lower part of the second through hole. The guide plate has two guide surfaces, one end of the guide surface is located below the second through hole, and the other end is located on the side of the second body.

[0020] Compared with the prior art, the advantages of the present invention are:

[0021] The present invention provides a first body and a second body that are fixedly connected, and a rotatable erecting beam is provided on the first body to carry a horizontally placed aircraft, and under the action of the first pushing part, it rotates together with the aircraft until it maintains an erected state. After the erecting beam and the aircraft are erected, the bottom of the aircraft is located on the support plate on the second body. During the rotation of the erecting beam, the clamping ring assembly on the erecting beam embraces the aircraft to prevent the aircraft from deflecting or falling. A limiting plate is also provided on the erecting beam, and the aircraft is fixed to the limiting plate by a locking member to further maintain the stability of the aircraft during the erection process. During the erection and launching process of the aircraft, the erecting beam is horizontally placed on the first body, and the opening and closing buckle on the clamping ring assembly at this time is In the separated state, the aircraft is moved to the erecting beam, and the two opening and closing buckles are driven to approach each other by the second pushing part until the opening and closing buckles rotate and embrace the aircraft, and the bottom of the aircraft is fixed to the limit plate by the locking piece, and then the erecting beam is driven to rotate by the first pushing part until the aircraft is in a vertical state. At this time, the support plate is supported under the limit plate. Before launching the aircraft, the locking piece is removed, and the two opening and closing buckles are driven to separate by the second pushing part until the opening and closing buckles loosen the aircraft to a certain extent, and the distance between the opening and closing buckles is not enough for the aircraft to move out radially. At this time, the aircraft maintains a vertical state and can be ignited and launched at any time. Without the cooperation of a crane, the preparation for erecting and launching the aircraft can be completed quickly, safely and easily. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0023] Figure 1 A schematic diagram of the launch platform structure provided in an embodiment of the present application;

[0024] Figure 2 A schematic diagram of the first main structure provided in an embodiment of the present application;

[0025] Figure 3 A schematic diagram of a vertical beam structure provided in an embodiment of the present application;

[0026] Figure 4 A schematic diagram of a second main structure provided in an embodiment of the present application;

[0027] Figure 5 A side view of a second body provided in an embodiment of the present application;

[0028] Figure 6 A schematic diagram of the structure of a clamping ring assembly provided in an embodiment of the present application;

[0029] Figure 7 A schematic diagram of the structure of the limit assembly provided in the embodiment of the present application;

[0030] Figure 8 A cross-sectional view of a position limiting assembly provided in an embodiment of the present application;

[0031] Fig. 9 A partial cross-sectional view of a positioning sleeve provided in an embodiment of the present application;

[0032] Fig.10 A schematic diagram of the principle of the hydraulic system provided in the embodiment of the present application;

[0033] Fig.11 A schematic diagram of an erecting beam provided in an embodiment of the present application in an erecting state;

[0034] In the figure: 1, first main body; 11, vertical beam; 12, first push part; 13, mounting block; 14, concave cross beam; 15, reinforcement; 2, second main body; 21, support plate; 22, support ear; 3, snap ring assembly; 31, base; 32, opening and closing buckle; 33, second push part; 4, limit assembly; 41, limit plate; 42, locking member; 43, positioning sleeve; 44, locking rod; 45, top tightening surface; 46, gland; 47 , first positioning nut; 48, second positioning nut; 49, fine-tuning hole; 51, first through hole; 52, second through hole; 61, turntable; 62, slewing support; 63, reducer; 64, gear box; 71, support block; 72, adjusting screw; 73, adjusting leg; 74, rotating pair; 81, oil tank; 82, power pump; 83, filter; 84, electric heater; 91, guide plate; 92, guide surface; 100, aircraft. DETAILED DESCRIPTION

[0035] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. It should be noted that the description of these embodiments is used to help understand the present invention, but does not constitute a limitation of the present invention. The specific structures and functional details disclosed herein are only used to describe the exemplary embodiments of the present invention. However, the present invention can be embodied in many alternative forms, and it should not be understood that the present invention is limited to the embodiments set forth herein.

[0036] like Figure 1-11 As shown, a launching platform comprises a first body 1, a second body 2, a clamping ring assembly 3 and a limiting assembly 4, wherein:

[0037] A vertical beam 11 is movably provided on the first main body 1, and a first end portion of the vertical beam 11 is rotatably connected to the first main body 1. The length of the vertical beam 11 is adapted to the length of the aircraft 100. When the aircraft 100 is horizontally placed on the vertical beam 11, the center line of the vertical beam 11 in the length direction is arranged parallel to the center line of the aircraft 100 in the length direction.

[0038] A first pushing portion 12 for driving the erecting beam 11 to rotate to a vertical state is provided between the first main body 1 and the middle portion of the erecting beam 11. The first main body 1 has the ability to be stably placed in the launching area. Driven by the first pushing portion 12, the erecting beam 11 rotates around the portion connected to the first main body 1, thereby realizing the reciprocating switching of the erecting beam 11 between the horizontal state and the vertical state. When the erecting beam 11 is in a horizontal state, it is convenient to take the aircraft 100 out of the transportation device or the storage device. Without operating the aircraft 100, it can be directly hoisted onto the horizontal erecting beam 11. When the erecting beam 11 after the aircraft 100 is fixed is in a vertical state, the aircraft 100 is also in a vertical state, which is convenient for subsequent launching.

[0039] The second body 2 is fixedly connected to the first body 1 . A support plate 21 is provided on the second body 2 . When the erecting beam 11 rotates to a vertical state, the support plate 21 is used to be supported on the lower part of the aircraft 100 .

[0040] A plurality of ears 22 may be provided between the first body 1 and the second body 2 , and the ears 22 are used to quickly install and disassemble the first body 1 and the second body 2 , thereby improving the connection stability and avoiding a reduction in the structural stability of the first body 1 and the second body 2 .

[0041] It is worth noting that, since the overall mass of the aircraft 100 is relatively large, and the connection position between the first body 1 and the erecting beam 11 is close to the end of the erecting beam 11 and the side of the first body 1, even when the erecting beam 11 and the aircraft 100 are carried by the first body 1 in a horizontal state, the force on the aircraft 100 is uniform and relatively stable. In the process of moving the erecting beam 11 and the aircraft 100 to a vertical state, since the aircraft 100 follows the erecting beam 11 to rotate around the connection position between the erecting beam 11 and the first body 1, the aircraft 100 and the first body 1 are connected. 1 is regarded as a whole, the center of gravity of the whole will shift, and there is a risk that the aircraft 100 drives the first body 1 to overturn toward the connection between the first body 1 and the vertical beam 11. When the first body 1 is fixedly connected to the second body 2, and the second body 2 also has the basic conditions of being stably placed in the launching area, then after the first body 1 is fixedly connected to the second body 2, the aircraft 100, the first body 1, and the second body 2 are a new whole. When the aircraft 100 is in a vertical state, the center of gravity of the new whole is more stable, thereby improving safety.

[0042] The clamping ring assembly 3 includes a base 31, two opening and closing buckles 32 and two second pushing parts 33. The base 31 is fixedly connected to the vertical beam 11, and the opening and closing buckle 32 is rotatably arranged on the base 31. The second pushing part 33 is arranged between the base 31 and the opening and closing buckle 32, and drives the two opening and closing buckles 32 to move closer or farther away, so that the clamping ring assembly 3 embraces or releases the aircraft 100.

[0043] It is worth noting that when the two opening and closing buckles 32 are close to each other and embrace the aircraft 100, the two opening and closing buckles 32 and the base 31 can be together enclosed into a complete circle, and the movement of the aircraft 100 is restricted by the circle. It can also be arranged that when the two opening and closing buckles 32 are close to each other and embrace the aircraft 100, the inner walls of the two opening and closing buckles 32 are attached to the outer wall of the aircraft 100, and there is a first gap between the ends of the two opening and closing buckles 32, and the first gap is smaller than the diameter of the aircraft 100, thereby restricting the movement of the aircraft 100. In addition, when the two opening and closing buckles 32 move away from each other and release the aircraft 100, the distance between the ends of the two opening and closing buckles 32 is greater than the diameter of the aircraft 100, so that the aircraft 100 can be launched without hindrance.

[0044] The limiting assembly 4 includes a limiting plate 41 connected to the first end of the vertical beam 11 , and a locking member 42 is detachably provided on the limiting plate 41 , and the locking member 42 is used to fix the aircraft 100 on the limiting plate 41 .

[0045] The locking member 42 can be configured to pass through the limiting plate 41 at one end of the limiting plate 41 away from the aircraft 100 and then be connected to the flame-spraying end of the aircraft 100, so that the aircraft 100 can be fixedly connected to the limiting plate 41. During the rotation of the erecting beam 11 together with the aircraft 100, the aircraft 100 is kept from moving radially. In order to prevent the aircraft 100 from rotating axially and further improve the stability of the aircraft 100, a plurality of locking members 42 can be provided.

[0046] The working principle of this embodiment is as follows: by setting a first main body 1 and a second main body 2 that are fixedly connected, a rotatable erecting beam 11 is set on the first main body 1 to carry the horizontally placed aircraft 100, and under the action of the first pushing part 12, it rotates together with the aircraft 100 until it maintains an erected state. After the erecting beam 11 and the aircraft 100 are erected, the bottom of the aircraft 100 is located on the supporting plate 21 on the second main body 2. During the rotation of the erecting beam 11, the clamping ring assembly 3 on the erecting beam 11 embraces the aircraft 100 to prevent the aircraft 100 from deflecting or falling. A limiting plate 41 is also provided on the erecting beam 11, and the aircraft 100 is fixed to the limiting plate 41 by a locking member 42 to further maintain the stability of the aircraft 100 during the erection process. During the erection and launching process of the aircraft 100, the erecting beam 11 is horizontally placed on the supporting plate 21. The first main body 1 is on the first main body 1, and the opening and closing buckles 32 on the clamping ring assembly 3 are in a separated state at this time. The aircraft 100 is moved to the vertical beam 11, and the two opening and closing buckles 32 are driven to approach each other by the second pushing part 33 until the opening and closing buckles 32 rotate and embrace the aircraft 100. At the same time, the bottom of the aircraft 100 is fixed to the limiting plate 41 by the locking member 42, and then the vertical beam 11 is driven to rotate by the first pushing part 12 until the aircraft 100 is in a vertical state. At this time, the support plate 21 is supported under the limiting plate 41. Before the aircraft 100 is launched, the locking member 42 is removed, and the two opening and closing buckles 32 are driven to separate by the second pushing part 33 until the opening and closing buckles 32 loosen the aircraft 100 to a certain extent, and the distance between the opening and closing buckles 32 is less than the radial movement of the aircraft 100. At this time, the aircraft 100 remains in a vertical state and can be ignited and launched at any time.

[0047] Furthermore, on the basis of the above embodiment, the locking member 42 includes a positioning sleeve 43 and a locking rod 44, the positioning sleeve 43 is fixed on the limiting plate 41, and the positioning sleeve 43 is parallel to the center line of the limiting plate 41, the positioning sleeve 43 has a first space for accommodating the locking rod 44, and the first space has a tightening surface 45 for blocking the locking rod 44, one end of the locking rod 44 can pass through the positioning sleeve 43 and be used to be threadedly connected to the aircraft 100.

[0048] When the erecting beam 11 is placed horizontally on the first main body 1, the aircraft 100 is hoisted onto the erecting beam 11, and the locking rod 44 is inserted into the first space of the positioning sleeve 43 from the end of the limit plate 41 away from the aircraft 100. One end of the locking rod 44 passes through the positioning sleeve 43 and is threadedly connected to the aircraft 100. As the locking piece 42 is continuously tightened, the top tightening surface 45 in the first space is supported on the locking rod 44, so that the locking rod 44 fixes the aircraft 100 on the limit plate 41. After the aircraft 100 has been moved to a vertical state, the locking rod 44 needs to be removed, and the locking rod 44 is rotated to separate the locking rod 44 from the aircraft 100.

[0049] It is worth mentioning that in order to further improve the accuracy of the fixed position between the limit plate 41 and the aircraft 100, a positioning countersunk hole is provided on the positioning sleeve 43. The position and specification of the positioning countersunk hole are adapted to the end of the aircraft 100 close to the limit plate 41, that is, the flame-spraying end of the aircraft 100 has a convex portion, and the convex portion can extend into the positioning countersunk hole. During specific operation, the accuracy of the relative position of the aircraft 100 can be determined by the convex portion extending into the positioning countersunk hole, thereby improving the positioning of the aircraft 100 and facilitating the rapid and accurate installation process of the locking rod 44 and the aircraft 100.

[0050] Furthermore, on the basis of the above embodiment, the locking member 42 also includes a pressure cover 46, a first positioning nut 47 and a second positioning nut 48. The limiting plate 41 is provided with a fine-tuning hole 49 whose inner diameter is larger than the outer diameter of the positioning sleeve 43. The positioning sleeve 43 is arranged in the fine-tuning hole 49. The first positioning nut 47 and the second positioning nut 48 are threadedly connected to the positioning sleeve 43 and are respectively pressed on both sides of the limiting plate 41. The pressure cover 46 is detachably connected to the limiting plate 41. The pressure cover 46 has a first through hole 51 for the positioning sleeve 43 to pass through. The inner diameter of the first through hole 51 is smaller than the outer diameter of the positioning nut, so that the pressure cover 46 is pressed on the first positioning nut 47.

[0051] Since the overall mass of the aircraft 100 is relatively large, in order to avoid a certain degree of assembly error and under the premise of the assembly error, without relying on the re-movement and adjustment of the aircraft 100, the existing assembly error can be eliminated by the relative movement of the positioning sleeve 43 in the fine-tuning hole 49, thereby reducing the repeated adjustment operations on the aircraft 100, improving the operating efficiency and reducing the operating difficulty.

[0052] During specific operation, loosen the first positioning nut 47 or the second positioning nut 48 so that the distance between the first positioning nut 47 and the second positioning nut 48 is greater than the thickness of the limit plate 41. At this time, the positioning sleeve 43 can move radially in the fine-tuning hole 49 until the positioning sleeve 43 is aligned with the connecting position on the aircraft 100. Since the first nut is fixed by the pressure cover 46, tighten the second nut at this time until the first positioning nut 47 and the second positioning nut 48 are clamped on the end faces of both sides of the limit plate 41. At this time, the positioning sleeve 43 cannot move radially in the fine-tuning hole 49, and then the locking rod 44 is passed through the positioning sleeve 43 to connect the aircraft 100. The pressure cover 46 prevents the first positioning nut 47 from being lost, while further improving the stability of the positional relationship between the positioning sleeve 43 and the limit plate 41. It can also facilitate the disassembly and assembly of the first positioning nut 47 after removing the pressure cover 46.

[0053] Furthermore, on the basis of the above embodiment, a shooting direction adjustment component is also provided on the second main body 2, and the shooting direction adjustment component includes a turntable 61 and a slewing support 62, and the turntable 61 and the slewing support 62 are connected to each other through a reducer 63 and a gear box 64, so that the turntable 61 drives the slewing support 62 to rotate, and the slewing support 62 is fixedly connected to the support plate 21.

[0054] The operator can rotate the turntable 61 and drive the slewing support 62 to rotate under the transmission of the reducer 63 and the gear box 64, thereby driving the support plate 21 to rotate synchronously. When the support plate 21 carries the aircraft 100, the aircraft 100 can rotate along the axial direction of the aircraft 100 under the rotation of the supporting plate, thereby adjusting the shooting direction of the aircraft 100.

[0055] Furthermore, based on the above embodiment, a plurality of adjustment pairs are provided on the support plate 21, and the adjustment pairs include a threaded support block 71 and an adjustment screw 72, and the adjustment screw 72 is rotatably provided on the support plate 21, and the adjustment screw 72 rotates to drive the support block 71 to rise or fall.

[0056] By operating the adjustment screw 72 to rotate, the support block 71 rises or falls on the adjustment screw 72 relative to the support plate 21. The adjustment pair is located on the support plate 21. When the support plate 21 carries the aircraft 100, the adjustment pair is located between the support plate 21 and the aircraft 100. When the support block 71 rises or falls, the aircraft 100 is also lifted up or dropped. Since there are multiple adjustment pairs, the multiple support blocks 71 can be used to adjust to different position heights to slightly adjust the inclination state of the aircraft 100. The rotation adjustment of the slewing support 62 can also be used to accurately adjust the shooting direction of the aircraft 100. Correspondingly, when the flatness of the launch area is low, the state of the aircraft 100 can be corrected.

[0057] Further, based on the above embodiment, a plurality of adjusting legs 73 are respectively threadedly connected to the bottom of the first main body 1 and the bottom of the second main body 2 .

[0058] Since the first body 1 is a rigid part as a whole, in order to improve the overall stability of the first body 1 and the smoothness of the erection process of the aircraft 100, the rotation adjustment of multiple adjustment legs 73 can be used to make the first body 1 as a whole stably placed in the uneven launch area, thereby improving applicability and reducing the environmental conditions of the launch area.

[0059] Furthermore, based on the above embodiment, a plurality of mounting blocks 13 are provided on the erecting beam 11, each mounting block 13 is provided with a clamping ring assembly 3, and a plurality of concave cross beams 14 matching with the outer wall of the aircraft 100 are provided in the middle of the erecting beam 11.

[0060] Since the axial specification of the aircraft 100 is relatively long, in order to improve the stability of the erection process of the aircraft 100, multiple clamping ring assemblies 3 are provided to restrict the aircraft 100 at the same time, and each clamping ring assembly 3 is fixedly connected to the erection beam 11 through a mounting block 13, so that the clamping ring assembly 3 can be stably fixed while avoiding the fixed installation of the clamping ring assembly 3 from damaging the overall structural rigidity of the erection beam 11, and also improving the precise control of the installation position of the clamping ring assembly 3, avoiding the need to repeatedly position the clamping ring assembly 3 during the installation process of the clamping ring assembly 3, thereby improving efficiency.

[0061] The concave cross beam provided on the vertical beam 11 can, on the one hand, increase the bending resistance, and on the other hand, cooperate with the outer wall of the aircraft 100 to reduce the gap between the concave cross beam and the outer wall of the aircraft 100 when the aircraft 100 is placed on the vertical beam 11, thereby improving the stability of the aircraft 100 and preventing the aircraft 100 from shifting left and right or rotating radially.

[0062] In order to improve the structural strength of the erecting beam 11 , a reinforcing member 15 may be provided on the back side of the erecting beam 11 to improve the bending resistance of the erecting beam 11 .

[0063] Further, on the basis of the above embodiment, two ends of the first pushing portion 12 and two ends of the second pushing portion 33 are rotatably connected with a rotating pair 74 .

[0064] Since the length of the first pushing portion 12 will change during the process of driving the erecting beam 11 to rotate, the angle between the first pushing portion 12 and the first main body 1 and the erecting beam 11 will also continue to change. Therefore, in order to maintain the stability of the connection between the first pushing portion 12 and the first main body 1 and the erecting beam 11, it indicates that the first pushing portion 12 is bent, and the rotating pairs 74 arranged at both ends can maintain a stable connection relationship while rotating relative to the first pushing portion 12 to adapt to the continuously changing angle between the first pushing portion 12 and the first main body 1 and the erecting beam 11.

[0065] Further, on the basis of the above embodiment, the first pushing part 12 and the second pushing part 33 adopt hydraulic cylinders, the launching platform also includes a hydraulic system, the hydraulic system includes an oil tank 81, a power pump 82, a filter 83 and an electric heater 84, the oil tank 81 is provided with hydraulic oil, the power pump 82 is arranged between the oil tank 81 and the first pushing part 12 and the second pushing part 33, and is used to drive the hydraulic oil to flow to the first pushing part 12 and the second pushing part 33, the filter 83 is arranged at the oil outlet end and the oil return end of the oil tank 81, and the electric heater 84 is arranged in the oil tank 81 and is used to heat the hydraulic oil.

[0066] Hydraulic oil is installed in the oil tank 81. Under the action of the power pump 82, the hydraulic oil is injected into the first pushing part 12 or the second pushing part 33, so that the first pushing part 12 drives the erection beam 11 to rotate, or the second pushing part 33 drives the opening and closing buckle 32 to move. Since the windy and sandy environment is relatively common in the launching area, the filter 83 is used to filter impurities in the hydraulic oil, improve the driving accuracy of the first pushing part 12 and the second pushing part 33, and thereby improve the stability of the aircraft 100 during the restriction process and the accuracy of the aircraft 100 after erection.

[0067] In addition, the operating environment temperature of the erection and launching platform is -30℃~40℃. When the oil temperature is too low, the electric heater 84 works and heats the hydraulic oil so that the first pushing part 12 and the second pushing part 33 can be driven faster. A temperature sensor can also be set in the oil tank 81 to monitor the temperature of the hydraulic oil, and the control system can be cooperated to obtain and process the detection data of the temperature sensor to realize automatic control of the electric heater 84.

[0068] Furthermore, on the basis of the above-mentioned embodiment, a second through hole 52 is respectively provided on the limit plate 41 and the support plate 21, and the second through hole 52 is used to provide a channel for the tail flame of the aircraft 100 to pass through. A guide plate 91 is also provided on the second main body 2, and the guide plate 91 is located at the lower part of the second through hole 52 of the support plate 21. The guide plate 91 has two guide surfaces 92, and one end of the guide surface 92 is located under the second through hole 52 of the support plate 21, and the other end is located at the side of the second main body 2. When the aircraft 100 is ignited and launched, the tail flame generated during the launch of the aircraft 100 passes through the second through hole 52, and is then guided to both sides of the erection launch platform under the action of the two guide surfaces 92 on the guide plate 91, so as to prevent the tail flame from jumping back and reduce the erosion of the erection launch platform by the tail flame. Moreover, the guide plate 91 can be reused many times, and can be replaced separately when the guide plate 91 is severely ablated.

[0069] It should be understood that the terms first, second, etc. are only used to distinguish descriptions and should not be understood as indicating or suggesting relative importance. Although the terms first, second, etc. may be used herein to describe various units, these units should not be limited by these terms. These terms are only used to distinguish one unit from another unit. For example, the first unit may be referred to as the second unit, and similarly, the second unit may be referred to as the first unit without departing from the scope of the exemplary embodiments of the present invention.

[0070] It should be understood that the term "and / or" in this article is merely a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent three situations: A exists alone, B exists alone, and A and B exist at the same time. The term " / and" in this article describes another relationship between associated objects, indicating that two relationships may exist. For example, A / and B can represent two situations: A exists alone, and A and B exist alone. In addition, the character " / " in this article generally indicates that the previous and next associated objects are in an "or" relationship.

[0071] It should be understood that in the description of the present invention, the terms "upper", "vertical", "inside", "outside" and the like indicate orientations or positional relationships that are customarily placed when the disclosed product is used, or are orientations or positional relationships that are customarily understood by those skilled in the art. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0072] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "setting", "installation" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be a communication between the two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0073] The terms used herein are only used to describe specific embodiments and are not intended to limit the exemplary embodiments of the present invention. As used herein, the singular forms "a", "an", and "the" are intended to include the plural forms unless the context clearly indicates the opposite meaning. It should also be understood that the terms "include", "comprising", "including", and / or "comprising" when used herein specify the existence of the claimed features, integers, steps, operations, units, and / or components, and do not exclude the existence or increase of one or more other features, quantities, steps, operations, units, components, and / or their combinations.

[0074] Specific details are provided in the following description to facilitate a complete understanding of the exemplary embodiments. However, it should be understood by those of ordinary skill in the art that the exemplary embodiments may be implemented without these specific details. In other embodiments, well-known processes, structures, and techniques may not be shown in unnecessary detail to avoid making the exemplary embodiments unclear.

[0075] The above is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims

1. A launching platform, characterized in that: It includes: A first main body, on which a vertical beam is movably provided, a first end of the vertical beam is rotatably connected to the first main body, and a first pushing portion for driving the vertical beam to rotate to a vertical state is provided between the first main body and the middle portion of the vertical beam; A second body is fixedly connected to the first body, a support plate is provided on the second body, and when the erecting beam rotates to a vertical state, the support plate is used to be supported on the lower part of the aircraft, and a shooting direction adjustment component is provided on the second body, and the shooting direction adjustment component includes a turntable and a slewing support, and the turntable and the slewing support are connected to a gear box through a reducer so that the turntable drives the slewing support to rotate, and the slewing support is fixedly connected to the support plate; The clamping ring assembly comprises a base, two opening and closing buckles and two second pushing parts, wherein the base is fixedly connected to the vertical beam, the opening and closing buckle is rotatably arranged on the base, and the second pushing part is arranged between the base and the opening and closing buckle and drives the two opening and closing buckles to move closer or farther away, so that the clamping ring assembly embraces or releases the aircraft; The limiting assembly comprises a limiting plate connected to the first end of the vertical beam, and the limiting plate is detachably provided with a locking member, and the locking member is used to fix the aircraft on the limiting plate.

2. The launching platform according to claim 1, characterized in that: The locking member includes a positioning sleeve and a locking rod. The positioning sleeve is fixed on the limiting plate, and the positioning sleeve is parallel to the center line of the limiting plate. The positioning sleeve has a first space for accommodating the locking rod, and the first space has a tightening surface for blocking the locking rod. One end of the locking rod can pass through the positioning sleeve and be used to be threadedly connected to the aircraft.

3. The launching platform according to claim 2, characterized in that: The locking member also includes a pressure cover, a first positioning nut and a second positioning nut. The limiting plate is provided with a fine-tuning hole whose inner diameter is larger than the outer diameter of the positioning sleeve. The positioning sleeve is arranged in the fine-tuning hole. The first positioning nut and the second positioning nut are threadedly connected to the positioning sleeve and are respectively pressed on both sides of the limiting plate. The pressure cover is detachably connected to the limiting plate. The pressure cover has a first through hole for the positioning sleeve to pass through. The inner diameter of the first through hole is smaller than the outer diameter of the positioning nut so that the pressure cover is pressed on the first positioning nut.

4. The launching platform according to claim 1, characterized in that: The support plate is provided with a plurality of adjustment pairs, each of which comprises a support block and an adjustment screw connected in threaded connection. The adjustment screw is rotatably provided on the support plate, and the adjustment screw rotates to drive the support block to rise or fall.

5. The launching platform according to claim 1, characterized in that: The bottom of the first main body and the bottom of the second main body are respectively threadedly connected with a plurality of adjustment legs.

6. The launching platform according to claim 1, characterized in that: The erecting beam is provided with a plurality of mounting blocks, each mounting block is provided with a clamping ring assembly, and the middle part of the erecting beam is provided with a plurality of concave cross beams matched with the outer side wall of the aircraft.

7. The launching platform according to claim 1, characterized in that: Two ends of the first pushing portion and two ends of the second pushing portion are rotatably connected to a rotating pair respectively.

8. The launching platform according to claim 7, characterized in that: The first pushing part and the second pushing part adopt hydraulic cylinders, and the launching platform also includes a hydraulic system, which includes an oil tank, a power pump, a filter and an electric heater. Hydraulic oil is arranged in the oil tank, and the power pump is arranged between the oil tank and the first pushing part and the second pushing part, and is used to drive the hydraulic oil to flow to the first pushing part and the second pushing part. The filter is arranged at the oil outlet end and the oil return end of the oil tank, and the electric heater is arranged in the oil tank and is used to heat the hydraulic oil.

9. The launching platform according to claim 1, characterized in that: The limiting plate and the supporting plate are respectively provided with a second through hole, and the second through hole is used to provide a channel for the tail flame of the aircraft to pass through. The second body is also provided with a guide plate, and the guide plate is located at the lower part of the second through hole. The guide plate has two guide surfaces, one end of the guide surface is located below the second through hole, and the other end is located at the side of the second body.

Images