Rocket transport and erect launch integrated pylon

Abstract

The rocket transportation and erecting launch integrated bracket in the field of rocket transportation and launch is used for realizing the integrated design of transportation, erecting and launching of small rockets, and comprises a transportation unit, an erecting and launching unit and a hydraulic system, the erecting and launching unit comprises an erecting frame and an integrated moving bracket for bearing a rocket body which is slidably installed on the erecting frame, and a launching base is fixedly installed on the hinged end of the erecting frame; the hydraulic system drives the erecting and launching unit to rotate around the hinged end of the transportation unit. The rocket transfer, attitude adjustment and erecting support whole process operation are realized by the single bracket bearing, the ground supporting equipment is greatly simplified, the frequent equipment docking structure is cancelled, the occupied space and the whole machine weight of the complete set of equipment are effectively reduced, the launch preparation period is shortened, and the launch support cost is effectively reduced; the mobility is stronger, and the use scene of mobile deployment and rapid deployment in complex field can be adapted.

Description

Technical Field

[0001] This invention relates to the field of rocket transport, erection, and launch technology, specifically to an integrated support for rocket transport, erection, and launch. Background Technology

[0002] In recent years, the application scenarios of small rockets have been continuously expanding, demonstrating significant practical value in fields such as commercial aerospace, military target testing, space scientific research, and meteorological observation. In the commercial aerospace sector, numerous companies are deploying small satellite constellations to achieve internet communication, high-precision positioning, and IoT services. The lightweight nature of small satellites places high demands on the flexibility and economy of launch vehicles. Small rockets can precisely deploy multiple satellites in a single launch mode, effectively improving launch efficiency and reducing launch costs. In the military field, small rockets can serve as target rockets and near-field space exploration vehicles, offering advantages such as flexible deployment, short preparation time, and strong site adaptability, meeting the needs of mobile launches and rapid testing missions in the field. In scientific research and meteorology, small rockets are suitable for missions such as near-space environment exploration, atmospheric parameter sampling, and astronomical observation experiments. Their small structural size and light overall weight make them suitable for use in simple field launch sites.

[0003] The Long March 6 is my country's first small liquid-fueled launch vehicle to adopt a "three-horizontal" test and launch mode, namely, horizontal integrated testing, horizontal integrated satellite-rocket docking, and horizontal integrated transportation, erection, and launch. Currently, under the three-horizontal test and launch mode, rockets mostly employ independent designs for transportation, erection, and launch systems; however, for small launch vehicles, achieving integrated design of transportation, erection, and launch is an important development trend for future high-efficiency launch technology.

[0004] Patent 201811565362.X discloses a multi-functional rocket transport and erection vehicle, belonging to the technical field of ground transport and launch devices for launch vehicles. One end of the erection arm is hinged to the rear of the transport vehicle, and the other end is equipped with a lifting adjustment device. This device allows for horizontal, vertical, and lateral height adjustment of the booster rocket after the arm is erected. A clamping arm adjustment device is installed on the erection arm to lock and release the booster rocket, and it also allows for horizontal, vertical, and lateral adjustment. The lifting adjustment device has three pulleys: a movable pulley, a movable pulley group, and a fixed pulley group. The movable pulley is located at the movable end of a hydraulic servo cylinder, the fixed pulley group is fixed to the forward and backward moving device in the horizontal adjustment device, and the movable pulley group is located at the top of the lifting device. This device requires lifting tools to adjust the rocket's attitude, resulting in a complex and bulky structure. Therefore, how to simplify the ground-based supporting equipment and achieve an integrated rocket transport and erection design is a problem that needs to be solved. Summary of the Invention

[0005] In order to solve the problems in the background art, the present invention provides a simplified design for an integrated rocket transport, erection and launch bracket, so as to realize the integrated design of transport, erection and launch of small rockets.

[0006] The rocket transport, erection, and launch integrated bracket of the present invention includes a transport unit, and is characterized in that it also includes an erection and launch unit and a hydraulic system. One end of the erection and launch unit is hinged to one end of the transport unit. The erection and launch unit includes an erection frame and an integral movable bracket for supporting the rocket body that is slidably mounted on the erection frame. A launch base is also fixedly installed on one side of the hinged end of the erection frame. The hydraulic system drives the erection and launch unit to rotate around the hinged end of the transport unit.

[0007] As a further limitation of the present invention, the integral movable bracket includes two parallel concave square tubes and at least two shock-absorbing rotating brackets. The shock-absorbing rotating brackets are fixed across the two concave square tubes. The concave square tubes have a downward elongated opening. The concave square tubes can accommodate a rotating wheel. The rotating wheel is mounted on a rotating wheel fixing plate, and the rotating wheel fixing plate is fixed to the erecting frame.

[0008] As a further limitation of the present invention, the shock-absorbing rotating bracket includes a base with an arc-shaped bearing surface. The center of the arc-shaped bearing surface is recessed downward to form an arc-shaped groove. A side groove is provided on the side wall of the arc-shaped groove. An arc-shaped plate is embedded in the side groove. An airbag is fixed on the upper surface of the arc-shaped plate. A through hole is provided on the arc-shaped groove. The airbag is connected to an inflation tube. The inflation tube passes through the through hole and is connected to an air source. The air source is fixed on the integral movable bracket and moves with the integral movable bracket.

[0009] As a further limitation of the present invention, teeth are uniformly fixed on the lower surface of the arc-shaped plates of at least two of the shock-absorbing rotating brackets, and a gear that meshes with the teeth is installed in the base; the gear is driven by a motor, the motor is located outside the base and fixed on the integral movable bracket and moves with the integral movable bracket, and the motor drive shaft passes through the side wall of the base and is connected to the gear in the base.

[0010] As a further limitation of the present invention, the airbag is an elongated arc-shaped flexible bladder, and multiple transverse pressure seams are provided on the surface of the bladder to divide the airbag into multiple inflatable chambers; when the airbag is fully inflated, the upper surface of the airbag is higher than the arc-shaped bearing surface, and when the airbag is deflated, the upper surface of the airbag is lower than the arc-shaped bearing surface.

[0011] As a further limitation of the present invention, the integral mobile bracket is also equipped with a mobile power supply for supplying power to the airbag and the motor.

[0012] As a further limitation of the present invention, the erection frame of the launch unit is a truss structure consisting of several axial stringers, several transverse stringers, and several vertical stringers fixedly connected; the axial stringers are parallel to the central axis of the rocket, and the axial stringers include two upper axial stringers and two lower axial stringers; the transverse stringers are vertically fixed between the two lower axial stringers; the vertical stringers are used to connect the upper and lower axial stringers on the same side, and the vertical stringers are arranged vertically or obliquely between the upper and lower axial stringers.

[0013] As a further limitation of the present invention, each of the upper axial stringers is an L-shaped profile used to fix the vertical stringers; the lower axial stringers are T-shaped profiles or are formed by fixing two L-shaped profiles back to back to form a T-shaped structure, the outer side of the lower axial stringers is used to fix the vertical stringers, and the inner side of the lower axial stringers is used to install the wheels that cooperate with the integral movable bracket.

[0014] As a further limitation of the present invention, the hydraulic system includes an oil tank, a low-pressure high-flow pump, a high-pressure low-flow pump, a reversing valve, and a hydraulic cylinder. The low-pressure high-flow pump and the high-pressure low-flow pump are connected in parallel and supply oil by merging. The rated operating pressure range of the low-pressure high-flow pump is 0-7 MPa, and the rated output flow rate is 25-35 L / min. The rated operating pressure range of the high-pressure low-flow pump is 0-22 MPa, and the rated output flow rate is 4-8 L / min. The low-pressure high-flow pump is matched with a two-stage stepped linear unloading relief valve. The two-stage stepped linear unloading relief valve uses 4 MPa and 7 MPa as the working condition boundary. When the system load pressure is less than or equal to 4 MPa, the high-pressure and low-pressure pumps maintain a combined high-flow oil supply. When the load pressure is greater than 4 MPa but less than 7 MPa, the output flow rate of the low-pressure high-flow pump decreases linearly with the increase of pressure. When the load pressure is greater than or equal to a set high-pressure threshold of 7 MPa, the low-pressure high-flow pump is completely unloaded at zero pressure, and only the high-pressure low-flow pump independently maintains pressure and supplies oil. As a further limitation of the present invention, the transport unit is provided with a counterweight to prevent the rocket from overturning.

[0015] The advantages of this invention are: (1) This invention adopts an integrated structure with the transport unit and the erection and launch unit hinged together, breaking through the traditional structure of separate arrangement of transport, erection and launch equipment. The rocket transfer, attitude adjustment and erection support are carried by a single frame, greatly simplifying the ground supporting equipment and eliminating the frequent equipment docking structure. The overall structure is compact and highly integrated, effectively reducing the space occupied by the whole set of equipment and the weight of the whole machine, shortening the launch preparation cycle and effectively reducing the launch support cost. It is more mobile and can be adapted to the use scenarios of mobile deployment and rapid deployment in complex field sites, weakening the dependence on fixed launch sites, further broadening the launch application scenarios of small launch vehicles, and meeting the development needs of commercial aerospace and emergency aerospace missions.

[0016] (2) The present invention is equipped with an integral movable bracket that can slide as a whole. The integral movable bracket can slide as a whole through the cooperation of the built-in rotating wheel and the concave square tube, so as to realize the rapid mounting and docking of the rocket without hoisting, docking and transfer equipment assistance, simplify the equipment docking structure, reduce the supporting tooling, reduce docking deviation and assembly error from the structural level, and improve the positioning accuracy and operation efficiency of the rocket body; at the same time, the inverted structure of the concave square tube can prevent the rocket from overturning during the erection process.

[0017] (3) This invention integrates an adaptive shock-absorbing rotating bracket structure, which achieves multiple structural functions of rocket flexible support, attitude fine-tuning, and transportation shock absorption through a composite structure of an arc-shaped base bearing surface, an internal gear tooth transmission mechanism, and an inflatable flexible airbag. The shock-absorbing rotating bracket adopts a detachable base structure, which facilitates the disassembly and maintenance of the internal transmission structure and shock absorption structure; the multi-cavity segmented structure of the airbag can adaptively fit different rocket body diameters, and the flexible bearing structure replaces the traditional rigid support structure, effectively avoiding local stress concentration of the rocket body caused by transportation vibration and erection impact, thus providing good protection for the rocket body structure; the gear tooth meshing transmission structure has high transmission accuracy and good self-locking performance, which can stably achieve circumferential angle fine-tuning of the rocket body and meet the attitude requirements of maintenance and alignment operations.

[0018] (4) The present invention is equipped with a dual-pump stepped linear unloading hydraulic drive structure, which is different from the traditional single-stage pressure step unloading hydraulic circuit. By adding a linear flow attenuation range of 4MPa to 7MPa, the flow rate of the low-pressure pump is continuously and gradually adjusted with the load pressure. From the hydraulic power structure level, the sudden flow and pressure shock during the rapid advance in the early stage of erection and the pressure switching when the load increases are eliminated, making the erection and rotation process smoother. It significantly reduces the alternating impact load on the frame, hinge pair and sliding structure, reduces the vibration and fatigue loss of the whole machine structure, and improves the stability and structural durability of the whole set of equipment. Attached Figure Description

[0019] Figure 1 : A schematic diagram of the overall structure of the present invention; Figure 2 : A schematic diagram of the erecting frame structure of the present invention; Figure 3 : Schematic diagram of the hinge structure of the present invention; Figure 4 : Schematic diagram of the integral movable bracket structure of the present invention; Figure 5 : Figure 4 A schematic diagram showing the connection between the central rotating wheel and the concave square tube; Figure 6 Schematic diagram of the shock-absorbing rotating bracket structure; Figure 7 : A schematic diagram of the fit between the arc-shaped plate and the gear of the present invention; Figure 8 : Schematic diagram of the airbag structure of the present invention; Figure 9 : A schematic diagram of the transportation status of the present invention; Figure 10 : Schematic diagram of the erection and launch state of the present invention.

[0020] The components include: 100, transport unit; 101, transport bracket; 102, lifting support leg; 103, moving wheel; 104, counterweight; 105, hinge shaft; 107, movable hinge seat; 108, double-hinged fixed hinge seat; 200, erection and launch unit; 201, erection frame; 2011, upper axial stringer; 2012, lower axial stringer; 2013, transverse stringer; 2014, vertical stringer; 2 02. Launch base; 203. Shock-absorbing rotating bracket; 2031. Arc-shaped groove; 2032. Side groove; 2033. Through hole; 2034. Arc-shaped plate; 2035. Gear; 2036. Airbag; 2037. Concave square tube; 2038. Rotating wheel; 2039. Rotating wheel fixing plate; 20301. Arc-shaped bearing surface; 20302. Base side wall; 204. Support tube; 300. Hydraulic system. Detailed Implementation

[0021] This invention proposes an integrated support for rocket transport, erection, and launch. The principle and working steps of this invention will be described in detail below with reference to the accompanying drawings. For ease of description, [the following text is incomplete and requires further context]. Figure 9 , Figure 10 The left end is the front end, and the right end is the back end.

[0022] like Figure 1 As shown, the present invention includes a transport unit 100, an erection and launch unit 200, and a hydraulic system 300. One end of the erection and launch unit 200 is hinged to one end of the transport unit 100. The erection and launch unit 200 includes an erection frame 201 and an integral movable bracket for supporting the rocket body that is slidably mounted on the erection frame 201. A launch base 202 is also fixedly installed on one side of the hinged end of the erection frame 201. The hydraulic system 300 drives the erection and launch unit 200 to rotate around the hinged end of the transport unit 100 to achieve switching between horizontal transport state and vertical launch state.

[0023] Specifically, the transport unit 100 uses the transport bracket 101 as its basic load-bearing structure, with four lifting support legs 102 and four casters 103 at the bottom. The main body of the transport bracket 101 is welded from 40mm*40mm*5mm aluminum alloy square tubing. Special locations, such as the lugs connecting the hydraulic rods of the hydraulic system 300, use 80mm*80mm*5mm square tubing. The maximum force at the lugs is approximately 1.3t, and the material is low-alloy high-strength structural steel Q345B. The casters 103 are swivel casters with foot brakes. The lifting support legs 102 are mechanical hand-cranked lifting legs with a maximum load capacity of 2t. Preferably, a tray is welded to the front bottom of the transport bracket 101 for placing a counterweight 104. The counterweight 104 adopts a modular design, and its weight is adjusted according to the rocket's weight and erection height, with a total adjustable weight range of 150kg to 200kg to prevent the rocket from tipping over during erection.

[0024] like Figure 2 The erection frame 201 of the launch erection unit 200 is a truss structure consisting of several axial stringers, several transverse stringers 2013, and several vertical stringers 2014 fixedly connected, preferably made of aluminum alloy. The axial stringers are parallel to the central axis of the rocket and include two upper axial stringers 2011 and two lower axial stringers 2012. The transverse stringers 2013 are vertically fixed between the two lower axial stringers 2012, providing support for the integral movable bracket. The vertical stringers 2014 are used to connect the upper and lower axial stringers on the same side. The vertical stringers 2014 are arranged vertically or obliquely between the upper and lower axial stringers to improve the overall stability of the erection frame 201. Each upper axial stringer 2011 is an L-shaped profile used to fix the vertical stringer 2014; the lower axial stringer 2012 is a T-shaped profile or two L-shaped profiles fixed back-to-back to form a T-shaped structure. The outer side of the lower axial stringer 2012 is used to fix the vertical stringer 2014, and the inner side of the lower axial stringer 2012 is used to install the rotating wheel 2038 that cooperates with the integral movable bracket. Preferably, each axial stringer is divided into front and rear sections, including a front axial stringer and a rear axial stringer, to facilitate the disassembly and maintenance of the rocket. Preferably, the lower axial stringer 2012 of the erecting frame 201 extends from the hinge end to the launch end, and its right end is longer than the right end of the transport bracket 101, forming a cantilever section, that is, the rear end of the lower axial stringer 2012 extends beyond the length range of the transport bracket 101, avoiding interference with the transport unit 100 during the erection process.

[0025] A launch base 202 is fixedly installed at the rear end of the erecting frame 201. Specifically, the launch base 202 is installed on the rear end of the erecting frame 201 via a support tube 204, and the bearing surface of the launch base 202 is perpendicular to the length direction of the erecting frame 201. The launch base 202 not only supports the rocket but also limits the sliding of the integral movable bracket on the erecting frame 201. The launch base 202 consists of two symmetrical arc-shaped support pieces arranged opposite each other, providing support for the rocket placed on it. The arc-shaped space reserved between the two launch base pieces 202 serves as a maintenance and inspection space for internal observation and component disassembly and maintenance. The rocket tube wall rests only on the support surface of the arc-shaped support pieces and does not fall into the arc-shaped space.

[0026] like Figure 3 The rear end of the transport bracket 101 is fixed with two U-shaped double-hinged lug fixed hinge seats 108. The rear end of the erecting frame 201 is fixed with a movable hinge seat 107 that matches the double-hinged lug fixed hinge seats 108. One end of the movable hinge seat 107 is welded to the bottom of the erecting frame 201, and the other end is inserted into the U-shaped opening of the double-hinged lug fixed hinge seat 108. The two form a coaxial rotary pair through the hinge shaft 105, constituting the hinge structure of the present invention. This allows the erecting and launching unit 200 to rotate relative to the transport unit 100 around the axis of the hinge shaft 105, realizing the switching between transport and erection postures. A triangular support plate is welded to the bottom of the double-hinged lug fixed hinge seat 108 to improve the overall strength. This double-hinged lug structure can evenly distribute the shear load during the erection and launch process, avoiding the problem of uneven load deformation that is prone to occur in single-point hinges. The hinge shaft 105 is made of Q345B material, and the surface is treated with QPQ or hard chrome plating.

[0027] like Figure 4 The integrated mobile support includes two parallel concave square tubes 2037 and at least two shock-absorbing rotating brackets 203. The shock-absorbing rotating brackets 203 are fixed across the two concave square tubes 2037. The shock-absorbing rotating brackets 203 not only provide shock absorption during transportation but also connect the two concave square tubes 2037, making them a single unit. The installation position of the shock-absorbing rotating brackets 203 can be rationally set according to the rocket's weight distribution. The shock-absorbing rotating brackets 203 can be made of wood, plastic, aluminum alloy, or other materials. Figure 5The concave square tube 2037 is made by opening a long strip opening in the side wall of a conventional square tube, with the long strip opening facing downwards. The concave square tube 2037 is parallel to the upper axial stringer 2011. The concave square tube 2037 can accommodate a rotating wheel 2038, which is mounted on a rotating wheel fixing plate 2039. The rotating wheel fixing plate 2039 is an L-shaped metal plate, with one side of two rotating wheel fixing plates 2039 welded back-to-back, and the other side of the two rotating wheel fixing plates 2039 fixedly mounted on the upper surface of the lower axial stringer 2012. The concave square tube 2037 and the shock-absorbing rotating bracket 203, as a whole, can slide on the lower axial stringer 2012. At the previous station, the rocket is placed on the integrated movable bracket. By pushing the integrated movable bracket, the rocket can be transferred from the previous station to the erecting frame 201 without lifting tools.

[0028] Before transport, the rocket is placed on an integrated mobile carrier. Pushing the integrated mobile carrier allows the rocket to be transferred from the previous position to the erecting frame 201. The rocket's outriggers can be installed at any time thereafter. During transport, the erecting frame 201 is horizontally stacked on top of the transport carrier 101, and the launch base 202 limits the rocket's front and rear positions. During erection, the hydraulic system 300 drives the erecting launch unit 200 to rotate slowly around the hinged pivot 105. The rocket is raised synchronously with the erecting frame 201. The rotating wheel 2038 is housed in the concave square tube 2037, which limits the rocket's radial direction and prevents the rocket from detaching from the erecting frame 201 and tipping over during erection. When the erecting frame 201 rotates to a vertical position, the rocket stands vertically on the launch base 202. The attitude of the rocket's outriggers is adjusted to transfer the rocket's weight from the launch base 202 to the outriggers, maintaining the rocket's launch attitude.

[0029] like Figures 6-7The shock-absorbing rotating bracket 203 includes a base with an arc-shaped bearing surface 20301. The center of the arc-shaped bearing surface 20301 is recessed downward to form an arc-shaped groove 2031. A side groove 2032 is provided on the side wall of the arc-shaped groove 2031. An arc-shaped plate 2034 is embedded in the side groove 2032. An airbag 2036 is fixed on the upper surface of the arc-shaped plate 2034. A through hole 2033 is provided on the arc-shaped groove 2031. The airbag 2036 is connected to an inflation tube, which passes through the through hole 2033 and is connected to an air source. The air source is fixed on the integral movable bracket and moves with the integral movable bracket. Teeth are evenly fixed on the lower surface of the arc-shaped plate 2034 of at least two shock-absorbing rotating brackets 203, and gears 2035 that mesh with the teeth are installed in the base. The gear 2035 is driven by a motor located outside the base and fixed to an integral movable bracket, moving with the integral movable bracket. The integral movable bracket is also equipped with a mobile power supply for powering the airbag 2036 and the motor. The motor drive shaft passes through the side wall 20302 of the base and connects to the gear 2035 inside the base. The motor drives the gear 2035 to rotate, thereby driving the arc plate 2034 to slide along the arc groove 2031.

[0030] like Figure 8 The airbag 2036 is an elongated, arc-shaped flexible bladder with multiple transverse seams on its surface, dividing it into several interconnected inflatable chambers. When fully inflated, the upper surface of the airbag 2036 is higher than the arc-shaped support surface 20301; when deflated, its upper surface is lower than the arc-shaped support surface 20301. To facilitate the installation and maintenance of the arc-shaped plate 2034 and gear 2035 within the base, the base sidewall 20302 is an independent, removable shelf. When inflated, the airbag 2036 provides elastic cushioning, shock absorption, and pressure resistance. After assembly, it fits snugly against the inner arc surface of the arc-shaped plate 2034, providing flexible clamping and shock absorption protection for the rocket placed on it. The gear 2035's toothed transmission structure below allows for adjustment of the rocket's angle rotation. Different inflation volumes of the airbag 2036 can accommodate rockets of different diameters.

[0031] The hydraulic system 300 uses a bidirectional hydraulic rod with a maximum thrust of 2.2t, a maximum pull of 1.3t, and a stroke range of 1240mm to 2290mm. The piping connection uses a direct hose connection, and the surface is treated with QPQ or hard chrome plating. One end of the hydraulic rod is hinged to the middle of the erecting frame 201, and the other end is hinged to the front end of the transport bracket 101. The hydraulic system 300 includes an oil tank, a low-pressure high-flow pump, a high-pressure low-flow pump, a reversing valve, and a hydraulic cylinder. The low-pressure high-flow pump and the high-pressure low-flow pump are connected in parallel and can combine for oil supply. The rated operating pressure range of the low-pressure high-flow pump is 0–7MPa, and the rated output flow rate is 25–35L / min. The rated operating pressure range of the high-pressure low-flow pump is 0–22MPa, and the rated output flow rate is 4–8L / min. The low-pressure high-flow pump is matched with a two-stage stepped linear unloading relief valve. The stepped linear unloading relief valve uses 4MPa and 7MPa as the operating condition boundaries. When the system load pressure is less than or equal to 4MPa, the high and low pressure dual pumps maintain a combined flow and large flow rate for oil supply. When the load pressure is greater than 4MPa but less than 7MPa, the output flow rate of the low-pressure high-flow pump continuously and linearly decreases as the pressure increases. When the load pressure is greater than or equal to the set high-pressure threshold of 7MPa, the low-pressure high-flow pump is completely unloaded at zero pressure, and only the high-pressure low-flow pump independently maintains pressure and supplies oil. This achieves a seamless transition between operating conditions without sudden pressure changes or flow rate jumps. Preferably, the two-stage stepped linear unloading relief valve adopts a gradual throttling pressure regulating structure, making the pump inlet pressure and flow rate exhibit continuous gradual changes, eliminating the pressure jumps and system vibrations caused by the opening and closing of traditional single-stage relief valves.

[0032] Estimated weight: Transport unit 100 (including hydraulic system 300): 75kg; Erection and launch unit 200: 60kg; Rocket: 140kg; Additional counterweight required: 150kg~200kg.

[0033] The usage process of this invention is as follows: S1. On the workbench of the previous station, there are also casters 2038 that match the concave square tube 2037. The entire invention is moved to the front of the workbench of the previous station by the moving wheels 103 of the transport unit 100. The lifting support legs 102 are adjusted to adjust the transport bracket 101 to the specified height and level it. The integral moving bracket is pushed onto the workbench of the previous station, the rocket is placed on it, and the integral moving bracket is pushed. Without the need for hoisting tools, the rocket can be transferred from the previous station to the erecting frame 201. Figure 9 .

[0034] S2, the inflatable airbag 2036, the retracting lifting support leg 102, and the ground contact wheels 103 allow for transport by towing vehicle. After the device reaches the designated launch position, the lifting support leg 102 extends and supports the ground. Before erection, appropriate maintenance work is performed on the rocket, including support leg installation, airtightness checks, and equipment replacement. If the rocket's attitude is unsuitable for operation, the motor is started to adjust the rocket's angle.

[0035] S3. After maintenance is completed, start the hydraulic system 300 to slowly rotate the launch erector 200 around the hinge shaft 105. As the rocket gradually rises to a vertical position along with the launch erector frame 201, ... Figure 10 .

[0036] S4. Adjust the lifting support leg 102 to lower the transport bracket 101 so that the rocket support leg touches the ground, and then wait for the rocket to ignite and launch.

[0037] The process of delegating is the reverse of the process of establishing. I will not elaborate further.

[0038] In the description of this application, the terms "up," "down," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate directions or positional relationships based on the exemplary directions or positional relationships shown in the accompanying drawings. They are used to facilitate the description or simplification of the embodiments of this application and are not intended to indicate or imply that the device or component referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0039] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0040] In the description of this specification, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0041] The above description is only a partial implementation of this application. It should be noted that for those skilled in the art, other similar implementation methods based on the technical concept of this application, without departing from the technical concept of this application, also fall within the protection scope of the embodiments of this application.

Claims

1. Rocket transport and launch integration cradle, comprising a transport unit (100), characterized in that, It also includes an erecting and launching unit (200) and a hydraulic system (300). One end of the erecting and launching unit (200) is hinged to one end of the transport unit (100). The erecting and launching unit (200) includes an erecting frame (201) and an integral movable bracket for carrying the rocket body, which is slidably mounted on the erecting frame (201). A launch base (202) is also fixedly installed on one side of the hinge end of the erecting frame (201). The hydraulic system (300) drives the erecting and launching unit (200) to rotate around the hinge of the transport unit (100). The connecting end rotates; the integral movable bracket includes two parallel concave square tubes (2037) and at least two shock-absorbing rotating brackets (203). The shock-absorbing rotating brackets (203) are fixed across the two concave square tubes (2037). The concave square tubes (2037) have a downward elongated opening. The concave square tubes (2037) can accommodate a rotating wheel (2038). The rotating wheel (2038) is mounted on a rotating wheel fixing plate (2039). The rotating wheel fixing plate (2039) is fixed on the erecting frame (201).

2. The rocket-transport erect-launch-integrated cradle of claim 1, wherein, The shock-absorbing rotating bracket (203) includes a base with an arc-shaped bearing surface (20301). The arc-shaped bearing surface (20301) is recessed downward in the middle to form an arc-shaped groove (2031). The side wall of the arc-shaped groove (2031) is provided with a side groove (2032). An arc-shaped plate (2034) is embedded in the side groove (2032). An airbag (2036) is fixed on the upper surface of the arc-shaped plate (2034). A through hole (2033) is provided on the arc-shaped groove (2031). The airbag (2036) is connected to an inflation tube. The inflation tube passes through the through hole (2033) and is connected to an air source. The air source is fixed on the integral movable bracket and moves with the integral movable bracket.

3. The rocket-transport erect-launch-integrated cradle of claim 2, wherein, At least two of the shock-absorbing rotating brackets (203) have teeth evenly fixed on the lower surface of the arc plate (2034). A gear (2035) that meshes with the teeth is installed in the base. The gear (2035) is driven by a motor. The motor is located outside the base and fixed on the integral movable bracket. It moves with the integral movable bracket. The motor drive shaft passes through the side wall (20302) of the base and is connected to the gear (2035) in the base.

4. The rocket-transport erect-launch-integrated cradle of claim 3, wherein, The airbag (2036) is an elongated arc-shaped flexible bladder with multiple transverse pressure seams on its surface, dividing the airbag (2036) into multiple inflatable chambers. When the airbag (2036) is fully inflated, the upper surface of the airbag (2036) is higher than the arc-shaped support surface (20301), and when the airbag (2036) is deflated, the upper surface of the airbag (2036) is lower than the arc-shaped support surface (20301).

5. The rocket-transported vertical-launch monobloc launcher of Claim 4, wherein, The integrated mobile bracket is also equipped with a mobile power supply for powering the airbag (2036) and the motor.

6. The integrated launch pad for rocket transportation and erection according to any of claims 1-5, characterized in that, The erection frame (201) of the launch unit (200) is a truss structure consisting of several axial stringers, several transverse stringers (2013) and several vertical stringers (2014) fixedly connected. The axial stringers are parallel to the central axis of the rocket and include two upper axial stringers (2011) and two lower axial stringers (2012). The transverse stringers (2013) are vertically fixed between the two lower axial stringers (2012). The vertical stringers (2014) are used to connect the upper and lower axial stringers on the same side and are arranged vertically or obliquely between the upper and lower axial stringers.

7. The rocket-transported vertical-launch monobloc launcher of Claim 6, wherein, Each of the upper axial stringers (2011) is an L-shaped profile used to fix the vertical stringers (2014); the lower axial stringer (2012) is a T-shaped profile or is formed by fixing two L-shaped profiles back to back to form a T-shaped structure. The outer side of the lower axial stringer (2012) is used to fix the vertical stringers (2014), and the inner side of the lower axial stringer (2012) is used to install the wheels (2038) that cooperate with the integral movable bracket.

8. The integrated launch pad for rocket transportation and erection according to any of claims 1-5, characterized in that, The hydraulic system (300) includes an oil tank, a low-pressure high-flow pump, a high-pressure low-flow pump, a directional valve, and a hydraulic cylinder. The low-pressure high-flow pump and the high-pressure low-flow pump are connected in parallel and supply oil together. The rated working pressure range of the low-pressure high-flow pump is 0-7 MPa, and the rated output flow is 25-35 L / min. The rated working pressure range of the high-pressure low-flow pump is 0-22 MPa, and the rated output flow is 4-8 L / min. The low-pressure high-flow pump is matched with a two-stage stepped linear unloading relief valve. The two-stage stepped linear unloading relief valve uses 4 MPa and 7 MPa as the working condition boundary. When the system load pressure is less than or equal to 4 MPa, the high-pressure and low-pressure pumps maintain a combined high-flow oil supply. When the load pressure is greater than 4 MPa and less than 7 MPa, the output flow of the low-pressure high-flow pump decreases linearly with the increase of pressure. When the load pressure is greater than or equal to 7 MPa and a high-pressure threshold is set, the low-pressure high-flow pump is completely unloaded at zero pressure, and only the high-pressure low-flow pump independently maintains pressure and supplies oil.

9. The integrated launch-to-orbit vehicle transport and erecting cradle of any of claims 1-5, wherein, The transport unit (100) is equipped with a counterweight (104) to prevent the rocket from overturning.

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