CN110566630A - load supporting device integrating vibration reduction of launching section and vibration isolation of on-track section - Google Patents

Abstract

The invention provides a load support device integrating vibration reduction in the launch section and vibration isolation in the rail section, which can realize the variable stiffness requirements of high stiffness and high damping in the launch section, low stiffness and low damping in the rail section, and realize vibration reduction in the launch section and vibration isolation in the rail section. The vibration isolation function of the rail section is integrated, and it has high reliability. Including load platform, vibration isolation module and connecting support module. Among them, the upper and lower ends of the vibration isolation module are respectively connected with the load platform and the connection support module. The vibration isolation module is a closed parallel structure, which can meet the large load and high reliability performance requirements of the launching section for the mechanical environment; at the same time, it adopts symmetrical and inclined support design , to achieve three-way equal stiffness and equal fundamental frequency functions in the space coordinate system, and has good stability. By adjusting the compression amount of rubber vibration isolation components in two directions, the design requirements of variable stiffness can be realized, and it has strong adaptability to the complex space mechanical environment. The supporting device is light in weight, small in size, simple in structure, low in manufacturing cost, and has broad application prospects.

Description

A load support device integrating vibration reduction in launch section and vibration isolation in rail section

technical field

The invention relates to a load support device, in particular to a load support device used for the integration of anti-mechanical environment and on-orbit vibration isolation in a spacecraft, and belongs to the technical field of spacecraft vibration reduction and isolation.

Background technique

With the rapid development of spacecraft technology, the accuracy, sensitivity and complexity of spacecraft payloads continue to increase. On the one hand, during the launch phase, it is necessary to reduce the vibration level of the payload installation to prevent the vibration environment caused by the rocket from affecting the high Precision loads cause damage; on the other hand, during the on-orbit working phase, it is necessary to reduce the micro-vibration interference generated by moving parts on the star (such as control moment gyro, reaction wheel, solar wing drive mechanism, etc.) to ensure that the accuracy of the payload meets the requirements.

In engineering, special load support devices are usually used to meet the above requirements, but these two requirements have certain contradictions in the requirements for load support devices. For the vibration reduction requirements of the launch section, the load support device needs to have high damping, which can reduce the vibration level of the launch section through the damping effect, and also needs to have high stiffness to avoid resonance coupling with the spacecraft structure and improve load support. The carrying capacity of the device. For the vibration isolation requirements of the rail section, the load support device needs to have lower damping to avoid too much damping and reduce the vibration isolation efficiency. At the same time, it also needs to have a lower frequency, so as to avoid the vibration excitation frequency of the disturbance source and improve the medium and high vibration frequency. The effect of frequency band vibration isolation. The contradictory requirements of the above two aspects have caused great difficulties to the design of the load support device.

At present, the relevant patents for spacecraft vibration reduction and isolation devices include: (1) A parallel truss-type CMG group vibration reduction and isolation device, which uses a parallel combination of multiple vibration isolation rods to achieve overall vibration isolation for multiple CMGs in the form of a truss layout , and by adjusting the layout angle of the vibration isolation rods and the stiffness and damping parameters of the vibration isolator, the characteristics of the vibration isolation system can be adjusted to meet the requirements of different types of CMG vibration reduction and isolation (patent number ZL201610329702.3); (2) a Micro-vibration vibration isolator with high load capacity and high damping, adopts external main stiffness spring and internal fluid damping in parallel, realizes high sensitivity to micro-vibration, effectively improves micro-vibration, high-precision spacecraft vibration control on orbit (application number 201618001923.9) (3) An active-passive integrated four-legged converging vibration isolator, which adopts three-legged inclined support, improves the load-carrying capacity by adding piezoelectric ceramics, vibration-isolation springs and metal rubber in parallel, and has better resonance suppression Peak action (application number CN201810057862.6); (4) A three-way stiffness adjustable vibration isolator, which realizes its own The adjustment of stiffness can meet the needs of different vibration conditions, and has a wide range of vibration environments (application number 201710560814.4); (5) A vibration isolator with variable stiffness, through the stiffness of the magnetorheological elastomer in the shear direction Vibration isolation or vibration reduction by changing the frequency of the vibration source, so that it can achieve a better vibration reduction effect even when the frequency of the vibration source is constantly changing (application number CN201120115405.1); (6) variable stiffness adjustable rubber vibration isolator, through The clamping mechanism adjusts the pre-tightening force on the rubber to change the stiffness and natural frequency of the rubber vibration isolator (application number CN200720076571.9); (7) a variable stiffness shock-resistant wire rope vibration isolator, by adjusting the coil spring and The distance between the rubber guide pillars realizes the function of variable stiffness and variable natural frequency characteristics (application number CN201210449630.8); (8) patent: a vibration isolation unit module that can reduce nonlinear effects, using "S" type structure and vibration The source is connected to the base body, and rubber pads are arranged between them, which can effectively reduce vibration transmission and have better bearing capacity (application number US201415033600).

The vibration isolation device designed by the above-mentioned patent is helpful to achieve high load, has better anti-mechanical environment and good high-frequency vibration isolation effect, and can suppress the peak response of the resonance frequency band, but there are still some unknown points, specifically appears in:

(1) The load-carrying capacity can only be increased without taking into account the variable stiffness, and the applicable environment is limited. Although the traditional vibration isolator uses vibration isolation springs connected in parallel with rubber to increase its load-carrying capacity, it cannot achieve variable stiffness adjustment, which in turn leads to the inability to achieve natural frequency adjustment in complex mechanical environments, and the application environment is limited. The addition of active control links to achieve variable stiffness and variable damping functions can effectively improve adaptability, but at the same time increases the complexity of the system, thereby reducing reliability.

(2) The low-order natural frequency distribution is scattered, and the effect of vibration reduction and isolation is not ideal. For the complex space mechanics environment, it is necessary to make the low-order natural frequency of the vibration isolation device itself avoid all external interference frequency points, as well as the payload work disturbance vibration frequency points. Due to its scattered natural frequency distribution, the existing vibration isolators cannot effectively avoid the above-mentioned interference frequency points, and are prone to coupling resonance with the entire star structure and payload. An ideal vibration isolation device can achieve equal stiffness and equal frequency design, and the distribution is concentrated to avoid resonance points.

Contents of the invention

In view of this, the present invention provides a load support device that integrates vibration reduction in the launching section and vibration isolation in the on-rail section, which can realize the variable stiffness requirements of high stiffness and high damping in the launching section and low stiffness and low damping in the on-rail section, and realize The functions of vibration reduction and on-rail vibration isolation are integrated, and at the same time, it has high reliability.

The load supporting device integrating the vibration reduction of the launch section and the vibration isolation of the on-rail section includes: a load platform, a vibration isolation module and a connection support module;

The vibration isolation module is arranged between the load platform and the connection support module, including: more than three variable stiffness vibration isolators;

The variable stiffness vibration isolator includes: a spring vibration isolation assembly and a rubber vibration isolation assembly; the spring vibration isolation assembly includes: an end cover, a limit cylinder I, a coil spring and a limit cylinder II; the limit cylinder I is the same as The shafts are relatively placed, and there is a set distance between the opposite surfaces; the end cap is screwed to the open end of the limit cylinder I; the coil spring is sleeved on the limit cylinder I and the limit cylinder II outside, its two ends are respectively connected with the limit cylinder I and the limit cylinder II through fasteners;

The rubber vibration isolation assembly includes: two rubber pads, a piston rod and a limit nut; one end of the piston rod is coaxially located inside the limit cylinder I, and the other end passes through the limit cylinder I and extends into the limit cylinder I. The inside of the position cylinder II39; the piston rod is located in the middle of the limit cylinder I and has a shoulder, which divides the internal space of the limit cylinder I into upper and lower parts, and one is installed in each of the upper and lower spaces. A rubber pad; the part of the piston rod extending into the limit cylinder II is threaded to a limit nut, and the limit nut is in conflict with the inner bottom surface of the limit cylinder II;

Adjusting the length of the screw fit between the end cap and the limit cylinder I can adjust the compression amount of the rubber pad in the upper space of the limit cylinder I; adjust the length of the screw fit between the limit nut and the piston rod, Can adjust the compression amount that is positioned at the rubber pad in the upper space in the limiting cylinder 1.

Preferably: the normal direction of the upper surface of the connection support module is the x direction, the left and right direction of the upper surface of the connection support module is the y direction, and the direction perpendicular to the xy plane is the z direction;

More than three variable stiffness vibration isolators are arranged obliquely, so that the stiffness components of the vibration isolation module in the three directions of x, y, and z are the same.

Preferably: the axes of more than three variable stiffness vibration isolators intersect at the centroid of the load platform.

Preferably: the vibration isolation module includes: four variable stiffness vibration isolators, the four variable stiffness vibration isolators are in groups of two, symmetrically distributed between the load platform and the connecting support module ;

The variable stiffness vibration isolator is arranged inclined inward, and the angle between its axis and the y direction is β;

The two variable stiffness vibration isolators in each group are arranged obliquely toward their opposite directions, and the angle between the axes of the two variable stiffness vibration isolators in each group is α;

The values of the included angle β and the included angle α ensure that the stiffness components of the vibration isolation module in the three directions x, y, and z are the same.

Beneficial effect:

(1) The spring vibration isolation component and the rubber vibration isolation component adopt a closed parallel design, which effectively realizes the large load and high reliability performance requirements in an anti-mechanical environment. Through the double space cooperation of the limit cylinder I and the piston rod, it can not only effectively improve the rigidity and increase its load-bearing capacity against the mechanical environment in the launching section, but also help reduce the vibration response peak value of the launching section, and improve the working environment of the rubber vibration isolation component in orbit need.

(2) The compression amount of the rubber vibration isolation component can be adjusted in two directions to meet the design requirements of variable stiffness, and the adaptability is stronger. By adjusting the thread length of the end cover and the limit cylinder I, as well as the piston rod and the limit nut, the compression state of the upper and lower layers of rubber pads can be adjusted to realize the variable stiffness adjustment of the vibration isolation module, thereby increasing the ability to avoid all external The flexibility of interference frequency points and payloads makes it more adaptable to complex space mechanics environments.

(3) The symmetrical distribution and inclined support design for the variable stiffness vibration isolators can realize the three-way equal stiffness design requirements in the space coordinate system; by symmetrically supporting multiple variable stiffness vibration isolators under the load platform, and By making the axes of multiple variable stiffness vibration isolators intersect at the center of mass of the load platform, it is easy to realize the equivalence of the three-way fundamental frequency of the support device, making its low-order natural frequency distribution compact, which can effectively avoid many external interference frequency points and effectively The load itself works to disturb the vibration frequency point, which has good stability.

Description of drawings

Fig. 1 is the overall structural diagram of the on-rail vibration isolation integrated high-load load support device of the present invention;

Fig. 2 is a structural sectional view of the vibration isolation module of the support device of the present invention;

Fig. 3 is a top view of the vibration isolation module structure of the support device of the present invention;

Fig. 4 is a schematic diagram of the inclination angle and arrangement of the supporting device connected to the supporting module of the present invention.

Among them: A-load platform, B-vibration isolation module, C-connection support module, D-spring vibration isolation component, E-rubber vibration isolation component, 1-load mounting plate, 2-upper bracket, 3-variable stiffness vibration isolation Device, 4-lower bracket, 5-base, 31-end cover, 32-set screw, 33-limit cylinder I, 34-rubber pad, 35-piston rod, 36-inside limit nut, 37-outside limit Position nut, 38-helical spring, 39-limit cylinder II.

Detailed ways

The present invention will be described in detail below with reference to the accompanying drawings and examples.

This embodiment provides a load support device that integrates vibration reduction in the launch section and vibration isolation in the orbit section. In order to overcome the problem that the existing vibration isolation device has a wide distribution of low-order modes and is easy to resonate with the spacecraft structure, The load support device adopts a three-way equal stiffness layout design in space to realize the concentrated distribution of the low-order modes of the load support device and effectively avoid the frequency of the spacecraft structure itself; at the same time, in order to overcome the inability to adjust the stiffness of the existing passive The rigidity adjustment method is complicated and low in reliability. Passive variable stiffness design is adopted. Through the two-way adjustment design, the variable stiffness requirements of high stiffness and high damping in the launch section and low stiffness and low damping in the orbit section are realized.

As shown in FIG. 1 , the load support device includes: a load platform A, a vibration isolation module B and a connecting support module C. The load platform A includes: a load mounting plate 1 and an upper bracket 2, the upper bracket 2 is connected to the lower surface of the load mounting plate 1 through fasteners (such as screws), and the upper surface of the load mounting plate 1 is used as the load mounting surface; the connecting support module C includes : The lower bracket 4 and the base 5, the lower bracket 4 is connected to the upper surface of the base 5 through fasteners (such as screws); the vibration isolation module B is located between the load platform A and the connecting support module C, and the upper and lower ends are respectively connected to the upper surface The bracket 2 and the lower bracket 4 are connected by fasteners (such as screws) to ensure reliable connection.

The vibration isolation module B is composed of more than two groups of variable stiffness vibration isolators 3. In this embodiment, the vibration isolation module B is composed of four groups of variable stiffness vibration isolators 3 (corresponding to four upper brackets 2 in the load platform A, connected to There are four lower brackets 4) in the supporting module C. As shown in Figures 2 and 3, the variable stiffness vibration isolator 3 includes two parts: a spring vibration isolation assembly D and a rubber vibration isolation assembly E. Among them, the rubber vibration isolation component E is located in the closed space inside the spring vibration isolation component D, which helps to ensure the on-orbit working environment of the rubber vibration isolation component E, and prevents the impact of the harsh space environment on the working performance of the rubber vibration isolation component E.

Wherein, the spring vibration isolation assembly D includes: an end cover 31 , a limiting cylinder I33 , a coil spring 38 and a limiting cylinder II39 . Both the limit cylinder I33 and the limit cylinder II39 are cylindrical structures with one end open and one end processed with a through hole, and the opening ends of the limit cylinder I33 and the limit cylinder II39 are all provided with shoulders; the end cover 31 is threaded on the limit The opening end of the limit cylinder I33 closes the opening end of the limit cylinder I33; the limit cylinder I33 and the limit cylinder II39 are coaxially placed, and the open end of the limit cylinder I33 faces upward, and the end with the through hole is processed with the limit cylinder II39 is processed with one end of the through hole facing each other, and there is an interval of a set distance between its opposite surfaces; the coil spring 38 is sleeved on the outside of the limiting cylinder I33 and the limiting cylinder II39, and its two ends are passed through fasteners (such as screws) respectively. ) is connected with the shoulder of the limit cylinder I33 and the open end of the limit cylinder II39. A positioning screw 32 is respectively provided at the relative positions of the shoulders of the opening ends of the limit cylinder I33 and the limit cylinder II39 to facilitate effective positioning during installation.

The rubber vibration isolation assembly E includes: a rubber pad 34, a piston rod 35, an inner limit nut 36 and an outer limit nut 37; one end of the piston rod 35 is coaxially located inside the limit cylinder I33, and the other end passes through the limit cylinder I33 in turn and the through hole at the end of the limiting cylinder II39 is located inside the limiting cylinder II39; the part of the piston rod 35 located inside the limiting cylinder I33 is a "ten" type structure, that is, the middle part of the piston rod 35 located at the inside of the limiting cylinder I33 is processed with a Shaft shoulder, this shaft shoulder divides the inner space of the spacer cylinder I33 into upper and lower parts, and a rubber pad 34 is respectively installed in the upper and lower parts of the space, and the rubber pad 34 is compacted by the end cover 31. One end of the piston rod 35 passing through the through hole at the end of the limiting cylinder II39 has an external thread, and the outside and inside of the through hole of the limiting cylinder II39 are respectively provided with an outer limiting nut 37 and The inner limit nut 36 is used to tighten the piston rod 35 in the limit cylinder II39 through the inner limit nut 36 and the outer limit nut 37, wherein the outer limit nut 37 and the inner limit nut 36 can be loosened or coated with double nuts Thread anti-loosening glue to prevent loosening during use. For the convenience of the assembly and debugging of the piston rod 35, the end face of the piston rod 35 extending into the limit cylinder II39 end is processed with a "one" groove for cooperating with an external tool (such as a screwdriver), and the outer limit nut 37 and the inner limit nut are installed. When setting the nut 36 and adjusting the threaded length of the outer limit nut 37 and the piston rod 35, cooperate with the "one" word groove on the end of the screwdriver and the piston rod 35 to withstand the piston rod 35 so that the piston rod 35 does not rotate with the nut.

By adjusting the length of the end cap 31 threaded with the limit cylinder I33, and the length of the piston rod 35 threaded with the limit nut, the compression state of the upper and lower layers of rubber pads can be adjusted to realize the vibration isolation module. Stiffness adjustment.

In order to facilitate the observation of the compressed state of the rubber pad in the limit cylinder I33 during installation, a through hole is processed on the outer peripheral surface of the limit cylinder I33 as an observation window.

As shown in Figure 4, let the normal direction of the upper surface of the base be the x direction, the left and right direction of the upper surface of the base be the y direction, and the direction perpendicular to the xy plane be the z direction to establish a space coordinate system; in order to achieve three-way equal stiffness Design, that is, the stiffness components of the variable stiffness vibration isolator 3 in the three directions of x, y, and z are the same, and the following layout method is adopted for the variable stiffness vibration isolator 3:

The variable stiffness vibration isolator 3 is connected between the corresponding lower bracket 4 and the upper bracket 2 through fasteners (such as screws), wherein the connection surface between the lower bracket 4 and the variable stiffness vibration isolator 3 is a slope A, and the upper bracket The connection surface between 2 and the variable stiffness vibration isolator 3 is the slope B parallel to the slope A, and the angle between the normal direction of the slope A and the slope B and the horizontal direction is β. The axis of the variable stiffness vibration isolator 3 is parallel to the normal direction of the two slopes, so that after the variable stiffness vibration isolator 3 is connected with the upper bracket 2 and the lower bracket 4, it has a certain inclination angle β, that is, the variable stiffness vibration isolator The isolator 3 is inclined inwardly and upwardly, and the angle between the axis of the variable stiffness vibration isolator 3 and the horizontal direction is β. Four variable stiffness vibration isolators 3 are distributed on the four corners of the upper surface of the base 5, and they are symmetrically distributed left and right; the two variable stiffness vibration isolators 3 on the same side (left or right) are inclined inward, Let the included angle between the axes of two variable stiffness vibration isolators 3 located on the same side (left or right) be α, and by designing the angle value β and angle value α, the spiral in the variable stiffness vibration isolator 3 The stiffness components of the spring 38 in the three directions of x, y, and z are the same, so as to realize the three-way equal stiffness design in the space coordinate system, ensure the compact distribution of the low-order modes of the support device, and effectively avoid the coupling between the launching section and the on-rail section Resonance, and preferably the axes of the four variable stiffness vibration isolators intersect at the center of mass of the load platform, it is easy to realize the three-way fundamental frequency equivalent of the support device. The value of inclination angle β and roll angle α can be analyzed and designed according to the quality characteristics of the payload to achieve the above functional requirements.

Therefore, under the large vibration load of the launch section, the two-way dynamic compression of the rubber can be realized through the millimeter-level displacement of the piston rod 35, which increases the dynamic structural damping of the support device, dissipates a large amount of vibration energy, and quickly attenuates the vibration energy to ensure a good launch section. the damping effect. In the rail section, the rubber vibration isolation component E is in a micro-vibration dynamic environment, the displacement of the piston rod 35 is generally in the order of microns, the compression of the rubber is extremely small, and usually there is no restoring force, thereby reducing the frequency of the support device and improving high-frequency vibration isolation Effect.

The load support device is a vibration isolation system with variable stiffness. As long as the relevant dimensions and technical parameters of the spring isolator vibration components and rubber vibration isolation components, as well as the arrangement and inclination angle are adaptively modified, it can meet the mechanical resistance of different payload launching sections. Environmental requirements and on-orbit vibration isolation performance requirements have high versatility and broad application prospects.

The modal and frequency response analysis and tests of the load support device have proved that the load support device has achieved the high load capacity of the active section and the better vibration reduction effect of the rail section, and can effectively avoid the coupling of all external interference frequency points resonance. At the same time, the load supporting device is light in weight, small in size, simple in structure, low in manufacturing cost, and has good adaptability.

To sum up, the above are only preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims (9)

1. A load supporting device integrating vibration reduction in the launch section and vibration isolation in the rail section, comprising: a load platform, a vibration isolation module and a connection support module; The vibration isolation module is arranged between the load platform and the connection support module, including: more than three variable stiffness vibration isolators (3); The variable stiffness vibration isolator (3) includes: a spring vibration isolation assembly and a rubber vibration isolation assembly; the spring vibration isolation assembly includes: an end cover (31), a limiting cylinder I (33), a coil spring (38) and The limiting cylinder II (39); the limiting cylinder I (33) is coaxially placed oppositely, and there is a set distance between the opposite surfaces; the end cap (31) is threaded on the limiting cylinder I The open end of (33); the coil spring (38) is sleeved on the outside of the limiting cylinder I (33) and the limiting cylinder II (39), and its two ends are respectively connected to the limiting cylinder by fasteners I (33) links to each other with limit cylinder II (39); The rubber vibration isolation assembly includes: two rubber pads (34), a piston rod (35) and a limit nut; one end of the piston rod (35) is coaxially located inside the limit cylinder I (33), and the other end passes through The limit cylinder I (33) extends into the inside of the limit cylinder II39; the piston rod (35) has a shoulder in the middle of the inner part of the limit cylinder I (33), and this shoulder will limit the limit cylinder. The inner space of the position cylinder I (33) is divided into upper and lower parts, and a rubber pad (34) is respectively installed in the upper and lower two parts of the space; Partially connect the limit nut through threads, and the limit nut is in conflict with the inner bottom surface of the limit cylinder II (39); Adjusting the length of the end cap (31) threaded with the limit cylinder I (33) can adjust the compression of the rubber pad (34) in the upper space of the limit cylinder I (33); adjust the limit cylinder I (33); The length that bit nut is threaded with described piston rod (35) can adjust the compression amount that is positioned at the rubber pad (34) in the inner upper space of position-limiting tube 1 (33). 2. The load support device for the integrated vibration reduction of the launching section and the vibration isolation of the on-rail section as claimed in claim 1, characterized in that: the normal direction of the upper surface of the connecting support module is x-direction, and the upper surface of the connecting support module The left and right direction in the surface is the y direction, and the direction perpendicular to the xy plane is the z direction; More than three variable stiffness vibration isolators (3) are arranged obliquely, so that the stiffness components of the vibration isolation module in the three directions of x, y, and z are the same. 3. The integrated load support device for launching section vibration reduction and on-rail section vibration isolation as claimed in claim 1, characterized in that: the axes of more than three variable stiffness vibration isolators (3) intersect at the load The center of mass of the platform. 4. The load support device integrated with the launch section vibration reduction and on-rail section vibration isolation as claimed in claim 2, characterized in that: The vibration isolation module includes: four variable stiffness vibration isolators (3), four variable stiffness vibration isolators (3) in pairs, symmetrically distributed on the load platform and the connecting support between modules; The variable stiffness vibration isolator (3) is arranged inclined inward, and the angle between its axis and the y direction is β; The two variable stiffness vibration isolators (3) in each group are arranged obliquely toward their relative directions, and the angle between the axes of the two variable stiffness vibration isolators (3) in each group is α; The values of the included angle β and the included angle α ensure that the stiffness components of the vibration isolation module in the three directions x, y, and z are the same. 5. The integrated load support device of launching section vibration reduction and on-rail section vibration isolation as claimed in claim 4, characterized in that: said load platform comprises: a load mounting plate (1) and an upper support (2), the The load mounting plate (1) provides a load mounting surface externally, the upper bracket (2) corresponds to the variable stiffness vibration isolator (3) one by one, and the variable stiffness vibration isolator (3) passes through the upper bracket (2) linking to each other with the load mounting plate (1); The connection surface between the upper bracket (2) and the variable stiffness vibration isolator (3) is an inclined plane B, and the included angle between the normal direction of the inclined plane B and the y direction is β. 6. The integrated load support device of launching section vibration reduction and on-rail section vibration isolation as claimed in claim 4, characterized in that: the connection support module comprises: a base (5) and a lower bracket (4), the The lower bracket (4) is in one-to-one correspondence with the variable stiffness vibration isolator (3), and the variable stiffness vibration isolator (3) is connected to the base (5) through the lower bracket (4); The connection surface between the lower bracket (4) and the variable stiffness vibration isolator (3) is an inclined plane A, and the included angle between the normal direction of the inclined plane A and the y direction is β. 7. The integrated load support device for launching section vibration reduction and on-rail section vibration isolation as claimed in claim 1 or 2 or 3, characterized in that: in the limit cylinder I (33) and the limit cylinder II ( 39) A set screw (32) is respectively arranged at the relative position on the end face. 8. The load supporting device integrating vibration reduction in the launch section and vibration isolation in the rail section as claimed in claim 1, 2 or 3, characterized in that: when the piston rod (35) extends into the limit cylinder II (39) The inner and outer sides of the inner part are respectively connected with a limit nut by threads, which are respectively made as an outer limit nut (37) and an inner limit nut (36); The end surface of the limiting cylinder II (39) is in conflict, and the inner limit nut (36) is in conflict with the inner bottom surface of the limiting cylinder II (39). 9. The integrated load support device for vibration reduction in launching section and vibration isolation in rail section as claimed in claim 1, 2 or 3, characterized in that: a There are through holes as viewing windows.