A large phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environments

Abstract

The present invention discloses a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment, including: an deployment locking mechanism, a deployment arm, a two-dimensional attitude adjustment mechanism, a compression release mechanism, an antenna frame and a connecting frame; wherein the deployment locking mechanism is fixed on the mounting surface by screws; one end of the deployment arm is connected to the rotating end of the deployment locking mechanism by screws, and the other end of the deployment arm is connected to the Y-axis fixed end of the two-dimensional attitude adjustment mechanism by screws; one end of the connecting frame is connected to the X-axis rotating end of the two-dimensional attitude adjustment mechanism by screws, and the other end of the connecting frame is connected to the antenna frame by screws; the phased array antenna is installed on the antenna frame by screws; there are five sets of compression release mechanisms, which are respectively installed on the Y-axis rotating end of the two-dimensional attitude adjustment mechanism and the four corners of the antenna frame symmetrical with the center of the phased array antenna. The present invention solves the difficult problems of installation and fixation, on-orbit deployment and two-dimensional attitude adjustment of large-scale phased array antennas.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace electromechanical technology, and in particular relates to a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment. Background Art

[0002] The antenna pointing mechanism is the core component of the satellite communication system. It is the actuator for the antenna to track and locate the ground receiving station or the intersatellite communication object. At present, the mature space antenna pointing mechanisms are mostly used for tracking and pointing of parabolic antennas such as data transmission antennas and relay antennas. The weight and inertia of their loads are generally small, the antenna installation method is simple, and the requirements for the bearing and driving capacity of the mechanism are not high. With the continuous development of space technology, phased array antennas have become an important form of application in many satellite communication systems due to their more powerful functions and flexible and changeable working methods. With the increasing demand for intersatellite link communication, the one-dimensional or two-dimensional electronic scanning of fixed phased array antennas can no longer meet the requirements of different working modes, and new requirements are also put forward for the attitude adjustment and precise angle pointing of phased array antennas. Generally, phased array antennas are flat-plate type, and their size, weight, and inertia are larger than those of ordinary parabolic antennas. The traditional parabolic antenna installation method and the corresponding antenna pointing mechanism are no longer applicable. At the same time, the current space antenna pointing mechanism is mostly used in low- and medium-orbit satellites, and is less used in high-orbit satellites. The high-orbit environment is more severe than the low- and medium-orbit environment, and higher requirements are put forward for the environmental adaptability of the antenna pointing mechanism. Therefore, with the needs of aerospace development, there is an urgent need for deployment and attitude adjustment mechanisms suitable for high-orbit environments and large phased array antennas. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environments, and to solve the problems of installation, fixation, on-orbit deployment and two-dimensional attitude adjustment of large-scale phased array antennas.

[0004] The object of the present invention is achieved through the following technical solutions: A large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment, comprising: an deployment locking mechanism, a deployment arm, a two-dimensional attitude adjustment mechanism, a compression and release mechanism, an antenna frame and a connecting frame; wherein the deployment locking mechanism is fixed to a mounting surface by screws; one end of the deployment arm is connected to the rotating end of the deployment locking mechanism by screws, and the other end of the deployment arm is connected to the Y-axis fixed end of the two-dimensional attitude adjustment mechanism by screws; one end of the connecting frame is connected to the X-axis rotating end of the two-dimensional attitude adjustment mechanism by screws, and the other end of the connecting frame is connected to the antenna frame by screws; the phased array antenna is mounted on the antenna frame by screws; there are five sets of the compression and release mechanisms, which are respectively mounted on the Y-axis rotating end of the two-dimensional attitude adjustment mechanism and the four corners of the antenna frame symmetrical with the center of the phased array antenna.

[0005] In the above-mentioned large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment, the deployment locking mechanism includes a drive assembly, a deployment axis base, a deployment axis swivel, a locking device, a bearing assembly and a light shield; wherein, the locking hook is integrated with the deployment axis swivel, and the locking device completes the mechanical locking of the deployment axis swivel after being deployed into place; the bearing assembly includes four deep groove ball bearings, one end of the deployment axis base is connected to one end of the deployment axis swivel through two deep groove ball bearings, and the other end of the deployment axis base is connected to the other end of the deployment axis swivel through two deep groove ball bearings; the light shield is installed on the relative rotating surface of the deployment axis base and the deployment axis swivel, a multi-layer heat insulation assembly is installed in the light shield, and the light shield is sprayed with thermal control white paint on the outside for heat dissipation and light blocking to adapt to the high-orbit temperature environment.

[0006] In the above-mentioned large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment, the deployment arm includes a carbon fiber arm and a metal joint; wherein the carbon fiber arm and the metal joint are connected, and the carbon fiber arm is a hollow structure for cable routing.

[0007] In the above-mentioned large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment, the two-dimensional attitude adjustment mechanism includes two one-dimensional mechanisms; wherein one one-dimensional mechanism is connected to the middle part of another one-dimensional mechanism; and the central axis directions of the two one-dimensional mechanisms are perpendicular.

[0008] In the above-mentioned large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment, the two one-dimensional mechanisms have the same structure, and each one-dimensional mechanism includes a second drive component; wherein the second drive component drives the one-dimensional mechanism to rotate; a second deep groove ball bearing is installed at the active end and the driven end of each one-dimensional mechanism; a second light baffle is installed on the relative rotating surface of each one-dimensional mechanism, a multi-layer heat insulation component is installed in the second light baffle, and the second light baffle is sprayed with thermal control white paint on the outside for heat dissipation and light blocking to adapt to the high-orbit temperature environment; the driven end rotating shaft of each one-dimensional mechanism is a hollow shaft for cable routing.

[0009] In the above-mentioned large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment, the clamping and releasing mechanism includes a clamping base, a clamping head cover, a shock-absorbing head cover, a clamping rod and a pyrotechnic cutter; wherein, the clamping base is fixed to the mounting surface by screws, the clamping head cover is connected and fixed to the clamped part by screws, the clamping rod passes through the mounting hole of the clamping head cover and is screwed into the threaded hole of the clamping base, thereby fixing the clamped part on the clamping base, and when in use, a pre-tightening force is applied to the clamping rod so that it bears the load of the launching section; the pyrotechnic cutter is arranged on the clamping base, and before being deployed on the track, the pyrotechnic cutter works to cut off the clamping rod, releases the clamping state, and the clamped part can be separated; the shock-absorbing head cover is connected to the clamping head cover by screws, and plays a role in absorbing impact and reducing shock at the moment when the clamping rod is cut off.

[0010] In the above-mentioned large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment, the antenna frame includes a carbon fiber rod, a carbon fiber joint, a metal joint and a metal boss; wherein a plurality of carbon fiber rods are connected by a carbon fiber joint to form a frame; metal joints are provided at the interfaces between the four corners of the frame and the clamping and releasing mechanism;

[0011] The metal boss is bonded to the outer surface of the carbon fiber rod.

[0012] The above-mentioned large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment also includes: fiberglass thermal insulation pads; wherein, there are six fiberglass thermal insulation pads, which are respectively installed under the five sets of clamping and releasing mechanisms and under the deployment locking mechanism.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] (1) The present invention provides a phased array antenna installation interface through a high-rigidity, high-strength composite antenna frame, and can effectively ensure the antenna installation accuracy by bonding and then assembling the metal bosses;

[0015] (2) The mechanism of the present invention adopts an active drive mode with a large output torque, adopts a large load-bearing shaft system design structure, and adopts a lock hook type mechanical locking to ensure high deployment accuracy and locking stiffness;

[0016] (3) The present invention installs light shields on the outside of the main exposed parts, installs multi-layer heat insulation components inside the light shields, and sprays thermal control white paint on the outside of the light shields, so that the mechanism can better adapt to the high-rail temperature environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0018] FIG. 1( a ) is an external view of an embodiment of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment in a folded state provided by an embodiment of the present invention;

[0019] FIG1( b ) is an external view of an embodiment of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment in a deployed state provided by an embodiment of the present invention;

[0020] Figure 2 It is a top view of an embodiment of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment provided by an embodiment of the present invention (the phased array antenna is hidden);

[0021] FIG3( a ) is an appearance diagram of a deployment and locking mechanism of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment in a folded state provided by an embodiment of the present invention;

[0022] FIG3( b ) is an appearance diagram of a deployment and locking mechanism of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment in a deployed state provided by an embodiment of the present invention;

[0023] FIG3( c ) is a partial cross-sectional view of a deployment and locking mechanism of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment in a folded state provided by an embodiment of the present invention;

[0024] Figure 4 It is an appearance diagram of a two-dimensional attitude adjustment mechanism of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment according to the present invention;

[0025] Figure 5 This is an outline diagram of a compression and release mechanism of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment according to the present invention (shown by a dashed line of a shock-absorbing headgear);

[0026] Figure 6 The present invention is an antenna frame appearance diagram of a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for a high-orbit environment. DETAILED DESCRIPTION

[0027] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to be able to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features described in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0028] The present invention provides a large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment, which comprises: a deployment locking mechanism 1, a deployment arm 2, a two-dimensional attitude adjustment mechanism 3, a compression release mechanism 4, an antenna frame 5, a connecting frame 6, and a fiberglass heat insulation pad 7.

[0029] As shown in Figure 1(a), Figure 1(b) and Figure 2 As shown, the unfolding locking mechanism 1 is fixed on the mounting surface by screws; one end of the unfolding arm 2 is connected to the rotating end of the unfolding locking mechanism 1 by screws, and the other end is connected to the Y-axis fixed end of the two-dimensional posture adjustment mechanism 3 by screws; one end of the connecting frame 6 is connected to the X-axis rotating end of the two-dimensional posture adjustment mechanism 3 by screws, and the other end is connected to the antenna frame 5 by screws; the phased array antenna 8 is installed on the antenna frame 5 by screws; the clamping and releasing mechanism 4 has a total of five sets, which are respectively installed at the Y-axis rotating end of the two-dimensional posture adjustment mechanism 3 and the four corners of the antenna frame 5 symmetrical with the center of the phased array antenna 8; the fiberglass thermal insulation pads 7 have a total of six, which are respectively installed under the five sets of clamping and releasing mechanisms 4 and under the unfolding locking mechanism 1.

[0030] As shown in Figures 3(a), 3(b) and 3(c), the deployment locking mechanism 1 is composed of a drive assembly 101, an deployment shaft base 102, an deployment shaft swivel 103, a locking device 104, a bearing assembly 105, and a light shield 106. The side where the drive assembly 101 is located is the active end, and the other side is the driven end. The deployment method adopts an active drive, and drive assemblies with different driving capabilities and accuracy levels can be selected for replacement and installation according to the load conditions. The lock hook is designed to be integrated with the deployment shaft swivel 103. After being deployed in place, the locking device 104 completes the mechanical locking of the deployment shaft swivel 103, and the locking stiffness is high. By adjusting the position of the locking device 104, the locking angle accuracy can be better than 0.1°, and the repeatability accuracy can be better than 0.04°. The bearing assembly 105 includes four deep groove ball bearings, two at the active end and two at the driven end, to improve the load-bearing capacity. The light shield 106 is installed on the relative rotation surface of the deployment shaft base 102 and the deployment shaft swivel 103. A multi-layer heat insulation component is installed inside the light shield 106. The light shield 106 is sprayed with thermal control white paint for heat dissipation and light blocking to adapt to the high rail temperature environment. The driven end shaft is a hollow shaft for cable routing. The deployment locking mechanism has an adjustable deployment speed, a smooth deployment process, high deployment accuracy and locking stiffness, and no locking impact.

[0031] The deployment arm 2 is composed of a carbon fiber arm rod and a metal joint, and is light in weight and has good strength and rigidity; the deployment arm 2 is a hollow structure and is used for cable routing.

[0032] As shown in FIG. 3( c ), a certain axial clearance is formed between the expansion shaft base 102 , the expansion shaft swivel 103 , and the bearing assembly 105 under the cooperation of the adjustment gasket, and the specific relationship is as follows:

[0033] δ1=δ2=(C1-C2-(B1-A1)-(B2-A2)+Δ) / 2

[0034] Among them: C1 is the span of the unfolded shaft swivel, C2 is the span of the bearing installation end face of the unfolded shaft base, B1 is the width of the driven shaft, B2 is the width of the driving shaft, A1 is the width of the driven end bearing assembly, A2 is the width of the driving end bearing assembly, δ1 is the thickness of the driven end adjustment gasket, δ2 is the thickness of the active end adjustment gasket, and Δ is the design value of the axial clearance.

[0035] Effect: 1) The required adjustment gasket thickness can be calculated through the axial clearance design value to ensure that the axial clearance meets the design requirements; 2) Ensure that the symmetry plane of the expansion shaft swivel overlaps with the symmetry plane of the expansion shaft base after installation, thereby ensuring that the spacing between the light baffles on both sides is consistent to avoid interference during rotation.

[0036] like Figure 4As shown, the two-dimensional posture adjustment mechanism 3 is composed of two large-load-bearing, high-precision one-dimensional mechanisms with the same structure. It is driven by a drive component 301 to realize rotation and precise pointing in two directions around the X-axis and the Y-axis; wherein the Y-axis rotating end is connected to the X-axis fixed end by screws, and the axis of rotation of the X-axis is perpendicular to the axis of rotation of the Y-axis and is in the same plane. According to the load conditions, drive components with different driving capabilities and accuracy levels can be selected for replacement and installation. The side where the drive component 301 is located is the active end, and the other side is the driven end. A deep groove ball bearing is installed at the active end and the driven end of each one-dimensional mechanism to improve the load-bearing capacity. A light baffle 302 is installed on the relative rotating surface of each one-dimensional mechanism, and a multi-layer heat insulation component is installed in the light baffle 302. The light baffle 302 is sprayed with thermal control white paint on the outside for heat dissipation and light blocking to adapt to the high rail temperature environment. The driven end shaft of each one-dimensional mechanism is a hollow shaft for cable routing. The two-dimensional attitude adjustment mechanism has a large load-bearing capacity, the verticality of the X-axis and Y-axis is better than 0.006mm, and the pointing accuracy is better than 0.1°.

[0037] like Figure 5 As shown, the clamping release mechanism 4 is composed of a clamping base 401, a clamping head cover 402, a shock absorbing head cover 403, a clamping rod 404, and a pyrotechnic cutter 405; the clamping base 401 is fixed to the mounting surface by screws, the clamping head cover 402 is connected and fixed to the clamped part by screws, the clamping rod 404 passes through the mounting hole of the clamping head cover 402 and is screwed into the threaded hole of the clamping base 401, thereby fixing the clamped part on the clamping base 401, and when in use, a pre-tightening force is applied to the clamping rod 404 to make it bear the load of the launch section. Before the on-track deployment, the pyrotechnic cutter 405 works to cut off the clamping rod 404, release the clamping state, and the clamped part can be separated. The shock absorbing head cover 403 is connected to the clamping head cover 402 by screws, and plays a role in absorbing impact and reducing shock at the moment when the clamping rod 404 is cut off.

[0038] like Figure 6 As shown, the antenna frame 5 is composed of a carbon fiber rod 501, a carbon fiber joint 502, a metal joint 503, and a metal boss 504, and is light in weight and has good strength and stiffness; the internal intersection of the antenna frame 5 is a carbon fiber joint 502, and the interfaces between the four corners of the antenna frame 5 and the clamping and releasing mechanism 4 are metal joints 503; the antenna frame 5 provides a mounting surface interface with the phased array antenna 8, and the mounting surface is ensured to have high precision by bonding the metal boss 504 to the carbon fiber rod 501 and then combining and processing.

[0039] The present invention provides a phased array antenna installation interface through a high-rigidity, high-strength composite material antenna frame, and can effectively ensure the antenna installation accuracy by bonding metal bosses and then assembling and processing; the mechanism part of the present invention adopts an active drive mode with a large output torque, adopts a large-load shaft system design structure, and adopts a lock hook type mechanical locking to ensure high deployment accuracy and locking stiffness; the present invention installs light shielding plates on the outside of major exposed parts, installs multi-layer heat insulation components in the light shielding plates, and sprays thermal control white paint on the outside of the light shielding plates, so that the mechanism can better adapt to the high-orbit temperature environment.

[0040] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A large phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environments, characterized in that include: An unfolding locking mechanism (1), an unfolding arm (2), a two-dimensional posture adjustment mechanism (3), a pressing and releasing mechanism (4), an antenna frame (5) and a connecting frame (6); wherein, The unfolding locking mechanism (1) is fixed on the mounting surface by means of screws; One end of the deployment arm (2) is connected to the rotating end of the deployment locking mechanism (1) through a screw, and the other end of the deployment arm (2) is connected to the Y-axis fixed end of the two-dimensional posture adjustment mechanism (3) through a screw; One end of the connecting frame (6) is connected to the X-axis rotating end of the two-dimensional posture adjustment mechanism (3) through a screw, and the other end of the connecting frame (6) is connected to the antenna frame (5) through a screw; The phased array antenna (8) is mounted on the antenna frame (5) by means of screws; There are five sets of the clamping and releasing mechanisms (4), which are respectively installed at the Y-axis rotating end of the two-dimensional posture adjustment mechanism (3) and the four corners of the antenna frame (5) symmetrical with the center of the phased array antenna (8); The deployment locking mechanism (1) comprises a driving assembly (101), a deployment shaft base (102), a deployment shaft swivel (103), a locking device (104), a bearing assembly (105) and a light shield (106); wherein: The locking hook is designed to be integrated with the deployment shaft rotating body (103), and after being deployed in place, the locking device (104) completes the mechanical locking of the deployment shaft rotating body (103); The bearing assembly (105) includes four deep groove ball bearings, one end of the unfolding shaft base (102) is connected to one end of the unfolding shaft swivel (103) through two deep groove ball bearings, and the other end of the unfolding shaft base (102) is connected to the other end of the unfolding shaft swivel (103) through two deep groove ball bearings; The light shield (106) is installed on the relatively rotating surface of the deployment shaft base (102) and the deployment shaft swivel (103), a multi-layer heat insulation component is installed inside the light shield (106), and the light shield (106) is sprayed with thermal control white paint on the outside to dissipate heat and block light to adapt to the high rail temperature environment; The two-dimensional posture adjustment mechanism (3) comprises two one-dimensional mechanisms; wherein one one-dimensional mechanism is connected to the middle of another one-dimensional mechanism; and the central axis directions of the two one-dimensional mechanisms are perpendicular; The two one-dimensional mechanisms have the same structure, and each one-dimensional mechanism comprises a second driving component (301); wherein, The second driving component (301) drives the one-dimensional mechanism to rotate; A second deep groove ball bearing is installed at the driving end and the driven end of each one-dimensional mechanism; A second light shield (302) is installed on the relative rotation surface of each one-dimensional mechanism, a multi-layer heat insulation component is installed inside the second light shield (302), and the second light shield (302) is sprayed with thermal control white paint on the outside to dissipate heat and block light to adapt to the high rail temperature environment; The driven end shaft of each one-dimensional mechanism is a hollow shaft for cable routing; The clamping release mechanism (4) comprises a clamping base (401), a clamping head cover (402), a shock-absorbing head cover (403), a clamping rod (404) and an explosive device cutter (405); wherein: The clamping base (401) is fixed to the mounting surface by means of screws, the clamping head cover (402) is connected and fixed to the clamped part by means of screws, the clamping rod (404) passes through the mounting hole of the clamping head cover (402) and is screwed into the threaded hole of the clamping base (401), thereby fixing the clamped part on the clamping base (401), and when in use, a pre-tightening force is applied to the clamping rod (404) so ​​that it bears the load of the launch section; The pyrotechnic cutter (405) is arranged on the clamping base (401). Before the rail is unfolded, the pyrotechnic cutter (405) works to cut off the clamping rod (404), thereby releasing the clamping state and allowing the clamped parts to be separated. The shock-absorbing head cover (403) is connected to the pressing head cover (402) by means of screws, and plays a role in absorbing impact and reducing shock at the moment when the pressing rod (404) is cut off; The antenna frame (5) comprises a carbon fiber rod (501), a carbon fiber joint (502), a metal joint (503) and a metal boss (504); wherein: A plurality of carbon fiber rods (501) are connected via carbon fiber joints (502) to form a frame; Metal joints (503) are provided at the interfaces between the four corners of the frame and the compression and release mechanism (4); The metal boss (504) is bonded to the outer surface of the carbon fiber rod (501); A certain axial clearance is formed between the expansion shaft base, the expansion shaft swivel, and the bearing assembly with the cooperation of the adjustment gasket. The specific relationship is as follows: δ1=δ2=(C1-C2-(B1-A1)-(B2-A2)+Δ) / 2 Among them: C1 is the span of the unfolded shaft swivel, C2 is the span of the bearing installation end face of the unfolded shaft base, B1 is the width of the driven shaft, B2 is the width of the driving shaft, A1 is the width of the driven end bearing assembly, A2 is the width of the driving end bearing assembly, δ1 is the thickness of the driven end adjustment gasket, δ2 is the thickness of the active end adjustment gasket, and Δ is the design value of the axial clearance.

2. According to claim 1, the large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment is characterized in that: The deployment arm (2) comprises a carbon fiber arm and a metal joint; wherein the carbon fiber arm and the metal joint are connected, and the carbon fiber arm is a hollow structure used for cable routing.

3. The large-scale phased array antenna deployment and attitude adjustment mechanism suitable for high-orbit environment according to claim 1 is characterized in that It also includes: a glass fiber reinforced plastic heat insulation pad; wherein, there are six glass fiber reinforced plastic heat insulation pads in total, which are respectively installed at the lower part of the five sets of compression and release mechanisms (4) and the lower part of the unfolding and locking mechanism (1).

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