CN110595294B

CN110595294B - Rocket heat preservation protector in extremely cold region

Info

Publication number: CN110595294B
Application number: CN201910999469.3A
Authority: CN
Inventors: 郭全全; 勾永宝; 王泽易
Original assignee: Beihang University
Current assignee: Beihang University
Priority date: 2019-10-21
Filing date: 2019-10-21
Publication date: 2020-10-30
Anticipated expiration: 2039-10-21
Also published as: CN110595294A

Abstract

The invention discloses a rocket heat-insulation protection device capable of being quickly retracted and a method, comprising an openable truss barrel, a power device, a slide rail and a heating and heat-insulation device; the vertical surface of the cylinder is provided with a hinge and an opening, thereby realizing the opening and closing function of the cylinder; the power device provides power for withdrawing the truss barrel; the sliding rail is an I-shaped steel rail fixed on the bottom surface, the sliding rail can facilitate the withdrawing of the truss barrel, and the pulling resistance of the truss barrel can be realized through the pulley device, so that the stability of the truss barrel under wind load is realized; the protection device has high construction speed, and can quickly finish rocket assembly in extremely cold weather; and can realize rapid removal and shorten the preparation time for rocket launching.

Description

Rocket heat preservation protector in extremely cold region

Technical Field

The invention relates to an independent rocket heat-insulation protection device and method, in particular to a rocket heat-insulation protection device and method capable of being quickly retracted and used in extremely cold areas.

Background

The rocket is a complex system integrating nearly thousands of single machines and thousands of large and small components, wherein some composite materials, especially rubber materials for sealing, such as shock absorbers in the rocket fairing, sealing storage tanks and sealing parts in pipelines, look like some small components, and can have a crucial influence on the overall performance of the rocket. These parts and materials are often sensitive to low temperature and are easily damaged and failed under extremely cold conditions. When the rocket is in an extremely low external temperature condition, a special heat preservation protection device needs to be arranged to ensure that the temperature of a microenvironment where the rocket is located is not too low, and meanwhile, the device needs to have the characteristic of rapid withdrawal to realize timely response of rocket launching. The vehicle-mounted missile is often provided with a vertical launching device (Wang Huayu, research on safety protection system of vertical launching device [ D ], 2017, Wuhan engineering university), and the safety protection system mainly comprises a monitoring system and a process protection device, and the protection device is formed by a protection cross beam, a protection longitudinal beam and a variable amplitude oil cylinder. The missile launching device plays a role in supporting the missile, meets the preparation conditions before launching, can achieve the aiming precision, can correctly assist the missile to take off, but does not have the function of heat preservation and protection. At present, a rocket heat preservation device for realizing the heat preservation effect is not searched yet, and the field still belongs to the blank.

Disclosure of Invention

The invention provides a rocket heat-preservation protection device and method capable of being quickly retracted aiming at the requirement of rocket heat-preservation protection in extremely cold areas, and fills the blank. The key technical problems to be solved are as follows:

1) the material of the heat-insulating layer needs to have the characteristics of air tightness, flame retardance and the like, and the performance is kept stable under the extremely low temperature condition;

2) heating measures are required, and the environment temperature in the heat preservation device can be kept at a higher level when the external environment temperature is lower;

3) the heat-insulating protective device needs to have considerable strength and rigidity in the closing and withdrawing processes so as to resist external wind load;

4) can be quickly withdrawn without influencing rocket launching.

In order to solve the technical problem, the invention designs a rocket heat-insulation protection device capable of being quickly disassembled and folded, which comprises an openable truss barrel, a power device, a slide rail and a heating and heat-insulation device; a hinge and an opening are arranged on the vertical surface of the openable truss barrel so as to realize the opening and closing function of the truss barrel, and a pulley device is arranged at the bottom of the openable truss barrel; the power device provides power for withdrawing the truss barrel; the sliding rail is an I-shaped steel rail fixed on the bottom surface, the sliding rail can facilitate the removal and the collection of the truss barrel, and the pulling resistance of the truss barrel can be realized through the cooperation with the pulley device, so that the stability of the truss barrel under wind load is realized.

The openable truss cylinder is formed by welding an I-shaped steel column and an angle steel connecting piece, and the truss cylinder rotates by welding lug plates at the web positions of two upright posts and connecting the lug plates with hinges. Rubber materials are pasted on the two upright columns at the opening of the truss barrel, so that the sealing performance of the barrel is guaranteed, and the heat dissipation is reduced.

The opening and closing power of the truss barrel can be realized by driving a bottom pulley to roll through hydraulic mechanical transmission, motor or cable stretching. Because the center of gravity of the truss barrel is higher, greater instability exists in the opening and closing and withdrawing processes. In order to ensure the safety, reliability and rapidness of the truss barrel in the opening and closing and withdrawing processes, the power device preferably uses the combination of a hydraulic arm and a mechanical transmission device to provide power for withdrawing the truss barrel; the hydraulic arm realizes the opening and closing of the truss through a 'scissors-twisting' type component.

The heating and heat-insulating device comprises a truss outer coating material, a heat-insulating material and/or a heating device and is used for preventing wind, insulating heat and heating. The truss outer wrapping film material is an ethylene-tetrafluoroethylene copolymer (ETFE) film, the heat insulation material is a heat insulation coating or a heat insulation filler, the heat insulation filler is one or more of an aerosol heat insulation felt, phenolic foam and expanded and vitrified micro bubbles, the heating device is a heating blanket, and the heat insulation material is arranged between the film material and the heating device. In addition, a ventilating duct can be arranged in the cylinder wall, and a blower connected with the ventilating duct is arranged at the bottom of the launching platform to serve as a heating device.

The middle part of the truss barrel is provided with a 'scissors-type' connecting device, the whole structure can be driven to open and close through the extension of the hydraulic arms, when the rocket needs to be launched, the truss structure is opened through the extension of the first hydraulic arm through the 'scissors-type' transmission device, and then the second hydraulic arm contracts to pull the whole truss structure to move outwards, so that the structure can be withdrawn.

The truss cylinder can be divided into two semi-cylinders, pulley devices are respectively arranged at the hinge column, the semi-circle midpoint column and the column bottom of the opening position, 5 pulley devices and 5 sliding rails are used together, the pulley devices are rotating pulleys, in the opening process, the first hydraulic arm contracts to generate rotating torque to enable the pulleys to slide along the arc-shaped sliding rails, and the two semi-cylinder trusses are respectively driven by the rotating pulleys to rotate to the straight rails; then under the drive of the second hydraulic arm, the truss barrel integrally moves and is far away from the rocket main body, so that the truss barrel is retracted.

Preferably, the truss barrel is divided into 3 parts to form a semicircular truss and two 1/4 circular trusses, pulley devices are respectively arranged at a midpoint column of the semicircular truss, hinge columns of the two 1/4 circular trusses and column bottoms of opening positions, the truss barrel totally uses 5 pulley devices, 3 pulleys on a straight rail can be fixed by using a fixed pulley, the other two pulleys use a rotating pulley, opening and withdrawing of the rail can be completed only by laying 3 rails by adding a rail steering device, the bottom of the semicircular truss is fixed in the opening process and serves as acting points of the other two 1/4 circular trusses, hydraulic arms on two sides contract to generate rotating torque to enable the pulleys to slide along the arc-shaped rail, and after the 1/4 circular truss rotates for 45 degrees, the pulleys reach the positions of the sliding rail rotating devices. The motor of the track steering device rotates to drive the pulley to steer the straight rail through the sliding rail, so that the sliding direction is changed, then the hydraulic arm extends along the direction of the straight rail, the truss barrel integrally moves through the transmission arm and is far away from the rocket main body, and the truss barrel is retracted.

A truss section of thick bamboo passes through the post lower pulley group and is connected with the guide rail, realizes a truss section of thick bamboo resistance to plucking, and its concrete structure is: the I-shaped rail is fixed on a concrete slab through a buckle, a main wheel slides along the rail in the opening and withdrawing processes, two anti-pulling pulleys are arranged in the I-shaped rail to counteract vertical pulling force caused by lateral force in the movement process of a part of trusses and guarantee stable structure, and a bearing is arranged at the upper part of the I-shaped rail, so that the steering of the pulleys is realized. The main wheel bears the dead weight and pressure of the truss main body, and the two anti-pulling pulleys can provide wind load anti-pulling force for the truss barrel.

The device is in a closed state for a long time, and the retracting hydraulic arm in the scheme is in an open state for a long time. The long-term exposure of the hydraulic arm causes loss of the hydraulic arm, so that the reliability of the hydraulic arm is reduced, and therefore, a transmission arm, a support truss and a diagonal brace are added at the hydraulic arm. Therefore, the hydraulic arm can extend outwards to drive the whole truss to withdraw.

The invention has the beneficial effects that: a) the truss barrel structure is high in construction speed, and rocket assembly in extremely cold weather can be completed quickly; b) Can realize rapid removal and shorten the preparation time for rocket launching.

Drawings

Fig. 1 is a schematic view of the main structure and mechanical transmission of the present invention.

Fig. 2 is a schematic diagram of the withdrawing process of the present invention.

Figure 3 is a schematic view of the truss barrel bottom pulley of the present invention.

Fig. 4 is a schematic view of the guide rail rotating apparatus of the present invention.

Fig. 5 is a schematic view of the hinge between posts of the present invention.

Fig. 6 is a layout view of the heat-retaining and heating means of the present invention.

In the drawings, like reference numerals are used to designate like elements or structures, wherein: 1-truss barrel, 2-support truss, 3-slide rail, 4-hydraulic arm, 5-driving arm, 6-reinforced connecting beam, 7-track steering device, 8-hinge between columns, 9-rotating bearing, 10-main pulley, 11-anti-pulling pulley, 12-rail fastening device, 13-concrete bottom plate, 14-inclined strut, 15-heating blanket, 16-thermal insulation material, 17-windproof membrane material and 18-rocket.

Detailed Description

Example 1:

a rocket heat preservation protection device capable of being quickly retracted comprises an openable truss barrel, a power device, a slide rail and a heating and heat preservation device; a hinge and an opening are arranged on the vertical surface of the openable truss barrel so as to realize the opening and closing function of the truss barrel, and a pulley device is arranged at the bottom of the openable truss barrel; the power device provides power for withdrawing the truss barrel; the sliding rail is an I-shaped steel rail fixed on the bottom surface, the sliding rail can facilitate the removal and the collection of the truss barrel, and the pulling resistance of the truss barrel can be realized through the cooperation with the pulley device, so that the stability of the truss barrel under wind load is realized.

The truss barrel main body is a cylinder truss which is formed by welding two I-shaped columns and angle steel, the cross sections of the cylinder truss are semicircular, and pulleys are arranged at the bottoms of the hinge columns, the semicircular midpoint columns and the opening positions. The middle part of the truss barrel is provided with a 'scissors-type' connecting device, and the integral structure can be driven to open and close by the extension of the hydraulic arm. When the rocket needs to be launched, the truss structure is expanded by extending the first hydraulic arm through the scissor transmission device, and then the second hydraulic arm is contracted to pull the whole truss structure to move outwards, so that the structure can be withdrawn. 5 tracks are paved for opening, closing and withdrawing the truss barrel. The pulleys are all rotating pulleys, the track of the pulleys is two concentric circles in the opening process, and then the pulleys are converted into straight lines from curves. The rotatable pulley of truss barrel bottom is shown in figure 3, and the I-shaped track passes through buckle 12 to be fixed on concrete bottom plate 13, and main pulley 10 slides along the track in the process of opening and withdrawing, sets up two resistance to plucking pulleys 11 in the I-shaped track to offset the vertical pulling force that lateral force arouses in some truss motion processes, guarantee stable in structure. The main wheel 10 is provided with bearings 9 above it, whereby the turning of the pulleys is achieved. Fig. 5 is a schematic view of the hinge 8 between the pillars. In order to realize the rotation of the truss, double columns are arranged at the rotating positions, lug plates are welded between the two columns, and rotating shafts are added. Fig. 6 is a layout view of the heat-retaining and heating means. In order to realize the wind-resistant and heat-insulating functions, a wind-resistant film material is laid on the outer surface of the truss barrel so as to ensure the internal sealing property. The heat blanket is hung on the inner side of the column surface of the truss barrel by means of the connecting rod piece, and heat is provided to ensure the temperature balance around the arrow body. And a heat insulation material is filled between the windproof film material and the heating blanket to reduce heat loss.

Example 2:

The truss barrel is divided into 3 parts as shown in figure 2 to form a semicircular truss and two 1/4 circular trusses, and the trusses can be symmetrically opened and closed to form force points and are not easy to be clamped. The middle point column of the semicircular truss, the two 1/4 circular truss hinge columns and the column bottom of the opening position are respectively provided with a pulley device, the truss barrel uses 5 pulley devices, wherein 3 pulleys on the straight rail use fixed pulleys, through adding a rail steering device, the opening and the withdrawing of the rail can be completed only by laying 3 rails, the bottom of the semicircular truss barrel is fixed in the opening process of the truss barrel, the semicircular truss barrel is used as an acting point of the other two 1/4 circular trusses, the first hydraulic arms on the two sides can be contracted simultaneously, a rotating torque is generated to enable the pulleys to slide along the arc-shaped rail, after the 1/4 circular truss rotates 45 degrees, the pulleys reach the position of the sliding rail rotating device, and the truss barrel is opened quickly. In the rail steering device, the sliding rail is driven to rotate through the rotation of the motor, the rail drives the pulley to steer, so that the change of the sliding direction is realized, the pulley is not easy to block, and the motor of the rail steering device drives the pulley to steer to the straight rail through the sliding rail; and the second hydraulic arm extends along the straight rail direction, the truss barrel integrally moves through the transmission arm and is far away from the rocket main body, and therefore the truss barrel is retracted.

From figure 4 can obtain through increasing "track turns to the device", in the track turns to the device, through the rotation drive slide rail rotation of motor, the track drives the pulley and turns to realized the change of slip direction, thereby only need lay 3 tracks and can accomplish orbital opening and remove. The motor of the rail steering device rotates to drive the pulley to steer to the straight rail through the sliding rail. The hydraulic arm extends along the direction of the straight rail, the truss barrel integrally moves through the transmission arm and is far away from the rocket main body, and therefore the truss barrel is retracted. Fig. 3 is a schematic view of a rotatable pulley at the bottom of a truss barrel, an I-shaped rail is fixed on a concrete slab through a buckle, and a main wheel slides along the rail in the opening and withdrawing processes. Two anti-pulling pulleys are arranged in the I-shaped rail to offset vertical pulling force caused by lateral force in the movement process of a part of trusses and guarantee stable structure. The upper part of the main wheel is provided with a bearing, so that the steering of the pulley is realized. FIG. 5 is a schematic view of an intercolumnar hinge. In order to realize the rotation of the truss, double columns are arranged at the rotating positions, lug plates are welded between the two columns, and rotating shafts are added. Fig. 6 is a layout view of the heat-retaining and heating means. In order to realize the wind-resistant and heat-insulating functions, a wind-resistant film material is laid on the outer surface of the truss barrel so as to ensure the internal sealing property. The heat blanket is hung on the inner side of the column surface of the truss barrel by means of the connecting rod piece, and heat is provided to ensure the temperature balance around the arrow body. And a heat insulation material is filled between the windproof film material and the heating blanket to reduce heat loss. Rubber materials are adhered to the two upright columns at the opening of the truss barrel, so that the sealing performance of the barrel is guaranteed, and the heat dissipation is reduced; the truss cylinder column is connected with the guide rail through the lower column pulley, so that the pulling resistance of the truss cylinder is realized; the hydraulic arm realizes the opening and closing of the truss through a 'scissors-type' component. The device is in a closed state for a long time, and the retracting hydraulic arm in the scheme is in an open state for a long time. The long term exposure of the hydraulic arms causes losses to the hydraulic arms, reducing their reliability, and therefore the addition of the driving arms 5, the supporting girder 2 and the diagonal braces 14. Therefore, the hydraulic arm can extend outwards to drive the whole truss to withdraw.

Furthermore, the foregoing describes only some embodiments and alterations, modifications, additions and/or changes may be made without departing from the scope and spirit of the disclosed embodiments, which are intended to be illustrative rather than limiting. Furthermore, the described embodiments are directed to embodiments presently contemplated to be the most practical and preferred, it being understood that the embodiments should not be limited to the disclosed embodiments, but on the contrary, are intended to cover various modifications and equivalent arrangements included within the spirit and scope of the embodiments. Moreover, the various embodiments described above can be used in conjunction with other embodiments, e.g., aspects of one embodiment can be combined with aspects of another embodiment to realize yet another embodiment. In addition, each individual feature or element of any given assembly may constitute additional embodiments.

The foregoing description of the embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or to limit the disclosure. The various elements or features of a particular embodiment are generally not limited to that particular embodiment, but, where applicable, are interchangeable and can be used in a selected embodiment, even if not specifically shown or described. Such variations are not to be regarded as a departure from the disclosure, and all such modifications are intended to be included within the scope of the disclosure.

Accordingly, it is to be understood that the drawings and description are proffered by way of example to facilitate comprehension of the invention and should not be construed to limit the scope thereof.

Claims

1. A rocket heat preservation protection device capable of being quickly retracted comprises an openable truss barrel, a power device, a slide rail and a heating and heat preservation device; a hinge and an opening are arranged on the vertical surface of the openable truss barrel so as to realize the opening and closing function of the truss barrel, and a pulley device is arranged at the bottom of the openable truss barrel; the power device provides power for withdrawing the truss barrel; the sliding rail is an I-shaped rail fixed on the bottom surface, and can be matched with the pulley device to realize the anti-pulling of the truss barrel besides providing convenience for withdrawing and withdrawing the truss barrel, so that the stability of the truss barrel under wind load is realized;

the power device is realized by driving the bottom pulley to roll through hydraulic pressure, motor or cable stretching, and the heating and heat-insulating device comprises a truss outer coating material, a heat-insulating material and a heating device and is used for preventing wind, insulating heat and heating;

the truss outer wrapping film material is an ethylene-tetrafluoroethylene copolymer (ETFE) film, the heat insulation material is a heat insulation coating or a heat insulation filler, the heat insulation filler is one or more of aerosol heat insulation felt, phenolic foam and expanded and vitrified micro balls, the heating device is a heating blanket, the heat insulation material is arranged between the film material and the heating device, a ventilating pipeline is arranged in the cylinder wall, and an air blower connected with the ventilating pipeline is arranged at the bottom of the transmitting platform and also serves as the heating device.

2. A rocket thermal protection device according to claim 1, characterized in that: the truss barrel capable of being opened and closed is formed by welding an I-shaped steel column and an angle steel connecting piece, rotation of the truss barrel is achieved by welding lug plates at web positions of two stand columns and connecting the two stand columns through hinges, rubber materials are attached to the two stand columns at the opening of the truss barrel, accordingly, sealing performance of the barrel is guaranteed, heat dissipation is reduced, the power device is a combination of a hydraulic arm and a mechanical transmission device, and the hydraulic arm achieves opening and closing of a truss through a scissor-twisting type component.

3. A rocket thermal protection device according to claim 2, characterized in that: the middle part of the truss barrel is provided with a 'scissors-type' connecting device, the whole structure can be driven to open and close through the extension of the hydraulic arms, when the rocket needs to be launched, the truss structure is opened through the extension of the first hydraulic arm through the 'scissors-type' transmission device, and then the second hydraulic arm contracts to pull the whole truss structure to move outwards, so that the structure can be withdrawn.

4. A rocket thermal protection device according to any one of claims 1-3, wherein: the truss barrel is divided into 3 parts to form a semicircular truss and two 1/4 circular trusses, a plurality of pulley devices are respectively arranged at the middle point column of the semicircular truss, the hinge columns of the two 1/4 circular trusses and the column bottom of an opening position, the truss barrel further comprises a track steering device, the bottom of the semicircular truss is fixed in the opening process and serves as an acting point of the other two 1/4 circular trusses, first hydraulic arms on two sides contract to generate a rotating torque to enable the pulleys to slide along the arc-shaped sliding rails, and after the 1/4 circular trusses rotate for 45 degrees, the pulleys reach the position of the track steering device; the motor of the rail steering device rotates to drive the pulley to steer to the straight rail through the sliding rail, so that the change of the sliding direction is realized; and the second hydraulic arm extends along the straight rail direction, the truss barrel integrally moves through the transmission arm and is far away from the rocket main body, and therefore the truss barrel is retracted.

5. A rocket thermal protection device according to claim 4, characterized in that: the total number of the pulley devices is 5, the pulley devices are respectively arranged on the midpoint column of the semicircular truss, the hinge columns of the two 1/4 circular trusses and the two column bottoms at the opening positions, wherein 3 pulleys on the straight rail use fixed pulleys, and the other 2 pulleys use rotating pulleys.

6. A rocket thermal protection device according to any one of claims 1-3, wherein: the truss barrel is divided into two semi-barrels, pulley devices are respectively arranged at the hinge column, the semi-circle midpoint column and the column bottom of the opening position, 5 pulley devices and 5 sliding rails are used together, the pulley devices are all rotating pulleys, in the opening process, the first hydraulic arm contracts to generate rotating torque to enable the pulleys to slide along the arc-shaped sliding rails, and the two semi-barrel trusses are respectively driven by the rotating pulleys to rotate to the straight rails; then under the drive of the second hydraulic arm, the truss barrel integrally moves and is far away from the rocket main body, so that the truss barrel is retracted.

7. A rocket thermal protection device according to any one of claims 1-3, wherein: a truss section of thick bamboo passes through the post lower pulley group and is connected with the guide rail, realizes a truss section of thick bamboo resistance to plucking, and its concrete structure is: the I-shaped rail is fixed on a concrete slab through a buckle, a main wheel slides along a sliding rail in the opening and withdrawing processes, two anti-pulling pulleys are arranged in the I-shaped rail to offset vertical pulling force caused by lateral force in the movement process of a part of truss and ensure stable structure, a bearing is arranged at the upper part of the I-shaped rail, so that the steering of the pulleys is realized, the main wheel bears the dead weight and pressure of a truss main body, the two anti-pulling pulleys can provide wind load pull-out resistance for a truss barrel, a withdrawing hydraulic arm is in an opening state for a long time, and a transmission arm, a support truss and an inclined strut are arranged at the hydraulic arm, so that the hydraulic arm extends outwards to drive the whole truss to withdraw.

8. A method of using the rocket thermal insulation protection device of claim 3, wherein when the rocket needs to be launched, the first hydraulic arm is extended to open the truss structure through the 'scissor' type transmission device, and then the second hydraulic arm is contracted to pull the whole truss structure to move outwards, so that the structure can be withdrawn.