Carrier rocket transfer launching system
By installing thermal protection components on key components of the launch vehicle transport and launch system, the problem of gas flow ablation is solved, the component life is extended, and the maintenance cost and time is reduced.
Patent Information
- Application Number
- CN202510068767.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-16
- Publication Date
- 2025-04-01
AI Technical Summary
The gas flow ablation problem of the carrier rocket transport and launch system in the early stages of launch has caused serious damage to the rear parts of the vehicle, increasing maintenance costs and time.
A launch vehicle transport and launch system is designed to reduce the degree of ablation of these components by installing thermal protection components, including a heat-resistant scouring layer and a thermal shield, on the tail sections of the vehicle-mounted launch pad, tail bracket, gas baffle and hatch cover.
It effectively reduces the degree of ablation of components such as the vehicle-mounted launch pad, tail bracket, gas baffle and tail section of the hatch cover, extends its service life, increases the number of cycles, reduces maintenance costs and time, and reduces the performance requirements for trusses for installation of large parts.
Smart Images
Figure CN119737820A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of launch gas flow protection for carrier rockets, and in particular to a carrier rocket transport launch system. Background Art
[0002] Most launch vehicles still use vertical hot launch for launch. For the launch vehicle transfer launch system, at the beginning of the launch vehicle ignition and takeoff, the gas flow discharged from the tail of the launch vehicle acts on the tail of the launch vehicle transfer launch vehicle, severely burning the components at the tail of the vehicle.
[0003] Therefore, how to effectively reduce the degree of ablation of the components at the rear of the vehicle by the gas flow at the rear has become a technical problem that needs to be solved urgently by those skilled in the art. Summary of the invention
[0004] The invention provides a carrier rocket transfer and launch system, which is used to solve the problem of how to effectively reduce the degree of ablation of components and assemblies at the rear of the vehicle.
[0005] The present invention provides a carrier rocket transport launch system, comprising: Vehicle, capable of movement; The transport erection system, including the vehicle-mounted launch platform and the rocket body insulation cabin, is installed on the vehicle and can move with the vehicle; A first thermal protection assembly is mounted on the vehicle-mounted launch platform; The second thermal protection component is installed on the rocket body insulation cabin.
[0006] In some of the embodiments, the vehicle-mounted launch platform is provided with a deflector, support legs and a support plate; The first heat protection assembly includes: A first heat protection layer, applied on the deflector; A first heat-resistant scour layer, covering the outside of the supporting leg; A second heat-resistant scour layer is coated on the upper outer side of the support plate; The heat protection cover is arranged on the lower outer side of the support plate.
[0007] In some embodiments, the flow director comprises: deflector body; The heat protection cap is detachably connected to the top of the deflector body.
[0008] In some of the embodiments, the rocket body heat preservation cabin is provided with an openable and closable hatch cover, and one end is provided with an openable and closable gas damper; The second thermal protection assembly includes: A third heat-resistant scour layer is coated on the outside of one end of the hatch cover close to the gas damper; The second heat protection layer is coated on the outer surface of the third heat-resistant scour layer.
[0009] In some embodiments, the second heat protection assembly further comprises: The third heat protection layer is coated on the outer side of the gas baffle.
[0010] In some of the embodiments, the hatch cover is provided with a first hatch cover section and a second hatch cover section; the first hatch cover section is detachably connected to the second hatch cover section.
[0011] In some embodiments, it also includes: The tail bracket is arranged in the rocket body insulation cabin; when the gas damper is in the open state, the tail bracket can rotate so that one end surface of the tail bracket presses against the top surface of the support plate of the vehicle-mounted launch platform; The third thermal protection assembly can be installed on the tail bracket.
[0012] In some embodiments, the tailstock includes: Tail bracket body; The first lug, one end of which is connected to one side of the tailstock body; The second lug has one end rotatably connected to the bottom of the rocket body thermal insulation compartment, and the other end connected to the first lug; A locking block is mounted on the top surface of the tailstock body; The third thermal protection assembly includes: The fourth heat-resistant scour layer is coated on the top surface of the tail bracket body.
[0013] In some embodiments, the first ear is detachably connected to the tail bracket body; the second ear is detachably connected to the first ear; The third thermal protection assembly also includes: The fifth heat-resistant scouring layer; when the first ear is disconnected from the tail bracket body, the fifth heat-resistant scouring layer can cover the first disconnected portion of the tail bracket body.
[0014] In some embodiments, the locking block is detachably connected to the tailstock body; The third thermal protection assembly also includes: The sixth heat-resistant scouring layer; when the locking block is disconnected from the tail bracket body, the sixth heat-resistant scouring layer can be coated on the second disconnected portion of the tail bracket body.
[0015] The beneficial effects of the present invention are as follows: The carrier rocket transport launch system of the present invention provides thermal protection for the vehicle-mounted launching platform, tail bracket, gas baffle and the tail section of the hatch, and provides thermal protection for the main objects to be burned in the initial stage of the launch of the carrier rocket, thereby effectively reducing the degree of burning of the vehicle-mounted launching platform, tail bracket, gas baffle and the tail section of the hatch, and other rear vehicle parts and components, extending their service life, increasing their number of cycles, reducing maintenance costs, reducing maintenance time, and reducing the performance requirements for the truss crane used to install large parts. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] Figure 1 This is a schematic diagram of the launch vehicle before erection; Figure 2 This is a schematic diagram of the launch vehicle during erection; Figure 3 This is a schematic diagram of the launch vehicle after erection; Figure 4 This is a schematic diagram of the carrier rocket before launch.
[0017] In the attached drawings, 110, vehicle; 120, vehicle-mounted launching platform; 121, deflector; 1211, deflector body; 1212, heat protection cap; 122, support leg; 123, support plate; 130, rocket body insulation cabin; 131, hatch; 1311, first hatch section; 1312, second hatch section; 132, gas baffle; 140, tail bracket; 141, tail bracket body; 142, first ear; 143, second ear; 144, locking block; 150, erection arm; 200, launch vehicle. DETAILED DESCRIPTION
[0018] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.
[0019] According to the practice at the launch site, when a certain type of carrier rocket is launched to a height of 5m from the vehicle-mounted launch pad, the surface temperature of the tail bracket can reach a maximum of 2460K, and the maximum surface dynamic pressure is about 0.16MPa. When a certain type of carrier rocket is launched to a height of 7.8m from the vehicle-mounted launch pad, the surface temperature of the gas baffle reaches a maximum of 1816.4K, and the maximum surface dynamic pressure is about 0.15MPa. When a certain type of carrier rocket is launched to a height of 12.6m from the vehicle-mounted launch pad, the surface temperature of the tail section of the hatch of the rocket body insulation compartment reaches a maximum of 1379.1K, and the maximum surface dynamic pressure is about 0.13MPa. When a certain type of carrier rocket ignites but before taking off, the top surface temperature of the deflector reaches a maximum of 2960K, and the maximum dynamic pressure is about 0.74MPa; when a certain type of carrier rocket ignites and takes off at a height of 1.5m, the top surface temperature of the deflector reaches a maximum of 3290K, and the maximum dynamic pressure is about 1.08MPa; when a certain type of carrier rocket ignites and takes off at a height of 5m, the top surface temperature of the deflector reaches a maximum of 1650K, and the maximum dynamic pressure is about 0.24MPa. It can be seen that in the early stage of the launch of the carrier rocket, the gas flow discharged from the tail of the carrier rocket mainly ablates the vehicle-mounted launch platform, the tail bracket, the gas baffle of the rocket body insulation cabin, and the tail section of the hatch cover of the rocket body insulation cabin.
[0020] As described in the background technology, when a carrier rocket is launched in a vertical hot launch mode, at the initial stage of ignition and takeoff, the gas flow discharged from the tail of the carrier rocket acts on the tail of the carrier rocket transfer launch vehicle, which will seriously burn the parts and components at the tail of the vehicle. Due to the ablation of the rocket gas flow, a large number of parts and components at the tail of the rocket transfer launch vehicle need to be replaced or repaired and maintained after each launch of the rocket, which not only increases the maintenance cost and maintenance time of the transfer launch vehicle, but also requires the guarantee conditions of the truss crane to replace large parts. Such a maintenance method is not only time-consuming and labor-intensive, and inefficient, but also increases the production cost of the parts and components that need to be replaced, and has poor economic efficiency.
[0021] Therefore, how to effectively reduce the degree of ablation of components at the rear of the vehicle and solve the problems of high repair and maintenance cost and low efficiency caused by the ablation of the rocket gas flow on its transport and launch vehicle has become a technical problem that needs to be urgently solved by technical personnel in this field.
[0022] To improve the above problems, refer to Figure 1 , Figure 2 , Figure 3 and Figure 4The present invention provides a carrier rocket transport and launch system, including a carrier 110, a transport and erection system, a first thermal protection component and a second thermal protection component. The transport and erection system includes a vehicle-mounted launch platform 120, a rocket body insulation cabin 130, an erection arm 150 and a tail bracket 140. The carrier 110 can move on the ground. The transport and erection system is installed on the carrier 110 and can move with the carrier 110. Specifically, the vehicle-mounted launch platform 120 is installed at the tail of the carrier 110. When the carrier rocket 200 is erected and launched, the vehicle-mounted launch platform 120 supports the carrier rocket 200. The rocket body insulation cabin 130 is installed on the top of the carrier 110. The erection arm 150 is arranged in the rocket body insulation cabin 130. The carrier rocket 200 is carried on the erection arm 150. The tail bracket 140 is arranged in the rocket body insulation cabin 130 and installed at the tail of the carrier rocket 200. It should be noted that before the launch vehicle 200 is erected, the erection arm 150, the launch vehicle 200 and the tail bracket 140 are contained in the rocket body insulation cabin 130. When the launch vehicle 200 needs to be launched, the vehicle-mounted launch platform 120, the rocket body insulation cabin 130 and the launch vehicle 200 are brought to the launch position by means of the carrier 110. Then, the hatch 131 and the gas damper 132 are opened, the erection arm 150 and the tail bracket 140 can rotate, the erection arm 150 is converted from a horizontal state to a vertical state, and the launch vehicle 200 is driven to be converted from a horizontal state to a vertical state, and one end face of the tail bracket 140 is pressed against the top surface of the support plate 123 of the vehicle-mounted launch platform 120, and the launch vehicle 200 is located on the top surface of the tail bracket 140. The first thermal protection assembly is mounted on the vehicle-mounted launch platform 120, and the second thermal protection assembly is mounted on the rocket body insulation cabin 130. At the initial stage of the launch of the carrier rocket 200, the first thermal protection component provides thermal protection for the vehicle-mounted launch platform 120. The second thermal protection component provides thermal protection for the rocket body insulation cabin 130. Thermal protection is provided for the main objects to be ablated at the initial stage of the launch of the carrier rocket 200, effectively reducing the degree of ablation of the vehicle-mounted launch platform 120, the rocket body insulation cabin 130 and other components, extending their service life, increasing their number of cycles, reducing maintenance costs, reducing maintenance time, and reducing the performance requirements for the truss crane used to install large components.
[0023] Preferably, the vehicle 110 can be a hydraulic modular vehicle with multiple tires, which can evenly distribute the huge load to each tire, avoid a single axle or tire from bearing excessive load, ensure transportation safety, reduce damage to the road surface, and have relatively stable and efficient steering.
[0024] Specifically, in the example, Figure 1 , Figure 3 and Figure 4As shown, the vehicle-mounted launch platform 120 is provided with a deflector 121, a plurality of support legs 122 and a support plate 123. The deflector 121 is used to guide the gas flow at the tail of the launch vehicle 200. The support plate 123 is used to support the tail bracket 140. The first thermal protection assembly includes a first thermal protection layer, a first heat-resistant scouring layer, a second heat-resistant scouring layer and a thermal protection cover. The first thermal protection layer is coated on the deflector 121. It should be noted that since the part of the deflector 121 that is subjected to thermal scouring is mainly the top surface of the deflector 121, a thermal protection coating is coated on the top surface of the deflector 121 to form a first thermal protection layer on the top surface of the deflector 121 to achieve a heat insulation effect, effectively reduce the degree of ablation of the top surface of the deflector 121, and mitigate the thermal shock effect. The outer side of each support leg 122 is coated with a first heat-resistant scouring layer to improve the heat scouring resistance of each support leg 122. The outer side of each support arm of the upper part of the support plate 123 is coated with a second heat erosion resistant layer to improve the heat erosion resistance of each support plate 123. The heat protection cover is arranged outside the lower part of the support plate 123 to improve the high temperature erosion resistance of the support plate 123.
[0025] Preferably, the first heat-resistant scouring layer is a steel plate, and the steel plate is used to cover the support leg 122 to mitigate the scouring effect of the gas flow on the support leg 122 .
[0026] Preferably, the second heat-resistant scouring layer is FD105 dust-free asbestos cloth, and the FD105 dust-free asbestos cloth is used to wrap and cover each support arm on the upper part of the support plate 123 to reduce the scouring effect of the gas flow on the upper part of the support plate 123.
[0027] Preferably, the heat shield is made of stainless steel, which has the ability to resist high temperature erosion of 300°C-400°C.
[0028] Preferably, the deflector 121 includes a deflector body 1211 and a heat protection cap 1212. The top surface of the deflector body 1211 is coated with a first heat protection layer. The heat protection cap 1212 is detachably connected to the top of the deflector body 1211, replacing the traditional non-detachable form, so that only the heat protection cap 1212 can be disassembled, replaced and installed for use.
[0029] Preferably, the heat protection cap 1212 and the top of the deflector body 1211 can be detachably connected by means of snap connection, screw connection or riveting.
[0030] Specifically, in the example, Figure 1 , Figure 2 and Figure 3As shown, a hatch cover 131 that can be opened and closed is provided on the top of the rocket body insulation compartment 130. An openable and closed gas damper 132 is provided at one end of the rocket body insulation compartment 130 close to the vehicle-mounted launch platform 120, that is, an openable and closed gas damper 132 is provided at the tail end of the rocket body insulation compartment 130. Before the launch vehicle 200 is launched, the hatch cover 131 and the gas damper 132 are in a closed state to prevent the gas flow from invading the rocket body insulation compartment 130.
[0031] Specifically, in the exemplary embodiment, the second heat protection component includes a third heat-resistant scouring layer, a second heat protection layer and a third heat protection layer. The third heat-resistant scouring layer is coated on the outside of one end of the hatch cover 131 in a closed state near the gas damper 132. The second heat protection layer is coated on the outer surface of the third heat-resistant scouring layer. The third heat-resistant scouring layer and the second heat protection layer can provide heat protection for the tail section of the hatch cover 131. A heat protection coating is coated on the outer surface of the third heat-resistant scouring layer to form a second heat protection layer on the outer surface of the third heat-resistant scouring layer to achieve a heat insulation effect, effectively reduce the degree of ablation of the tail section of the hatch cover 131, and mitigate the thermal shock effect. Since the gas damper 132 is connected to the rocket body insulation cabin 130 through an opening and closing mechanism, it is not easy for the gas damper 132 to be separated from the rocket body insulation cabin 130. Therefore, the outer side of the gas damper 132 in a closed state is coated with a third heat protection layer to provide heat protection for the gas damper 132. Specifically, a thermal protection coating is applied to the outer side of the gas baffle 132 to form a third thermal protection layer on the outer side of the gas baffle 132 to achieve a heat insulation effect, effectively reduce the degree of ablation of the outer side of the gas baffle 132, and mitigate the thermal shock effect. It can also effectively prevent the outer side of the gas baffle 132 from thermal fatigue, thermal cracking and thermal fracture under multiple thermal shock loads, ensure the reliability of the gas baffle 132, and extend the service life of the gas baffle 132. It has been verified in practice that each time a launch mission of the carrier rocket 200 is completed, the third thermal protection layer on the outer side of the gas baffle 132 only partially falls off. Therefore, the gas baffle 132 can be reused by simply filling the fallen part with thermal protection coating.
[0032] Preferably, the third heat-resistant scour layer is a steel plate with a thickness of 5 mm, which can better resist the thermal scour of the tail section of the hatch cover 131 by the gas flow.
[0033] Preferably, the second thermal protection layer extends from the rear end of the hatch cover 131 to the front end of the hatch cover 131, with a length of 1.5m-2.5m. It has been verified in practice that each time the launch mission of the carrier rocket 200 is completed, the second thermal protection layer does not partially fall off.
[0034] Preferably, the hatch cover 131 is provided with a first hatch cover section 1311 and a second hatch cover section 1312, and the first hatch cover section 1311 is detachably connected to the second hatch cover section 1312. The hatch cover 131 adopts a modular design and is assembled in a detachable connection manner. Compared with the traditional non-detachable form, it is convenient for the installation, use, and removal and replacement of the tail section of the hatch cover 131. The second hatch cover section 1312 is arranged close to the gas damper 132, while the first hatch cover section 1311 is arranged away from the gas damper 132. The third heat-resistant scour layer is coated on the outside of the second hatch cover section 1312 of the hatch cover 131 in the closed state. The second heat protection layer is coated on the outer surface of the third heat-resistant scour layer. The third heat-resistant scour layer and the second heat protection layer can provide heat protection for the second hatch cover section 1312.
[0035] Preferably, the first hatch cover section 1311 and the second hatch cover section 1312 can be connected by means of snap connection, screw connection or riveting.
[0036] Specifically, in the exemplary embodiment, the third heat protection assembly can be installed on the tail bracket 140. The third heat protection assembly can provide heat protection for the tail bracket 140, effectively reducing the degree of ablation of the tail bracket 140 and other components, extending their service life, increasing their number of cycles, reducing maintenance costs, reducing maintenance time, and reducing the performance requirements for the truss crane used to install large components.
[0037] Specifically, in the example, Figure 2 , Figure 3 and Figure 4 As shown, the tail bracket 140 includes a tail bracket body 141, a first ear 142, a second ear 143 and a locking block 144. One end of the first ear 142 is connected to one side of the tail bracket body 141. One end of the second ear 143 is rotatably connected to the bottom of the rocket body insulation compartment 130, and the other end is connected to the first ear 142. The locking block 144 is installed on the top surface of the tail bracket body 141, and can be connected or disconnected with the tail of the carrier rocket 200, so that the tail bracket body 141 is connected or disconnected with the tail of the carrier rocket 200. After the carrier rocket 200 is completed, as shown in FIG. Figure 3 As shown in FIG. 1 , the tail bracket 140 and the carrier rocket 200 are mounted on the top surface of the vehicle-mounted launch platform 120. Before the carrier rocket 200 is launched, Figure 4 As shown, the second ear 143 is disconnected from the first ear 142 , the hatch 131 is closed, the gas damper 132 is closed, and the locking block 144 is disconnected from the launch vehicle 200 .
[0038] Specifically, in the exemplary embodiment, the third heat protection component includes a fourth heat-resistant scouring layer, a fifth heat-resistant scouring layer and a sixth heat-resistant scouring layer. The fourth heat-resistant scouring layer is coated on the top surface of the tail bracket body 141 to provide heat protection for the tail bracket body 141. The first ear 142 is detachably connected to the tail bracket body 141, and the second ear 143 is detachably connected to the first ear 142, replacing the traditional non-detachable form. Before launching, the first ear 142 is disconnected from the tail bracket body 141 to separate the first ear 142 from the gas flow scouring area. At the same time, the first ear 142 and the second ear 143 are disconnected so that the second ear 143 can be flipped back into the arrow body insulation cabin 130 to avoid the gas flow. When the first lug 142 is disconnected from the tail bracket body 141, the fifth heat-resistant scour layer can be coated on the first disconnected portion of the tail bracket body 141 to provide heat protection for the first disconnected portion of the tail bracket body 141. The locking block 144 is detachably connected to the tail bracket body 141, replacing the traditional non-detachable form, so that the locking block 144 can be separated from the tail bracket body 141 before the launch of the carrier rocket 200, so that the locking block 144 avoids the gas flow. When the locking block 144 is disconnected from the tail bracket body 141, the sixth heat-resistant scour layer can be coated on the second disconnected portion of the tail bracket body 141 to provide heat protection for the second disconnected portion of the tail bracket body 141.
[0039] Preferably, the first ear 142 and the rear bracket body 141 can be connected by clamping, screwing or riveting. The second ear 143 and the first ear 142 can be connected by clamping, screwing or riveting. There are more than two locking blocks 144, which are evenly distributed along the circumference of the rear bracket body 141 and are respectively connected to the top surface of the rear bracket body 141 by clamping, screwing or riveting.
[0040] Preferably, the fourth heat-resistant scour layer is a steel plate with a thickness of 20 mm, 30 mm or 40 mm, which can resist the scour of the gas flow. The thicker the fourth heat-resistant scour layer is, the more times it can be recycled; the thinner the fourth heat-resistant scour layer is, the lower the manufacturing cost. The fourth heat-resistant scour layer can be recycled for more than or equal to 6 times.
[0041] Preferably, the fifth heat-resistant scour layer is a steel plate. When the first lug 142 is separated from the rear bracket body 141, the steel plate is used to cover the first disconnected portion of the rear bracket body 141. Here, it should be noted that the first disconnected portion of the rear bracket body 141 refers to a first mounting hole reserved on the rear bracket body 141 for mounting the first lug 142.
[0042] Preferably, the sixth heat-resistant scour layer is a steel plate. When the locking block 144 is separated from the rear bracket body 141, the steel plate is used to cover the second disconnected portion of the rear bracket body 141. Here, it should be pointed out that the second disconnected portion of the rear bracket body 141 refers to a second mounting hole reserved on the rear bracket body 141 for mounting the locking block 144.
[0043] The carrier rocket transfer launch system of this scheme provides thermal protection for the vehicle-mounted launch platform, tail bracket, gas baffle and the tail section of the hatch respectively, and provides thermal protection for the main objects that are burned in the early stage of the carrier rocket launch, thereby effectively reducing the degree of burning of the vehicle-mounted launch platform, tail bracket, gas baffle and the tail section of the hatch, and other rear components, extending their service life, increasing their number of cycles, reducing maintenance costs, reducing maintenance time, and reducing performance requirements for truss cranes used to install large components.
[0044] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.
[0045] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.
[0046] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0047] In the present invention, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.
[0048] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.
Claims
1. A carrier rocket transport launch system, characterized in that: include: Vehicle, capable of movement; The transport and erection system includes a vehicle-mounted launch platform and a rocket body insulation cabin, which is installed on the vehicle and can move with the vehicle; A first thermal protection assembly is installed on the vehicle-mounted launch platform; The second thermal protection component is installed on the rocket body insulation cabin.
2. The carrier rocket transport launch system according to claim 1, characterized in that: The vehicle-mounted launch platform is provided with a deflector, support legs and a support plate; The first heat protection component comprises: A first heat protection layer, coated on the deflector; A first heat-resistant scour layer, covering the outer side of the supporting leg; A second heat-resistant scour layer, covering the upper outer side of the support plate; A heat protection cover is arranged on the outer side of the lower part of the support plate.
3. The carrier rocket transport launch system according to claim 2, characterized in that: The deflector comprises: deflector body; A heat protection cap is detachably connected to the top of the deflector body.
4. The carrier rocket transport launch system according to claim 2, characterized in that: The rocket body heat preservation cabin is provided with an openable and closable cabin cover, and one end is provided with an openable and closable gas damper; The second heat protection component comprises: A third heat-resistant scour layer, covering the exterior of one end of the hatch cover close to the gas damper; The second heat protection layer is coated on the outer surface of the third heat-resistant scour layer.
5. The carrier rocket transport launch system according to claim 4, characterized in that: The second heat protection component also includes: The third heat protection layer is coated on the outer side of the gas baffle.
6. The carrier rocket transport launch system according to claim 4, characterized in that: The hatch cover is provided with a first hatch cover section and a second hatch cover section; the first hatch cover section is detachably connected to the second hatch cover section.
7. The carrier rocket transport launch system according to claim 4, characterized in that: Also includes: A tail bracket is arranged in the arrow body thermal insulation cabin; When the gas damper is in an open state, the tail bracket can rotate so that one end surface of the tail bracket presses against the top surface of the support plate of the vehicle-mounted launch platform; The third heat protection assembly can be installed on the tail bracket.
8. The carrier rocket transport launch system according to claim 7, characterized in that: The tail bracket comprises: Tail bracket body; A first lug, one end of which is connected to one side of the tail bracket body; A second lug, one end of which is rotatably connected to the bottom of the rocket body thermal insulation compartment, and the other end of which is connected to the first lug; A locking block is mounted on the top surface of the tail bracket body; The third heat protection component comprises: The fourth heat-resistant scouring layer is coated on the top surface of the tail bracket body.
9. The carrier rocket transport launch system according to claim 8, characterized in that: The first support ear is detachably connected to the tail bracket body; the second support ear is detachably connected to the first support ear; The third heat protection assembly also includes: A fifth heat-resistant scouring layer; when the first lug is disconnected from the tail bracket body, the fifth heat-resistant scouring layer can be coated on the first disconnected portion of the tail bracket body.
10. The carrier rocket transport launch system according to claim 8, characterized in that: The locking block is detachably connected to the tail bracket body; The third heat protection assembly also includes: The sixth heat-resistant scouring layer; when the locking block is disconnected from the tail bracket body, the sixth heat-resistant scouring layer can be coated on the second disconnected portion of the tail bracket body.