A detachable guide rail type launch vehicle pre-flight heating and holding device
By designing a detachable rail-mounted pre-launch heating and insulation device for launch vehicles, the reliability of heating and insulation and the impact on launch of small and medium-sized launch vehicles in low-temperature environments have been solved, achieving reliable heating and insulation functions and normal launch in low-temperature environments.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- XIAN AEROSPACE PROPULSION TECH INST
- Filing Date
- 2023-02-07
- Publication Date
- 2026-06-23
AI Technical Summary
Existing heating and insulation methods for small and medium-sized launch vehicles before launch have problems such as affecting aerodynamic performance, causing foreign objects to fall off, and limiting the launch window, making it impossible to reliably complete the heating and insulation function in low-temperature environments.
Design a detachable rail-mounted launch vehicle pre-launch heating and insulation device, including a detachment mechanism and a heating and insulation mechanism, which are stored separately in the storage state. During launch, the heating and insulation mechanism is heated by the detachment mechanism. During launch separation, the detachment mechanism takes the rail-mounted launch vehicle away to ensure normal derailment.
It achieves reliable heating and insulation functions in low-temperature environments, ensuring normal launch of the launch vehicle without affecting aerodynamic performance and launch window. Furthermore, the heating components are reusable and adaptable to launch vehicles of different sizes and specifications.
Smart Images
Figure CN116238721B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to a detachable pre-launch heating and insulation device for launch vehicles, applicable to the heating and insulation of launch vehicles for certain rail-guided launch systems, and belongs to the field of heating and insulation for small and medium-sized launch vehicles. Background Technology
[0002] A certain type of launch vehicle requires the launch device to be heated and kept warm before launch, with the main object to be kept warm being the launch vehicle's payload bay.
[0003] Current heating methods for small and medium-sized launch vehicles generally involve wrapping the exterior of the launch vehicle with insulating foam panels or with heating blankets. The former, for launches of small and medium-sized vehicles, has drawbacks due to the slow initial launch vehicle speed, potentially affecting the vehicle's aerodynamic performance and causing debris to detach and impact control surfaces and wings. The latter, for inclined launches of small and medium-sized vehicles, requires the removal of the heating blankets before launch due to launch window and testing procedures, which can lead to the inability to heat the vehicle after it has been erected. Summary of the Invention
[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a detachable rail-mounted pre-launch heating and insulation device for launch vehicles, which can reliably complete the heating and insulation function of the launch vehicle in a low-temperature environment, while ensuring normal derailment and launch.
[0005] The solution of the present invention is: a detachable rail-mounted pre-launch heating and insulation device for a launch vehicle, the device comprising a detachment mechanism and a heating and insulation mechanism;
[0006] In storage, the detachment mechanism and the heating and insulation mechanism are independent of each other and stored separately.
[0007] In the heating operation state, the heating and insulation mechanism is supported by the detachment mechanism, and the heating and insulation mechanism heats and insulates the carrier.
[0008] In the launch separation state, the detachment mechanism will remove the heating and insulation mechanism from the rail-mounted launch device of the rail-mounted launch vehicle, ensuring that the launch vehicle leaves the rail normally.
[0009] Preferably, the heating and heat preservation mechanism includes an electronic temperature controller, a first heating and heat preservation component, and a second heating and heat preservation component;
[0010] The first and second heating and insulation components have symmetrical structures, with their inner surfaces fitting against the side walls of the payload compartment of the launch vehicle, and are used to heat and insulate the payload compartment of the launch vehicle.
[0011] An electronic temperature controller is connected to the first heating and insulation component and the second heating and insulation component via cables, and is used to regulate the heating temperature of the first heating and insulation component and the second heating and insulation component in real time.
[0012] Preferably, the first heating and insulation component and the second heating and insulation component have the same structure, including an insulation layer, a heating layer and an antistatic layer; the innermost layer closest to the carrier is the antistatic layer, the middle layer is the heating layer, and the outermost layer is the insulation layer. The antistatic layer is made of conductive material and is used for electrostatic protection. The heating layer contains resistance wires with a shielding layer wrapped around its surface for heating. The insulation layer is made of heat-insulating foam material and is used to isolate internal and external heat exchange.
[0013] Preferably, the electronic temperature controller includes a power supply, a four-loop controller, a first single-pole switch, a second single-pole switch, a third single-pole switch, a solid-state relay SSR1, a solid-state relay SSR2, and a fuse;
[0014] The power supply outputs AC power. The negative terminal of the power supply is connected to one end of a fuse. The other end of the fuse is connected to the first stationary terminals of the second and third single-pole switches and the second stationary terminal of the first single-pole switch. The second stationary terminals of the first and second single-pole switches and the first stationary terminal of the third single-pole switch are left floating. A solid-state relay SSR1 is connected in series between the moving terminal of the first single-pole switch and the resistance wire T1 in the first heating and insulation component. A solid-state relay SSR2 is connected in series between the moving terminal of the first single-pole switch and the resistance wire T2 in the second heating and insulation component. The moving terminal of the second single-pole switch is also connected between the solid-state relay SSR1 and the resistance wire T1 in the first heating and insulation component. The moving terminal of the third single-pole switch is also connected between the solid-state relay SSR2 and the resistance wire T2 in the second heating and insulation component.
[0015] The switching on and off of solid-state relays SSR1 and SSR2 is controlled by a four-loop controller.
[0016] Preferably, the electronic temperature controller further includes a first mechanical overheat protector KT1 and a second mechanical overheat protector KT2;
[0017] The first mechanical overheat protector KT1 is connected between the resistance wire T1 in the first heating and insulation assembly and the positive terminal of the power supply.
[0018] The second mechanical overheat protector KT2 is connected between the resistance wire T2 in the second heating and insulation assembly and the positive terminal of the power supply.
[0019] The first mechanical overheat protector KT1 and the second mechanical overheat protector KT2 contain a thermistor element, which will automatically disconnect the circuit when the heating temperature exceeds the set first threshold.
[0020] Preferably, the electronic temperature controller further includes a first temperature sensor T1 and a second temperature sensor T2;
[0021] The first temperature sensor T1 is used to detect the temperature of the insulation layer of the first heating and insulation component and feed it back to the four-loop controller.
[0022] The second temperature sensor T2 is used to detect the temperature of the insulation layer of the second heating and insulation component and feed it back to the four-loop controller.
[0023] When the temperature of the insulation layer of the first or second heating and insulation component exceeds the set second threshold, the four-loop controller controls the solid-state relay SSR1 or solid-state relay SSR2 to disconnect the circuit.
[0024] Preferably, the electronic temperature controller further includes an alarm;
[0025] The four-loop controller is connected to the alarm. When the four-loop controller detects that the insulation layer of the first heating and insulation component 4-1 or the second heating and insulation component 4-2 is overheated, it sends an alarm signal to the alarm for overheating alarm.
[0026] Preferably, the detachment mechanism includes a first support component and a second support component. The first support component and the second support component have the same structure and are used opposite to each other. Both include a rotating support base, a rotating shaft, and a rotating arm. The rotating support base is used to be fixedly installed on the guide rail launching device. The rotating shaft cooperates with the arc-shaped sliding groove of the rotating support base and can reciprocate in the sliding groove under the action of external force. The lower part of the rotating arm is connected to the rotating shaft, and the upper part is inserted into the first heating and heat preservation component or the second heating and heat preservation component for fixation. When the rotating shaft moves in the rotating support base, it helps to drive the first heating and heat preservation component or the second heating and heat preservation component to rotate and separate.
[0027] Preferably, the first support component and the second support component further include a nylon rope. One end of the nylon rope is tied to the top of the rotating arm, and the other end is suspended in the air. When the first heating and heat preservation component and the second heating and heat preservation component need to be detached, the nylon rope is pulled to separate the first heating and heat preservation component and the second heating and heat preservation component. The rotating shaft slides out of the arc-shaped groove of the rotating support seat to complete the detachment action.
[0028] Preferably, the heating and heat preservation mechanism further includes Velcro, which is installed on the inner surfaces of the top of the first heating and heat preservation component and the second heating and heat preservation component, and is used to connect the first heating and heat preservation component and the second heating and heat preservation component during heating.
[0029] The advantages of this invention compared to the prior art are:
[0030] (1) The present invention adopts a detachable pre-launch heating and insulation device for the launch vehicle, which can ensure normal heating and insulation function before and after the erection of small and medium-sized launch vehicles. At the same time, the heating and insulation device can be reliably detached manually or electrically 5 minutes before the launch vehicle, without affecting the normal launch of the launch vehicle.
[0031] (2) The heating and insulation component of the present invention adopts a design method that combines an antistatic layer, a heating layer and an insulation layer. The heating and insulation device provided is highly safe and has high heating efficiency. It can enable the carrier to reach the required temperature environment in a short time. At the same time, the matching detachment mechanism is simple, reliable, and the detachment process is controllable.
[0032] (4) The heating and heat preservation mechanism of the present invention measures the temperature of the heat preservation component in real time and is equipped with a solid-state relay and a mechanical protector. It automatically protects the heating and heat preservation mechanism from overheating in two levels, which greatly improves the safety of the heating and heat preservation mechanism.
[0033] (5) Because the heating and insulation mechanism and the detachment mechanism are separable, the heating and insulation device provided by this invention can be replaced and reused multiple times. Compared with the existing method of pasting insulation foam boards or heating blankets, this invention can be adapted and optimized to meet the heating and insulation needs of orbital launch vehicles of different sizes and specifications under low-temperature conditions. Attached Figure Description
[0034] Figure 1 This is a schematic diagram of the heating and heat preservation device according to an embodiment of the present invention;
[0035] Figure 2 This is a schematic diagram of the composition of the first heating and heat preservation component and the second heating and heat preservation component of the present invention;
[0036] Figure 3 This is a schematic diagram of the working circuit of the electronic temperature controller for the heating and heat preservation mechanism of the present invention.
[0037] Figure 4 This is a schematic diagram of the heating and heat preservation device of the present invention used on a launching device;
[0038] Figure 5(a) is a schematic diagram of the intermediate state during the detachment process of the heating and heat preservation device of the present invention.
[0039] Figure 5(b) is a schematic diagram of the final state of the heating and heat preservation device of the present invention during the detachment process.
[0040] Figure 6 This is a schematic diagram of the installation of the heating and heat preservation device according to an embodiment of the present invention. Detailed Implementation
[0041] The present invention will be further described below with reference to the embodiments.
[0042] To address this requirement and drawing upon mature domestic and international launch vehicle heating and insulation devices, this invention designs a heating and insulation device suitable for use with this type of launch vehicle in a rail-guided launch system. This heating and insulation device operates in an ambient temperature of -20°C and, in conjunction with a temperature controller, can provide continuous heating and insulation for over 12 hours. Furthermore, the portion of the heating and insulation device in close contact with the launch vehicle includes an anti-static layer and a temperature sensor, significantly improving operational safety. In addition to its heating and insulation function, this device is designed to detach before launch, even at a launch elevation angle of 87°, without interfering with the launch vehicle's normal derailment.
[0043] like Figure 1 As shown, the detachable rail-mounted vehicle heating and insulation device designed in this invention consists of two parts: a detachment mechanism and a heating and insulation mechanism. In conjunction with the launch device, it heats and insulates the vehicle to ensure that the vehicle can leave the rail normally.
[0044] In storage, the detachment mechanism and the heating and insulation mechanism are independent of each other and stored separately.
[0045] In the heating operation state, the heating and insulation mechanism is supported by the detachment mechanism, and the heating and insulation mechanism heats and insulates the carrier.
[0046] In the launch separation state, the detachment mechanism will remove the heating and insulation mechanism from the rail-mounted launch device of the rail-mounted launch vehicle, ensuring that the launch vehicle leaves the rail normally.
[0047] In storage, these two parts can be separated and stored independently; when used on a launching device, they can be quickly assembled and used on a rack. Furthermore, the heating and insulation device uses common materials, is low in cost, easy to manufacture, requires minimal storage conditions, and is simple to operate.
[0048] The heating and heat preservation mechanism includes an electronic temperature controller, a first heating and heat preservation component 4-1, and a second heating and heat preservation component 4-2;
[0049] The first heating and insulation component 4-1 and the second heating and insulation component 4-2 are symmetrical in structure, with their inner surfaces fitting against the side walls of the payload compartment of the launch vehicle, and are used to heat and insulate the payload compartment of the launch vehicle.
[0050] An electronic temperature controller is connected to the first heating and insulation component 4-1 and the second heating and insulation component 4-2 via cables, and is used to adjust the heating temperature of the first heating and insulation component 4-1 and the second heating and insulation component 4-2 in real time.
[0051] like Figure 2As shown, the first heating and insulation component 4-1 and the second heating and insulation component 4-2 have the same structure, including an insulation layer, a heating layer and an antistatic layer; the innermost layer closest to the carrier is the antistatic layer, the middle layer is the heating layer, and the outermost layer is the insulation layer. The antistatic layer is made of conductive material and is used for electrostatic protection; the heating layer contains resistance wires with a shielding layer wrapped on the surface for heating; the insulation layer is made of heat-insulating foam material and is used to isolate internal and external heat exchange.
[0052] like Figure 3 As shown, the electronic temperature controller includes a power supply, an OHR-E704A four-loop controller, a first single-pole switch, a second single-pole switch, a third single-pole switch, a solid-state relay SSR1, a solid-state relay SSR2, and a fuse RT18-32.
[0053] The power supply outputs 220V AC. The negative terminal of the power supply is connected to one end of fuse RT18-32. The other end of fuse RT18-32 is connected to the first stationary terminal of the second single-pole switch and the third single-pole switch, and the second stationary terminal of the first single-pole switch. The second stationary terminal of the first single-pole switch, the second stationary terminal of the second single-pole switch, and the first stationary terminal of the third single-pole switch are left floating. A solid-state relay SSR1 is connected in series with the resistance wire T1 in the first heating and insulation component 4-1. A solid-state relay SSR2 is connected in series with the resistance wire T2 in the first heating and insulation component 4-2. The solid-state relay SSR1 is also connected to the moving terminal of the second single-pole switch between the resistance wire T1 in the first heating and insulation component 4-1 and the moving terminal of the third single-pole switch between the resistance wire T2 in the second heating and insulation component 4-2.
[0054] The switching on and off of solid-state relays SSR1 and SSR2 is controlled by a four-loop controller.
[0055] This invention uses three sets of single-pole switches to select the solid-state relays to be connected in the heating circuit. When the first single-pole switch is closed (i.e., the moving end of the first single-pole switch is connected to the second stationary end), both solid-state relays SSR1 and SSR2 are connected to the heating circuit. When the second single-pole switch is closed (i.e., the moving end of the second single-pole switch is connected to the first stationary end), solid-state relay SSR2 is disconnected from the heating circuit. When the third single-pole switch is closed (i.e., the moving end of the third single-pole switch is connected to the first stationary end), solid-state relay SSR1 is connected to the heating circuit.
[0056] The electronic temperature controller also includes a first mechanical overheat protector KT1 and a second mechanical overheat protector KT2.
[0057] The first mechanical overheat protector KT1 is connected between the resistance wire T1 in the first heating and insulation assembly 4-1 and the positive terminal of the power supply.
[0058] The second mechanical overheat protector KT2 is connected between the resistance wire T2 in the second heating and insulation component 4-2 and the positive terminal of the power supply.
[0059] The first mechanical overheat protector KT1 and the second mechanical overheat protector KT2 contain a thermistor element, which will automatically disconnect the circuit when the heating temperature exceeds the set first threshold.
[0060] The electronic temperature controller also includes a first temperature sensor T1 and a second temperature sensor T2;
[0061] The first temperature sensor T1 is used to detect the temperature of the insulation layer of the first heating and insulation component 4-1 and feed it back to the four-loop controller.
[0062] The second temperature sensor T2 is used to detect the temperature of the insulation layer of the second heating and insulation component 4-2 and feed it back to the four-loop controller;
[0063] When the temperature of the insulation layer of the first heating and insulation component 4-1 or the second heating and insulation component 4-2 exceeds the set second threshold, the four-loop controller controls the solid-state relay SSR1 or solid-state relay SSR2 to disconnect the circuit. If the first threshold is higher than the second threshold, the entire circuit automatically provides overheat protection for the heating and insulation mechanism in two levels, greatly improving the safety of the heating and insulation mechanism.
[0064] The electronic temperature controller also includes an LTE-1101M alarm;
[0065] The four-loop controller is connected to the alarm LTE-1101M. When the four-loop controller detects that the insulation layer of the first heating and insulation component 4-1 or the second heating and insulation component 4-2 is overheated, it sends an alarm signal to the alarm LTE-1101M for overheat alarm.
[0066] The electronic temperature controller is powered by 220V AC and uses a four-loop temperature controller and temperature sensors to control the heating and insulation of the launch vehicle cabin. To ensure heating safety, a mechanical overheat protector is connected in series in the control loop as a protective switch, ensuring high reliability and safety throughout the heating and insulation process.
[0067] The detachment mechanism includes a first support component and a second support component. The first and second support components have the same structure and are used relative to each other. Both include a rotating support base 1, a rotating shaft 2, and a rotating arm 3. The rotating support base 1 is used to be fixedly installed on the guide rail launching device by screws. The rotating shaft 2 cooperates with the arc-shaped sliding groove of the rotating support base 1 and can reciprocate in the sliding groove under the action of external force. The lower part of the rotating arm 3 is connected to the rotating shaft 2, and the upper part is inserted into the first heating and heat preservation component 4-1 or the second heating and heat preservation component 4-2 for fixation. When the rotating shaft 2 moves in the rotating support base 1, it helps to drive the first heating and heat preservation component 4-1 or the second heating and heat preservation component 4-2 to rotate and separate.
[0068] The heating and heat preservation mechanism also includes Velcro 5, which is installed on the inner surfaces of the top of the first heating and heat preservation component 4-1 and the second heating and heat preservation component 4-2, and is used to connect the first heating and heat preservation component 4-1 and the second heating and heat preservation component 4-2 during heating.
[0069] The first and second support components also include nylon ropes. One end of the nylon rope is tied to the top of the rotating arm 3, and the other end is suspended in the air. When it is necessary for the first heating and insulation component 4-1 and the second heating and insulation component 4-2 to detach, the nylon rope is pulled to separate the first heating and insulation component 4-1 and the second heating and insulation component 4-2. The rotating shaft 2 then slides out of the arc-shaped groove of the rotating support seat 1, completing the detachment action. Other ropes can also be used instead of nylon ropes.
[0070] The heating and insulation device operates as follows: Assemble the heating and insulation mechanism and the detachment mechanism, connect the temperature controller cable, then install the heating and insulation device into the launch vehicle support base, and secure it with Velcro straps on both sides to ensure reliable fixation. Finally, tidy up the power supply cable of the heating and insulation device and connect the power supply for heating and insulation. When the launch vehicle is launched at a high elevation angle, the nylon rope needs to be pulled to detach the heating and insulation device to prevent collisions between the launch vehicle's rudders and wings and the heating and insulation device, allowing the launch vehicle to derail normally.
[0071] The assembly method of the above-mentioned detachable rail-mounted pre-launch heating and insulation device for a launch vehicle includes the following steps:
[0072] S1. The rotating support base 1 is mounted on the rail-type launcher by screws.
[0073] S2. The rotating shaft, rotating arm and first heating and heat preservation component 4-1 of the first support component are fixedly connected in sequence. The rotating shaft, rotating arm and second heating and heat preservation component 4-2 of the second support component are fixedly connected in sequence. Then the rotating shaft 2 of the first support component and the second support component are installed into the rotating support base 1.
[0074] S3. Adjust the height of the first heating and heat preservation component 4-1 and the second heating and heat preservation component 4-2 so that their inner arc surfaces are in close contact with the outer wall of the carrier, and fix the first heating and heat preservation component 4-1 and the second heating and heat preservation component 4-2 together with Velcro.
[0075] S4. Tie a nylon rope to the top of the first and second support component swing arms and connect it to the power supply cable. Figure 4 As shown;
[0076] S5. After the launching device is erected to the specified launch elevation angle, pull the nylon rope to unlock the Velcro 5. At the same time, the pivot of the first support component slides upward along the slide groove of the rotating support base, driving the rotating arm and the first heating and insulation component to rotate until they fall to the safe area on the ground; the pivot of the second support component slides upward along the slide groove of the rotating support base, driving the rotating arm and the second heating and insulation component to rotate until they fall to the safe area on the ground; as shown in Figure 5(a) and Figure 5(b).
[0077] In a specific embodiment of the present invention, the launch vehicle heating and insulation device consists of two parts: the aforementioned heating and insulation mechanism and the detachment mechanism. In storage, these two parts can be separated and stored independently; when used on the launch device, they can be quickly assembled and used on the launch platform. This heating and insulation device operates in an ambient temperature of -20°C and, with the aid of a temperature controller, can provide continuous heating and insulation for more than 12 hours. Simultaneously, the heating and insulation device has an anti-static layer on the part of the launch vehicle in close contact with it, greatly improving the operational safety of the heating and insulation device. In addition to its heating and insulation function, this heating and insulation device can also detach before launch under inclined launch conditions (e.g., an elevation angle of 87°), without affecting the normal derailment of the launch vehicle. Multiple heating and insulation devices can be placed side-by-side to adapt to the length requirements of the launch vehicle, such as... Figure 6 As shown.
[0078] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.
Claims
1. A detachable rail-mounted pre-launch heating and insulation device for a launch vehicle, characterized in that... The shedding mechanism and the heating and keeping warm mechanism are independent of each other and are stored separately in a storage state. In a heating and working state, the heating and keeping warm mechanism is lifted by the shedding mechanism, and the heating and keeping warm mechanism heats and keeps warm the carrier. In a launching and separating state, the shedding mechanism takes the heating and keeping warm mechanism away from the guide rail type launching device of the guide rail type launching carrier, and ensures normal orbiting of the carrier. The heating and keeping warm mechanism comprises an electronic temperature controller, a first heating and keeping warm component (4-1) and a second heating and keeping warm component (4-2). The first heating and keeping warm component (4-1) and the second heating and keeping warm component (4-2) are symmetrical in structure, and the inner profile surface is attached to the side wall of the carrier load cabin for heating and keeping warm of the carrier load cabin. The electronic temperature controller is connected with the first heating and keeping warm component (4-1) and the second heating and keeping warm component (4-2) through cables for real-time temperature control of the heating temperature of the first heating and keeping warm component (4-1) and the second heating and keeping warm component (4-2). The first heating and keeping warm component (4-1) and the second heating and keeping warm component (4-2) are the same in structure, and comprise a keeping warm layer, a heating layer and an anti-static layer. The electronic temperature controller comprises a power supply, a four-circuit controller, a first single-throw switch, a second single-throw switch, a third single-throw switch, a solid-state relay SSR1, a solid-state relay SSR2 and a fuse. The power supply outputs alternating current, and the negative terminal of the power supply is connected with one end of the fuse. The other end of the fuse is connected with the first fixed terminal of the second single-throw switch and the third single-throw switch and the second fixed terminal of the first single-throw switch. The second fixed terminal of the second single-throw switch and the third single-throw switch and the first fixed terminal of the first single-throw switch are suspended. The movable terminal of the first single-throw switch is connected in series with the solid-state relay SSR1 between the resistance wire T1 in the first heating and keeping warm component (4-1). The movable terminal of the first single-throw switch is connected in series with the solid-state relay SSR2 between the resistance wire T2 of the second heating and keeping warm component (4-2). The solid-state relay SSR1 is connected with the movable terminal of the second single-throw switch. The solid-state relay SSR2 is connected with the movable terminal of the third single-throw switch. The on-off of the solid-state relay SSR1 and the solid-state relay SSR2 is controlled by the four-circuit controller. The detachment mechanism includes a first support component and a second support component. The first support component and the second support component have the same structure and are used relative to each other. Both include a rotating support base (1), a rotating shaft (2), and a rotating arm (3). The rotating support base (1) is used to be fixedly installed on the guide rail launching device. The rotating shaft (2) is engaged with the arc-shaped slide groove of the rotating support base (1) and can reciprocate in the slide groove under the action of external force. The lower part of the rotating arm (3) is connected to the rotating shaft (2), and the upper part is inserted into the first heating and heat preservation component (4-1) or the second heating and heat preservation component (4-2) for fixation. When the rotating shaft (2) moves in the rotating support base (1), it helps to drive the first heating and heat preservation component (4-1) or the second heating and heat preservation component (4-2) to rotate and separate. The first and second support components also include nylon ropes. One end of the nylon rope is tied to the top of the rotating arm (3), and the other end is suspended in the air. When the first heating and heat preservation component (4-1) and the second heating and heat preservation component (4-2) need to be detached, the nylon rope is pulled to separate the first heating and heat preservation component (4-1) and the second heating and heat preservation component (4-2). The rotating shaft (2) slides out of the arc-shaped groove of the rotating support seat (1) to complete the detachment action.
2. The launch vehicle pre-launch heating and insulation device of claim 1, wherein The electronic temperature controller also includes a first mechanical overheat protector KT1 and a second mechanical overheat protector KT2. The first mechanical overheat protector KT1 is connected between the resistance wire T1 in the first heating and insulation assembly (4-1) and the positive terminal of the power supply; The second mechanical overheat protector KT2 is connected between the resistance wire T2 in the second heating and insulation assembly (4-2) and the positive terminal of the power supply; The first mechanical overheat protector KT1 and the second mechanical overheat protector KT2 contain a thermistor element, which will automatically disconnect the circuit when the heating temperature exceeds the set first threshold.
3. The launch vehicle pre-launch heating and insulation device of claim 1, wherein The electronic temperature controller also includes a first temperature sensor T1 and a second temperature sensor T2; The first temperature sensor T1 is used to detect the temperature of the insulation layer of the first heating and insulation component (4-1) and feed it back to the four-loop controller; The second temperature sensor T2 is used to detect the temperature of the insulation layer of the second heating and insulation component (4-2) and feed it back to the four-loop controller; When the temperature of the insulation layer of the first heating and insulation component (4-1) or the second heating and insulation component (4-2) exceeds the set second threshold, the four-loop controller controls the solid-state relay SSR1 or solid-state relay SSR2 to disconnect the circuit.
4. The launch vehicle pre-launch heating and insulation device of claim 1, wherein The electronic temperature controller also includes an alarm; The four-loop controller is connected to the alarm. When the four-loop controller detects that the insulation layer of the first heating and insulation component 4-1 or the second heating and insulation component 4-2 is overheated, it sends an alarm signal to the alarm for overheating alarm.
5. The launch vehicle pre-launch heating and insulation device of claim 1, wherein The heating and heat preservation mechanism also includes Velcro (5), which is installed on the inner surfaces of the top of the first heating and heat preservation component (4-1) and the second heating and heat preservation component (4-2) to connect the first heating and heat preservation component (4-1) and the second heating and heat preservation component (4-2) during heating.