Rocket insulation device

Abstract

The present invention relates to the field of rocket technology, and specifically to a rocket insulation device. It includes a temperature control device and an insulation cabin for accommodating a rocket, the insulation cabin includes an insulation cabin body and an insulation cabin frame fixedly connected to the surface of the insulation cabin body, the temperature control device includes an air conditioning unit, a temperature and humidity sensor, and a temperature control controller, the air conditioning unit is fixedly arranged on both sides of the bottom of the insulation cabin frame, the air conditioning units on both sides are connected to the inside of the insulation cabin body through air ducts, the temperature and humidity sensor is arranged on the insulation cabin frame and is used to detect the air outlet, air inlet, and temperature and humidity environmental data of the air conditioning unit, the data output end of the temperature and humidity sensor is connected to the data input end of the temperature control controller, and the control signal output end of the temperature control controller is connected to the control signal input end of the air conditioning unit. It can automatically adjust the cabin temperature, has good insulation effect, strong anti-interference ability, high cleanliness, and is simple to operate and takes little time.

Description

Technical Field

[0001] The invention relates to the field of rocket technology, and in particular to a rocket heat preservation device. Background Art

[0002] With the development of science and technology in the new era, the rapid launch capability of rockets has become an important research direction for rocket launches, among which the temperature guarantee of the payload cabin before rocket launch has become an important condition for launch. The shock absorbers in the rocket fairing, the seals in the closed tanks and pipelines in the attitude control system, high-precision devices, and optical elements have a crucial impact on the overall performance of the rocket, but these components and materials are often temperature sensitive and are easily damaged and fail in extremely cold conditions. Therefore, the ambient temperature of the head payload cabin needs to be adjusted before the rocket is launched to ensure that the ambient temperature of the payload is always in the best state; when the external temperature is extremely low, a special thermal insulation protection device needs to be set up to ensure that the temperature of the microenvironment in which the rocket is located is not too low, and at the same time, this device needs to have the characteristics of rapid withdrawal to achieve timely response to the rocket launch.

[0003] Existing rocket insulation devices generally connect the rocket fairing cover to an external temperature control system through an air-conditioning hose to achieve insulation. Before launch, the air-conditioning hose is manually disconnected and the fairing cover is sealed, which often requires experienced personnel to operate, is time-consuming, and the cleanliness cannot be guaranteed. It is not automatically adjusted by the system, so it cannot meet the expected requirements. The cleanliness requirement inside the fairing is high, and it is affected by the wind and sand weather at the launch site, so the cleanliness cannot be guaranteed to meet the expected requirements, and the anti-interference ability is not strong. Due to the high cleanliness requirement inside the rocket fairing, especially the optical components are crucial to the launch of the rocket, which affects the normal progress of the subsequent launch process.

[0004] In summary, the existing rocket insulation devices have the defects of poor insulation effect, poor anti-interference ability, long operation time and low cleanliness. Summary of the invention

[0005] The purpose of the present invention is to address the defects of the prior art and provide a rocket insulation device, which can automatically adjust the temperature of the cabin, has good insulation effect, does not require an external temperature adjustment device at the rocket fairing cover, has strong anti-interference ability and high cleanliness, does not require personnel to operate the air-conditioning hose, and is simple to operate and time-saving.

[0006] A rocket insulation device provided by the present invention comprises a temperature control device and an insulation cabin for accommodating a rocket, wherein the insulation cabin comprises an insulation cabin body and an insulation cabin frame fixedly connected to the surface of the insulation cabin body, the temperature control device comprises an air-conditioning unit, a temperature and humidity sensor and a temperature control controller, the air-conditioning unit is fixedly arranged on both sides of the bottom of the insulation cabin frame, the air-conditioning units on both sides are connected to the inside of the insulation cabin body through air ducts respectively, the temperature and humidity sensor is arranged on the insulation cabin frame and is used to detect the temperature and humidity environmental data of the air outlet and air inlet of the air-conditioning unit and the insulation cabin, the data output end of the temperature and humidity sensor is connected to the data input end of the temperature control controller, and the control signal output end of the temperature control controller is connected to the control signal input end of the air-conditioning unit.

[0007] More preferably, the thermal insulation cabin also includes an thermal insulation cabin cover, which is hingedly arranged on the thermal insulation cabin body and forms a closed thermal insulation cabin structure together with the thermal insulation cabin body, the main section of the thermal insulation cabin body is a semi-cylindrical structure, the main section of the thermal insulation cabin cover is a semi-cylindrical structure formed by splicing two 1 / 4 cylindrical cabin covers, and the curved surface of the 1 / 4 cylindrical cabin cover is hinged to the thermal insulation cabin body.

[0008] More preferably, it also includes two hatch cover driving cylinders, the bottoms of the two hatch cover driving cylinders are respectively hinged to the two sides of the thermal insulation cabin body, the piston rod ends of the hatch cover driving cylinders are respectively hinged to the arc surface of a 1 / 4 cylindrical hatch cover, and the 1 / 4 cylindrical hatch cover can be opened and closed under the drive of the hatch cover driving cylinders.

[0009] More preferably, the insulation cabin frame includes a plurality of ring-shaped frames evenly distributed along the axial direction of the insulation cabin body, a plurality of strip-shaped frames evenly distributed along the radial direction of the insulation cabin body, and an insulation cabin support frame for connecting the bottom of the insulation cabin body with the rocket erection frame, and the ring-shaped frames, strip-shaped frames and insulation cabin support frame are connected to each other.

[0010] Preferably, the thermal insulation cabin further comprises a thermal insulation garment, and the thermal insulation garment is coated on the surface of the thermal insulation cabin frame.

[0011] More preferably, the air-conditioning unit includes an electric compressor, an electric heater, an evaporating fan, a condensing fan, a circuit breaker, a soft starter, a first relay, a second relay and a third relay, the AC power supply output end is connected to one end of the circuit breaker, the other end of the circuit breaker is connected to the electric compressor through the soft starter, connected to the electric heater through the first relay, connected to the evaporating fan through the second relay, and connected to the condensing fan through the third relay.

[0012] More preferably, the air-conditioning unit includes an electric compressor, a four-way valve, a condenser, a condensing fan, a dryer, a two-way flow expansion valve, an electric heater, an evaporating fan, an evaporator, an air flow separator, a low-pressure switch, a high-pressure switch, a first one-way valve and a second one-way valve. The output end of the electric compressor is connected to the condenser inlet via the first one-way valve and the four-way valve in sequence, the condenser outlet is connected to one end of the evaporator via the dryer and the two-way flow expansion valve, the other end of the evaporator is connected to the electric compressor inlet via the four-way valve and the air flow separator, a high-pressure switch is provided between the electric compressor and the first one-way valve, the condensing fan is integrated on the condenser, the second one-way valve is connected to both ends of the dryer, the electric heater and the evaporating fan are integrated on the evaporator, and a low-pressure switch is provided between the air flow separator and the electric compressor inlet.

[0013] The beneficial effects of the present invention are:

[0014] 1. This solution is to set up a heat preservation cabin for accommodating rockets and integrate a temperature control device for adjusting the temperature in the heat preservation cabin. The air conditioning unit, temperature and humidity sensor and temperature control controller automatically detect the air outlet, air inlet and temperature and humidity environment data in the heat preservation cabin, and realize the automatic control of the air conditioning unit by the temperature control controller, so as to realize the automatic adjustment of the temperature in the heat preservation cabin. It does not need to connect an external temperature control device to the cover of the rocket fairing, has strong anti-interference ability and high cleanliness, does not require personnel to operate the air conditioning hose, and is easy to operate and time-saving.

[0015] 2. The thermal insulation cabin adopts a hinged thermal insulation cabin body and thermal insulation cabin cover. The opening and closing of the thermal insulation cabin cover is driven by the cabin cover driving cylinder. When the cabin cover is closed, it and the thermal insulation cabin body together provide an enclosed space for the rocket payload cabin and have good thermal insulation functions. It has good sealing, easy opening and closing, and good insulation effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the main structure of the present invention;

[0017] Figure 2 It is a schematic diagram of the connection between the air conditioning unit and the heat preservation cabin of the present invention;

[0018] Figure 3 It is a side view structural schematic diagram of the thermal insulation cabin of the present invention;

[0019] Figure 4 This is a schematic diagram of the thermal insulation cabin of the present invention in an open state (the cabin cover driving cylinder is not shown);

[0020] Figure 5 This is a schematic diagram of electrical connections of the air conditioning unit of the present invention;

[0021] Figure 6 Schematic diagram of the pipeline connection of the air conditioning unit of the present invention.

[0022] In the figure: 1-insulation cabin, 2-erecting frame, 3-air conditioning unit, 4-insulation cabin body, 5-insulation cabin frame, 6-insulation cabin support frame, 7-air duct, 8-insulation cabin cover, 9-cabin cover driving cylinder, 10-electric compressor, 11-four-way valve, 12-condenser, 13-condensing fan, 14-dryer, 15-two-way flow expansion valve, 16-electric heater, 17-evaporation fan, 18-evaporator, 19-air flow separator, 20-low pressure switch, 21-high pressure switch, 22-first one-way valve, 23-second one-way valve. DETAILED DESCRIPTION

[0023] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0024] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0025] It should be understood that the orientation or position relationship indicated by terms such as "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0026] 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. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0027] Embodiment 1

[0028] Figure 1 , 2 The schematic diagram of the structure of the rocket heat preservation device provided by the preferred embodiment of the present application is shown. For the convenience of explanation, only the parts related to the present embodiment are shown, which are described in detail as follows:

[0029] A rocket insulation device includes a temperature control device and an insulation cabin 1 for accommodating a rocket, wherein the insulation cabin 1 includes an insulation cabin body 4 and an insulation cabin frame 5 fixedly connected to the surface of the insulation cabin body 4, and the temperature control device includes an air conditioning unit 3, a temperature and humidity sensor, and a temperature control controller. The insulation cabin body provides an installation interface and space for the temperature control device, the air conditioning unit 3 is fixedly arranged on both sides of the bottom of the insulation cabin, and the air conditioning units 3 on both sides are connected to the inside of the insulation cabin body 4 through air ducts 7, respectively. The temperature and humidity sensor is arranged on the insulation cabin frame 5 and is used to detect the air outlet and air inlet of the air conditioning unit 3 and the temperature and humidity environment data in the insulation cabin 1. The data output end of the temperature and humidity sensor is connected to the data input end of the temperature control controller, and the control signal output end of the temperature control controller is connected to the control signal input end of the air conditioning unit 3. In addition, the insulation cabin frame 5 includes a plurality of ring-shaped frames evenly distributed along the axial direction of the insulation cabin body 4, a plurality of strip-shaped frames evenly distributed along the radial direction of the insulation cabin body 4, and an insulation cabin support frame 6 for connecting the bottom of the insulation cabin body 4 with the rocket erection frame 2. The ring-shaped frames, strip-shaped frames and insulation cabin support frame 6 are connected to each other.

[0030] After the insulation cabin support frame 6 is connected to the erection frame 2, the insulation cabin can be erected together with the erection arm, and the temperature adjustment in the horizontal transportation and vertical launch states can be realized by turning over the compressor installation shaft. By setting an insulation cabin for accommodating rockets and integrating a temperature adjustment device for adjusting the temperature in the insulation cabin, the air outlet, air inlet and temperature and humidity environment data of the air conditioning unit are automatically detected by the air conditioning unit, the temperature and humidity sensor and the temperature adjustment controller, and the temperature adjustment controller automatically controls the air conditioning unit, thereby realizing the automatic adjustment of the temperature in the insulation cabin. It does not need to connect an external temperature adjustment device at the rocket fairing cover, has strong anti-interference ability and high cleanliness, does not require personnel to operate the air conditioning hose, and is simple to operate and time-consuming.

[0031] like Figure 3 , 4 As shown, in one embodiment, the thermal insulation cabin 1 also includes a thermal insulation cabin cover 8, which is hingedly arranged on the thermal insulation cabin body 4 and forms a closed thermal insulation cabin structure together with the thermal insulation cabin body 4, the main section of the thermal insulation cabin body 4 is a semi-cylindrical structure, the main section of the thermal insulation cabin cover 8 is a semi-cylindrical structure formed by splicing two 1 / 4 cylindrical cabin covers, and the curved surface of the 1 / 4 cylindrical cabin cover is hinged to the thermal insulation cabin body 4.

[0032] In one embodiment, two hatch cover driving cylinders 9 are further included, the bottoms of the two hatch cover driving cylinders 9 are respectively hinged to the two sides of the thermal insulation cabin body 4, and the piston rod ends of the hatch cover driving cylinders 9 are respectively hinged to the arc surface of a 1 / 4 cylindrical hatch cover, and the 1 / 4 cylindrical hatch cover can be opened and closed under the drive of the hatch cover driving cylinders 9. The thermal insulation cabin body provides a structural installation interface for the thermal insulation hatch cover and the opening mechanism (i.e., the hatch cover driving cylinder). The thermal insulation hatch cover can be opened and closed by the opening mechanism. When the hatch cover is closed, it provides a closed space for the rocket payload cabin together with the thermal insulation cabin body and has good thermal insulation functions.

[0033] In one embodiment, the thermal insulation cabin 1 further includes a thermal insulation garment, which is coated on the surface of the thermal insulation cabin frame 5 to play a role of thermal insulation and sealing.

[0034] like Figure 5 As shown, in one embodiment, the air-conditioning unit 3 mainly includes an electric compressor 10, an electric heater 16, an evaporating fan 17, a condensing fan 13, a circuit breaker, a soft starter, a first relay, a second relay and a third relay. The output end of the AC power supply is connected to one end of the circuit breaker, and the other end of the circuit breaker is connected to the electric compressor 10 through the soft starter, connected to the electric heater 16 through the first relay, connected to the evaporating fan 17 through the second relay, and connected to the condensing fan 13 through the third relay.

[0035] like Figure 6As shown, in one embodiment, the temperature control device adopts an integrated air conditioning unit with an evaporator and a condenser, which is an integrated type with dual cooling and heating. The air conditioning unit 3 includes an electric compressor 10, a four-way valve 11, a condenser 12, a condensing fan 13, a dryer 14, a two-way flow expansion valve 15, an electric heater 16, an evaporating fan 17, an evaporator 18, an air flow separator 19, a low-pressure switch 20, a high-pressure switch 21, a first one-way valve 22 and a second one-way valve 23. The output end of the electric compressor 10 is connected to the inlet of the condenser 12 through the first one-way valve 22 and the four-way valve 11 in sequence, and the outlet of the condenser 12 is connected to the outlet of the condenser 12 through the dryer 14, the two-way flow expansion valve 15, the electric heater 16, the evaporating fan 17, the evaporator 18, the air flow separator 19, the low-pressure switch 20, the high-pressure switch 21, the first one-way valve 22 and the second one-way valve 23. The valve 15 is connected to one end of the evaporator 18, and the other end of the evaporator 18 is connected to the inlet of the electric compressor 10 through the four-way valve 11 and the air flow separator 19. A high-pressure switch 21 is provided between the electric compressor 10 and the first one-way valve 22. The condenser 12 is integrated with a condensing fan 13. The two ends of the dryer 14 are connected with a second one-way valve 23. The evaporator 18 is integrated with an electric heater 16 and an evaporating fan 17. A low-pressure switch 20 is provided between the air flow separator 19 and the inlet of the electric compressor 10. Under the control of the thermostat, the left and right air-conditioning units can work independently or simultaneously; the air-conditioning units can both cool and heat. The air-conditioning units use PTC electric heating and heat pump heating functions. The thermostat automatically selects the heating mode (electric heating mode, heat pump heating mode, combined heating mode) according to the power supply. The thermostat controls the two (left and right) air-conditioning units according to the set temperature and the detected ambient temperature, and automatically selects the cooling, heating or ventilation working mode to meet the requirements of the ambient temperature in the cabin.

[0036] In addition, the compressor structure of the air conditioner can control its rotation through an external movable handle, so that when the insulation cabin is erected, the compressor can rotate synchronously, thereby ensuring that the angle of the compressor is always consistent with the insulation cabin, further ensuring its normal operation and achieving a good insulation effect.

[0037] The embodiments described above are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, a person skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be included in the protection scope of the present application.

Claims

1. A rocket heat preservation device, characterized in that: The invention comprises a temperature control device and a heat preservation chamber (1) for accommodating a rocket, wherein the heat preservation chamber (1) comprises a heat preservation chamber body (4) and a heat preservation chamber frame (5) fixedly connected to the surface of the heat preservation chamber body (4), wherein the temperature control device comprises an air conditioning unit (3), a temperature and humidity sensor and a temperature control controller, wherein the air conditioning unit (3) is fixedly arranged on both sides of the bottom of the heat preservation chamber, and the air conditioning units (3) on both sides are respectively connected to the inside of the heat preservation chamber body (4) through air ducts (7), wherein the temperature and humidity sensor is arranged on the heat preservation chamber frame (5) and is used to detect the temperature and humidity environmental data of the air outlet and air inlet of the air conditioning unit (3) and the heat preservation chamber (1), wherein the data output end of the temperature and humidity sensor is connected to the data input end of the temperature control controller, and the control signal output end of the temperature control controller is connected to the control signal input end of the air conditioning unit (3); The thermal insulation cabin (1) further comprises a thermal insulation cabin cover (8), wherein the thermal insulation cabin cover (8) is hingedly arranged on the thermal insulation cabin body (4) and together with the thermal insulation cabin body (4) forms a closed thermal insulation cabin structure, wherein the main section of the thermal insulation cabin body (4) is a semi-cylindrical structure, and the main section of the thermal insulation cabin cover (8) is a semi-cylindrical structure formed by splicing two 1 / 4 cylindrical cabin covers, and the arc surface of the 1 / 4 cylindrical cabin cover is hingedly connected to the thermal insulation cabin body (4).

2. The rocket heat preservation device according to claim 1, characterized in that: It also includes two hatch cover driving cylinders (9), the bottoms of the two hatch cover driving cylinders (9) are respectively hinged to the two sides of the thermal insulation cabin body (4), the piston rod ends of the hatch cover driving cylinders (9) are respectively hinged to the arc surface of a 1 / 4 cylindrical hatch cover, and the 1 / 4 cylindrical hatch cover is opened and closed under the drive of the hatch cover driving cylinders (9).

3. The rocket heat preservation device according to claim 1, characterized in that: The insulation cabin frame (5) comprises a plurality of ring-shaped frames evenly distributed along the axial direction of the insulation cabin body (4), a plurality of strip-shaped frames evenly distributed along the radial direction of the insulation cabin body (4), and an insulation cabin support frame (6) for connecting the bottom of the insulation cabin body (4) and the erection frame (2), wherein the ring-shaped frames, the strip-shaped frames and the insulation cabin support frame (6) are connected to each other.

4. The rocket heat preservation device according to claim 1, characterized in that: The thermal insulation cabin (1) also includes thermal insulation clothing, which is coated on the surface of the thermal insulation cabin frame (5).

5. The rocket heat preservation device according to claim 1, characterized in that: The air conditioning unit (3) comprises an electric compressor (10), an electric heater (16), an evaporating fan (17), a condensing fan (13), a circuit breaker, a soft starter, a first relay, a second relay and a third relay, wherein the output end of the AC power supply is connected to one end of the circuit breaker, and the other end of the circuit breaker is connected to the electric compressor (10) through the soft starter, connected to the electric heater (16) through the first relay, connected to the evaporating fan (17) through the second relay, and connected to the condensing fan (13) through the third relay.

6. The rocket heat preservation device according to claim 1, characterized in that: The air conditioning unit (3) comprises an electric compressor (10), a four-way valve (11), a condenser (12), a condensing fan (13), a dryer (14), a two-way flow expansion valve (15), an electric heater (16), an evaporating fan (17), an evaporator (18), an air flow separator (19), a low-pressure switch (20), a high-pressure switch (21), a first one-way valve (22) and a second one-way valve (23). The output end of the electric compressor (10) is connected to the inlet of the condenser (12) via the first one-way valve (22) and the four-way valve (11) in sequence. The outlet of the condenser (12) is connected to the outlet of the condenser (12) via the dryer (14), the two-way flow The expansion valve (15) is connected to one end of the evaporator (18), and the other end of the evaporator (18) is connected to the inlet of the electric compressor (10) via a four-way valve (11) and an air flow separator (19). A high-pressure switch (21) is provided between the electric compressor (10) and the first one-way valve (22). A condensing fan (13) is integrated on the condenser (12). Two ends of the dryer (14) are connected to a second one-way valve (23). An electric heater (16) and an evaporating fan (17) are integrated on the evaporator (18), and a low-pressure switch (20) is provided between the air flow separator (19) and the inlet of the electric compressor (10).

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