CN111547276A - Intelligent autonomous temperature control structure and temperature control method for deep space impactor - Google Patents
Intelligent autonomous temperature control structure and temperature control method for deep space impactor Download PDFInfo
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- CN111547276A CN111547276A CN202010245760.4A CN202010245760A CN111547276A CN 111547276 A CN111547276 A CN 111547276A CN 202010245760 A CN202010245760 A CN 202010245760A CN 111547276 A CN111547276 A CN 111547276A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/01—Control of temperature without auxiliary power
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Abstract
The invention relates to an intelligent autonomous temperature control structure and a temperature control method for a deep space impactor, wherein the structure comprises the following components: the energy production device comprises an energy production unit outer cover, a first energy production unit component, a second energy production unit component, a phase change energy storage material and a heat conduction belt; the phase change energy storage material is positioned between the outer cover of the energy production unit and the heat conduction belt, the phase change energy storage material, the outer cover of the energy production unit and the heat conduction belt are parallelly attached and serially installed, and the phase change energy storage material and the control module of the deep space impactor are closely attached through the heat conduction belt; the two components are arranged inside the outer cover of the capacity unit. Before the deep space impactor impacts, two components in the housing of the capacity unit are in a separation state; the device generates overload acceleration during impact, the two components are fused to generate heat energy, the heat energy is stored in the phase-change energy storage material, and the phase-change energy storage material gradually releases energy after impact, so that the device is used for preserving heat of a control module of the deep space impactor and supporting the deep space impactor to survive.
Description
Technical Field
The invention relates to the technical field of deep space exploration aircrafts, in particular to an intelligent autonomous temperature control structure and method for a deep space impactor by using a phase change energy storage material.
Background
With the development and progress of space technology, the deep space exploration means is developed from initial fly-by exploration to multi-mode combined exploration such as encircling, landing, patrol, sampling and the like, the spanning from encircling to landing and from surface to interior is realized, and the deep space exploration means is developing towards the directions of three-dimensional exploration and interior depth exploration. The impact detection is an efficient means for realizing internal detection, has the characteristics of simple and reliable structure, high integration level and flexible configuration, and can be penetrated into the inside of a celestial body by consuming less resources.
The temperature condition of a detection target is difficult to accurately estimate, and in order to ensure the normal work of electronic components and adapt to the characteristics of high integration and miniaturization of a deep space impactor, the deep space impactor needs to have an autonomous temperature control capability, so that the aim of providing scientific detection data after collision survival is fulfilled.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and an intelligent autonomous temperature control structure and a control method of the deep space impactor by using the phase change energy storage material are provided.
The technical solution of the invention is as follows:
an intelligent autonomous temperature control structure for a deep space impactor, comprising: the energy production device comprises an energy production unit outer cover, a first energy production unit component, a second energy production unit component, a phase change energy storage material and a heat conduction belt;
the phase change energy storage material is positioned between the outer cover of the energy production unit and the heat conduction belt, the phase change energy storage material, the outer cover of the energy production unit and the heat conduction belt are parallelly attached and serially installed, and the phase change energy storage material and the control module of the deep space impactor are closely attached through the heat conduction belt; the first capacity unit component and the second capacity unit component are arranged inside the outer cover of the capacity unit.
Further, the outer cover of the capacity unit, the first capacity unit component and the second capacity unit component are made into the capacity unit of the deep space impactor together.
Furthermore, the energy generating unit, the phase change energy storage material and the heat conducting strip are all located in the head shell of the deep space impactor.
Further, before the deep space impactor impacts, the first capacity unit component and the second capacity unit component in the capacity unit shell are in a separation state; the device generates overload acceleration during impact, the first energy production unit component and the second energy production unit component are fused to generate heat energy, the heat energy is stored in the phase change energy storage material, and the phase change energy storage material gradually releases energy after impact, so that the device is used for keeping the temperature of a control module of the deep space impactor and supporting the deep space impactor to survive.
Preferably, the first energy production unit component and the second energy production unit component are mixed when the deep space impactor impacts, and chemical energy is converted into heat energy; the first energy production unit component is tin, and the second energy production unit component is hydrogen peroxide.
Preferably, the first energy producing unit component and the second energy producing unit component are cubic structures with sides between 40mm and 42 mm.
Preferably, the distance between the first energy producing unit component and the second energy producing unit component is 4mm to 7mm in the separated state.
Preferably, the phase-change energy storage material is a dielectric material with the phase-change temperature of-10-45 ℃, absorbs stored energy when the temperature is higher than 45 ℃, and releases heat energy when the temperature is lower than-10 ℃, so that autonomous temperature control is realized.
Preferably, the phase change energy storage material is prepared by mixing paraffin and graphite, and the mass percentage is as follows: paraffin: graphite 93: 7.
Furthermore, the invention also provides a temperature control method of the deep space impactor, which comprises the following steps:
step one, setting the distance between a first energy production unit component and a second energy production unit component to be a preset size, placing the first energy production unit component and the second energy production unit component in an outer cover of an energy production unit to form an integral energy production unit, sequentially attaching the energy production unit, a phase change energy storage material and a heat conduction belt, and finally attaching the heat conduction belt to a control module of a deep space impactor;
step two, when the impact occurs, the first energy production unit component and the second energy production unit component are mixed in the outer cover of the energy production unit, and chemical energy is converted into heat energy;
absorbing and storing energy by using a phase-change energy storage material;
after the impact is finished, because the temperature inside the deep space impactor is reduced or increased due to the influence of the external environment temperature, when the temperature inside the deep space impactor is lower than minus 10 ℃, the phase-change energy storage material releases heat energy, and the heat energy released by the phase-change energy storage material is transferred to the control module through the heat conduction belt to preserve heat of the control module and support the deep space impactor to survive; and when the temperature is higher than 45 ℃, the phase change energy storage material absorbs heat to cool the control module.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention provides an intelligent autonomous temperature control method for a deep space impactor by using a phase change energy storage material, which is simple and reasonable, high in cost performance, safe, reliable, free of environmental pollution, capable of effectively realizing intelligent autonomous temperature control of the deep space impactor, capable of meeting the requirement of heat preservation of the deep space impactor and guaranteeing the survival of the deep space impactor, and has extremely high engineering application value.
(2) The phase change energy storage material selects a medium material with the phase change temperature of-10-45 ℃, absorbs stored energy when the temperature is higher than 45 ℃, releases heat energy when the temperature is lower than-10 ℃, and effectively realizes autonomous temperature control.
(3) The two components of the capacity unit realize contact capacity through large impact overload during impact; the phase-change energy storage material stores energy released by the energy generating unit, and thermal interaction is carried out between the heat conduction belt and a high reinforcement control module, which is a key electronics part of the deep space impactor, so that the temperature requirement of the high reinforcement control module is effectively met.
(4) According to the invention, the energy production unit and the phase-change energy storage material are placed in the deep space impactor, different components of the energy production unit are separated before impact, overload acceleration is generated during impact, different components of the energy production unit are fused to generate heat energy, the heat energy is stored in the phase-change energy storage material, and the energy is gradually released after impact, so that the deep space impactor is kept warm and the deep space impactor is supported to survive.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the heat conduction of the present invention.
Detailed Description
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
The temperature condition of a deep space detection target is difficult to accurately estimate, in order to ensure the normal work of electronic components and adapt to the characteristics of high integration and miniaturization of a deep space impactor, the developed deep space impactor needs to have an autonomous temperature control capability, and then the aim of providing scientific detection data after collision survival is fulfilled.
Since impact detection is different from landing detection, it needs to penetrate into the target at the impact moment with high speed, and the impact load generated by the impact can be as high as ten thousands of g. The method takes the carbon dioxide as the trigger condition of mixed heating of the capacity unit, is simple and easy to implement, and simultaneously greatly improves the safety.
Specifically, the invention provides an intelligent autonomous temperature control structure of a deep space impactor, as shown in fig. 1, comprising: the energy production device comprises an energy production unit outer cover 1, a first energy production unit component 2, a second energy production unit component 3, a phase change energy storage material 4 and a heat conduction belt 5;
the phase change energy storage material 4 is positioned between the outer cover 1 of the energy production unit and the heat conduction belt 5, the three are parallelly attached and serially installed, and the phase change energy storage material 4 and the control module 6 of the deep space impactor are closely attached through the heat conduction belt 5; the capacity first capacity unit component 2 and the second capacity unit component 3 are disposed inside the capacity unit housing 1.
The capacity unit housing 1, the first capacity unit component 2 and the second capacity unit component 3 together form a capacity unit of a deep space impactor. The energy generating unit, the phase change energy storage material 4 and the heat conducting strip 5 are all located in a head shell of the deep space impactor.
Before the deep space impactor impacts, a first capacity unit component 2 and a second capacity unit component 3 in a capacity unit shell 1 are in a separation state; preferably, when the energy generating unit is in a separated state, the distance between the first energy generating unit component 2 and the second energy generating unit component 3 is 4-7 mm, so that safety can be guaranteed, and sensitive triggering during collision can be guaranteed.
The overload acceleration is generated during the impact, the first energy production unit component 2 and the second energy production unit component 3 are mixed to convert chemical energy into heat energy and store the heat energy in the phase change energy storage material 4, and the phase change energy storage material 4 gradually releases energy after the impact, so that the heat is preserved for the control module 6 of the deep space impactor, and the deep space impactor is supported to survive.
Preferably, the best proposal of the invention is that the first energy-producing unit component 2 is tin, and the second energy-producing unit component 3 is hydrogen peroxide. The first energy-producing unit component 2 and the second energy-producing unit component 3 are cubic structures with side length between 40mm and 42 mm.
The phase change energy storage material 4 is a medium material with the phase change temperature of-10-45 ℃, absorbs stored energy when the temperature is higher than 45 ℃, and releases heat energy when the temperature is lower than-10 ℃ to realize autonomous temperature control.
The intelligent autonomous temperature control means that after energy is stored, if the temperature of a control module of the deep space impactor is lower than-10 ℃, the stored heat is released to improve the temperature of the control module; if the temperature of the deep space impactor control module is higher than 45 ℃, the temperature is conducted to the phase change energy storage material for absorption and storage, and the service life of components of the control module is greatly prolonged.
Preferably, the phase change energy storage material 4 is prepared by mixing paraffin and graphite, and the mass percentage is as follows: paraffin: graphite 93: 7.
Preferably, the size of the phase change energy storage material (4) provided by the invention is 100mm multiplied by 50 mm; therefore, the requirement of being installed in the narrow head space of the deep space impactor can be met, and the requirement of heat transfer and heat absorption can be met.
Preferably, the heat conduction belt (5) is arranged between the phase change energy storage material and the deep space impactor high reinforcement control module, so that the phase change energy storage material (5) and the high reinforcement control module (6) are conveniently subjected to heat interaction, and the heat insulation performance of the deep space impactor high reinforcement control module (6) is effectively improved; the size of the heat conducting strip is 100mm multiplied by 10 mm.
Working process and heat transfer path:
step one, setting the distance between a first capacity unit component 2 and a second capacity unit component 3 to be a preset size, placing the preset size in a capacity unit outer cover 1 to form an integral capacity unit, sequentially attaching the capacity unit, a phase change energy storage material 4 and a heat conduction belt 5, and finally attaching the heat conduction belt 5 to a control module of a deep space impactor;
step two, when the impact occurs, mixing the first energy production unit component 2 and the second energy production unit component 3 in the outer cover 1 of the energy production unit to convert chemical energy into heat energy;
step three, the phase-change energy storage material 4 absorbs energy storage;
after the impact is finished, because the temperature inside the deep space impactor is reduced or increased due to the influence of the external environment temperature, when the temperature inside the deep space impactor is lower than minus 10 ℃, the phase-change energy storage material 4 releases heat energy, and the heat energy released by the phase-change energy storage material 4 is transferred to the control module through the heat conduction belt 5 to preserve the heat of the control module and support the deep space impactor to survive; if the temperature of the deep space impactor control module is higher than 45 ℃, the temperature is conducted to the phase change energy storage material for absorption and storage, and the service life of components of the control module is greatly prolonged.
FIG. 2 is a schematic view of the heat conduction of the present invention, with arrows indicating the direction of conduction. The heat transfer path is the heat transfer from the energy generating unit to the phase change energy storage material 4, the phase change energy storage material 4 and the high reinforcement control module 6 are in heat conduction, and meanwhile, the full link is independent, so that the independent triggering and the independent heat preservation are realized. It should be noted that heat conduction is two-way, and when control module temperature was too high, its radiating heat also can be conducted phase change energy storage material and carry out the energy storage to reduce high reinforcement control module 6's temperature, when high reinforcement control module 6 temperature was low, phase change energy storage material 4 was exothermic in order to improve high reinforcement control module 6 temperature, thereby realized independently controlling the temperature.
The intelligent autonomous temperature control method for the deep space impactor provided by the invention is simple and reasonable, high in cost performance, safe and reliable, free of environmental pollution, capable of effectively realizing intelligent autonomous temperature control of the deep space impactor, capable of meeting the requirement of heat preservation of the deep space impactor and guaranteeing the survival of the deep space impactor, and has engineering application value.
Those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. The utility model provides a deep space impinger intelligence is temperature control structure independently which characterized in that includes: the energy production device comprises an energy production unit outer cover (1), a first energy production unit component (2), a second energy production unit component (3), a phase change energy storage material (4) and a heat conduction belt (5);
the phase change energy storage material (4) is positioned between the energy production unit outer cover (1) and the heat conduction belt (5), the phase change energy storage material (4) and the control module (6) of the deep space impactor are parallelly attached and serially installed, and the phase change energy storage material (4) and the control module (6) of the deep space impactor are tightly attached through the heat conduction belt (5); the first capacity unit component (2) and the second capacity unit component (3) are arranged inside the capacity unit housing (1).
2. The deep space impactor intelligent autonomous temperature control structure according to claim 1, characterized in that: the outer cover (1) of the capacity unit, the first capacity unit component (2) and the second capacity unit component (3) are made into the capacity unit of the deep space impactor together.
3. The deep space impactor intelligent autonomous temperature control structure according to claim 2, characterized in that: the energy generating unit, the phase change energy storage material (4) and the heat conducting strip (5) are all located in a head shell of the deep space impactor.
4. The deep space impactor intelligent autonomous temperature control structure according to claim 1, characterized in that: before the deep space impactor impacts, a first capacity unit component (2) and a second capacity unit component (3) in a capacity unit shell (1) are in a separated state; the overload acceleration is generated during the impact, the first energy generation unit component (2) and the second energy generation unit component (3) are fused to generate heat energy, the heat energy is stored in the phase change energy storage material (4), and the phase change energy storage material (4) gradually releases energy after the impact, so that the heat is preserved for a control module (6) of the deep space impactor, and the deep space impactor is supported to survive.
5. The deep space impactor intelligent autonomous temperature control structure according to claim 4, characterized in that: the first energy production unit component (2) and the second energy production unit component (3) are mixed when the deep space impactor impacts, and chemical energy is converted into heat energy; the first productivity unit component (2) is tin and the second productivity unit component (3) is hydrogen peroxide.
6. The deep space impactor intelligent autonomous temperature control structure according to claim 4, characterized in that: the first energy-producing unit component (2) and the second energy-producing unit component (3) are in a cubic structure, and the side length is between 40mm and 42 mm.
7. The deep space impactor intelligent autonomous temperature control structure according to claim 4, characterized in that: when the first energy-producing unit component (2) and the second energy-producing unit component (3) are in a separated state, the distance between the first energy-producing unit component (2) and the second energy-producing unit component (3) is 4-7 mm.
8. The deep space impactor intelligent autonomous temperature control structure according to claim 1, characterized in that: the phase change energy storage material (4) is a medium material with the phase change temperature of-10-45 ℃, absorbs stored energy when the temperature is higher than 45 ℃, releases heat energy when the temperature is lower than-10 ℃, and realizes autonomous temperature control.
9. The deep space impactor intelligent autonomous temperature control structure according to claim 8, characterized in that: the phase change energy storage material (4) is prepared by mixing paraffin and graphite, and comprises the following components in percentage by mass: paraffin: graphite 93: 7.
10. The deep space impactor temperature control method realized by the deep space impactor intelligent autonomous temperature control structure according to any one of claims 1-9, is characterized by comprising the following steps:
step one, setting the distance between a first capacity unit component (2) and a second capacity unit component (3) to be a preset size, placing the preset size in a capacity unit outer cover (1) to form an integral capacity unit, sequentially attaching the capacity unit, a phase change energy storage material (4) and a heat conduction belt (5) closely, and finally attaching the heat conduction belt (5) closely to a control module of a deep space impactor;
step two, when the impact occurs, mixing the first energy-producing unit component (2) and the second energy-producing unit component (3) in the outer cover (1) of the energy-producing unit to convert chemical energy into heat energy;
step three, when the temperature is higher than 45 ℃, the phase change energy storage material (4) absorbs energy storage;
after the impact is finished, because the temperature inside the deep space impactor is reduced or increased under the influence of the external environment temperature, when the temperature of the control module of the deep space impactor is lower than minus 10 ℃, the phase change energy storage material releases heat energy, and the heat energy is transferred to the control module through the heat conduction belt to preserve the heat of the control module; and when the temperature of the control module is higher than 45 ℃, the phase change energy storage material absorbs heat to cool the control module.
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